Gas turbine engine with power density range

Information

  • Patent Grant
  • 11608786
  • Patent Number
    11,608,786
  • Date Filed
    Wednesday, April 27, 2022
    2 years ago
  • Date Issued
    Tuesday, March 21, 2023
    a year ago
Abstract
A gas turbine engine includes a propulsor section including a propulsor, a compressor section including a low pressure compressor and a high pressure compressor, a geared architecture, a turbine section including a low pressure turbine and a high pressure turbine, and a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section.
Description
BACKGROUND OF THE INVENTION

This application relates to a geared turbofan gas turbine engine, wherein the low and high pressure spools rotate in the same direction relative to each other.


Gas turbine engines are known, and typically include a fan delivering air into a compressor section, and outwardly as bypass air to provide propulsion. The air in the compressor is delivered into a combustion section where it is mixed with fuel and burned. Products of this combustion pass downstream over turbine rotors, driving them to rotate. Typically there are low and high pressure compressors, and low and high pressure turbines.


The high pressure turbine typically drives the high pressure compressor as a high spool, and the low pressure turbine drives the low pressure compressor and the fan. Historically, the fan and low pressure compressor were driven at a common speed.


More recently, a gear reduction has been provided on the low pressure spool such that the fan and low pressure compressor can rotate at different speeds. It desirable to have more efficient engines that have more compact turbines to limit efficiency loses.


SUMMARY

In a featured embodiment, a gas turbine engine turbine comprises a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis. A low pressure turbine is configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/in3. A fan is connected to the low pressure spool via a speed changing mechanism and will rotate in a second direction opposed to the first direction.


In another embodiment according to the previous embodiment, the power density is greater than or equal to about 2.0.


In another embodiment according to any of the previous embodiments, the power density is greater than or equal to about 4.0.


In another embodiment according to any of the previous embodiments, the power density thrust is calculated using a value that is sea level take-off, flat-rated static thrust.


In another embodiment according to any of the previous embodiments, guide vanes are positioned upstream of a first stage in the low pressure turbine to direct gases downstream of the high pressure turbine as they approach the low pressure turbine.


In another embodiment according to any of the previous embodiments, a mid-turbine frame supports the high pressure turbine.


In another embodiment according to any of the previous embodiments, the guide vanes are positioned intermediate the mid-turbine frame and the low pressure turbine.


In another embodiment according to any of the previous embodiments, the guide vanes are highly cambered such that the vanes direct products of combustion downstream of the high pressure turbine to be properly directed when initially encountering the first stage of the low pressure turbine.


In another embodiment according to any of the previous embodiments, the fan section delivers a portion of air into a bypass duct and a portion of the air into the low pressure compressor as core flow, and has a bypass ratio greater than 6.


In another embodiment according to any of the previous embodiments, the speed changing mechanism is a gear reduction.


In another embodiment according to any of the previous embodiments, a star gear is utilized to change the direction of rotation between the fan and the low pressure spool.


In another embodiment according to any of the previous embodiments, the star gear arrangement has a gear ratio above 2.3:1, meaning that the low pressure spool turns at least or equal to about 2.3 times as fast as the fan.


In another embodiment according to any of the previous embodiments, the speed changing mechanism is a gear reduction.


In another embodiment according to any of the previous embodiments, a star gear is utilized to change the direction of rotation between the fan and the low pressure spool.


In another embodiment according to any of the previous embodiments, the star gear arrangement has a gear ratio above 2.3:1, meaning that the low pressure spool turns at least or equal to about 2.3 times as fast as the fan.


In another featured embodiment, a gas turbine engine turbine comprises a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis. A low pressure turbine is configured to rotate in the first direction about the central axis. A power density is greater than or equal to about 4.0. A fan is connected to the low pressure turbine via a gear reduction and will rotate in a second direction opposed to the first direction.


In another embodiment according to the previous embodiment, the power density is a ratio of a thrust provided by the engine to a volume of a turbine section including both the high pressure turbine and the low pressure turbine. The thrust is sea level take-off, flat-rated static thrust.


In another embodiment according to any of the previous embodiments, the fan section delivers a portion of air into a bypass duct and a portion of the air into the low pressure compressor as core flow, and has a bypass ratio greater than 6.


In another embodiment according to any of the previous embodiments, a star gear is utilized to change the direction of rotation between the fan and the low pressure spool.


In another embodiment according to any of the previous embodiments, there is an intermediate turbine section, which drives a compressor rotor.


In another embodiment according to any of the previous embodiments, the gear reduction is positioned intermediate the fan and a compressor rotor driven by the low pressure turbine.


In another embodiment according to any of the previous embodiments, the gear reduction is positioned intermediate the low pressure turbine and a compressor rotor driven by the low pressure turbine.


These and other features may be best understood from the following drawings and specification.





BRIEF DESCRIPTION OF THE DRAWINGS


FIG. 1 schematically shows a gas turbine engine.



FIG. 2 schematically shows rotational features of one type of such an engine.



FIG. 3 is a detail of the turbine section volume.



FIG. 4 shows another embodiment.



FIG. 5 shows yet another embodiment.





DETAILED DESCRIPTION


FIG. 1 schematically illustrates a gas turbine engine 20. The gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. Alternative engines might include, for example, three-spools, an augmentor section, or a different arrangement of sections, among other systems or features. The fan section 22 drives air along a bypass flowpath B while the compressor section 24 drives air along a core flowpath C for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines. For purposes of this application, the terms “low” and “high” as applied to speed or pressure are relative terms. The “high” speed and pressure would be higher than that associated with the “low” spools, compressors or turbines, however, the “low” speed and/or pressure may actually be “high.”


The engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided.


The low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a low pressure compressor 44 and a low pressure turbine 46. The inner shaft 40 is connected to the fan 42 through a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30. The high speed spool 32 includes an outer shaft 50 that interconnects a high pressure compressor 52 and high pressure turbine 54. The terms “high” and “low” in relation to both the speed and pressure of the components are relative to each other, and not to an absolute value. A combustor 56 is arranged between the high pressure compressor 52 and the high pressure turbine 54. A mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46. The mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28. The inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.


The core airflow C is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the combustor 56, then expanded over the high pressure turbine 54 and low pressure turbine 46. The mid-turbine frame 57 includes airfoils 59 which are in the core airflow path and act as inlet stator vanes to turn the flow to properly feed the first blades of the low pressure turbine. The turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.


The engine 20 has bypass airflow B, and in one example is a high-bypass geared aircraft engine. The bypass ratio may be defined as the amount of air delivered into the bypass duct divided by the amount delivered into the core flow. In a further example, the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than ten (10), the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and the low pressure turbine 46 has a pressure ratio that is greater than about 5. In one disclosed embodiment, the engine 20 bypass ratio is greater than about ten (10:1), the fan diameter is significantly larger than that of the low pressure compressor 44, and the low pressure turbine 46 and the low pressure turbine has a pressure ratio that is greater than about 5:1. Low pressure turbine 46 pressure ratio is the total pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle. The geared architecture 48 may be a star gear arrangement such that the fan will rotate in a different direction than the low spool. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.


A greatest amount of thrust is provided by the bypass flow B due to the high bypass ratio. The fan section 22 of the engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet. The flight condition of 0.8 Mach and 35,000 ft, with the engine at its best fuel consumption—also known as “bucket cruise Thrust Specific Fuel Consumption (‘TSFC’)”—is the industry standard parameter of lbm of fuel being burned per hour divided by lbf of thrust the engine produces at that minimum point. “Low fan pressure ratio” is the pressure ratio across the fan blade alone, before the Fan Exit Guide Vane (“FEGV”) system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram deg R)/518.7){circumflex over ( )}0.5]. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second at the same cruise point.



FIG. 2 shows detail of an engine 120, which may generally have the features of engine 20 of FIG. 1. A fan 122 is positioned upstream of a low pressure compressor 124, which is upstream of a high pressure compressor 126. A combustor 128 is positioned downstream of the high pressure compressor 126. A mid-turbine frame 142 may be positioned at a downstream end of the high pressure turbine 130, and supports a bearing 138, shown schematically, to support the aft end of the high pressure turbine 130, and a high pressure spool 132. A low pressure turbine 134 is positioned downstream of a mid-turbine frame 142. A low spool 136, driven by the low pressure turbine 134, drives the low pressure compressor 124. The speed change mechanism 48 causes the fan 122 to rotate at a different speed than the low pressure compressor 134. In embodiments of this invention, the speed input to output ratio for the speed change mechanism is above or equal to 2.3:1, and up to less than or equal to 13:1. The gear also causes fan 122 to rotate in an opposed direction relative to the low pressure compressor 124. As mentioned above, a star gear arrangement may be utilized to cause the fan 122 to rotate in the opposed direction (“+”) relative to the low pressure compressor 124. In this embodiment the fan generally has less than 26 blades, and the low pressure turbine has at least three stages, and up to six stages. The high pressure turbine generally has one or two stages as shown.


In this particular embodiment, the low pressure compressor 124 and the low pressure turbine 134 rotate in one direction (“−”) and the high pressure turbine 130, the high pressure compressor 126, rotate in the same direction (“−”).


A strut 140 is shown between the low pressure compressor 124 and the high pressure compressor 126. The strut 140 spans the gas path, and has an airfoil shape, or at least a streamline shape. The combination of a blade at the exit of the low pressure compressor 124, the strut 140, and a variable vane, and then the first blade of the high pressure compressor 126 is generally encompassed within the structure illustrated as the strut 140.


Since the compressor sections 124 and 126 rotate in the same direction, the several airfoils illustrated as the element 140 are required to do less turning of the air flow.


As will be explained below, since the turbine section is provided with a highly cambered vane, there is less turning required between the two turbine sections. Since the compressor is forcing flow with an adverse pressure gradient, and whereas the turbine has a favorable pressure gradient, this overall engine architecture is benefited by the illustrated combination.


Highly cambered inlet guide vanes 143 are positioned in a location intermediate the mid-turbine frame 142 and the most upstream rotor in the low pressure turbine 134. The vanes 143 must properly direct the products of combustion downstream of the high pressure turbine 130 as they approach the first rotor of the low pressure turbine 134. It is desirable for reducing the overall size of the low pressure turbine that the flow be properly directed when it initially encounters the first stage of the low pressure turbine section.


The above features achieve a more compact turbine section volume relative to the prior art, including both the high and low pressure turbines. A range of materials can be selected. As one example, by varying the materials for forming the low pressure turbine, the volume can be reduced through the use of more expensive and more exotic engineered materials, or alternatively, lower priced materials can be utilized. In three exemplary embodiments the first rotating blade of the Low Pressure Turbine can be a directionally solidified casting blade, a single crystal casting blade or a hollow, internally cooled blade. All three embodiments will change the turbine volume to be dramatically smaller than the prior art by increasing low pressure turbine speed. In addition, high efficiency blade cooling may be utilized to further result in a more compact turbine section.


Due to the compact turbine section, a power density, which may be defined as thrust in pounds force produced divided by the volume of the entire turbine section, may be optimized. The volume of the turbine section may be defined by an inlet of a first turbine vane in the high pressure turbine to the exit of the last rotating airfoil in the low pressure turbine, and may be expressed in cubic inches. The static thrust at the engine's flat rated Sea Level Takeoff condition divided by a turbine section volume is defined as power density. The sea level take-off flat-rated static thrust may be defined in lbs force, while the volume may be the volume from the annular inlet of the first turbine vane in the high pressure turbine to the annular exit of the downstream end of the last rotor section in the low pressure turbine. The maximum thrust may be Sea Level Takeoff Thrust “SLTO thrust” which is commonly defined as the flat-rated static thrust produced by the turbofan at sea-level.


The volume V of the turbine section may be best understood from FIG. 3. As shown, the frame 142 and vane 143 are intermediate the high pressure turbine section 130, and the low pressure turbine section 134. The volume V is illustrated by dashed line, and extends from an inner periphery I to an outer periphery O. The inner periphery is somewhat defined by the flowpath of the rotors, but also by the inner platform flow paths of vanes. The outer periphery is defined by the stator vanes and outer air seal structures along the flowpath. The volume extends from a most upstream end of the vane 400, typically its leading edge, and to the most downstream edge 401 of the last rotating airfoil in the low pressure turbine section 134. Typically this will be the trailing edge of that airfoil.


The power density in the disclosed gas turbine engine is much higher than in the prior art. Eight exemplary engines are shown below which incorporate turbine sections and overall engine drive systems and architectures as set forth in this application, and can be found in Table I as follows:














TABLE 1








Thrust
Turbine
Thrust/turbine




SLTO
section volume
section volume



Engine
(lbf)
from the Inlet
(lbf/in3)





















1
17,000
3,859
4.41



2
23,300
5,330
4.37



3
29,500
6,745
4.37



4
33,000
6,745
4.84



5
96,500
31,086
3.10



6
96,500
62,172
1.55



7
96,500
46,629
2.07



8
37,098
6,745
5.50










Thus, in embodiments, the power density would be greater than or equal to about 1.5 lbf/in3. More narrowly, the power density would be greater than or equal to about 2.0 lbf/in3.


Even more narrowly, the power density would be greater than or equal to about 3.0 lbf/in3.


More narrowly, the power density is greater than or equal to about 4.0 lbf/in3. More narrowly, the power density is greater than or equal to about 4.5 lbf/in3. Even more narrowly, the power density is greater than or equal to about 4.75 lbf/in3. Even more narrowly, the power density is greater than or equal to about 5.0 lbf/in3.


Also, in embodiments, the power density is less than or equal to about 5.5 lbf/in3.


While certain prior engines have had power densities greater than 1.5, and even greater than 3.2, such engines have been direct drive engines and not associated with a gear reduction. In particular, the power density of an engine known as PW4090 was about 1.92 lbf/in3, while the power density of an engine known as V2500 had a power density of 3.27 lbf/in3.


Engines made with the disclosed architecture, and including turbine sections as set forth in this application, and with modifications coming from the scope of the claims in this application, thus provide very high efficient operation, and increased fuel efficiency and lightweight relative to their trust capability.



FIG. 4 shows an embodiment 200, wherein there is a fan drive turbine 208 driving a shaft 206 to in turn drive a fan rotor 202. A gear reduction 204 may be positioned between the fan drive turbine 208 and the fan rotor 202. This gear reduction 204 may be structured and operate like the gear reduction disclosed above. A compressor rotor 210 is driven by an intermediate pressure turbine 212, and a second stage compressor rotor 214 is driven by a turbine rotor 216. A combustion section 218 is positioned intermediate the compressor rotor 214 and the turbine section 216.



FIG. 5 shows yet another embodiment 300 wherein a fan rotor 302 and a first stage compressor 304 rotate at a common speed. The gear reduction 306 (which may be structured as disclosed above) is intermediate the compressor rotor 304 and a shaft 308 which is driven by a low pressure turbine section.


The FIG. 4 or 5 engines may be utilized with the density features disclosed above.


Although an embodiment of this invention has been disclosed, a person of ordinary skill in this art would recognize that certain modifications would come within the scope of this application. For that reason, the following claims should be studied to determine the true scope and content of this invention.

