Patent Application
20180171815
This disclosure relates to a traction drive transmission for an accessory drive gearbox of a gas turbine engine.
A gas turbine engine typically includes a fan section, a compressor section, a combustor section, and a turbine section. Air entering the compressor section is compressed and delivered into the combustor section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section. The compressor section typically includes low and high pressure compressors, and the turbine section includes low and high pressure turbines.
A typical gas turbine engine utilizes one or more gearboxes to drive accessory components, such as generators, fuel pumps and oil pumps. Each of the accessory drive components must be driven at a desired rotational speed. As a result, the accessory is coupled to either the low or high speed spool and geared accordingly to obtain the speed at which the accessory operates more efficiently. Thus, it is not uncommon to use one gearbox coupled to the low speed spool to drive lower speed accessory drive components, and use a separate gearbox coupled to the high speed spool to drive the other accessory drive components at a higher speed.
One gearbox has been proposed in which the accessory drive components are driven by a single towershaft. Other gearboxes have been proposed in which some accessory drive components are driven by a first towershaft, and other accessory drive components are driven by a second towershaft.
A gas turbine engine assembly according to an example of the present disclosure includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, an accessory drive gearbox a first towershaft interconnecting the accessory drive gearbox and the first or second turbine shaft, and a multispeed transmission interconnecting the accessory drive gearbox and at least one accessory component.
In a further embodiment of any of the foregoing embodiments, the multispeed transmission includes an output shaft coupled to the at least one accessory component, and the multispeed transmission varies a rotational speed of the output shaft relative to the first towershaft during operation.
In a further embodiment of any of the foregoing embodiments, the multispeed transmission is a traction drive transmission.
In a further embodiment of any of the foregoing embodiments, the at least one accessory component includes at least one of an electric machine and a hydraulic pump.
In a further embodiment of any of the foregoing embodiments, the first towershaft is geared to the first or second turbine shaft such that a rotational speed of the first towershaft and a first set of gears of the accessory drive gearbox varies linearly with a rotational speed of the first or second turbine shaft, with the multispeed transmission driven by the first set of gears.
A further embodiment of any other embodiments includes an oil pump driven by the first set of gears at a fixed ratio relative to the rotational speed of the first towershaft, wherein the oil pump delivers fluid to a bearing system including a bearing that supports the first turbine shaft, and the first towershaft is rotatably coupled to the first turbine shaft.
A further embodiment of any other embodiments includes an electronic engine control coupled to the multispeed transmission that causes the output shaft to rotate within a defined range.
In a further embodiment of any of the foregoing embodiment, the first and second turbine shafts are inner and outer shafts, respectively, and the first and second turbines are low and high pressure turbines, respectively.
In a further embodiment of any of the foregoing embodiments, the second turbine shaft is rotatable at a higher speed than the first turbine shaft during operation.
In a further embodiment of any of the foregoing embodiments, the multispeed transmission includes an output shaft coupled to the at least one accessory component, and the multispeed transmission varies a rotational speed of the output shaft relative to the first towershaft during operation.
In a further embodiment of any of the foregoing embodiments, the multispeed transmission is a continuously variable transmission defining a continuous range of effective gear ratios.
A further embodiment of any other embodiments includes a second towershaft rotatably coupled to another one of the first or second turbine shaft. The accessory drive gearbox includes a housing in which a first set of gears and a second set of gears are arranged. The first towershaft interconnects the first set of gears and the first turbine shaft, and the second towershaft interconnects the second set of gears and the second turbine shaft.
A method of driving accessories through an accessory gearbox of a gas turbine engine according to an example of the present disclosure includes rotating a first turbine shaft to drive a first towershaft. The first turbine shaft is mounted for rotation about a common rotational axis with a second turbine shaft. The first turbine shaft is coupled to a first turbine, and the second turbine shaft coupled to a second turbine driving a first set of gears of an accessory drive gearbox with the first towershaft. The method includes the step of driving a multispeed transmission with the first set of gears to rotate at least one accessory component at a first speed that differs from a second speed of the first towershaft.
In a further embodiment of any of the foregoing embodiments, the multispeed transmission includes an output shaft that drives the at least one accessory component, and the step of driving the multispeed transmission includes varying a rotational speed of the output shaft relative to the first towershaft.
