Patent Application
20160201516
This disclosure relates to a gas turbine engine mid-turbine frame tie rod arrangement.
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 mid-turbine frame (MTF) is arranged axially between the high and low pressure turbines. One example MTF includes inner and outer cases secured to one another with tie rods extending radially between the cases. Airfoils are provided between the inner and outer cases, and the tie rods extend through some of the airfoils. In one arrangement, one end of the tie rod is threaded and secured to the outer case. The inner end of the rod includes a flange secured to the inner case by multiple fasteners.
In one exemplary embodiment, a gas turbine engine mid-turbine frame includes an annular case which includes a first face. A tie rod includes a flange that is secured to the annular case. The flange has a perimeter that provides a second face that engages the first face and is configured to retain the flange in a generally axial direction.
In a further embodiment of the above, the annular case is an inner case. The tie rod includes a first end secured to an outer case.
In a further embodiment of any of the above, the inner case includes an outer diameter surface that provides a pocket. The flange is arranged in the pocket.
In a further embodiment of any of the above, the first end includes a threaded portion. A fastener is secured to the threaded portion to clamp the tie rod between the inner and outer cases.
In a further embodiment of any of the above, the first face is provided on an aft side of the pocket.
In a further embodiment of any of the above, the first face is provided on a forward side of the pocket.
In a further embodiment of any of the above, the first face is provided on each of an aft side and a forward side of the pocket. The perimeter provides second faces that engage both of the aft side and forwards side faces.
In a further embodiment of any of the above, multiple fasteners secure the flange to the inner case.
In a further embodiment of any of the above, the inner case includes an inner diameter surface that has a flat. The fasteners are seated on the flat.
In another exemplary embodiment, a gas turbine engine includes a turbine section including high and low pressure turbines. A mid-turbine frame is arranged axially between the high and low pressure turbines. The mid-turbine frame includes an annular case which includes a first face. A tie rod includes a flange secured to the annular case. The flange has a perimeter that provides a second face that engages the first face and is configured to retain the flange in a generally axial direction.
In a further embodiment of any of the above, the annular case is an inner case. The tie rod includes a first end secured to an outer case.
In a further embodiment of any of the above, the inner case includes an outer diameter surface that provides a pocket. The flange is arranged in the pocket.
In a further embodiment of any of the above, the first end includes a threaded portion. A fastener is secured to the threaded portion to clamp the tie rod between the inner and outer cases.
In a further embodiment of any of the above, the first face is provided on an aft side of the pocket.
In a further embodiment of any of the above, the first face is provided on a forward side of the pocket.
In a further embodiment of any of the above, the first face is provided on each of an aft side and a forward side of the pocket. The perimeter provides second faces that engage both of the aft side and forwards side faces.
In a further embodiment of any of the above, multiple fasteners secure the flange to the inner case.
In a further embodiment of any of the above, the inner case includes an inner diameter surface that has a flat. The fasteners seated on the flat.
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 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 exemplary gas turbine 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 engine 20 in one example is a high-bypass geared aircraft engine. In a further example, the 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 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 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).
One example of the mid-turbine frame (MTF) 57 is shown in more detail in
Each tie rod 70 includes first and second opposing ends 72, 74, which respectively include a threaded portion 76 and a flange 78. In one embodiment, the flange 78 is received in a pocket 86 in the outer diameter of the inner case 60. Bolts 82 extend through holes 77, 79 in the flange 78 and inner case 60 and are secured by nuts 80. A flat 90 is provided at an inner diameter of the inner case 60 against which the bolts 82 seat (see also
Referring to
In the example embodiment shown in
During assembly, the flange 78 is seated within the pocket 86 and secured to the inner case 60 by nuts 80 and bolts 82. The faces 92, 94 engage one another. The airfoil 59 is arranged over the tie rod 70. The first end 72 is aligned with a boss 96 in the outer case 62, and a fastener 98 is secured to the threaded portion 76 to clamp the inner and outer cases 60, 62 to the tie rod 70.
It should also be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom. For example, the disclosed arrangement can be used for a turbine exhaust case. 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.
