公开(公告)号：US20210010584A1

公开(公告)日：2021-01-14

申请号：US17038724

申请日：2020-09-30

Applicant: Raytheon Technologies Corporation

Inventor： Michael E. McCune ,  Lawrence E. Portlock

IPC: F16H57/04 ,  F16H57/08 ,  F01D5/02 ,  F02C7/36 ,  F16D1/076 ,  F01D25/18 ,  F02C7/28 ,  F16H1/28

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a turbo fan supported on a turbo fan shaft, a turbine section including a turbine shaft, and an epicyclic gear train interconnecting the turbo fan 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 supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth, the first and second portions arranged about and intermeshing with the intermediate gears, the first and second portions abutting one another at a radial interface, the first and second portions including respective flanges extending along the radial interface radially outward from the teeth, and the teeth of the first and second portions being oppositely angled teeth.

公开(公告)号：US12084978B2

公开(公告)日：2024-09-10

申请号：US18196048

申请日：2023-05-11

Applicant: Raytheon Technologies Corporation

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

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

CPC classification number: F01D15/12 ,  F01D1/02 ,  F01D5/02 ,  F01D5/027 ,  F01D25/16 ,  F01D25/18 ,  F02C7/32 ,  F16H57/04 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/40311 ,  F16H57/0423 ,  F16H57/0479 ,  F16H57/0486 ,  F16H2057/085

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, 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：US11913349B2

公开(公告)日：2024-02-27

申请号：US18104375

申请日：2023-02-01

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

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

CPC classification number: F01D25/164 ,  F01D15/12 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, a compressor section, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, first and second bearings, and a fan drive shaft interconnecting the gear system and the fan. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：US20240003268A1

公开(公告)日：2024-01-04

申请号：US18300558

申请日：2023-04-14

Applicant: Raytheon Technologies Corporation

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

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

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：US20230304416A1

公开(公告)日：2023-09-28

申请号：US18196048

申请日：2023-05-11

Applicant: Raytheon Technologies Corporation

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

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

CPC classification number: F01D15/12 ,  F01D25/18 ,  F01D25/16 ,  F01D1/02 ,  F01D5/02 ,  F01D5/027 ,  F02C7/32 ,  F16H57/04 ,  F05D2220/32 ,  F16H57/0423 ,  F16H57/0479 ,  F16H57/0486 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/40311 ,  F16H2057/085

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, 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：US11674415B2

公开(公告)日：2023-06-13

申请号：US17512824

申请日：2021-10-28

Applicant: Raytheon Technologies Corporation

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

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

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：US11560852B2

公开(公告)日：2023-01-24

申请号：US17484331

申请日：2021-09-24

Applicant: Raytheon Technologies Corporation

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

IPC: F02C7/36 ,  F01D25/16

Abstract: A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend 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 fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.

公开(公告)号：US11492932B2

公开(公告)日：2022-11-08

申请号：US16992727

申请日：2020-08-13

Applicant: Raytheon Technologies Corporation

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F01D25/34 ,  F01D5/02 ,  F02C7/32 ,  F02C7/36 ,  F16H1/28

Abstract: A gas turbine engine includes a turbine section that includes a fan drive turbine. A geared architecture includes a sun gear in driving engagement with the fan drive turbine. A plurality of planet gears surrounds the sun gear. A ring gear surrounds the plurality of planet gears. A deflection limiter mechanically attaches the ring gear to an engine static structure. The deflection limiter includes a first support fixed to the ring gear that has a first interlocking feature and a second support fixed to the engine static structure that has a second interlocking feature. The first and second interlocking features define at least one of a radial clearance of between 0.005 inches (0.127 mm) and 0.080 inches (2.032 mm) or a circumferential clearance of between 0.005 inches (0.127 mm) and 0.250 inches (2.032 mm). A fan section includes a plurality of fan blades in driving engagement with the geared architecture through a fan drive shaft.

公开(公告)号：US20220260022A1

公开(公告)日：2022-08-18

申请号：US17729129

申请日：2022-04-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  William G. Sheridan

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

Abstract: A method of assembling a gear train includes providing a unitary carrier. The unitary carrier has a central axis that includes spaced apart walls and circumferentially spaced connecting structure defining spaced apart apertures provided at an outer circumference of the carrier, gear pockets provided between the walls and extending to the apertures, and a central opening in at least one of the walls. The method includes inserting a plurality of intermediate gears through the central opening and moving the intermediate gears radially outwardly into the gear pockets to extend into the apertures, placing a ring gear on an outer periphery of the intermediate gears to engage the intermediate gears, and securing the gear train to a fan shaft by a connection.

公开(公告)号：US20220243802A1

公开(公告)日：2022-08-04

申请号：US17540400

申请日：2021-12-02

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  Lawrence E. Portlock

IPC: F16H57/04 ,  F16H57/08 ,  F01D5/02 ,  F02C7/36 ,  F16D1/076 ,  F01D25/18 ,  F02C7/28 ,  F16H1/28

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, 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 supporting the intermediary gears, and a ring gear including first and second portions each having an inner periphery with teeth intermeshing with the intermediate gears. The first and second portions have axially opposed faces abutting one another at a radial interface and respective flanges extending along the radial interface radially outward from the teeth. The first and second portions define a trough axially between and separating the teeth of the first portion from the teeth of the second portion. The first and second portions include facing recesses that form an internal annular cavity along the radial interface.