In a further embodiment of any of the foregoing embodiments, the step of driving a multispeed transmission includes driving the at least one accessory component within a first range of rotational speeds that is less than a second range of rotational speeds of the first towershaft.
In a further embodiment of any of the foregoing embodiments, the multispeed transmission is a traction drive transmission.
In a further embodiment of any of the foregoing embodiments, the at least one accessory component includes at least one of an electric machine and a hydraulic pump.
A further embodiment of any other embodiments includes driving an oil pump with the first set of gears to supplying oil to a bearing system. The bearing system has a bearing supporting the first turbine shaft, and the first turbine shaft coupled to a geared architecture driving a fan through the geared architecture such that the fan rotates at a lower speed than the first turbine shaft.
A further embodiment of any other embodiments includes rotating the second turbine shaft at a higher speed than the first turbine shaft.
In a further embodiment of any of the foregoing embodiments, the step of driving the oil pump includes supplying oil to the bearing system during a windmilling event.
A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, an accessory drive gearbox driven by a towershaft rotatable coupled to the first or second turbine shaft, and a traction drive transmission to drive at least one component rotatably coupled to the accessory drive gearbox.
In a further non-limiting embodiment of the foregoing assembly, an electric machine is driven by the traction drive transmission.
The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
The embodiments, examples and alternatives of the preceding paragraphs, the claims, or the following description and drawings, including any of their various aspects or respective individual features, may be taken independently or in any combination. Features described in connection with one embodiment are applicable to all embodiments, unless such features are incompatible.
The exemplary gas turbine engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis X 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, and the location of bearing systems 38 may be varied as appropriate to the application.
The low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46. The inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as 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 second (or high) pressure compressor 52 and a second (or high) pressure turbine 54. A combustor 56 is arranged in the exemplary gas turbine engine 20 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 X which is collinear with their longitudinal axes.
The core airflow 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 C. The turbines 46, 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion. It will be appreciated that each of the positions of the fan section 22, compressor section 24, combustor section 26, turbine section 28, and fan drive gear system 48 may be varied. For example, gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28, and fan section 22 may be positioned forward or aft of the location of gear system 48.
The gas turbine engine 20 in one example is a high-bypass geared aircraft engine. In a further example, the gas turbine engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about 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 five. In one disclosed embodiment, the gas turbine 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 has a pressure ratio that is greater than about five 5:1. Low pressure turbine 46 pressure ratio is 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 an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1. 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 significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The fan section 22 of the gas turbine engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (10,668 meters). The flight condition of 0.8 Mach and 35,000 ft (10,668 meters), 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 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, without a 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 ° R)/(518.7° R)]0.5. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 meters/second).
Referring to
Although the exemplary accessory drive gearbox 60 is described as incorporating the first and second sets of gears 64, 66, another example of the accessory drive gearbox 60 could include a set of gears driven by the first towershaft 68, without any gears being driven by the second towershaft 70. Yet another example of the accessory drive gearbox 60 could include a set of gears driven by the second towershaft 70, without any gears being driven by the first towershaft 68.
Referring now to
In this example, the oil pump 80 is driven by the first towershaft 68 such that the rotational speed of the oil pump 80 varies linearly with the rotational speed of the first towershaft 68.
The electric machine 92 and the hydraulic pump 96 are driven by the first towershaft 68, but through the transmission 84. The transmission 84 can step up or step down the rotational speed of the output shaft 88 from the transmission 84 relative to the rotational speed of the first towershaft 68. This permits the electric machine 92 and the hydraulic pump 96 to rotate relative to the first towershaft 68 at different ratios.
Although the oil pump 80 is directly driven by the first towershaft 68, other examples could include directly driving other accessories instead of, or in addition to, the oil pump 80 with the first towershaft 68.
Although the electric machine 92 and the hydraulic pump 96 are driven by the output shaft 88 from the transmission 84, other examples could include driving other accessories instead of, or in addition to, the electric machine 92 or the hydraulic pump 96.