Claims
  • 1. A gas turbine engine comprising: a propulsor section including a propulsor having a plurality of blades;a compressor section including a low pressure compressor and a high pressure compressor;a geared architecture;a turbine section including a low pressure turbine and a high pressure turbine, the low pressure turbine including three stages, the high pressure turbine including two stages, the high pressure turbine rotatable with the high pressure compressor as a high pressure spool about an engine longitudinal axis, and the low pressure turbine rotatable as a low pressure spool about the engine longitudinal axis, the propulsor driven by the low pressure turbine through the geared architecture, and the low pressure compressor having a greater number of stages than the high pressure turbine; anda power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section, the thrust is sea level take-off, flat-rated static thrust, and the volume of the turbine section is defined by an inlet of a first turbine vane in the high pressure turbine to an exit of a last rotating airfoil in the low pressure turbine.
  • 2. The gas turbine engine as recited in claim 1, wherein the geared architecture is an epicyclic gear train.
  • 3. The gas turbine engine as recited in claim 2, wherein a gear ratio of the geared architecture is greater than 2.3, and the propulsor has 26 or fewer blades.
  • 4. The gas turbine engine as recited in claim 3, wherein: the low pressure turbine includes no more than six stages; andthe low pressure turbine includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to the inlet as related to pressure at the outlet prior to an exhaust nozzle.
  • 5. The gas turbine engine as recited in claim 4, wherein a compressor rotor of the compressor section is driven by the low pressure turbine through the geared architecture.
  • 6. The gas turbine engine as recited in claim 4, wherein the low pressure compressor is rotatable with the low pressure turbine as the low pressure spool such that the low pressure turbine drives both the low pressure compressor and the geared architecture.
  • 7. The gas turbine engine as recited in claim 6, wherein the high pressure compressor includes eight stages.
  • 8. The gas turbine engine as recited in claim 7, wherein the turbine section includes a mid-turbine frame arranged between the high pressure turbine and the low pressure turbine with respect to the engine longitudinal axis, the mid-turbine frame supports a bearing, and the mid-turbine frame includes airfoils in a core airflow path.
  • 9. The gas turbine engine as recited in claim 8, wherein the power density is between 4.84 lbf/in3 and 5.5 lbf/in3.
  • 10. The gas turbine engine as recited in claim 9, wherein the high pressure spool and the low pressure spool are rotatable in a first direction about the engine longitudinal axis, and the propulsor is rotatable about the engine longitudinal axis in a second direction opposed to the first direction.
  • 11. The gas turbine engine as recited in claim 7, wherein the geared architecture is a star gear arrangement, the low pressure spool is rotatable in a first direction about the engine longitudinal axis, and the propulsor is rotatable in a second direction opposed to the first direction.
  • 12. The gas turbine engine as recited in claim 11, wherein: the propulsor section is a fan section, the propulsor is a fan, and an outer housing surrounds the fan to define a bypass duct;the fan section delivers a portion of air into the compressor section, and a portion of air into the bypass duct, and a bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than 10; andthe fan has a low fan pressure ratio of less than 1.45 across the fan blades alone at cruise at 0.8 Mach and 35,000 feet.
  • 13. The gas turbine engine as recited in claim 12, wherein the power density is at least 4.84 lbf/in3.
  • 14. The gas turbine engine as recited in claim 13, wherein the high pressure compressor and the low pressure compressor have an equal number of stages.
  • 15. The gas turbine engine as recited in claim 13, wherein the low pressure compressor includes a greater number of stages than the low pressure turbine.
  • 16. The gas turbine engine as recited in claim 13, wherein the turbine section includes a mid-turbine frame arranged between the high pressure turbine and the low pressure turbine with respect to the engine longitudinal axis, the mid-turbine frame supports a bearing arranged to support the high pressure turbine, and the mid-turbine frame includes airfoils in a core airflow path.
  • 17. The gas turbine engine as recited in claim 16, wherein the power density is greater than or equal to 5.0.
  • 18. The gas turbine engine as recited in claim 7, wherein the geared architecture is a planetary gear system.
  • 19. The gas turbine engine as recited in claim 18, wherein: the propulsor section is a fan section, the propulsor is a fan, and an outer housing surrounds the fan to define a bypass duct;the fan section delivers a portion of air into the compressor section, and a portion of air into the bypass duct, and a bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than 10; andthe fan has a low fan pressure ratio of less than 1.45 across the fan blades alone at cruise at 0.8 Mach and 35,000 feet.
  • 20. The gas turbine engine as recited in claim 19, wherein the power density is at least 4.84 lbf/in3.
  • 21. The gas turbine engine as recited in claim 20, wherein the high pressure compressor and the low pressure compressor have an equal number of stages.
  • 22. The gas turbine engine as recited in claim 20, wherein the low pressure compressor includes a greater number of stages than the low pressure turbine.
  • 23. The gas turbine engine as recited in claim 20, wherein the turbine section includes a mid-turbine frame arranged between the high pressure turbine and the low pressure turbine with respect to the engine longitudinal axis, the mid-turbine frame supports a bearing arranged to support the high pressure turbine, and the mid-turbine frame includes airfoils in a core airflow path.
  • 24. The gas turbine engine as recited in claim 23, wherein the power density is greater than or equal to 5.0.
  • 25. A gas turbine engine comprising: a propulsor section including a propulsor having a plurality of blades;a compressor section including a low pressure compressor and a high pressure compressor;a geared architecture;a turbine section including a low pressure turbine and a high pressure turbine, the low pressure turbine including three stages, the high pressure turbine including two stages, the high pressure turbine rotatable with the high pressure compressor as a high pressure spool about an engine longitudinal axis, the low pressure turbine rotatable as a low pressure spool about the engine longitudinal axis, the propulsor driven by the low pressure turbine through the geared architecture, the turbine section including a mid-turbine frame arranged between the high pressure turbine and the low pressure turbine with respect to the engine longitudinal axis, and the mid-turbine frame supporting a bearing arranged to support the high pressure turbine; anda power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, wherein the power density is a ratio of a thrust provided by the engine to a volume of the turbine section, and the thrust is sea level take-off, flat-rated static thrust, and the volume of the turbine section is defined by an inlet of a first turbine vane in the high pressure turbine to an exit of a last rotating airfoil in the low pressure turbine.
  • 26. The gas turbine engine as recited in claim 25, wherein the geared architecture is an epicyclic gear train.
  • 27. The gas turbine engine as recited in claim 26, wherein: the low pressure turbine includes no more than six stages; andthe low pressure turbine includes an inlet, an outlet and a pressure ratio of greater than 5, the pressure ratio being pressure measured prior to the inlet as related to pressure at the outlet prior to an exhaust nozzle.
  • 28. The gas turbine engine as recited in claim 27, wherein: the propulsor section is a fan section, the propulsor is a fan, and an outer housing surrounds the fan to define a bypass duct;the fan section delivers a portion of air into the compressor section, and a portion of air into the bypass duct, and a bypass ratio, which is defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section, is greater than 10; andthe fan has a low fan pressure ratio of less than 1.45 across the fan blades alone at cruise at 0.8 Mach and 35,000 feet.
  • 29. The gas turbine engine as recited in claim 28, wherein the geared architecture is a star gear arrangement, the low pressure spool is rotatable in a first direction about the engine longitudinal axis, and the propulsor is rotatable in a second direction opposed to the first direction.
  • 30. The gas turbine engine as recited in claim 28, wherein the geared architecture is a planetary gear system.
CROSS-REFERENCE TO RELATED APPLICATION

This application is a continuation of U.S. patent application Ser. No. 17/037,916, filed Sep. 30, 2020, which is a continuation of U.S. patent application Ser. No. 16/186,811, filed Nov. 12, 2018, which is a continuation of U.S. patent application Ser. No. 14/593,056, filed Jan. 9, 2015, which is a continuation-in-part of U.S. patent application Ser. No. 13/446,312, filed Apr. 13, 2012, which claims priority to U.S. Provisional Application No. 61/619,111, filed Apr. 2, 2012.

