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公开(公告)号：US12123373B2
公开(公告)日：2024-10-22
申请号：US16931685
申请日：2020-07-17
CPC分类号： F02K3/06 , F02C7/36 , F05D2220/323 , F05D2220/36 , F05D2240/35 , F05D2240/60 , F05D2260/40311
摘要： A gas turbine engine includes a fan shaft rotatable about an axis, a fan connected to the fan shaft, and an outer housing surrounding the fan to define a bypass passage. A compressor section has both a low pressure compressor that is fixed to rotate with the fan shaft and a high pressure compressor. A turbine section has a low pressure turbine driving a low speed spool and a high pressure turbine driving the high pressure compressor. The low pressure turbine includes rotating blades and a static structure aft of the rotating blades. A fan drivetrain includes a geared architecture connecting the low speed spool to the fan shaft such that the fan and low pressure compressor rotate at a lower speed than the low pressure turbine. A thrust bearing is axially aft of the geared architecture and axially forward of the high pressure compressor. A tower shaft is rotatably driven by the low speed spool.
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公开(公告)号：US11746664B2
公开(公告)日：2023-09-05
申请号：US17483210
申请日：2021-09-23
CPC分类号： F01D9/041 , F01D25/162 , F01D25/28 , F05D2220/32
摘要： A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction. An inner core engine has an inner core engine housing surrounding a compressor section, including a low pressure compressor. A rigid connection between a fan case and the inner core engine includes A-frames rigidly connected at a connection point to the fan case. Fan exit guide vanes rigidly connect to the fan case, and to the inner core engine. A fan intermediate case is positioned forward of a first rotor stage in the low pressure compressor. A rigid structure is connected to the inner core engine and to the fan exit guide vanes. The rigid structure defines a structure moment stiffness. The fan intermediate case defines an intermediate case moment stiffness. A ratio of the structure moment stiffness to the intermediate case moment stiffness is between 5 and 15.
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公开(公告)号：US11698007B2
公开(公告)日：2023-07-11
申请号：US17321018
申请日：2021-05-14
发明人： Michael E. McCune , Jason Husband
IPC分类号： F01D25/16 , F02C7/32 , F02C7/36 , F01D15/12 , F01D25/28 , F01D5/06 , F01D9/02 , F02K3/06 , F04D25/04 , F04D29/053 , F04D29/32 , F04D19/02 , F04D29/056
CPC分类号： F01D25/164 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/16 , F01D25/28 , F02C7/32 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/045 , F04D29/053 , F04D29/056 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/60 , F05D2260/40311 , F05D2260/96 , Y02T50/60 , Y10T29/49321
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft configured to drive a fan, a support configured to support at least a portion of the fan shaft, the support defining a support transverse stiffness and a support lateral stiffness, a gear system coupled to the fan shaft, and a flexible support configured to at least partially support the gear system. The flexible support defines a flexible support transverse stiffness with respect to the support transverse stiffness and a flexible support lateral stiffness with respect to the support lateral stiffness. The input defines an input transverse stiffness with respect to the support transverse stiffness and an input lateral stiffness with respect to the support lateral stiffness.
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公开(公告)号：US20230122298A1
公开(公告)日：2023-04-20
申请号：US18068660
申请日：2022-12-20
摘要： A gas turbine engine includes a propulsor section and a speed change mechanism for driving the propulsor section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers extending from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first propulsor section support bearing is mounted on a first axial side of the speed change mechanism and a second propulsor section support bearing is mounted on the bearing support on a second axial side of the speed change mechanism. The second propulsor section support bearing is a propulsor thrust bearing. Each of the plurality of fingers include a pin opening with a pin extending through the pin opening and into the epicyclic gear train.
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公开(公告)号：US11608779B2
公开(公告)日：2023-03-21
申请号：US16786421
申请日：2020-02-10
摘要： A turbofan engine includes a fan that delivers air into a bypass duct and into a core engine. A fan drive gear system includes a gear carrier and at least one ring gear. The at least one ring gear is coupled to an engine case of the turbofan engine with a compliant flexure. A fan shaft couples the gear carrier in the fan drive gear system to the fan. A first bearing is forward of the fan drive gear system and supports the fan drive gear system. A second bearing is aft of the fan drive gear system and supports the fan drive gear system.
