公开(公告)号：US11994074B2

公开(公告)日：2024-05-28

申请号：US18068660

申请日：2022-12-20

Applicant: RTX Corporation

Inventor： Gary D. Roberge ,  Michael E. McCune ,  William G. Sheridan

IPC: F02C7/36 ,  F01D25/16

CPC classification number: F02C7/36 ,  F01D25/16 ,  F05D2260/40311 ,  F05D2260/98

Abstract: 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.

公开(公告)号：US11885252B2

公开(公告)日：2024-01-30

申请号：US16006327

申请日：2018-06-12

Applicant: RTX CORPORATION

Inventor： William G. Sheridan ,  Michael E. McCune ,  Lawrence E. Portlock

IPC: F01D25/16 ,  F01N3/20 ,  F01D25/18 ,  F02C3/10 ,  F02K3/06 ,  F02C7/36 ,  F02C7/06 ,  F02C7/10 ,  F01N11/00 ,  F16N7/34

CPC classification number: F01N3/208 ,  F01D25/16 ,  F01D25/18 ,  F01N3/2066 ,  F01N11/00 ,  F02C3/10 ,  F02C7/06 ,  F02C7/10 ,  F02C7/36 ,  F02K3/06 ,  F01N2610/01 ,  F01N2610/02 ,  F01N2610/142 ,  F01N2610/1406 ,  F01N2610/148 ,  F01N2900/1814 ,  F05D2260/40311 ,  F16N7/34 ,  Y02T10/12 ,  Y02T50/60 ,  Y10T29/4932 ,  Y10T137/0324 ,  Y10T137/7297

Abstract: In an embodiment of the present disclosure, a gas turbine engine includes a fan, a first compressor stage and a second compressor stage, a first turbine stage and a second turbine stage, and wherein said first turbine stage drives said second compressor stage as a high spool, and wherein said second turbine stage drives said first compressor stage as part of a low spool, and a gear train driving said fan with said low spool, and such that said fan and said first compressor stage rotate in the same direction, and wherein said high spool operates at higher pressures than said low spool.

公开(公告)号：US11846237B2

公开(公告)日：2023-12-19

申请号：US17195848

申请日：2021-03-09

Applicant: RTX CORPORATION

Inventor： Gabriel L. Suciu ,  Hung Duong ,  Jonathan F. Zimmitti ,  William G. Sheridan ,  Michael E. McCune ,  Brian Merry

IPC: F02C7/32 ,  F02C3/06 ,  F02C7/18 ,  F02C7/36 ,  F02C7/268 ,  F01D15/10 ,  F01D25/12 ,  F16H1/22 ,  H02K7/116 ,  H02K7/18 ,  F01D15/12 ,  F02C7/275

CPC classification number: F02C7/32 ,  F01D15/10 ,  F01D15/12 ,  F01D25/12 ,  F02C3/06 ,  F02C7/185 ,  F02C7/268 ,  F02C7/275 ,  F02C7/36 ,  F16H1/222 ,  H02K7/116 ,  H02K7/1823 ,  F05D2220/32 ,  F05D2260/4031 ,  F05D2260/85

Abstract: 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.

公开(公告)号：US20250084785A1

公开(公告)日：2025-03-13

申请号：US18959834

申请日：2024-11-26

Applicant: RTX CORPORATION

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine includes a plurality of blades that deliver air into a compressor section and a drive gear system including an epicyclic transmission. A drive shaft interconnects a gear carrier of the epicyclic transmission and the plurality of blades. A turbine section drives an input of the drive gear system through a turbine shaft. The drive gear system is straddle mounted by a first bearing forward of the drive gear system and a second bearing aft of the drive gear system. A ring gear of the epicyclic transmission is coupled to an engine case with a compliant flexure at a position between the first bearing and the second bearing.