US Referenced Citations (243)
Number Name Date Kind
2258792 New Oct 1941 A
2608821 Hunsaker Sep 1952 A
2620157 Walton et al. Dec 1952 A
2748623 Hill Jun 1956 A
2936655 Peterson et al. May 1960 A
3021731 Stoeckicht Feb 1962 A
3033002 William et al. May 1962 A
3111005 Howell et al. Nov 1963 A
3194487 Tyler et al. Jul 1965 A
3250512 Alexander et al. May 1966 A
3287906 McCormick Nov 1966 A
3352178 Lindgren et al. Nov 1967 A
3412560 Gaubatz Nov 1968 A
3434288 Petrie et al. Mar 1969 A
3526092 Steel et al. Sep 1970 A
3527054 Hemsworth et al. Sep 1970 A
3620020 Halliwell et al. Nov 1971 A
3664612 Skidmore et al. May 1972 A
3673802 Krebs et al. Jul 1972 A
3713748 Langley Jan 1973 A
3729957 Petrie et al. May 1973 A
3747343 Rosen Jul 1973 A
3754484 Roberts Aug 1973 A
3765623 Donelson et al. Oct 1973 A
3820719 Clark et al. Jun 1974 A
3843277 Ehrich Oct 1974 A
3861139 Jones Jan 1975 A
3876330 Pearson et al. Apr 1975 A
3886737 Grieb Jun 1975 A
3892358 Gisslen Jul 1975 A
3932058 Harner et al. Jan 1976 A
3935558 Miller et al. Jan 1976 A
3986720 Knudsen et al. Oct 1976 A
3988889 Chamay et al. Nov 1976 A
4005575 Scott et al. Feb 1977 A
4130872 Haloff Dec 1978 A
4220171 Ruehr et al. Sep 1980 A
4240250 Harris Dec 1980 A
4251987 Adamson Feb 1981 A
4284174 Salvana et al. Aug 1981 A
4289360 Zirin Sep 1981 A
4304522 Newland Dec 1981 A
4446696 Sargisson et al. May 1984 A
4448019 Klees May 1984 A
4463553 Boudigues Aug 1984 A
4478551 Honeycutt, Jr. et al. Oct 1984 A
4611464 Hetzer et al. Sep 1986 A
4649114 Miltenburger et al. Mar 1987 A
4660376 Johnson Apr 1987 A
4693616 Rohra et al. Sep 1987 A
4696156 Burr et al. Sep 1987 A
4722357 Wynosky Feb 1988 A
4809498 Giffin, III et al. Mar 1989 A
4827712 Coplin May 1989 A
4887424 Geidel et al. Dec 1989 A
4909031 Grieb Mar 1990 A
4916894 Adamson et al. Apr 1990 A
4947642 Grieb et al. Aug 1990 A
4979362 Vershure, Jr. Dec 1990 A
5010729 Adamson et al. Apr 1991 A
5058617 Stockman et al. Oct 1991 A
5074109 Mandet et al. Dec 1991 A
5102379 Pagluica et al. Apr 1992 A
5141400 Murphy et al. Aug 1992 A
5307622 Ciokajlo et al. May 1994 A
5317877 Stuart Jun 1994 A
5361580 Ciokajlo et al. Nov 1994 A
5433674 Sheridan et al. Jul 1995 A
5447411 Curley et al. Sep 1995 A
5466198 McKibbin et al. Nov 1995 A
5520512 Walker et al. May 1996 A
5524847 Brodell et al. Jun 1996 A
5634767 Dawson Jun 1997 A
5677060 Terentieva et al. Oct 1997 A
5778659 Duesler et al. Jul 1998 A
5857836 Stickler et al. Jan 1999 A
5915917 Eveker et al. Jun 1999 A
5971706 Glista et al. Oct 1999 A
5975841 Lindemuth et al. Nov 1999 A
5985470 Spitsberg et al. Nov 1999 A
6209311 Itoh et al. Apr 2001 B1
6223616 Sheridan May 2001 B1
6315815 Spadaccini et al. Nov 2001 B1
6318070 Rey et al. Nov 2001 B1
6339927 DiPietro, Jr. Jan 2002 B1
6378308 Pfluger Apr 2002 B1
6381948 Klingels May 2002 B1
6387456 Eaton, Jr. et al. May 2002 B1
6506022 Bunker Jan 2003 B2
6517341 Brun et al. Feb 2003 B1
6607165 Manteiga et al. Aug 2003 B1
6619030 Seda et al. Sep 2003 B1
6647707 Dev Nov 2003 B2
6669393 Schilling Dec 2003 B2
6708482 Seda Mar 2004 B2
6709492 Spadaccini et al. Mar 2004 B1
6732502 Seda et al. May 2004 B2
6814541 Evans et al. Nov 2004 B2
6855089 Poulin et al. Feb 2005 B2
6883303 Seda Apr 2005 B1
7021042 Law Apr 2006 B2
7219490 Dev May 2007 B2
7328580 Lee et al. Feb 2008 B2
7374403 Decker et al. May 2008 B2
7409819 Henry Aug 2008 B2
7451592 Taylor et al. Nov 2008 B2
7513102 Moniz et al. Apr 2009 B2
7513103 Orlando et al. Apr 2009 B2
7591754 Duong et al. Sep 2009 B2
7594404 Somanath et al. Sep 2009 B2
7600370 Dawson Oct 2009 B2
7626259 Wehrly, Jr. et al. Dec 2009 B2
7632064 Somanath et al. Dec 2009 B2
7662059 McCune Feb 2010 B2
7685808 Orlando et al. Mar 2010 B2
7694505 Schilling Apr 2010 B2
7716914 Schilling May 2010 B2
7721549 Baran May 2010 B2
7762086 Schwark Jul 2010 B2
7765786 Klingels et al. Aug 2010 B2
7806651 Kennepohl et al. Oct 2010 B2
7824305 Duong et al. Nov 2010 B2
7828682 Smook Nov 2010 B2
7832193 Orlando et al. Nov 2010 B2
7882683 Studer et al. Feb 2011 B2
7882693 Schilling Feb 2011 B2
7926259 Orlando et al. Apr 2011 B2
7926260 Sheridan et al. Apr 2011 B2
7997868 Liang Aug 2011 B1
8002520 Dawson et al. Aug 2011 B2
8015798 Norris et al. Sep 2011 B2
8015828 Moniz et al. Sep 2011 B2
8061969 Durocher et al. Nov 2011 B2
8083472 Maguire Dec 2011 B2
8083474 Hashimoto et al. Dec 2011 B2
8091371 Durocher et al. Jan 2012 B2
8191352 Schilling Jun 2012 B2
8205432 Sheridan Jun 2012 B2
8297916 McCune et al. Oct 2012 B1
8297917 McCune et al. Oct 2012 B1
8747055 McCune et al. Jun 2014 B2
8756908 Sheridan et al. Jun 2014 B2
8834099 Topol et al. Sep 2014 B1
8899915 McCune et al. Dec 2014 B2
9133729 McCune et al. Sep 2015 B1
9297917 Mah et al. Mar 2016 B2
9540948 Schwarz et al. Jan 2017 B2
9631558 McCune et al. Apr 2017 B2
20030163983 Seda et al. Sep 2003 A1
20030163984 Seda et al. Sep 2003 A1
20050025627 Harding et al. Feb 2005 A1
20050226720 Harvey et al. Oct 2005 A1
20050241292 Taylor et al. Nov 2005 A1
20050279100 Graziosi et al. Dec 2005 A1
20060101804 Stretton May 2006 A1
20060130456 Suciu et al. Jun 2006 A1
20060179818 Merchant Aug 2006 A1
20060228206 Decker et al. Oct 2006 A1
20060236675 Weiler Oct 2006 A1
20060288686 Cherry et al. Dec 2006 A1
20070012026 Dev Jan 2007 A1
20070022735 Henry et al. Feb 2007 A1
20070084183 Moniz et al. Apr 2007 A1
20070084189 Moniz et al. Apr 2007 A1
20070087892 Orlando et al. Apr 2007 A1
20070265133 Smook Nov 2007 A1
20080003096 Kohli et al. Jan 2008 A1
20080022653 Schilling Jan 2008 A1
20080098714 Orlando et al. May 2008 A1
20080098718 Henry et al. May 2008 A1
20080112791 Lee et al. May 2008 A1
20080116009 Sheridan et al. May 2008 A1
20080148707 Schilling Jun 2008 A1
20080148881 Moniz et al. Jun 2008 A1
20080190095 Baran Aug 2008 A1
20080317588 Grabowski et al. Dec 2008 A1
20090007569 Lemmers, Jr. et al. Jan 2009 A1
20090056306 Suciu et al. Mar 2009 A1
20090056343 Suciu et al. Mar 2009 A1
20090080700 Lau et al. Mar 2009 A1
20090090096 Sheridan Apr 2009 A1
20090092480 Kupratis Apr 2009 A1
20090092494 Cairo et al. Apr 2009 A1
20090094961 Stern Apr 2009 A1
20090097967 Smith et al. Apr 2009 A1
20090145102 Roberge et al. Jun 2009 A1
20090229242 Schwark Sep 2009 A1
20090245997 Hurwitz et al. Oct 2009 A1
20090266912 Gukeisen Oct 2009 A1
20090288384 Granitz et al. Nov 2009 A1
20090293445 Ress, Jr. Dec 2009 A1
20090304518 Kodama et al. Dec 2009 A1
20090314881 Suciu et al. Dec 2009 A1
20100005778 Chaudhry Jan 2010 A1
20100005810 Jarrell et al. Jan 2010 A1
20100080700 Venter Apr 2010 A1
20100089019 Knight et al. Apr 2010 A1
20100105516 Sheridan et al. Apr 2010 A1
20100126141 Schilling May 2010 A1
20100132376 Durocher et al. Jun 2010 A1
20100148396 Xie et al. Jun 2010 A1
20100162683 Grabowski et al. Jul 2010 A1
20100212281 Sheridan Aug 2010 A1
20100218478 Merry et al. Sep 2010 A1
20100218483 Smith Sep 2010 A1
20100326050 Schilling et al. Dec 2010 A1
20100331139 McCune Dec 2010 A1
20110081237 Durocher et al. Apr 2011 A1
20110159797 Beltman et al. Jun 2011 A1
20110293423 Bunker et al. Dec 2011 A1
20120017603 Bart et al. Jan 2012 A1
20120124964 Hasel et al. May 2012 A1
20120171018 Hasel et al. Jul 2012 A1
20120291449 Adams et al. Nov 2012 A1
20130186058 Sheridan et al. Jul 2013 A1
20130192191 Schwarz et al. Aug 2013 A1
20130192196 Suciu et al. Aug 2013 A1
20130192200 Kupratis et al. Aug 2013 A1
20130192201 Kupratis et al. Aug 2013 A1
20130192258 Kupratis et al. Aug 2013 A1
20130192263 Suciu et al. Aug 2013 A1
20130192266 Houston et al. Aug 2013 A1
20130195621 Schwarz et al. Aug 2013 A1
20130195648 Schwarz et al. Aug 2013 A1
20130223986 Kupratis et al. Aug 2013 A1
20130255219 Schwarz et al. Oct 2013 A1
20130259653 Schwarz et al. Oct 2013 A1
20130259654 Kupratis et al. Oct 2013 A1
20130283819 Schwarz et al. Oct 2013 A1
20130287575 McCune et al. Oct 2013 A1
20130292196 Ooka Nov 2013 A1
20130318998 Schwarz et al. Dec 2013 A1
20130336791 McCune et al. Dec 2013 A1
20140020404 Sheridan et al. Jan 2014 A1
20140109548 Virkler Apr 2014 A1
20140130479 Schwarz et al. May 2014 A1
20140196472 Kupratis et al. Jul 2014 A1
20140234079 McCune et al. Aug 2014 A1
20140271135 Sheridan et al. Sep 2014 A1
20150089959 Merry et al. Apr 2015 A1
20150096303 Schwarz et al. Apr 2015 A1
20150121844 Kupratis et al. May 2015 A1
20160032826 Rued et al. Feb 2016 A1
Foreign Referenced Citations (48)
Number Date Country
1952367 Apr 2007 CN
0791383 Aug 1997 EP
1142850 Oct 2001 EP
1340902 Sep 2003 EP
1403500 Mar 2004 EP
1577491 Sep 2005 EP
1607574 Dec 2005 EP
1703085 Sep 2006 EP
1712738 Oct 2006 EP
1777370 Apr 2007 EP
1921253 May 2008 EP
1921290 May 2008 EP
2071139 Jun 2009 EP
2071153 Jun 2009 EP
2192269 Jun 2010 EP
2192273 Jun 2010 EP
2270315 Jan 2011 EP
2532841 Dec 2012 EP
2532858 Dec 2012 EP
2551489 Jan 2013 EP
2809575 Dec 2014 EP
2809931 Dec 2014 EP
2809934 Dec 2014 EP
2809939 Dec 2014 EP
2809953 Dec 2014 EP
2811120 Dec 2014 EP
2841718 Mar 2015 EP
2896785 Jul 2015 EP
3032084 Jun 2016 EP
2809931 Jul 2016 EP
3070315 Sep 2016 EP
3070316 Sep 2016 EP
2563865 Nov 1985 FR
2912181 Aug 2008 FR
745239 Feb 1956 GB
1516041 Jun 1978 GB
2041090 Sep 1980 GB
2426792 Dec 2006 GB
S57171032 Oct 1982 JP
2014156861 Aug 2014 JP
2007038674 Apr 2007 WO
2013102191 Jul 2013 WO
2013116257 Aug 2013 WO
2013116262 Aug 2013 WO
2014018142 Jan 2014 WO
2014028085 Feb 2014 WO
2014047040 Mar 2014 WO
2015031143 Mar 2015 WO
Non-Patent Literature Citations (529)
Entry
2003 NASA seal/secondary air system workshop. (2003). NASA/CP-2004-212963/vol. 1. Sep. 1, 2004. pp. 1-408.
(2012). Gas Power Cycle—Jet Propulsion Technology, A case study. Machine Design Magazine. Nov. 5, 1998. Retrieved from: http://machinedesign.com/content/pw8000-0820.
About GasTurb. Retrieved Jun. 26, 2018 from: http://gasturb.de/about-gasturb.html.
Adamson, A.P. (1975). Quiet Clean Short-Haul Experimental Engine (QCSEE) design rationale. Society of Automotive Engineers. Air Transportation Meeting. Hartford, CT. May 6-8, 1975. pp. 1-9.
Aerospace Information Report. (2008). Advanced ducted propulsor in-flight thrust determination. SAE International AIR5450. Aug. 2008. p. 1-392.
Agarwal, B.D and Broutman, L.J. (1990). Analysis and performance of fiber composites, 2nd Edition. John Wiley & Sons, Inc. New York: New York. pp. 1 -11, 13-23, 26-33, 50-51, 56-58, 60-61, 64-71, 87-89, 324-329, 436-437.
AGMA Information Sheet, “Double Helical Epicyclic Gear Units,” ANSI-AGMA 940-A09, Approved Jan. 6, 2009, pp. 1-22.
AGMA Standard (1997) Design and selection of components for enclosed gear drives. lexandria, VA: American Gear Manufacturers Association. pp. 1-48.
AGMA Standard (1999). Flexible couplings—Mass elastic properties and other characteristics. Alexandria, VA: American Gear Manufacturers Association. pp. 1-46.
AGMA Standard (2006). Design manual for enclosed epicyclic gear drives. Alexandria, VA: American Gear Manufacturers Association. pp. 1-104.
Ahmad, F. and Mizramoghadam, A.V. (1999). Single v. two stage high pressure turbine design of modern aero engines. ASME. Prestend at the International Gast Turbine & Aeroengine Congress & Exhibition. Indianapolis, Indiana. Jun. 7-10, 1999. pp. 1-9.
Amezketa, M., Iriarte, X., Ros, J., and Pintor, J. (2009). Dynamic model of a helical gear pair with backlash and angle-varying mesh stiffness. Multibody Dynamics 2009, ECCOMAS Thematic Conference. 2009. pp. 1-36.
Anderson, N.E., Loewenthal, S.H., and Black, J.D. (1984). An analytical method to predict efficiency of aircraft gearboxes. NASA Technical Memorandum prepared for the Twentieth Joint Propulsion Conference. Cincinnati, OH. Jun. 11-13, 1984. pp. 1-25.
Anderson, R.D. (1985). Advanced Propfan Engine Technology (APET) definition study, single and counter-rotation gearbox/pitch change mechanism design. NASA CR-168115. Jul. 1, 1985 pp. 1-289.
Annex to the Notice on Article 94(3) EPC issued by the Examination Division for European Patent Application No. 13837107.5 dated Jan. 25, 2019.
Annexe Mesures—Methodologie de mesure et de calcul, cited in: Notice of Opposition for European Patent No. 2809932 mailed Oct. 1, 2018.
Annexe Mesures—Methodologie de mesure et de calcul. STF495M-4 and STF495M-5. Cited in: Documents by Rolls-Royce in anticipation of Oral Proceedings for Opposition of European Patent No. 2809932 dated Jan. 20, 2020.
Annotation of Edkins D.P., et al., “TF34 Turbofan Quiet Engine Study,” Final Report prepared for NASA, NASA-CR-120914, Jan. 1, 1972, p. 92.
Annotation of Gray D.E., “Energy Efficient Engine Preliminary Design and Integration Studies,” Prepared for NASA, NASA CR-135396, Nov. 1978, p. 70.
Appellant's Reply Brief. Raytheon Technologies Corporation v. General Electric Company. Inter Partes Review No. IPR2018-01442. Filed Oct. 26, 2020. pp. 1-32.
ASME International Gas Turbine Institute, “Trends in the Global Energy Supply and Implications for the Turbomachinery Industry”, Global Gas Turbine News, Apr. 2013, vol. 53, Issue. 2, pp. 49-53.
Attestation for Didier Escure Signed Sep. 17, 2018, cited in: Notice of Opposition for European Patent No. 2809932 mailed Oct. 1, 2018.
Attestation of Philippe Pellier signed Apr. 12, 2017, cited in: Notice of Opposition by Safran for European Patent No. EP 2809931 dated Apr. 20, 2017.
Avco Lycoming Divison. ALF 502L Maintenance Manual. Apr. 1981. pp. 1-118.
Aviadvigatel D-110. Jane's Aero-engines, Aero-engines—Turbofan. Jun. 1, 2010.
Aviation Investigation Report A14Q0068. Uncontained turbine rotor failure. Transportation Safety Board of Canada. May 29, 2014. pp. 1-53.
Awker, R.W. (1986). Evaluation of propfan propulsion applied to general aviation. NASA CR-175020. Mar. 1, 1986. pp. 1-140.
Baker, R.W. (2000). Membrane technology and applications. New York, NY: McGraw-Hill. pp. 87-153.
Baskharone E.A., “Principles of Turbomachinery in Air-Breathing Engines,” Cambridge University Press, 2006, pp. 261-263.
Berton, J.J. and Guynn, M.D. (2012). Multi-objective optimization of a turbofan for an advanced, single-aisle transport. NASA/TM-2012-217428. pp. 1-26.