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公开(公告)号：US11448310B2
公开(公告)日：2022-09-20
申请号：US17365220
申请日：2021-07-01
摘要： A method of assembling an epicyclic gear train includes positioning a carrier, the carrier being a unitary structure with side walls and mounts unitary with one another, inserting intermediate gears through a central opening of the carrier, moving each of the intermediate gears into intermediate gear pockets, inserting baffles into the carrier, inserting a sun gear through the central opening, and moving the intermediate gears to intermesh with the sun gear, and moving a ring gear into engagement with the intermediate gears.
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公开(公告)号：US11434829B2
公开(公告)日：2022-09-06
申请号：US17236850
申请日：2021-04-21
摘要： A gas turbine engine may include a high speed spool, a low speed spool, a first epicyclic gear system, and a second epicyclic gear system. Generally, the high speed spool mechanically connects a high pressure turbine to a high pressure compressor, and the low speed spool mechanically connects a low pressure turbine to at least one of a fan and a prop via the first epicyclic gear system and to a low pressure compressor via the second epicyclic gear system, according to various embodiments. The first epicyclic gear system and the second epicyclic gear system may include a common sun gear shaft.
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公开(公告)号：US20220128060A1
公开(公告)日：2022-04-28
申请号：US17570728
申请日：2022-01-07
IPC分类号： F04D25/16 , F02C7/06 , F01D21/04 , F01D21/02 , F02C7/36 , F01D5/02 , F01D15/12 , F04D25/04 , F04D29/041 , F04D29/046 , F16H1/28 , F16H57/10
摘要： A gas turbine engine has a fan drive turbine driving a gear reduction, the gear reduction, in turn, driving a fan rotor, the fan rotor delivering air into a bypass duct as bypass air and into a compressor section as core flow. A forward bearing is positioned between the gear reduction and the fan rotor and supports the gear reduction. A second bearing is positioned aft of the gear reduction and supports the gear reduction. The second bearing is a thrust bearing. A fan drive turbine drive shaft drives the gear reduction. The fan drive turbine drive shaft has a weakened link which is aft of the second bearing such that the fan drive turbine drive shaft will tend to fail at the weakened link, and at a location aft of the second bearing.
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公开(公告)号：US11174936B2
公开(公告)日：2021-11-16
申请号：US16747934
申请日：2020-01-21
发明人： Michael E. McCune , Jason Husband
IPC分类号： F01D25/16 , F02C7/36 , F16H57/028 , F02K3/06 , F04D25/02 , F04D29/053 , F04D29/056 , F16H1/28
摘要： A gas turbine engine includes a fan shaft that drives a fan that has fan blades. The fan delivers airflow to a bypass duct. A gear system is connected to the fan shaft and is driven through an input defining an input lateral stiffness and an input transverse stiffness. A gear system flex mount arrangement accommodates misalignment of the fan shaft and the input during operation. A frame for supporting the fan shaft defines a frame lateral stiffness and a frame transverse stiffness. The input lateral stiffness is less than 11% of the frame lateral stiffness and the input transverse stiffness is less that 11% of the frame transverse stiffness.
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公开(公告)号：US20210285380A1
公开(公告)日：2021-09-16
申请号：US17195848
申请日：2021-03-09
发明人： Gabriel L. Suciu , Hung Duong , Jonathan F. Zimmitti , William G. Sheridan , Michael E. McCune , Brian Merry
IPC分类号： F02C7/32 , F02C3/06 , F02C7/18 , F02C7/36 , F02C7/268 , F01D15/10 , F01D25/12 , F16H1/22 , H02K7/116 , H02K7/18 , F01D15/12 , F02C7/275
摘要： An exemplary gas turbine engine assembly includes a fan section including a fan, a first spool having a first turbine operatively mounted to a first turbine shaft, and a second spool having a second turbine operatively mounted to a second turbine shaft. The first and second towershafts are respectively coupled to the first and second turbine shafts. An accessory drive gearbox includes a set of gears. A compressor is driven by the first towershaft. A transmission couples a starter generator assembly to the set of gears. The transmission is transitionable between a first mode where the starter generator assembly is driven at a first speed relative to the second towershaft in response to rotation of the second towershaft, and a second mode where the starter generator assembly is driven at a different, second speed relative to the second towershaft in response to rotation of the second towershaft.
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