公开(公告)号：US20250043732A1

公开(公告)日：2025-02-06

申请号：US18919600

申请日：2024-10-18

Applicant: RTX CORPORATION

Inventor： Michael E. McCune ,  William G. Sheridan

IPC: F02C7/36 ,  F02C3/107 ,  F02C7/32 ,  F02K3/06 ,  F16H1/28 ,  F16H57/023 ,  F16H57/04 ,  F16H57/08

Abstract: A method of mounting a gear train to a torque frame comprises the steps of providing a unitary carrier having a central axis that includes spaced apart side walls and circumferentially spaced connecting structure defining mounts that interconnect the side walls, spaced apart apertures provided between the mounts at an outer circumference of the carrier, gear pockets provided between the side walls and the mounts extending to the apertures, and a central opening in at least one of the side walls. A plurality of intermediate gears are inserted in the carrier. A first ring gear half of a ring gear is placed about the outer periphery of the intermediate gears. A torque frame is attached to the carrier.

公开(公告)号：US12188407B2

公开(公告)日：2025-01-07

申请号：US18108270

申请日：2023-02-10

Applicant: RTX CORPORATION

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine includes a propulsor and a drive gear system. The drive gear system includes at least one ring gear, a plurality of intermediate gears positioned between and enmeshing with a sun gear and the at least one ring gear, with the plurality of intermediate gears carried by a gear carrier. A first bearing is configured to rotate with the gear carrier. A second bearing is on an opposite side of the drive gear system from the first bearing.

公开(公告)号：US20240110497A1

公开(公告)日：2024-04-04

申请号：US18536711

申请日：2023-12-12

Applicant: RTX CORPORATION

Inventor： William G. Sheridan ,  Michael E. McCune ,  Lawrence E. Portlock

IPC: F01N3/20 ,  F01D25/16 ,  F01D25/18 ,  F01N11/00 ,  F02C3/10 ,  F02C7/06 ,  F02C7/10 ,  F02C7/36 ,  F02K3/06

CPC classification number: F01N3/208 ,  F01D25/16 ,  F01D25/18 ,  F01N3/2066 ,  F01N11/00 ,  F02C3/10 ,  F02C7/06 ,  F02C7/10 ,  F02C7/36 ,  F02K3/06 ,  F05D2260/40311 ,  F16N7/34 ,  Y10T29/4932

Abstract: A gas turbine engine includes a fan shaft diving a fan having fan blades. The gas turbine engine also includes a gear system including a sun gear surrounded by a plurality of intermediate gear, a carrier at least partially supporting said plurality of intermediate gears, and a ring gear surrounding said plurality of intermediate gears, wherein said sun gear is driven by a turbine. The gas turbine engine also includes a flexible coupling fixing said ring gear from rotation relative to an engine static structure and a lubricating system for said gear system. Said lubricating system includes a lubricant input, there being a stationary first bearing receiving lubricant from said lubricant input. Said bearing has an inner first race in which lubricant flows, and a second bearing for rotation within said first bearing. Said second bearing has a first opening in registration with said inner first race such that lubricant may flow from said inner first race through said first opening into a first conduit. Said first conduit is in fluid communication with said plurality of intermediate gears. A gas turbine engine is also disclosed.

公开(公告)号：US20230407796A1

公开(公告)日：2023-12-21

申请号：US18242104

申请日：2023-09-05

Applicant: RTX CORPORATION

Inventor： Michael E. McCune ,  William G. Sheridan

IPC: F02C7/36 ,  F16H57/08 ,  F02K3/06 ,  F02C3/107 ,  F02C7/32 ,  F16H57/023 ,  F16H1/28

CPC classification number: F02C7/36 ,  F16H57/082 ,  F02K3/06 ,  F02C3/107 ,  F16H57/0486 ,  F16H57/023 ,  F16H1/28 ,  Y10T29/49464 ,  F02C7/32

Abstract: A gear reduction for a gas turbine engine includes intermediate gears, a single structure establishing a carrier centered on an axis and having a pair of axially spaced apart side walls, axially extending circumferentially spaced connecting structure for connecting the pair of side walls, a central opening in at least one of the side walls, and circumferentially spaced smaller openings spaced radially outwardly of the central opening, with internal surfaces of the circumferentially spaced connecting structure defining intermediate gear pockets that extend away from the central opening to the circumferentially spaced openings. The intermediate gears are receivable through the central opening and are secured in the intermediate gear pockets. A ring gear includes a first ring gear half and a second ring gear half placed on an outer periphery of the intermediate gears such that ring gear teeth of the first and second ring gear halves engage with teeth of the intermediate gears.