Bessarabov, D.G., Jacobs, E.P., Sanderson, R.D., and Beckman, I.N. (1996). Use of nonporous polymeric flat-sheet gas-separation membranes in a membrane-liquid contactor: experimental studies. Journal of Membrane Sciences, vol. 113. 1996. pp. 275-284.
Bijewitz J., et al., “Architectural Comparison of Advanced Ultra-High Bypass Ratio Turbofans for Medium to Long Range Application,” Deutscher Luft—und Raumfahrtkongress, 2014, pp. 1-12.
Bloomer, H.E. and Loeffler, I.J. (1982). QCSEE over-the-wing engine acoustic data. NASA-TM-82708. May 1, 1982. pp. 1-558.
Bloomer, H.E. and Samanich, N.E. (1982). QCSEE under-the-wing engine acoustic data. NASA-TM-82691. May 1, 1982. pp 1-28.
Bloomer, H.E. and Samanich, N.E. (1982). QCSEE under-the-wing enging-wing-flap aerodynamic profile characteristics. NASA-TM-82890. Sep. 1, 1982. pp. 1-48.
Bloomer, H.E., Loeffler, I.J., Kreim, W.J., and Coats, J.W. (1981). Comparison of NASA and contractor reslts from aeroacoustic tests of QCSEE OTW engine. NASA Technical Memorandum 81761. Apr. 1, 1981. pp. 1-30.
Boards of Appeal of the European Patent Office for European Patent Application No. 01992470.3, Sep. 27, 2016, 17 pages.
Bornstein, N. (1993). Oxidation of advanced intermetallic compounds. Journal de Physique IV, 1993, 03 (C9), pp. C9-367-C9-373.
Borzec R.L, “Reducteurs de vitesse a engrenages,” Techniques de L'Igenieur, Nov. 10, 1992, pp. 1-36.
Bradley A., “Presentation: Engine Design for the Environment,” Rolls-Royce, RAeS—Hamburg, Jun. 24, 2010, 64 pages.
Brennan, P.J. and Kroliczek, E.J. (1979). Heat pipe design handbook. Prepared for National Aeronautics and Space Administration by B & K Engineering, Inc. Jun. 1979. pp. 1-348.
Brief Communication from Opponent after Oral Proceedings for European Patent Application No. 13743283.7 (2809932), by Safran Aircraft Engines, dated Dec. 2, 2019.
Brief for Appellee. Raytheon Technologies Corporation v. General Electric Company. Inter Partes Review No. PR2018-01442. Filed Sep. 23, 2020. pp. 1-68.
Brines, G.L. (1990). The turbofan of tomorrow. Mechanical Engineering: The Journal of the American Society of Mechanical Engineers,108(8), 65-67.
Bucknell, R.L. (1973). Influence of fuels and lubricants on turbine engine design and performance, fuel and lubircant analyses. Final Technical Report, Mar. 1971-Mar. 1973. pp. 1-252.
Bunker, R.S. (2005). A review of shaped hole turbine film-cooling technology. Journal of Heat Transfer vol. 127. Apr. 2005. pp. 441-453.
Carney, K., Pereira, M. Revilock, and Matheny, P. (2003). Jet engine fan blade containment using two alternate geometries. 4th European LS-DYNA Users Conference. pp. 1-10.
CFM International CFM56, Jane's Aero-Engines, Janes by IHS Markit, Jan. 31, 2011, 36 pages.
Chapman J.W., et al., “Control Design for an Advanced Geared Turbofan Engine”, AIAA Joint Propulsion Conference 2017, Jul. 10, 2017-Jul. 12, 2017, Atlanta, GA, pp. 1-12.
Cheryan, M. (1998). Ultrafiltration and microfiltration handbook. Lancaster, PA: Tecnomic Publishing Company, Inc. pp. 171-236.
Ciepluch, C. (1977). Quiet clean short-haul experimental engine (QCSEE) under-the-wing (UTW) final design report. Prepared for NASA. NASA-CP-134847. Retreived from: https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19800075257.pdf.
Clarke, D.R. and Levi, C.G. (2003). Materials design for the next generation thermal barrier coatings. Annual. Rev. Mater. Res. vol. 33. 2003. pp. 383-417.
Cramoisi, G. Ed. (2012). Death in the Potomac: The crash of Air Florida Flight 90. Air Crash Investigations. Accident Report NTSB/AAR-82-8. p. 45-47.
Cusick, M. (1981). Avco Lycoming's ALF 502 high bypass fan engine. Society of Automotive Engineers, Inc. Business Aircraft Meeting & Exposition. Wichita, Kansas. Apr. 7-10, 1981. pp. 1-9.
Daggett, D.L., Brown, S.T., and Kawai, R.T. (2003). Ultra-efficient engine diameter study. NASA/CR-2003-212309. May 2003. pp. 1-52.
Dalton, III, W.N. (2003). Ultra high bypass ratio low noise engine study. NASA/CR-2003-212523. Nov. 2003. pp. 1-187.
Daly, M. Ed. (2008). Jane's Aero-Engine. Issue Twenty-three. Mar. 2008. p. 707-12.
Daly, M. Ed. (2010). Jane's Aero-Engine. Issue Twenty-seven. Mar. 2010. p. 633-636.
Damerau, J. (2014) What is the mesh stiffness of gears? Screen shot of query submitted by Vahid Dabbagh, answered by Dr. Jochan Damerau, Research General Managerat Bosch Corp., Japan. Retrieved from: https://www.researchgate.net/post/What_is_the_mesh_stiffness_of_gears.
Darrah, S. (1987). Jet fuel deoxygenation. Interim Report for Period Mar. 1987-Jul. 1988. pp. 1-22.
Dassault Falcon 900EX Easy Systems Summary. Retrieved from: http://www.smartcockpit.com/docs/F900EX-Engines.pdf pp. 1-31.
Datasheet. CF6-80C2 high-bypass turbofan engines. Retreived from https://geaviation.com/sites/default/files/datasheet-CF6-80C2.pdf.
Datasheet. CFM56-5B For the Airbus A320ceo family and CFM56-7B for the Boeing 737 family. https://www.cfmaeroengines.com/.
Datasheet. Genx™ high bypass turbofan engines. Retreived from: https://www.geaviation.com/sites/default/files/datasheet-genx pdf.
Davies, D. and Miller, D.C. (1971). A variable pitch fan for an ultra quiet demonstrator engine. 1976 Spring Convention: Seeds for Success in Civil Aircraft Design in the Next Two Decades. pp. 1-18.
Davis, D.G.M. (1973). Variable-pitch fans: Progress in Britain. Flight International. Apr. 19, 1973. pp. 615-617.
Decision Denying Institution of Inter Partes Review, General Electric Company, Petitioner v. United technologies Corp., Patent Owner, IPR2017-00522, U.S. Pat. No. 8,899,915, Entered Jun. 23, 2017, pp. 1-18.
Decision Institution of Inter Partes Review. General Electric Company, Petitioner v. United Technologies Corporation, Patent Owner. IPR2018 01442. U.S. Pat. No. 9,695,751. Entered Feb. 21, 2019. pp. 1-25.
Decision of the Opposition Division, European Patent No. 2949882 (Application No. 15175205.2) dated Nov. 26, 2018.
Decision of the Opposition Division for European Patent No. 2809931, dated Nov. 26, 2018, 12 pages.
Decision of the Opposition Division for European Patent No. 2811120 (14155460.0), dated Jan. 15, 2020.
Decision on Appeal for U.S. Appl. No. 13/446,194, dated Mar. 30, 2016, Appeal 2014-002599.
Decision on Appeal for U.S. Appl. No. 13/446,510, dated Feb. 26, 2016, Appeal 2014-001580.
Decision on Appeal for U.S. Appl. No. 13/558,605, dated Mar. 30, 2016, Appeal 2014-004476.
Decision Revoking European Patent EP2809939 (13786893.1) by the Opposition Division mailed Aug. 5, 2021.
Decker, S. and Clough, R. (2016). GE wins shot at voiding pratt patent in jet-engine clash. Bloomberg Technology. Retrieved from: https://www.bloomberg.com/news/articles/2016-06-30/ge-wins-shot-to-invalidate-pratt-airplane-engine-patent-in-u-s.
Declaration of Courtney H. Bailey, In re U.S. Pat. No. 8,511,605, Executed Jul. 19, 2016, pp. 1-4.
Declaration of Dr. Magdy Attia, In re U.S. Pat. No. 8,313,280, Executed Oct. 21, 2016, pp. 1-88.
Declaration of Dr. Magdy Attia, In re U.S. Pat. No. 8,517,668, Executed Dec. 8, 2016, pp. 1-81.
Declaration of Dr. Magdy Attia In re U.S. Pat. No. 9,695,751, Executed Jul. 12, 2018, pp. 1-114 and appendices.
Declaration of John Eaton, Ph.D. In re U.S. Pat. No. 8,869,568, Executed Mar. 28, 2016, pp. 1-87.
Declaration of Magdy Attia in re U.S. Pat. No. 8,899,915, Executed Dec. 13, 2016, pp. 1-71.
Declaration of Raymond Drago., In re U.S. Pat. No. 8,297,916, IPR2018-01172, Executed May 29, 2018, pp. 1-115.
Declaration of Raymond Drago, In re U.S. Pat. No. 8,899,915 under 37 C.F.R. 1.68. Executed Dec. 9, 2016, pp. 1-38.
Declaration of Reza Abhari, In re U.S. Pat. No. 8,448,895, Executed Nov. 28, 2016, pp. 1-81.
Declaration of Reza Abhari. In re U.S. Pat. No. 8,695,920, claims 1-4, 7-14, 17 and 19, Executed Nov. 29, 2016, pp. 1-102.
Declaration of Reza Abhari. In re U.S. Pat. No. 8,695,920. Executed Nov. 30, 2016, pp. 1-67.
Declaration of Reza Abhari, Ph.D. In re U.S. Pat. No. 8,844,265, Executed Jun. 28, 2016, pp. 1-91.
DeFeo, A. and Kulina, M. (1977). Quiet clean short-haul experimental engine (QCSEE) main reduction gears detailed design final report. Prepared for NASA. NASA-CR-134872. Jul. 1977. pp. 1-157.
Diagram of Prior Art V2500 and PW4090 Engines, 1 page.
Dickey, T.A. and Dobak, E.R. (1972). The evolution and development status of ALF 502 turbofan engine. National Aerospace Engineering and Manufacturing Meeting. San Diego, California. Oct. 2-5, 1972. pp. 1-12.
Dr. Raymond G. Tronzo v. Biomet Inc. 156 F.3d 1154, 1998.
Drago, R.J. (1974). Heavy-lift helicopter brings up drive ideas. Power Transmission Design. Mar. 1987. pp. 1-15.
Drago, R.J. and Margasahayam, R.N. (1987). Stress analysis of planet gears with integral bearings; 3D finite-element model development and test validation. 1987 MSC NASTRAN World Users Conference. Los Angeles, CA. Mar. 1987. pp. 1-14.
Dudley, D.W., Ed. (1954). Handbook of practical gear design. Lancaster, PA: Technomic Publishing Company, Inc. pp. 3.96-102 and 8.12-18.
Dudley, D.W., Ed. (1962). Gear handbook. New York, NY: McGraw-Hill. pp. 14-17 (TOC, Preface, and Index).
Dudley, D.W., Ed. (1962). Gear handbook. New York, NY: McGraw-Hill. pp. 3.14-18 and 12.7-12.21.
Dudley, D.W., Ed. (1994). Practical gear design. New York, NY: McGraw-Hill. pp. 119-124.
EASA Type-Certificate Data Sheet for PW1500G Series Engines. Feb. 24, 2021. pp. 1-17.
“EASA Type-Certificate Data Sheet RB211 Trent 800 Series Engines,” EASA, TCDS E.047, Issue 02, Oct. 10, 2013.
Honeywell TFE731 Pilot Tips. pp. 1-143.
Honeywell TFE731-5AR to -5BR Engine Conversion Program. Sep. 2005. pp. 1-4.
Horikoshi, S. and Serpone, N. (2013). Introduction to nanoparticles. Microwaves in nanoparticle synthesis. Wiley-VCH Verlag GmbH & Co. KGaA. pp. 1-24.
Howard, D.F. (1976). QCSEE preliminary under the wing flight propulsion system analysis report. NASA CR-134868 Feb. 1, 1976. pp. 1-260.
Howe, D.C. and Wynosky, T.A. (1985). Energy efficient engine program advanced turbofan nacelle definition study. NASA CR-174942. May 1, 1985. pp. 174.
Howe, D.C., and Wynosky, T.A. (1985). Energy efficient engine program advanced turbofan nacelle definition study. NASA-CR-174942. May 1985. pp. 1-60.
Howe, D.C., and Wynosky, T.A. (1985). Energy efficient engine program advanced turbofan nacelle definition study. NASA-CR-174942. May 1985. University of Washington dated Dec. 13, 1990. pp. 1-14.
Huang, H., Sobel, D.R., and Spadaccini, L.J. (2002). Endothermic heat-sink of hydrocarbon fuels for scramjet cooling. AIAA/ASME/SAE/ASEE, Jul. 2002. pp. 1-7.
Hughes, C. (2002). Aerodynamic performance of scale-model turbofan outlet guide vanes designed for low noise. Prepared for the 40th Aerospace Sciences Meeting and Exhibit. Reno, NV. NASA/TM-2001-211352. Jan. 14-17, 2002. pp. 1-38.
Hughes, C. (2010). Geared turbofan technology. NASA Environmentally Responsible Aviation Project. Green Aviation Summit. NASA Ames Research Center. Sep. 8-9, 2010. pp. 1-8.
Interlocutory decision in opposition proceedings for European Patent Application No. 13743042.7 mailed Nov. 26, 2018.
Interlocutory decision in opposition proceedings for European Patent Application No. 13778330.4 mailed May 17, 2021.
International Preliminary Report on Patentability for International Application No. PCT/US2013/022378, dated Aug. 14, 2014, 9 pages.
International Preliminary Report on Patentability for PCT Application No. PCT/US2013/034518 dated Oct. 16, 2014.
International Preliminary Report on Patentability for PCT Application No. PCT/US2013/037675, dated Nov. 6, 2014, 13 pages.
International Preliminary Report on Patentability of PCT Application No. PCT/US2013/023559, dated Aug. 14, 2014, 7 pages.
International Preliminary Report on Patentability of PCT Application No. PCT/US2013/023715, dated Aug. 14, 2014, 8 pages.
International Preliminary Report on Patentability of PCT Application No. PCT/US2013/023719, dated Aug. 14, 2014, 6 pages.
International Preliminary Report on Patentability of PCT Application No. PCT/US2013/023724, dated Aug. 14, 2014, 9 pages.
International Preliminary Report on Patentability of PCT Application No. PCT/US2013/023730, dated Aug. 14, 2014, 13 pages.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/022388, dated Dec. 30, 2013.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/023559 dated Nov. 5, 2013.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/023603, dated Aug. 27, 2013, 13 pages.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/023715, dated Aug. 20, 2013, 10 pages.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/023719 dated Apr. 4, 2013.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/023724, dated Mar. 26, 2013, 11 pages.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/023730, dated Mar. 12, 2013, 14 pages.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/034518, dated Nov. 22, 2013, 8 pages.
International Search Report and Written Opinion for PCT Application No. PCT/US2013/037675 dated Mar. 7, 2014.
International Search Report and Written Opinion from parent counterpart PCT Application PCT/US2013/022378, dated Sep. 13, 2013, 10 pages.
Ivchenko-Progress AI-727M. Jane's Aero-engines, Aero-engines—Turbofan. Nov. 27, 2011.
Ivchenko-Progress D-436. Jane's Aero-engines, Aero-engines—Turbofan. Feb. 8, 2012.
Ivchenko-Progress D-727. Jane's Aero-engines, Aero-engines—Turbofan. Feb. 7, 2007.
Jacobson, N.S. (1993). Corrosion of silicon-based ceramics in combustion environments. J. Am. Ceram. Soc. 76(1). pp. 3-28.
Jeng, Y.-L., Lavernia, E.J. (1994). Processing of molybdenum disilicide. J. of Mat. Sci. vol. 29. 1994. pp. 2557-2571.
Johnston, R.P. and Hemsworth, M.C. (1978). Energy efficient engine preliminary design and integration studies. Jun. 1, 1978. pp. 1-28.
Johnston, R.P., Hirschkron, R., Koch, C.C., Neitzel, R.E., and Vinson, P.W. (1978). Energy efficient engine: Preliminary design and integration study—final report. NASA CR-135444. Sep. 1978. pp. 1-401.