During operation, the inner shaft 40 can experience a greater range of rotational speeds that the outer shaft 50. That is, the speed excursion for the inner shaft 40 can be higher than the speed excursion for the outer shaft 50. In a specific non-limiting embodiment, the inner shaft 40 can operate at speed excursions of up to 80% during operation of the gas turbine engine 20, whereas the outer shaft 50 can operate at speed excursions of up to 30% during operation of the gas turbine engine 20.
In this exemplary embodiment, the first towershaft 68 is geared to the inner shaft 40, such that the rotational speed of the first towershaft 68 and the first set of gears 64 varies linearly with the rotational speed of the inner shaft 40. Also, the second towershaft 70 is geared to the outer shaft 50 so that the rotational speed of the second towershaft 70 and the second set of gears 66 varies linearly with the rotational speed of the outer shaft 50.
The transmission 84 addresses issues associated with rotating the electric machine 92 and the hydraulic pump 96 with a rotatable input from the first towershaft 68 from the inner shaft 40. In the exemplary embodiments, the transmission 84 can vary the rotational speed of the output shaft 88 relative to the rotational speed of the first towershaft 68 to rotate the electric machine 92 and hydraulic pump 96 at a desired rotational speed.
An electronic engine control (EEC) 100 can control the transmission 84 so that the output shaft 88 is rotated at a desired speed or within a desired range.
In this example, the transmission 84 is a traction drive or multispeed transmission. The transmission 84 lacks a plurality of fixed gear ratios and instead can change through a continuous range of effective gear ratios. The transmission 84 can be considered a continuously variable transmission (CVT) in some examples.
In this example, the electric machine 92 is an integrated drive generator or a variable frequency generator that receives a rotational input to generate power utilized by components of the gas turbine engine 20. The transmission 84 permits operating the electric machine 92 to be driven in a narrower rpm range while still being driven by rotation of the inner shaft 40 and the first towershaft 68.
The hydraulic pump 96 generally moves hydraulic fluid needed to move components of an air frame to which the gas turbine engine 20 is mounted. The transmission 84 permits operating the hydraulic pump 96 to be driven in a narrower rpm range while still being driven by rotation of the inner shaft 40 and the first towershaft 68.
The oil pump 80 is driven at a fixed ratio relative to the speed of the first towershaft 68. That is, the transmission 84 transitioning between its continuous range of effective gear ratios does not substantially change a ratio of rotational speeds between the first towershaft 68 and the oil pump 80.
In this example, the oil pump 80 is dedicated to supplying oil to the number 1 bearing systems 38′, which incorporates thrust bearings directly supporting the inner shaft 40. The thrust bearings are tapered bearings in some examples.
The rotational speed of the first towershaft 68 increases when the rotational speed of the inner shaft 40 increases. The inner shaft 40 may require additional lubrication, such as oil, directed to bearing systems 38 supporting the inner shaft 40 when the rotational speed of the inner shaft 40 increases.
The increased lubrication demands due to increasing the rotational speed of the inner shaft 40 are met by increasing the rotational input speed to the oil pump 82. In other words, the amount of oil moved to the number 1 bearing system 38′ varies linearly with the rotational speed of the inner shaft 40. If the oil pump 82 were instead varying linearly with the rotational speed of the outer shaft 50, the oil pump 82 may move more oil than is required for lubrication. The excess oil would need to recirculated, or accommodated in some other way, which results in losses.
An added feature of coupling rotation of the oil pump 82 with rotation of the inner shaft 40 is that the inner shaft 40 spins with the fan 42. Thus, during a windmilling event when the fan 42 is spinning without being driven by the inner shaft 40, the oil pump 80 can continue to pump oil lubricating the bearings associated with the inner shaft 40, including bearing system 38 supporting a fan rotor of the fan 42 and the geared architecture 48 (
Features of the some of the disclosed examples include driving accessory components of an accessory gearbox using a traction drive transmission. This can provide an idle thrust reduction, a reduction in EGT and mission fuel burn.
It should also be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom. Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present invention.
Although the different examples have specific components shown in the illustrations, embodiments of this invention are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples.
Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of the claims. For that reason, the following claims should be studied to determine their true scope and content.
This application claims the benefit of U.S. Provisional Application No. 62/435,342, filed Dec. 16, 2016, incorporated by reference in its entirety.
| Number | Date | Country | |
|---|---|---|---|
| 62435342 | Dec 2016 | US |
