公开(公告)号：US12168959B2

公开(公告)日：2024-12-17

申请号：US18242104

申请日：2023-09-05

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 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.

公开(公告)号：US20240401500A1

公开(公告)日：2024-12-05

申请号：US18420862

申请日：2024-01-24

Applicant: RTX CORPORATION

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  William K. Ackermann ,  Daniel Bernard Kupratis ,  Michael E. McCune

IPC: F01D25/16 ,  F01D15/12 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, propulsor means, first compression means, second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means, and second expansion means. The reduction means includes an epicyclic gear system with a gear reduction. The gear system is straddle-mounted by first and second bearings on opposite sides of the gear reduction relative to an engine longitudinal axis.

公开(公告)号：US11970982B2

公开(公告)日：2024-04-30

申请号：US17987247

申请日：2022-11-15

Applicant: RTX CORPORATION

Inventor： Michael E. McCune

IPC: F02C7/36 ,  F01D15/12 ,  F02K3/04 ,  F02K3/072 ,  F16H1/28 ,  F16H1/46 ,  F16H57/00

CPC classification number: F02C7/36 ,  F01D15/12 ,  F02K3/04 ,  F02K3/072 ,  F16H1/28 ,  F16H1/46 ,  F16H57/0006 ,  F05D2260/40311 ,  Y02T50/60

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor, a gear reduction, a first spool including a first compressor, a first turbine and a first shaft, and a second spool including a second compressor, a second turbine and a second shaft. The gear reduction includes a carrier and a plurality of gears. The plurality of gears include a sun gear, a ring gear, and a plurality of intermediate gears that engage the sun gear and the ring gear. At least two of the plurality of gears are double helical gears in meshed engagement.

公开(公告)号：US20250092832A1

公开(公告)日：2025-03-20

申请号：US18370497

申请日：2023-09-20

Applicant: RTX CORPORATION

Inventor： Marc J. Muldoon ,  Michael E. McCune

IPC: F02C7/32 ,  F16H57/04

Abstract: A fan drive gear system for a turbine engine includes an auxiliary reservoir that is disposed radially outward of a rotating carrier and an oil director that is attached to the carrier. The oil director imparts a rotational flow direction into expelled oil to drive the expelled oil tangentially against an oil receiving surface and into the auxiliary reservoir.

公开(公告)号：US11933190B2

公开(公告)日：2024-03-19

申请号：US18300558

申请日：2023-04-14

Applicant: RTX Corporation

Inventor： Marc J. Muldoon ,  Michael E. McCune ,  Keith B. Allyn

IPC: F01D5/02 ,  F01D9/02 ,  F01D25/24 ,  F01D25/28

CPC classification number: F01D25/28 ,  F01D9/02 ,  F01D25/24 ,  F05D2240/14 ,  F05D2260/30 ,  F05D2260/606

Abstract: A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A rigid connection between a fan case and an inner core housing includes a plurality of A-frames connected at a connection point to the fan case. Legs in the A-frames extend away from the connection point in opposed circumferential directions to be connected to a compressor wall of the inner core housing. The rigid connection also includes a plurality of fan exit guide vanes rigidly connected to the fan case. A lateral stiffness ratio of the lateral stiffness of the plurality of fan exit guide vanes and a lateral stiffness of a combination of the plurality of A-frame, the compressor wall, and a fan intermediate case which is forward of the low pressure compressor being greater than or equal to 0.6 and less than or equal to 2.0.

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：US20250052202A1

公开(公告)日：2025-02-13

申请号：US18446088

申请日：2023-08-08

Applicant: RTX CORPORATION

Inventor： Mark A. Klein ,  Michael E. McCune

IPC: F02C7/36 ,  F02C7/06

Abstract: A fan drive gear system for a turbine engine includes a gear system with a plurality of compound intermediate gears that each include a first gear portion and a second gear portion. The second gear portion includes a forward gear portion and an aft gear portion and a ring gear assembly includes a forward ring gear that is engaged to the forward gear portion and an aft ring gear that is engaged to the aft gear portion. A carrier supports rotation of the plurality of intermediate gears with a plurality of corresponding journal bearing assemblies.

公开(公告)号：US20250052168A1

公开(公告)日：2025-02-13

申请号：US18818804

申请日：2024-08-29

Applicant: RTX CORPORATION

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

IPC: F01D15/12 ,  F01D1/02 ,  F01D5/02 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F02C7/36 ,  F02K3/06 ,  F16H57/04 ,  F16H57/08

Abstract: A gas turbine engine according to an example of the present disclosure includes a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier and a ring gear including first and second portions. The first and second portions have axially opposed faces abutting one another at a radial interface.

公开(公告)号：US12163582B2

公开(公告)日：2024-12-10

申请号：US17505015

申请日：2021-10-19

Applicant: RTX CORPORATION

Inventor： Michael E. McCune ,  Jason Husband

IPC: F01D25/16 ,  F02C7/36 ,  F02K3/06 ,  F04D25/02 ,  F04D29/053 ,  F04D29/056 ,  F16H1/28 ,  F16H57/028

Abstract: A gas turbine engine including a drive shaft that drives a propulsor. A frame which supports the drive shaft is a K-frame bearing support. A gear system is connected to the drive shaft. The gear system includes a gear mesh that defines a gear mesh lateral stiffness and a gear mesh transverse. A flexible support supports the gear system that defines a flexible support transverse stiffness and a flexible support lateral stiffness. The flexible support lateral stiffness is less than 8% of the gear mesh lateral stiffness.

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.