Jorgensen, P.J., Wadsworth, M.E., and Cutler, I.B. (1961). Effects of water vapor on oxidation of silicon carbide. J. Am. Ceram. Soc. 44(6). pp. 248-261.
Kahn, H., Tayebi, N., Ballarini, R., Mullen, R.L., Heuer, A.H. (2000). Fracture toughness of polysilicon MEMS devices. Sensors and Actuators vol. 82. 2000. pp. 274-280.
Kandebo, S.W. (1998). Geared-Turbofan engine design targets cost, complexity. Aviation Week & Space Technology, 148(8). p. 34-5.
Kandebo, S.W. (1998). Pratt & Whitney launches geared turbofan engine. Aviation Week & Space Technology, 148(8). p. 32-4.
Kaplan, B., Nicke, E., Voss, C. (2006), Design of a highly efficient low-noise fan for ultra-high bypass engines. Proceedings of GT2006 for ASME Turbo Expo 2006: Power for Land, Sea and Air. Barcelona, SP. May 8-11, 2006. pp 1-10.
Kasuba, R. and August, R. (1984). Gear mesh stiffness and load sharing in planetary gearing. American Society of Mechanical Engineers, Design Engineering Technical Conference, Cambridge, MA. Oct. 7-10, 1984. pp. 1-6.
Kerrebrock, J.L. (1977). Aircraft engines and gas turbines. Cambridge, MA: The MIT Press. p. 11.
Knip, Jr., G. (1987). Analysis of an advanced technology subsonic turbofan incorporating revolutionary materials. NASA Technical Memorandum. May 1987. pp. 1-23.
Kojima, Y., Usuki, A. Kawasumi, M., Okada, A., Fukushim, Y., Kurauchi, T., and Kamigaito, O. (1992). Mechanical properties of nylon 6-clay hybrid. Journal of Materials Research, 8(5), 1185-1189.
Kollar, L.P. and Springer, G.S. (2003). Mechanics of composite structures. Cambridge, UK: Cambridge University Press. p. 465.
Krantz, T.L. (1990). Experimental and analytical evaluation of efficiency of helicopter planetary stage. NASA Technical Paper. Nov. 1990. pp. 1-19.
Krenkel, W., Naslain, R., and Schneider, H. Eds. (2001). High temperature ceramic matrix composites pp. 224-229. Weinheim, DE: Wiley-VCH Verlag GmbH.
Neitzel, R., Lee, R., and Chamay, A.J. (1973). Engine and installation preliminary design. Jun. 1, 1973. pp. 1-333.
Neitzel, R.E., Hirschkron, R. and Johnston, R.P. (1976). Study of unconventional aircraft engines designed for low energy consumption. NASA-CR-135136. Dec. 1, 1976. pp. 1-153.
Newton, F.C., Liebeck, R.H., Mitchell, G.H., Mooiweer, M.A., Platte, M.M., Toogood, T.L., and Wright, R.A. (1986). Multiple Application Propfan Study (MAPS): Advanced tactical transport. NASA CR-175003. Mar. 1, 1986. pp. 1-101.
Norton, M. and Karczub, D. (2003). Fundamentals of noise and vibration analysis for engineers. Press Syndicate of the University of Cambridge. New York: New York. p. 524.
Notice of Opposition by Rolls Royce of European Patent No. 2809939 (European Patent Application No. 13786893.1) dated Sep. 26, 2018, 30 pages.
Notice of Opposition for European Patent No. 2809922 (13778330.4) dated Mar. 18, 2019 by Rolls-Royce plc.
Notice of Opposition for European Patent No. 2809922 (13778330.4) dated Mar. 20, 2019 by Safran Aircraft Engines.
Notice of Opposition for European Patent No. 2809932 (13743283.7) dated Sep. 20, 2018 by Safran Aircraft Engines.
Notice of Opposition for European Patent No. 2949882 (15175205.2) dated May 23, 2018 by Safran Aircraft Engines.
Notice of Opposition for European Patent No. 2949882 (15175205.2) dated May 22, 2018 by Rolls-Royce, 18 pages.
Notice of Opposition for European Patent No. EP3051078 dated Jul. 31, 2018, 45 pages.
Notice of Opposition of European Patent Application No. EP13786893.1 (European Patent No. 2809939), by Safran Aircraft Engines, dated Sep. 20, 2018, 86 pages.
Notice of Opposition of European Patent Application No. EP13786893.1 (European Patent No. 2809939) by Safran Aircraft Engines dated Sep. 24, 2018.
Notice of Opposition of European Patent No. 2811120 (14155460.0), mailed Apr. 12, 2018 by Rolls-Royce, 74 pages.
Notice of Opposition of European Patent No. 2811120 (14155460.0), mailed Apr. 12, 2018 by Safran Aircraft Engines, 123 pages.
Notice of Opposition of European Patent No. EP2834469 by Safran Aircraft Engines dated Mar. 27, 2019. [with English translation].
Notice of Opposition of European Patent No. EP2949881, by Rolls-Royce dated May 28, 2019, 19 pages.
Notice of Opposition of European Patent No. EP2949881, by Safran Aircraft Engines, dated May 28, 2019, 87 pages.
Notice of Opposition to European Patent No. EP2809931 (EP13743042.7), United Technologies Corporation opposed by Safran Aircraft Engines dated Apr. 20, 2017. [with English translation].
Notice of Opposition to Patent No. EP2811120 (14155460.0) by Safran Aircraft Engines dated Apr. 12, 2018. [with English translation].
Oates, G.C. (Ed). (1989). Aircraft propulsion systems and technology and design. Washington, D.C.: American Institute of Aeronautics, Inc. pp. 341-344.
Opinion Under Section 74(a) for European Patent Application No. 2809922, mailed May 9, 2019.
Parametric study of STOL short-haul transport engine cycles and operational techniques to minimize community noise impact. NASA-CR-114759. Jun. 1, 1974. pp. 1-397.
Parker, R.G. and Lin, J. (2001). Modeling, modal properties, and mesh stiffness variation instabilities of planetary gears. Prepared for NASA. NASA/CR-2001-210939. May 2001. pp. 1-111.
Patent Owner's Preliminary Response in U.S. Pat. No. 8,899,915, General Electric Company, Petitioner, v. United Technologies Corp., Patent Owner. IPR2017-00522, Entered Apr. 19, 2017. pp 1-54.
Petition for Inter Partes Review of U.S. Pat. No. 8,297,916, General Electric Company, Petitioner, v. United Technologies Corporation, Patent Owner, IPR2018-01171, May 30, 2018.
Petition for Inter Partes Review of U.S. Pat. No. 8,297,916, General Electric Company, Petitioner v, United Technologies Corporation, Patent Owner: IPR2018-01172, filed May 30, 2018, 83 pages.
Petition for Inter Partes Review of U.S. Pat. No. 8,899,915. General Electric Company, Petitioner, v. United technologies Corporation, Patent Owner. IPR2017-00522. Dec. 21, 2016, 72 pages.
Petition for Inter Partes Review of U.S. Pat. No. 9,695,751. General Electric Company, Petitioner, v. United Technologies Corporation, Patent Owner. IPR2018-01442. Filed Jul. 24, 2018.
Petrovic, J.J., Castro, R.G., Vaidya, R.U., Peters, M.I., Mendoza, D., Hoover, R.C., and Gallegos, D.E. (2001). Molybdenum disilicide materials for glass melting sensor sheaths. Ceramic Engineering and Science Proceedings. vol. 22(3). 2001. pp. 59-64.
Praisner T.J., et al., “Predictions of Unsteady Interactions Between Closely Coupled HP and LP Turbines With Co- and Counter-Rotation,” Proceedings of Asme Turbo Expo, Glasgow, UK, Jun. 14-18, 2010, pp. 1-10.
Pratt & Whitney PW2000, Jane's Aero-Engines: Jane's by IHS Markit, Sep. 29, 2010, 8 pages.
Pratt & Whitney PW6000, “Jane's Aero-Engines”, Jane's by IHS Markit, Nov. 22, 2010, 8 pages.
Pratt & Whitney PW8000, “Jane's Aero-Engines”, Jane's by IHS Markit, Sep. 30, 2010, 7 pages.
Pratt & Whitney PW1100G geared turbofan engine. The Flying Engineer. Retrieved Nov. 4, 2017 from: http://theflyingengineer.com/flightdeck/pw1100g-gtf/.
Press release. The GE90 engine. Retreived from: https://www.geaviation.com/commercial/engines/ge90-engine; https://www.geaviation.com/press-release/ge90-engine-family/ge90-115b-fan-completing-blade-testing-schedule-first-engine-test; and https://www.geaviation.com/press-release/ge90-engine-family/ge'scomposite-fan-blade-revolution-turns-20-years-old.
Principal Brief. Raytheon Technologies Corporation v. General Electric Company. Inter Partes Review No. IPR2018 01442. Filed Aug. 7, 2020. p. 1-59, appendices 1-98, and 60-1.
Prior Art Direct Drive Engines Statement, 1 page.
Product Brochure. Garrett TFE731. Allied Signal. Copyright 1987. pp. 1-24.
Product Brochure. The ALF 502R turbofan: technology, ecology, economy. Avco Lycoming Textron.
Product Brochure, BR710, Rolls-Royce, Copyright 2008, pp. 1-4.
Product Brochure, “TFE731 Engines: A new generation meeting your highest expectations for reliability, cost of ownership and performance”, Allied Signal Aerospace, Copyright 1996. pp. 1-10.
Pyrograf-III Carbon Nanofiber. Product guide. Retrieved Dec. 1, 2015 from: http://pyrografproducts.com/Merchant5/merchant.mvc?Screen=cp_nanofiber.
QCSEE ball spline pitch-change mechanism whirligig test report. (1978). NASA-CR-135354. Sep. 1, 1978. pp. 1-57.
QCSEE hamilton standard cam/harmonic drive variable pitch fan actuation system derail design report. (1976). NASA-CR-134852 Mar. 1, 1976. pp. 1-172.
QCSEE main reduction gears bearing development program final report. (1975). NASA-CR-134890. Dec. 1, 1975. pp. 1-41.
QCSEE over-the-wing final design report. (1977). NASA-CR-134848. Jun. 1, 1977. pp. 1-460.
QCSEE over-the-wing propulsion system test report vol. III—mechanical performance. (1978). NASA-CR-135325. Feb. 1, 1978. pp. 1-112.
QCSEE Preliminary analyses and design report. vol. 1. (1974). NASA-CR-134838. Oct. 1, 1974. pp. 1-337.
QCSEE preliminary analyses and design report. vol. II (1974). NASA-CR-134839. Oct. 1, 1974. pp. 340-630.
Schaefer, J.W., Sagerser, D.R., and Stakolich, E.G. (1977). Dynamics of high-bypass-engine thrust reversal using a variable-pitch fan. Technical Report prepared for NASA. NASA-TM-X-3524. May 1, 1977. pp. 1-33.
Seader, J.D. and Henley, E.J. (1998). Separation process principles. New York, NY: John Wiley & Sons, Inc. pp. 722-726 and 764-771.
Sessions R., “Turbo Hydra-Malic 350 Handbook”, 1985, The Berkley Publishing Group, pp. 24-25.
Shah, D.M. (1992). MoSi2 and other silicides as high temperature structural materials. Superalloys 1992. The Minerals, Metals, & Materials Society. pp. 409-422.
Shorter Oxford English Dictionary, 6th Edition. (2007), vol. 2, N-Z, pp. 1888.
Silverstein, C.C., Gottschlich, J.M., and Meininger, M. The feasibility of heat pipe turbine vane cooling. Presented at the International Gas Turbine and Aeroengine Congress and Exposition, The Hague, Netherlands. Jun. 13-16, 1994.pp. 1-7.
Singapore Search Report and Written Opinion for Application No. SG10201706005S, dated Feb. 15, 2018, 11 pages.
Singapore Search Report and Written Opinion for Application No. SG11201402667Q dated May 19, 2015.
Singapore Search Report and Written Opinion for Application No. SG11201402824R dated Apr. 19, 2016.
Singapore Search Report and Written Opinion for Application No. SG11201403011R, dated Nov. 17, 2015, 14 pages.
Singapore Search Report and Written Opinion for Application No. SG11201403015W dated Jun. 9, 2015.
Singapore Search Report and Written Opinion for Application No. SG11201403118S, dated Apr. 20, 2015, 29 pages.
Singapore Search Report for Application No. SG11201403615Q dated Jan. 4, 2016.
Singh, A. (2005). Application of a system level model to study the planetary load sharing behavior. Jounal of Mechanical Design. vol. 127. May 2005. pp. 469-476.
Singh, B. (1986). Small engine component technology (SECT) study. NASA CR-175079. Mar. 1, 1986. pp. 1-102.
Singh, R. and Houser, D.R. (1990). Non-linear dynamic analysis of geared systems. NASA-CR-180495. Feb. 1, 1990. pp. 1-263.
Smith, C.E., Hirschkron, R., and Warren, R.E. (1981). Propulsion system study for small transport aircraft technology (STAT). Final report. NASA-CR-165330. May 1, 1981. pp. 1-216.
Smith Jr M.G., et al., “P&W propulsion systems studies results/status,” National Aeronautics and Space Administration First Annual High Speed Research Workshop, May 14-16, 1991, pp. 921-948.
Smith-Boyd, L. and Pike, J. (1986). Expansion of epicyclic gear dynamic analysis program. Prepared for NASA. NASA CR-179563. Aug. 1986. pp. 1-98.
Sowers, H.D. and Coward, W.E. (1978). QCSEE over-the-wing (OTW) engine acuostic design. NASA-CR-135268. Jun. 1, 1978. pp. 1-52.
Spadaccini, L.J., and Huang, H. (2002). On-line fuel deoxygenation for coke suppression. ASME, Jun. 2002. pp. 1-7.
Spadaccini, L.J., Sobel, D.R., and Huang, H. (2001). Deposit formation and mitigation in aircraft fuels. Journal of Eng. For Gas Turbine and Power, vol. 123. Oct. 2001. pp. 741-746.
Statement of Appeal filed by Safran in European Patent No. EP2809931 (13743042.7) Mar. 22, 2019.
Statement of Grounds for Appeal for European Patent No. 2809931 (13743042.7) mailed Apr. 8, 2019.
Suchezky M., et al., “Variable-speed power-turbine for the large civil tilt rotor,” Prepared for NASA. NASA/CR-2012-217424, Feb. 2012, pp. 1-89.
Summons to Attend Oral Proceedings for European Application No. 17210308.7 dated Feb. 25, 2022.
Summons to Attend Oral Proceedings for European Patent Application No. 14155460.0 (2811120) mailed Oct. 15, 2021.
Summons to Attend Oral Proceedings for European Patent Application No. EP13743283.7 (Patent No. EP2809932), dated May 28, 2019.
Summons to Attend Oral Proceedings for European Patent Application No. EP13777804.9 dated Dec. 10, 2019.
Summons to attend oral proceedings for European Patent Application No. EP13777804.9, dated Jul. 7, 2020.
Summons to Attend Oral Proceedings for European Patent Application No. EP13778330.4 (EP2809922) dated Dec. 2, 2019.
Summons to Attend Oral Proceedings for European Patent Application No. EP13822569.3 (EP2841718), dated Oct. 23, 2019, 13 pages.
Summons to Oral Proceedings for European Patent Application No. 2809931 (13743042.7) mailed May 10, 2021.
Sundaram, S.K., Hsu, J-Y., Speyer, R.F. (1994). Molten glass corrosion resistance of immersed combustion-heating tube materials in soda-lime-silicate glass. J. Am. Ceram. Soc. 77(6). pp. 1613-1623.
Sundaram, S.K., Hsu, J-Y., Speyer, R.F. (1995). Molten glass corrosion resistance of immersed combustion-heating tube materials in e-glass. J. Am. Ceram. Soc. 78(7). pp. 1940-1946.
Supplementary European Search Report for Application No. EP13743282.9 dated Nov. 2, 2015.
Supplementary European Search Report for Application No. EP13775036.0 dated Sep. 7, 2015.
Supplementary European Search Report for Application No. EP13822569.3 dated Jan. 28, 2016.
Sutliff, D. (2005). Rotating rake turbofan duct mode measurement system. NASA TM-2005-213828. Oct. 1, 2005. pp. 1-34.
Suzuki, Y., Morgan, P.E.D., and Niihara, K. (1998). Improvement in mechanical properties of powder-processed MoSi2 by the addition of Sc2O3 and Y2O3. J. Am. Ceram. Soci. 81(12). pp. 3141-3149.
Sweetman, B. and Sutton, O. (1998). Pratt & Whitney's surprise leap. Interavia Business & Technology, 53.621, p. 25.
Taylor, W.F. (1974). Deposit formation from deoxygenated hydrocarbons. I. General features. Ind. Eng. Chem., Prod. Res. Develop., vol. 13(2). 1974. pp. 133-138.
Taylor, W.F. (1974). Deposit formation from deoxygenated hydrocarbons. II. Effect of trace sulfur compounds. Ind. Eng. Chem., Prod. Res. Dev., vol. 15(1). 1974. pp. 64-68.
Taylor, W.F. and Frankenfeld, J.W. (1978). Deposit fromation from deoxygenated hydrocarbons. 3. Effects of trace nitrogen and oxygen compounds. Ind. Eng. Chem., Prod. Res. Dev., vol. 17(1). 1978. pp. 86-90.
Technical Data. Teflon. WS Hampshire Inc. Retrieved from: http://catalog.wshampshire.com/Asset/psg_teflon_ptfe.pdf.
Technical Report. (1975). Quiet Clean Short-haul Experimental Engine (QCSEE) UTW fan preliminary design. NASA-CR-134842 Feb. 1, 1975. pp. 1-98.
Technical Report. (1977). Quiet Clean Short-haul Experimental Engine (QCSEE) Under-the-Wing (UTW) final design report. NASA-CR-134847. Jun. 1, 1977. pp. 1-697.
The jet engine. Rolls-Royce plc. 5th Edition. 1996. pp. 48.
The New Oxford Dictionary, Second Edition, Oxford University Press, New York, USA, 2005, p. 1400.
The Oxford English Dictionary, Second Edition, Oxford University Press, Oxford, UK, 1989, vol. XIII, pp. 150-151.
Third Party Observation submitted for EP Application No. EP16156289.7 (Patent No. EP3059393), by Rolls Royce dated Jun. 19, 2019, 5 pages.
Third Party Observations and Concise Description of Relevance of Document for U.S. Appl. No. 15/185,292 dated Jul. 5, 2018.
Third Party Observations and Concise Description of Relevance of Document for U.S. Appl. No. 15/816,487 dated Jul. 25, 2018.
Third Party Observations and Concise Description of Relevance of Document for U.S. Appl. No. 15/856,396 dated Aug. 31, 2018, 32 pages.
Third Party Observations and Concise Description of Relevance of Document for U.S. Appl. No. 15/881,240 dated Aug. 31, 2018.
Third Party Observations for EP Application No. EP11250208.3 (EP2362064), filed Jul. 20, 2018, dated Jul. 26, 2018, 12 pages.
Third Party Observations for EP Application No. EP113854452.3 by Rolls Royce dated Dec. 13, 2018, mailed Jan. 2, 2019, 9 pages.
Third Party Observations for EP Application No. EP12170483.7 by Rolls-Royce dated Oct. 24, 2019.
Third Party Observations for EP Application No. EP13743282.9 (EP2809953) by Rolls-Royce dated Dec. 13, 2018.
Third Party Observations for EP Application No. EP13743282.9 (EP2809953) by Rolls-Royce dated Sep. 20, 2018, 10 pages.
Third Party Observations for EP Application No. EP13775036.0 by Rolls Royce dated Dec. 13, 2018, mailed Jan. 2, 2019, 7 pages.
Third Party Observations for EP Application No. EP13775036.0 by Rolls Royce dated Oct. 11, 2018, mailed Oct. 17, 2018, 6 pages.
Third Party Observations for EP Application No. EP13775188.9 by Rolls Royce dated Dec. 13, 2018, mailed Jan. 2, 2019, 7 pages.
Third Party Observations for EP Application No. EP13775188.9 by Rolls Royce dated Sep. 10, 2018, mailed Sep. 17, 2018, 7 pages.
Third Party Observations for EP Application No. EP13775188.9 (EP2809575), dated May 12, 2020 by Rolls Royce.
Third Party Observations for EP Application No. EP13777804.9, by Rolls Royce dated Dec. 19, 2018, mailed Jan. 2, 2019, 8 pages.
Third Party Observations for EP Application No. EP13777804.9 (EP2809940), by Rolls-Royce, dated Nov. 21, 2019, 3 pages.
Third Party Observations for EP Application No. EP13822569.3 (EP2841718) by Rolls-Royce dated Sep. 10, 2018, 9 pages.
Third Party Observations for EP Application No. EP13822569.3 (EP2841718) dated Dec. 13, 2018.
Third Party Observations for EP Application No. EP14155460.0 (EP2811120) by Rolls Royce dated Oct. 29, 2018.
Third Party Observations for EP Application No. EP16159312.4 (EP3045684), filed Jun. 22, 2018, dated Jul. 3, 2018, 16 pages.
Third Party Observations for EP Application No. EP17199484.1 (EP3296526), filed Jul. 5, 2018, dated Jul. 12, 2018, 26 pages.
Third Party Observations for EP Application No. EP18191325.2 (EP3608515) by Rolls Royce dated Mar. 10, 2020.
Third Party Observations for EP Application No. EP18191325.2 (EP3608515) by Rolls Royce dated Mar. 6, 2020.
Third Party Observations for EP Application No. EP18191333.6 (EP3467273) by Rolls Royce dated Mar. 9, 2020.
Third Party Observations for EP Application No. EP2809940 by Rolls Royce dated Mar. 30, 2020.
Third Party Submission and Concise Description of Relevance of Document for U.S. Appl. No. 15/881,240 dated Aug. 28, 2018, 36 pages.
Thulin, R.D., Howe, D.C., and Singer, I.D. (1982). Energy efficient engine: High pressure turbine detailed design report. Prepared for NASA. NASA CR-165608. pp. 1-178.
Tong, M.T., Jones, S.M., Haller, W.J., and Handschuh, R.F. (2009). Engine conceptual design studies for a hybrid wing body aircraft. NASA/TM-2009-215680. Nov. 1, 2009. pp. 1-15.
Treager, I.E. (1995). Aircraft gas turbine engine technology, 3rd Edition. Glencoe Aviation Technology Series. McGraw-Hill. p. 445.
Trembley, Jr., H.F. (1977). Determination of effects of ambient conditions on aircraft engine emissions. ALF 502 combustor rig testing and engine verification test. Prepared for Environmental Protection Agency. Sep. 1977. pp. 1-256.
Tsirlin, M., Pronin, Y.E., Florina, E.K., Mukhametov, S. Kh., Khatsernov, M.A., Yun, H.M., . . . Kroke, E. (2001). Experimental investigation of multifunctional interphase coatings on SiC fibers for non-oxide high temperature resistant CMCs. High Temperature Ceramic Matrix Composites. 4th Int'l Conf. on High Temp. Ceramic Matrix Composites. Oct. 1-3, 2001. pp. 149-156.
Tummers, B. (2006). DataThief III. Retreived from: https://datathief.org/DatathiefManual.pdf pp. 1-52.
Turbomeca Aubisque. Jane's Aero-engines, Aero-engines—Turbofan. Nov. 2, 2009.
Turner, M. G., Norris, A., and Veres, J.P. (2004). High-fidelity three-dimensional simulation of the GE90. NASA/TM-2004-212981. pp. 1-18.
Type Certificate Data Sheet No. E6NE. Department of Transportation Federal Aviation Administration. Jun. 7, 2002. pp. 1-10.
U.S. Appl. No. 61/494,453, Geared engine flexible mount arrangement. filed Jun. 8, 2011.
United Technologies Pratt & Whitney, Jane's Aero-Engines, Jane's by IHS Markit, Aug. 30, 2000.
U.S. Department of Transportation: Federal Aviation Administration Advisory Circular. Calibration test, endurance test, and teardown inspection for turbine engine certification. Dated Apr. 13, 2006. pp. 1-41 and Appendices.
U.S. Department of Transportation: Federal Aviation Administration Advisory Circular, Engine Overtorque Test, Calibration Test, Endurance Test, and Teardown Inspection for Turbine Engine Certification, dated Mar. 9, 2015, pp. 1-37 and Appendices.
U.S. Department of Transportation: Federal Aviation Administration Advisory Circular, Runway overrun prevention, dated: Nov. 6, 2007, p. 1-8 and Appendix 1 pp. 1-15, Appendix 2 pp. 1-6, Appendix 3 pp. 1-3, and Appendix 4 pp. 1-5.
U.S. Department of Transportation: Federal Aviation Administration Advisory Circular. Standard operating procedures for flight deck crewmembers, Dated: Feb. 27, 2003, p. 1-6 and Appendices.
U.S. Department of Transportation: Federal Aviation Administration Type Certificate Data Sheet No. E00064EN. Dated: Nov. 24, 2006, pp. 1-5.
U.S. Department of Transportation: Federal Aviation Administration Type Certificate Data Sheet No. E6WE. Dated: May 9, 2000. p. 1-9.
Vasudevan, A.K. and Petrovic, J.J. (1992). A comparative overview of molybedenum disilicide composites. Materials Science and Engineering, A155, 1992. pp. 1-17.
Walsh, P.P. and Fletcher, P. (2004). Gas turbine performance, 2nd Edition. Oxford, UK: Blackwell Science. pp. 1-658.
Walsh P.P., et al., “Gas Turbine Performance,” Second Edition, Blackwell Science Ltd, Oxford, UK, 2004, p. 206.
Waters, M.H. and Schairer, E.T. (1977). Analysis of turbofan propulsion system weight and dimensions. NASA Technical Memorandum. Jan. 1977. pp. 1-65.
Web Article, GE Aviation, GEnx-28 first engine to test, Jan. 28, 2012, Retrieved from: http://www.geaviation.com/engines/commercial/genx/2b_fett.html, 1 page.
Webster, J.D., Westwood, M.E., Hayes, F.H., Day, R.J., Taylor, R., Duran, A., . . . Vogel, W.D. (1998). Oxidation protection coatings for C/SiC based on yttrium silicate. Journal of European Ceramic Society vol. 18. 1998. pp. 2345-2350.
Attestation by Didier Escure signed Oct. 20, 2020 as filed in the Opposition of European Patent Application No. 13786893.1 (2809939) by Safran Aircraft Engines dated May 4, 2022.
Reply to Appeal in the opposition of European Patent Application No. 13786893.1 (2809939) by Rolls-Royce plc dated Apr. 21, 2022.
Reply to Appeal in the opposition of European Patent Application No. 13786893.1 (2809939) by Safran dated May 4, 2022.
Summons to Attend Oral Proceedings in European Patent Application No. 13837107.5 mailed Jun. 27, 2022.
GE Reports (2009). GE's breakthrough GEnx debuts at the Paris Air Show. Retrieved Jun. 6, 2009 from: http://www.gereports.com/ges-breakthrough-genx-debuts-at-the-paris-air-show/.
General Electric CF34, “Jane's Aero-Engines”, Jane's by IHS Markit, Jul. 26, 2010, 24 pages.
General Electric GE90, “Jane's Aero-Engines”, Jane's by IHS Markit. Nov. 1, 2010, 12 pages.
Gibala, R., Ghosh, A.K., Van Aken, D.C., Srolovitz, D.J., Basu, A., Chang, H., . . . Yang, W. (1992). Mechanical behavior and interface design of MoSi2-based alloys and composites. Materials Science and Engineering, A155, 1992. pp. 147-158.
Gliebe, P.R. and Janardan, B.A. (2003). Ultra-high bypass engine aeroacoustic study. NASA/CR-2003-21252. GE Aircraft Engines, Cincinnati, Ohio. Oct. 2003. pp. 1-103.
Gliebe, P.R., Ho, P.Y., and Mani, R. (1995). UHB engine fan and broadband noise reduction study. NASA CR-198357. Jun. 1995. pp. 1-48.
Grady, J.E., Weir, D.S., Lamoureux, M.C., and Martinez, M.M. (2007). Engine noise research in NASA's quiet aircraft technology project. Papers from the International Symposium on Air Breathing Engines (ISABE). 2007.
Gray, D.E. (1978). Energy efficient engine preliminary design and integration studies. NASA-CP-2036-PT-1. Nov. 1978. pp. 89-110.
Gray, D.E. (1978). Energy efficient engine preliminary design and integration studies. Prepared for NASA. NASA CR-135396. Nov. 1978. pp. 1-366.
Gray, D.E. and Gardner, W.B. (1983). Energy efficient engine program technology benefit/cost study—vol. 2. NASA CR-174766. Oct. 1983. pp. 1-118.
Gray D.E., et al., “Energy Efficient Engine Program Technology Benefit/Cost Study vol. II,” 1983, NASA, pp. 29-43.
Greitzer, E.M., Bonnefoy, P.A., Delaroseblanco,E., Dorbian, C.S., Drela, M., Hall, D.K., Hansman, R.J., Hileman, J.I., Liebeck, R.H., Levegren, J. (2010). N+3 aircraft concept designs and trade studies, final report. vol. 1. Dec. 1, 2010. NASA/CR-2010-216794/vol. 1. pp. 1-187.
Griffiths, B. (2005). Composite fan blade containment case. Modem Machine Shop. Retrieved from: http://www.mmsonline.com/articles/composite-fan-blade-containment-case pp. 1-4.
Grose T.K. (2013). Reshaping flight for fuel efficiency: Five technologies on the runway. National Geographic. Mar. 16, 2016. Retrieved Apr. 23, 2013 from: http://news.nationalgeographic.com/news/energy/2013/04/130423-reshaping-flight-for-fuel-efficiency.html.
Groweneweg, J.F. (1994). Fan noise research at NASA. NASA-TM-106512. Prepared for the 1994 National Conference on Noise Control Engineering. Fort Lauderdale, FL. May 1-4, 1994. pp. 1-10.
Groweneweg, J.F. (1994). Fan noise research at NASA. Noise-CON 94. Fort Lauderdale, FL. May 1-4, 1994. pp. 1-10.
Guha, “Optimum Fan Pressure Ratio for Bypass Engines with Separate or Mixed Exhaust Streams”, Journal of Propulsion and Power, vol. 17, No. 5. Sep.-Oct. 2001, pp. 1117-1122, [retrieved on Aug. 21, 2013]. Retrieved from the Internet: http://www.facweb.iitkgp,ernet.in/.about.aguha/research/AIAA2001- .pdfentire document.
Gunston B., “Allied Signal TFE731,” Jane's Aero Engine Issue Five, Mar. 1999.
Gunston, B. (Ed.) (2000). Jane's aero-engines, Issue seven. Coulsdon, Surrey, UK: Jane's Information Group Limited. pp. 510-512.
Gunston, B. (Ed.)(2000). Jane's aero-engines. Jane's Information Group Inc. VA: Alexandria. Issue Seven pp. 1-47 and 510-512.
Gunston B., “Pratt & Whitney PW6000,” Jane's Aero Engine Issue Six, Sep. 1999.
Gunston B., “The Cambridge Aerospace Dictionary,” Second Edition, Cambridge University Press, Cambridge, UK, 2009, p. 543.
Guynn, M. D., Berton, J.J., Fisher, K. L., Haller, W.J., Tong, M. T., and Thurman, D.R. (2011). Refined exploration of turbofan design options for an advanced single-aisle transport. NASA/TM-2011-216883. pp. 1-27.
Guynn, M.D., et al., “Analysis of turbofan design options for an advanced single-aisle transport aircraft”, American Institute of Aeronautics and Astronautics, 2009, pp. 1-13.
Guynn, M.D., Berton, J.J., Fisher, K.L., Haller, W.J., Tong, M.T., and Thurman, D.R. (2009). Engine concept study for an advanced single-aisle transport. NASA/TM-2009-215784. pp. 1-97.
Haldenbrand, R. and Norgren, W.M. (1979). Airesearch QCGAT program [quiet clean general aviation turbofan engines]. NASA-CR-159758. pp. 1-199.
Hall, C.A. and Crichton, D. (2007). Engine design studies for a silent aircraft. Journal of Turbomachinery, 129, 479-487.
Halle J.E., et al., “Energy Efficient Engine Fan Component Detailed Design Report,” NASA-CR-165466, 1984, pp. 1-135.
Halliwell, I and Justice, K. (2012). Fuel burn benefits of a variable-pitch geared fan engine. AIAA 2012-3912. 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Jul. 30-Aug. 1, 2012. pp. 1-24.
Han, J., Dutta, S., and Ekkad, S.V. (2000). Gas turbine heat transfer and cooling technology. New York, NY: Taylor & Francis. pp. 1-25, 129-157, and 160-249.
Haque, A. and Shamsuzzoha, M., Hussain, F., and Dean, D. (2003). S20-glass/epoxy polymer nanocomposites: Manufacturing, structures, thermal and mechanical properties. Journal of Composite Materials, 37 (20), 1821-1837.
Hazlett, R.N. (1991). Thermal oxidation stability of aviation turbine fuels. Philadelphia, PA: ASTM. pp. 1-163.
Heidelberg, L.J., and Hall, D.G. (1992). Acoustic mode measurements in the inlet of a model turbofan using a continuously rotating rake. AIAA-93-0598. 31st Aerospace Sciences Meeting. Reno, NV. Jan. 11-14, 1993. pp. 1-30.
Heidelberg, L.J., and Hall, D.G. (1992). Acoustic mode measurements in the inlet of a model turbofan using a continuously rotating rake. NASA-TM-105989. Prepared for the 31st Aerospace Sciences Meeting. Reno, NV. Jan. 11-14, 1993. pp. 1-30.
Heingartner, P., Mba, D., Brown, D. (2003). Determining power losses in the helical gear mesh; Case Study. ASME 2003 Design Engineering Technical Conferences. Chicago, IL. Sep. 2-6, 2003. pp. 1-7.
Hemighaus, G., Boval, T., Bacha, J., Barnes, F., Franklin, M., Gibbs, L., . . . Morris, J. (2007). Aviation fuels: Techincal review. Chevron Products Company. pp. 1-94. Retrieved from: https://www.cgabusinessdesk.com/document/aviation_tech_review.pdf.
Hendricks, E.S. and Tong, M.T. (2012). Performance and weight estimates for an advanced open rotor engine. NASA/TM-2012-217710. pp 1-13.
Hendricks E.S., Jones, S.M., and Gray, J.S. (2014). Design optimization of a variable-speed power-turbine. American Institute of Aeronautics and Astronautics. pp. 1-17.
Hess, C. (1998). Pratt & Whitney develops geared turbofan. Flug Revue 43(7). Oct. 1998.
Hicks R.J., et al., “Optimised Gearbox Design for Modern Wind Turbines,” Orbital2 Ltd, Wales, UK, Nov. 20, 2014, pp. 1-8.
Hill, P.G., Peterson, C.R. (1965). Mechanics and thermodynamics of propulsion. Addison-Wesley Publishing Company, Inc. pp. 307-308.
Hill, P.G., Peterson, C.R. (1992). Mechanics and thermodynamics of propulsion, 2nd Edition. Addison-Wesley Publishing Company, Inc. pp. 400-406.
Holcombe, V. (2003). Aero-Propulsion Technology (APT) task V low noise ADP engine definition study. NASA CR-2003-212521. Oct. 1, 2003. pp. 1-73.
Holder's Response to Written Opinion of Sep. 29, 2015, European Patent Application No. 15175205.2 (2949882), dated Jun. 1, 2016, 27 pages.
Honeywell Learjet 31 and 35/36 TFE731-2 to 2C Engine Upgrade Program. Sep. 2005. pp. 1-4.
Honeywell LF502. Jane's Aero-engines, Aero-engines—Turbofan. Feb. 9, 2012.
Honeywell LF502. Jane's Aero-engines, Aero-engines—Turbofan. Aug. 17, 2016.
Honeywell LF507. Jane's Aero-engines, Aero-engines—Turbofan. Feb. 9, 2012.
Honeywell Sabreliner 65 TFE731-3 to -3D Engine Upgrade Program. Oct. 2005. pp. 1-4.
Honeywell TFE731. Jane's Aero-engines, Aero-engines—Turbofan. Jul. 18, 2012.
Welch G.E. (2010). Assessment of aerodynamic challenges of a variable-speed power turbine for large civil tilt-rotor application. Prepared for 66th Annual Forum and Technology Display. May 11-13, 2010. NASA/TM-2010-216758. pp. 1-15.
Welch, G.E., McVetta, A.B., Stevens, M.A., Howard, S.A., Giel, P.W., Ameri, A.A., To, W., et al. (2012). Variable-speed power-turbine research at Glenn Research Center. Prepared for the 68th Annual Forum and Technology Display. May 1-3, 2012. NASA/TM-2012-217605. pp. 1-23.
Wendus, B.E., Stark, D.F., Holler, R.P., and Funkhouse, M.E. (2003). Follow-on technology requirement study for advanced subsonic transport. Technical Report prepared for NASA. NASA/CR-2003-212467. Aug. 1, 2003. pp. 1-47.
Whitaker, R. (1982). ALF 502: plugging the turbofan gap. Flight International, p. 237-241, Jan. 30, 1982.
“Wide-chord fan—12 years of development”, Aircraft Engineering and Aerospace Technology, Jul. 1987, vol. 59, Issue 7, pp. 10-11, Retrieved Jul. 31, 2008 from: https://doi.org/10.1108/eb036471.
Wie, Y.S., Collier, F.S., Wagner, R.D., Viken, J.K., and Pfenniger, W. (1992). Design of a hybrid laminar flow control engine nacelle. AIAA-92-0400. 30th Aerospace Sciences Meeting & Exhibit. Jan. 6-9, 1992. pp. 1-14.
Wikipedia. Lycoming ALF 502. Retrieved from: https://en.wikipedia.org/wiki/Lycoming_ALF_502.
Wikipedia. Stiffness. Retrieved Jun. 28, 2018 from: https://en.wikipedia.org/wiki/Stiffness.
Wikipedia. Torsion spring. Retreived Jun. 29, 2018 from: https://en.wikipedia.org/wiki/Torsion_spring.
Wikipedia. Airbus A220. Retrieved from: https://en.wikipedia.org/wiki/Airbus_A220.
Wikipedia. Boeing 737 next generation. Retrieved from: https://en.wikipedia.org/wiki/Boeing_737_Next_Generation.
Wikipedia. CFM International CFM56. Retrieved from: https://en.wikipedia.org/wiki/CFM_International_CFM56.
Wikipedia. Mitsubishi SpaceJet. Retrieved from: https://en.wikipedia.org/wiki/Mitsubishi_SpaceJet.
Wilfert, G. (2008). Geared fan. Aero-Engine Design: From State of the Art Turbofans Towards Innovative Architectures, von Karman Institute for Fluid Dynamics, Belgium, Mar. 3-7, 2008. pp. 1-26.
Wilfert, G., Kriegl, B., Scheugenplug, H., Bernard, J., Ruiz, X., and Eury, S. (2005). Clean-validation of a high efficient low NOx core, a GTF high speed turbine and an integration of a recuperator in an environmental friendly engine concept. 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference. Tucson, AZ. Jul. 10-13, 2005. p. 1-11.
Wilfert, G., Kriegl, B., Wald, L., and Johanssen, O. (2005). Clean-Validation of a GTF high speed turbine and integration of heat exchanger technology in an environmental friendly engine concept. International Society on Air Breathing Engines. Feb. 2005. pp. 1-8.
Willis, W.S. (1979). Quiet clean short-haul experimental engine (QCSEE) final report. NASA/CR-159473 pp. 1-289.
Winn, A. (Ed). (1990). Wide Chord Fan Club. Flight International, 4217(137). May 23-29, 1990. pp. 34-38.
Wright, G.H. and Russell, J.G. (1990). The M.45SD-02 variable pitch geared fan engine demonstrator test and evaluation experience. Aeronautical Journal., vol. 84(836). Sep. 1980. pp. 268-277.
Wrong C. B., “An Introduction to the JT15D Engine,” ASME, 96-GT-119, 1969, 6 pages.
Xie, M. (2008). Intelligent engine systems: Smart case system. NASA/CR-2008-215233. pp. 1-31.
Xu, Y., Cheng, L., Zhang, L., Ying, H., and Zhou, W. (1999). Oxidation behavior and mechanical properties of C/SiC composites with Si—MoSi2 oxidation protection coating. J. of Mat. Sci vol. 34. 1999. pp. 6009-6014.
Youtube Video, “Pure Power PW1000G Engine: Customer Testimonials”, published Jul. 26, 2010 (-seconds 43-63) available at https:www.youtube.com/watch?v=vgQgEftEd8c on Aug. 9, 2018.
Zalud, T. (1998). Gears put a new spin on turbofan performance. Machine Design, 70(20), p. 104.
Zamboni, G. and Xu, L. (2009). Fan root aerodynamics for large bypass gas turbine engines: Influence on the engine performance and 3D design. Proceedings of ASME Turbo Expo 2009: Power for Land, Sea and Air. Jun. 8-12, 2009, Orlando, Florida, USA. pp. 1-12.
Zhao, J.C. and Westbrook, J.H. (2003). Ultrahigh-temperature materials for jet engines. MRS Bulletin. vol. 28(9). Sep. 2003. pp. 622-630.
QCSEE the aerodynamic and mechanical design of the QCSEE under-the-wing fan. (1977). NASA-CR-135009. Mar. 1, 1977. pp. 1-137.
QCSEE the aerodynamic and preliminary mechanical design of the QCSEE OTW fan. (1975). NASA-CR-134841. Feb. 1, 1975. pp. 1-74.
QCSEE under-the-wing engine composite fan blade design. (1975). NASA-CR-134840. May 1, 1975. pp. 1-51.
QCSEE under-the-wing engine composite fan blade final design test report. (1977). NASA-CR-135046. Feb. 1, 1977. pp. 1-55.
QCSEE under-the-wing engine composite fan blade preliminary design test report. (1975). NASA-CR-134846. Sep. 1, 1975. pp. 1-56.
QCSEE under-the-wing engine digital control system design report. (1978). NASA-CR-134920. Jan. 1, 1978. pp. 1-309.
Quiet clean general aviation turbofan (QCGAT) technology study final report vol. I. (1975). NASA-CR-164222. Dec. 1, 1975. pp. 1-186.
Ramsden, J.M. (Ed). (1978). The new European airliner. Flight International, 113(3590). Jan. 7, 1978. pp. 39-43.
Ratna, D. (2009). Handbook of thermoset resins. Shawbury, UK: iSmithers. pp. 187-216.
Rauch, D. (1972). Design study of an air pump and integral lift engine ALF-504 using the Lycoming 502 core. Prepare for NASA. Jul. 1972. pp. 1-182.
Raytheon Techs. Corp. V. General Electric Co., 993 F.3d 1374 (Fed. Cir. 2021).
Red Aviation, “Part or Material Certification Form for various engine components,” dated Apr. 5, 2017, 1 page.
Request for Opinion as to Validity for European Patent No. EP2809922 (13778330.4), dated Feb. 6, 2019 by Rolls Royce, 16 pages.
Request for Opinion as to Validity for European Patent No. EP2809922 (13778330.4), dated Feb. 14, 2019 by Rolls Royce, 16 pages.
“Request for Opinion as to Validity of European Patent No. EP2809922B1 (EP13778330.4) Observations-in-Reply,” by Rolls-Royce, dated Apr. 3, 2019.
Request for Opinion filed for European Patent No. EP2532841B1 by Rolls Royce granted Apr. 27, 2016, dated Nov. 7, 2018.
Request for Opinion filed for European Patent No. EP2532858B1 by Rolls Royce granted Oct. 19, 2016, dated Nov. 7, 2018.
Request for Opinion filed for European Patent No. EP2737180B1 by Rolls Royce granted Apr. 13, 2016, dated Jul. 11, 2018.
Reshotko, M., Karchmer, A., Penko, P.F. (1977). Core noise measurements on a YF-102 turbofan engine. NASA TM X-73587. Prepared for Aerospace Sciences Meeting sponsored by the American Institute of Aeronautics and Astronautics. Jan. 24-26, 2977.
Response from the Holder. European Patent Application No. 14155460.0 (2811120) dated Nov. 23, 2015.
Response from the Holder. European Patent Application No. 14155460.0 (2811120) dated Dec. 1, 2016.
Response from the Holder. European Patent Application No. 14155460.0 (2811120) dated Jun. 10, 2015.
Response to Appeal for European Patent No. 2809931 (13743042.7) mailed Aug. 22, 2019.
Response to Holder's Response European Patent No. EP2949882 by Safran Aircraft Engines dated Mar. 12, 2019. [with English translation].
Response to Observations by Patantee filed for European Patent No. EP2532841B1 by Rolls Royce granted Apr. 27, 2016, dated Jan. 18, 2019.
Response to Observations by Patantee filed for European Patent No. EP2532858B1 by Rolls Royce granted Oct. 19, 2016, dated Jan. 18, 2019.
Response to Observations by Patantee filed for European Patent No. EP2737180B1 by Rolls Royce granted Apr. 13, 2016, dated Jul. 18, 2018.
Response to Statement of Grounds of Appeal from the Patent Holder for European Patent No. 2809931 by Safran Aircraft Engine dated Aug. 21, 2019. [with English translation].
Response to the Observations Filed by Patent Holder for European Patent No. EP2809922, dated Apr. 29, 2020.
Response to the Summons of Oral Proceedings for European Patent No. EP2949882 by Rolls-Royce, dated Oct. 9, 2019.
Response to the Summons of Oral Proceedings for European Patent No. EP2949882 by Safran, dated Oct. 9, 2019.
Response to the Summons of Oral Proceedings for European Patent No. EP3051078 by Rolls-Royce, dated Oct. 17, 2019.
Rethinking jet engines to make commercial aviation less of a threat to the climate (and the human respiratory system). Fortune. Retrieved Sep. 29, 2016 from: http://beta.fortune.com/change-the-world/united-technologies-8.
Reuters. (2014). GE exec says avoided geared design in jet engine battle with Pratt. Retrieved from: https://www.reuters.com/article/us-general-electric-united-tech-engine/ge-exec-says-avoided-geared-design-in-jet-engine-battle-with-pratt-idUSKBN0HA2H620140915.
Reynolds, C.N. (1985). Advanced prop-fan engine technology (APET) single- and counter-rotation gearbox/pitch change mechanism. Prepared for NASA. NASA CR-168114 (vol. I). Jul. 1985. pp. 1-295.
Reynolds, C.N., “Advanced prop-fan engine technology (APET) single- and counter-rotation gearbox/pitch change mechanism,” Prepared for NASA, NASA CR-168114 (vol. II), Jul. 1985, pp. 1-175.
Riegler, C., and Bichlmaier, C. (2007). The geared turbofan technology—Opportunities, challenges and readiness status. Porceedings CEAS. Sep. 10-13, 2007. Berlin, Germany. pp. 1-12.
Rolls-Royce M45H. Jane's Aero-engines, Aero-engines—Turbofan. Feb. 24, 2010.
“Rolls-Royce Trent 900,” Jane's Aero-Engines, Jane's by IHS Markit, Feb. 8, 2012.
“Rolls-Royce Trent XWB,” Jane's Aero-Engines, Jane's by IHS Markit, Mar. 6, 2012.
Rotordynamic instability problems in high-performance turbomachinery. (1986). NASA conference publication 2443. Jun. 2-4, 1986.
Roux, E. (2007). Turbofan and turbojet engines database handbook. Editions Elodie Roux. Blagnac: France. pp. 1-595.
Roux E., “Turbofan and turbojet engines database handbook,” Editions Elodie Roux, Blagnac: France, 2007, pp. 41-43 and 464-469.
Roux E., “Turbofan and turbojet engines database handbook”, Editions Elodie Roux. Blagnac: France, 2007, pp. 41-42, pp. 465, pp. 468-469.
Sabnis, J. (2010). The PW1000G PurePower new engine concept and its impact on MRO. Av Week Engine MRO Forum. Dec. 1, 2010. pp. 1-45.
Sabnis U.S. (2005). Emissions and noise—Next frontier for aircraft engine technologies. Presented at the AIAA/ AAAF Aircraft Noise and Emissions Reduction Symposium. Monterey, California, USA. May 24-26, 2005.
Salemme, C.T. and Murphy, G.C. (1979). Metal spar/superhybrid shell composite fan blades. Prepared for NASA. NASA-CR-159594. Aug. 1979. pp. 1-127.
Sargisson, D.F. (1985). Advanced propfan engine technology (APET) and single-rotation gearbox/pitch change mechanism. NASA Contractor Report-168113. R83AEB592. Jun. 1, 1985. pp 1-476.
Savelle, S.A. and Garrard, G.D. (1996). Application of transient and dynamic simulations to the U.S. Army T55-L-712 helicopter engine. The American Society of Mechanical Engineers. Presented Jun. 10-13, 1996. pp. 1-8.
Schaber Reinhold, “Numerische Auslegung und Simulation von Gasturbinen,” Dec. 14, 2000, 115 pages.
Kurzke, J. (2001). GasTurb 9: A program to calculate design and off-design performance of gas turbines. Retrieved from: https://www.scribd.com/document/92384867/GasTurb9Manual.
Kurzke, J. (2012). GasTurb 12: Design and off-design performance of gas turbines. Retrieved from: https://www.scribd.com/document/153900429/GasTurb-12.
Kurzke, J. (2008). Preliminary Design, Aero-engine design: From state of the art turbofans towards innovative architectures. pp. 1-72.
Kurzke, J. (2009). Fundamental differences between conventional and geared turbofans. Proceedings of ASME Turbo Expo: Power for Land, Sea, and Air. 2009, Orlando, Florida. pp. 145-153.
Lacaze J., et al., “Directionally Solidified Materials: Nickel-Base Superalloys for Gas Turbines,” Textures and Microstructures, 1990, vol. 13, pp. 1-14.
Langston, L. and Faghri, A. Heat pipe turbine vane cooling. Prepared for Advanced Turbine Systems Annual Program Review. Morgantown, West Virginia. Oct. 17-19, 1995. pp. 3-9.
Lau, K., Gu, C., and Hui, D. (2005). A critical review on nanotube and nanotube/nanoclay related polymer composite materials. Composites: Part B 37(2006) 425-436.
Leckie, F.A. and Dal Bello, D.J. (2009). Strength and stiffness of engineering systems. Mechanical Engineering Series. Springer. pp. 1-10, 48-51.
Leckie F.A., et al., “Strength and Stiffness of Engineering Systems,” Mechanical Engineering Series, Springer, 2009, pp. 1-3.
Lee, K.N. (2000). Current status of environmental barrier coatings for Si-Based ceramics. Surface and Coatings Technology 133-134, 2000. pp. 1-7.
Letter from the Opponent for European Patent Application No. 2811120 (14155460.0) mailed Feb. 15, 2019 by Safran Aircraft Engines.
Letter from the Opponent (Safran) for European Patent 2809939 (13786893.1) dated Aug. 13, 2020.
Letter from the Opponent (Safran) for European Patent 2949881 (15175203.74) dated Mar. 25, 2021.
Levintan, R.M. (1975). Q-Fan demonstrator engine. Journal of Aircraft. vol. 12( 8). Aug. 1975. pp. 658-663.
Lewicki, D.G., Black, J.D., Savage, M., and Coy, J.J. (1985). Fatigue life analysis of a turboprop reduction gearbox. NASA Technical Memorandum. Prepared for the Design Technical Conference (ASME). Sep. 11-13, 1985. pp. 1-26.
Liebeck, R.H., Andrastek, D.A., Chau, J., Girvin, R., Lyon, R., Rawdon, B.K., Scott, P.W. et al. (1995). Advanced subsonic airplane design & economics studies. NASA CR-195443. Apr. 1995. pp. 1 187.
Litt, J.S. (2018). Sixth NASA Glenn Research Center propulsion control and diagnostics (PCD) workshop. NASA/CP-2018-219891. Apr. 1, 2018. pp. 1-400.
Lord, W.K., MacMartin, D.G., and Tillman, T.G. (2000). Flow control opportunities in gas turbine engines. American Institute of Aeronautics and Astronautics. pp. 1-15.
Lynwander, P. (1983). Gear drive systems: Design and application. New York, New York: Marcel Dekker, Inc. pp. 145, 355-358.
Macisaac, B. and Langston, R. (2011). Gas turbine propulsion systems. Chichester, West Sussex: John Wiley & Sons, Ltd. pp. 260-265.
Mancuso, J.R. and Corcoran, J.P. (2003). What are the differences in high performance flexible couplings for turbomachinery? Proceedings of the Thirty-Second Turbomachinery Symposium. 2003. pp. 189-207.
Manual. Student's Guide to Learning SolidWorks Software. Dassault Systemes—SolidWorks Corporation. pp. 1-156.
Matsumoto, T., Toshiro, U., Kishida, A., Tsutomu, F., Maruyama, I., and Akashi, M. (1996). Novel functional polymers: Poly (dimethylsiloxane)-polyamide multiblock copolymer. VII. Oxygen permeability of aramid-silicone membranes in a gas-membrane-liquid system. Journal of Applied Polymer Science, vol. 64(6). May 9, 1997. pp. 1153-1159.
Mattingly, J.D. (1996). Elements of gas turbine propulsion. New York, New York: McGraw-Hill, Inc. pp. 1-18, 60-62, 223-234, 462-479, 517-520, 757-767, and 862-864.
Mattingly, J.D. (1996). Elements of gas turbine propulsion. New York, New York: McGraw-Hill, Inc. pp. 1-18, 60-62, 85-87, 95-104, 121-123, 223-234, 242-245, 278-285, 303-309, 323-326, 462-179, 517-520, 563-565, 630-632, 668-670, 673-675, 682-685, 697-705, 726-727, 731-732, 802-805, 828-830 and appendices.
Mattingly, J.D. (1996). Elements of gas turbine propulsion. New York, New York: McGraw-Hill, Inc. pp. 1-18, 60-62, 85-87, 95-104, 121-123, 223-234, 242-245, 278-285, 303-309, 323-326, 462-179, 517-520, 563-565, 630-632, 673-675, 682-685, 697-699, 703-705, 802-805, 862-864, and 923-925.
Mattingly, J.D. (1996). Elements of gas turbine propulsion. New York, New York: McGraw-Hill, Inc. pp. 8-15.
Mattingly J.D., “Aircraft Engine Design,” American Institute of Aeronautics and Astronautics Inc, 2nd Edition, Jan. 2002, pp. 292-322.
Mattingly J.D., “Elements of Gas Turbine Propulsion”, New York, New York: McGraw-Hill, Inc. preface, 1996, pp. 719-720, 727-731, 735-738, 928-929, and 936-937.
Mattingly J.D., et al., “Aircraft Engine Design”, American Institute of Aeronautics and Astronautics Inc, 2nd ed, 2002, XP008175104, ISBN 1-56347-538-3, pp. 292-310.
Mattingly, J.D, Heiser, W.H., Boyer, K.M., Haven, B.A., and Pratt, D.T. (2002). Aircraft engine design. American Institute of Aeronautics and Astronautics Inc, 2nd ed, 2002, XP008175104, ISBN 1-56347-538-3, pp. 290-292.
Mavris, D.N., Schutte, J.S. (2016). Application of deterministic and probabilistic system design methods and enhancements of conceptual design tools for ERA project final report. NASA/CR-2016-219201. May 1, 2016. pp. 1-240.
McArdle, J.G. and Moore, A.S. (1979). Static test-stand performance of the YF-102 turobfan engine with several exhaust configurations for the Quiet Short-Haul Research Aircraft (QSRA). Prepared for NASA. NASA-TP-1556. Nov. 1979. pp. 1-68.
McCracken, R.C. (1979). Quiet short-haul research aircraft familiarization document. NASA-TM-81149. Nov. 1, 1979. pp 1-76.
McCune, M.E. (1993). Initial test results of 40,000 horsepower fan drive gear system for advanced ducted propulsion systems. AIAA 29th Joint Conference and Exhibit. Jun. 28-30, 1993. pp. 1-10.
McMillian, A. (2008) Material development for fan blade containment casing. Abstract. p. 1. Conference on Engineering and Physics: Synergy for Success 2006. Journal of Physics: Conference Series vol. 105. London, UK. Oct. 5, 2006.
Meier N. (2005) Civil Turbojet/Turbofan Specifications. Retrieved from http://jet-engine.net/civtfspec.html.
Merriam-Webster's collegiate dictionary, 10th Ed. (2001). p. 1125-1126.
Merriam-Webster's collegiate dictionary, 11th Ed. (2009). p. 824.
Meyer, A.G. (1988). Transmission development of Textron Lycoming's geared fan engine. Technical Paper. Oct. 1988. pp. 1-12.
Middleton, P. (1971). 614: VFW's jet feederliner. Flight International, Nov. 4, 1971. p. 725, 729-732.
Misel, O.W. (1977). QCSEE main reduction gears test program. NASA CR-134669. Mar. 1, 1977. pp. 1-222.
Moxon, J. How to save fuel in tomorrow's engines. Flight International. Jul. 30, 1983. 3873(124). pp. 272-273.
Muhlstein, C.L., Stach, E.A., and Ritchie, R.O. (2002). A reaction-layer mechanism for the delayed failure of micron-scale polycrystalline silicon structural films subjected to high-cycle fatigue loading. Acta Materialia vol. 50. 2002. pp. 3579-3595.
Munt, R. (1981). Aircraft technology assessment: Progress in low emissions engine. Technical Report. May 1981. pp. 1-171.
Nagendra S., et al., “Optimal rapid multidisciplinary response networks: RapidDisk,” Structural and Multidisciplinary Optimization, Springer, Berlin, DE, vol. 29, No. 3, Mar. 1, 2005, pp. 213-231.
Nanocor Technical Data for Epoxy Nanocomposites using Nanomer 1.30E Nanoclay. Nnacor, Inc. Oct. 2004.
NASA Conference Publication. (1978). CTOL transport technology. NASA-CP-2036-PT-1. Jun. 1, 1978. pp. 1-531.
NASA Conference Publication. Quiet, powered-lift propulsion. Cleveland, Ohio. Nov. 14-15, 1978. pp. 1-420.
NASA, Engine Weight Model, Glenn Research Center, Retrieved from, http://www.grc.nasa.gov/WWW/K-12/airplane/turbwt.html, Mar. 11, 2016.
Edkins, D.P., Hirschkron, R., and Lee, R. (1972). TF34 turbofan quiet engine study. Final Report prepared for NASA. NASA-CR-120914. Jan. 1, 1972. pp. 1-99.
Edwards, T. and Zabarnick, S. (1993). Supercritical fuel deposition mechanisms. Ind. Eng. Chem. Res. vol. 32. 1993. pp. 3117-3122.
El-Sayad, A.F. (2008). Aircraft propulsion and gas turbine engines. Boca Raton, FL: CRC Press. pp. 215-219 and 355-360.
Engine Alliance GP7200. Jane's Aero-Engines. Jane's by IHS Markit. Jul. 12, 2010.
English Translation of Measurement and Calculation Methodology on TFE731-2, TFE731-3A and TFE731-3D Models, 14 pages.
EP Office Action for Application No. EP16159312.4, dated Oct. 16, 2018, 10 pages.
EP Office Action for Application No. EP16174051.9, dated Oct. 15, 2018, 28 pages.
EP Office Action for Application No. EP17199484.1, dated Jan. 2, 2019, 5 pages.
Epstein, A. (2015). The Pratt & Whitney PurePower Geared Turbofan engine. Academie de l'Air et de l'Espace. Paris. Sep. 2015. pp. 1-27.
European Aviation Safety Agency, Type-Certificate Data Sheet for PW1500G Series Engines, No. M.E.090, Dec. 6, 2016, pp. 1-14.
European Search Report for Application No. EP13743042.7, dated Aug. 14, 2015, 9 pages.
European Search Report for Application No. EP13743283.7, dated Oct. 5, 2015, 8 pages.
European Search Report for Application No. EP13744335.4, dated Oct. 6, 2015, 9 pages.
European Search Report for Application No. EP13775188.9 dated Aug. 11, 2015.
European Search Report for Application No. EP13777804.9, dated Oct. 20, 2015, 9 pages.
European Search Report for Application No. EP13778330.4, dated Oct. 15, 2015, 7 pages.
European Search Report for Application No. EP13786893.1 dated Oct. 12, 2015, 7 pages.
European Search Report for Application No. EP15199577.6, dated May 4, 2016, 10 pages.
European Search Report for Application No. EP15199916.6, dated May 4, 2016, 9 pages.
European Search Report for Application No. EP16150651.4, dated May 24, 2016, 7 pages.
European Search Report for Application No. EP16161464.9, dated Jul. 22, 2016, 9 pages.
European Search Report for Application No. EP16161484.7, dated Jul. 22, 2016, 8 pages.
European Search Report for Application No. EP16170111.5 dated Dec. 12, 2016.
European Search Report for Application No. EP16174322.4, dated Nov. 18, 2016, 9 pages.
European Search Report for Application No. EP16195861.6, dated Mar. 20, 2017, 9 pages.
European Search Report for Application No. EP16196567.8, dated Mar. 17, 2017, 8 pages.
European Search Report for Application No. EP16197349.0 dated Mar. 20, 2017, 7 pages.
European Search Report for Application No. EP16197814.3, dated Mar. 21, 2017, 9 pages.
European Search Report for Application No. EP17204160.0, dated on Mar. 22, 2018.
European Search Report for Application No. EP19179274.6, dated Sep. 3, 2019, 12 pages.
European Search Report for Application No. EP20162850.0 dated Aug. 18, 2020.
European Search Report for European Patent Application No. 20207411.8 dated Mar. 4, 2021.
Extended European Search Report for Application No. EP17204153.5, dated Mar. 15, 2018.
Extended European Search Report for Application No. EP17210308.7, dated Apr. 19, 2018, 10 pages.
Faghri, A. (1995). Heat pipe and science technology. Washington, D.C.: Taylor & Francis. pp. 1-60.
Falchetti, F., Quiniou, H., and Verdier, L. (1994). Aerodynamic design and 3D Navier-Stokes analysis of a high specific flow fan. ASME. Presented at the International Gas Turbine and Aeroengine Congress and Exposition. The Hague, Netherlands. Jun. 13-16, 1994. pp. 1-10.
Fanchon J-L., “Guide De Sciences Et Technologies Industrielles,” Paris, France: Nathan, AFNOR, 1994, pp. 359-360.
File History for U.S. Appl. No. 12/131,876.
Final Written Decision. General Electric Company, Petitioner, v. United Technologies Corp., Patent Owner. IPR2018-01442. U.S. Pat. No. 9,695,751. Entered Feb. 20, 2020. pp. 1-72.
Fisher, K., Berton, J., Guynn, M., Haller B., Thurman, D., and Tong, M. (2012). NASA's turbofan engine concept study for a next-generation single-aisle transport. Presentation to ICAO's noise technology independent expert panel. Jan. 25, 2012. pp. 1-23.
Fitzpatrick G.A., et al., “Diffusion Bonding Aeroengine Components,” Def Scie J , Oct. 1998 , vol. 38, Issue. 4, pp. 477-485.
Fitzpatrick G.A., et al., “The Rolls-Royce Wide Chord Fan Blade, Rolls-Royce Reporting,” Mar. 19, 1987, pp. 1-19.
Fledderjohn, K.R. (1983). The TFE731-5: Evolution of a decade of business jet service. SAE Technical Paper Series. Business Aircraft Meeting & Exposition. Wichita, Kansas. Apr. 12-15, 1983. pp. 1-12.
Fowler T.W., “Jet Engines and Propulsion Systems for Engineers,” GE Aircraft Engines, Training and Educational Development and the University of Cincinnati for Human Resource Development, 1989, pp. 1-516.
Frankenfeld, J.W. and Taylor, W.F. (1980). Deposit fromation from deoxygenated hydrocarbons. 4. Studies in pure compound systems Ind. Eng. Chem., Prod. Res. Dev., vol. 19(1). 1978. pp. 65-70.
Gardner W.B., “Energy efficient engine flight propulsion system preliminary analysis and design report,” NASA CR-159487, 1979, pp. 1-450.
Gardner W.B. (1979). Energy efficient engine: High pressure turbine uncooled rig technology report. NASA-CR-165149. Oct. 1979, pp. 1-242.
Garret TFE731 Turbofan Engine (Cat C). Chapter 79: Lubrciation System. TTFE731 Issue 2. 2010. pp. 1-24.
Gas Turbine Technology, “Introduction to a Jet Engine”, Rolls-Royce plc, Dec. 2007.
Gates, D. Bombardier flies at higher market. Seattle Times. Jul. 13, 2008. pp. C6.
Related Publications (1)
Number Date Country
20220403788 A1 Dec 2022 US
Provisional Applications (1)
Number Date Country
61619111 Apr 2012 US
Continuations (3)
Number Date Country
Parent 17037916 Sep 2020 US
Child 17730782 US
Parent 16186811 Nov 2018 US
Child 17037916 US
Parent 14593056 Jan 2015 US
Child 16186811 US
Continuation in Parts (1)
Number Date Country
Parent 13446312 Apr 2012 US
Child 14593056 US