公开(公告)号：US10907579B2

公开(公告)日：2021-02-02

申请号：US16736013

申请日：2020-01-07

Applicant: Raytheon Technologies Corporation

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

IPC: F02K3/06 ,  F02C7/36 ,  F16H57/04

Abstract: A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. A gear system is connected to the fan shaft and a plurality of planetary gears. A first set of opposed angled ring gear teeth are separated from a second set of opposed angled ring gear teeth. A lubricant flow path is located axially between the first set of opposed angled ring gear teeth and the second set of opposed angled ring gear teeth. An annular channel axially is aligned with the lubricant flow path. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1. A low fan pressure ratio is less than 1.45 across the fan blade alone.

公开(公告)号：US20210010386A1

公开(公告)日：2021-01-14

申请号：US17038028

申请日：2020-09-30

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan ,  Michael E. McCune ,  Gabriel L. Suciu

IPC: F01D15/12 ,  F02C7/36 ,  F01D25/18 ,  F02K3/06 ,  F16H1/28 ,  F16H57/04

Abstract: A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.

公开(公告)号：US12234791B2

公开(公告)日：2025-02-25

申请号：US18161340

申请日：2023-01-30

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02K3/06 ,  F01D25/16 ,  F02C7/36 ,  F04D29/52

Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.

公开(公告)号：US11946540B2

公开(公告)日：2024-04-02

申请号：US17895301

申请日：2022-08-25

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Janice Jabido ,  Michael E. McCune

IPC: F16H57/04 ,  F01D15/12 ,  F01D25/18 ,  F02K3/02 ,  F16H1/28 ,  F16H57/08

CPC classification number: F16H57/0427 ,  F01D15/12 ,  F01D25/18 ,  F02K3/025 ,  F16H1/28 ,  F16H57/0442 ,  F16H57/0479 ,  F16H57/0486 ,  F16H57/082

Abstract: A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

公开(公告)号：US11773787B2

公开(公告)日：2023-10-03

申请号：US17729129

申请日：2022-04-26

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Michael E. McCune ,  William G. Sheridan

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

CPC classification number: F02C7/36 ,  F02C3/107 ,  F02C7/32 ,  F02K3/06 ,  F16H1/28 ,  F16H57/023 ,  F16H57/082 ,  F05D2230/60 ,  F05D2260/40311 ,  F16H57/0423 ,  F16H57/0456 ,  F16H57/0479 ,  F16H57/0486 ,  Y02T50/60 ,  Y10T29/49464

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：US20230167752A1

公开(公告)日：2023-06-01

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 ,  F02K3/06 ,  F02C3/107 ,  F01D15/12 ,  F01D25/162 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  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：US20230160466A1

公开(公告)日：2023-05-25

申请号：US17895301

申请日：2022-08-25

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Janice Jabido ,  Michael E. McCune

IPC: F16H57/04 ,  F01D15/12 ,  F01D25/18 ,  F02K3/02 ,  F16H1/28 ,  F16H57/08

CPC classification number: F16H57/0427 ,  F01D15/12 ,  F01D25/18 ,  F02K3/025 ,  F16H1/28 ,  F16H57/082 ,  F16H57/0442 ,  F16H57/0479 ,  F16H57/0486

Abstract: A fan drive gear system for a turbofan engine according to an exemplary embodiment of this disclosure, among other possible things includes a sun gear that is rotatable about an axis, a plurality of intermediate gears driven by the sun gear, and a baffle that is disposed between at least two of the plurality of intermediate gears for defining a lubricant flow path from an interface between the sun gear and at least one of the plurality of intermediate gears. The baffle includes a channel with at least one ramp portion directing lubricant.

公开(公告)号：US20230056571A1

公开(公告)日：2023-02-23

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: F01D25/28 ,  F01D9/02 ,  F01D25/24

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：US11566587B2

公开(公告)日：2023-01-31

申请号：US16812636

申请日：2020-03-09

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan ,  Michael E. McCune

IPC: F02K3/06 ,  F02C7/36 ,  F01D25/16 ,  F04D29/52

Abstract: An exemplary gas turbine engine includes a fan section including a fan rotor and at least one fan blade. A fan pressure ratio across the at least one fan blade is less than 1.45, noninclusive of the pressure across any fan exit guide vane system. The engine further includes a low-pressure compressor having a low-pressure compressor rotor that rotates together with the fan rotor at a common speed in operation, and a geared architecture that drives the low-pressure compressor rotor and the fan rotor. The geared architecture has a gear reduction ratio of greater than 2.5. The engine further includes a high-pressure compressor having a pressure ratio greater than 20, a low-pressure turbine having a pressure ratio greater than 5, and a bypass ratio greater than 10.

公开(公告)号：US11549399B2

公开(公告)日：2023-01-10

申请号：US17676520

申请日：2022-02-21

Applicant: Raytheon Technologies Corporation

Inventor： Paul H. Dolman ,  Michael E. McCune

IPC: F01D25/20 ,  F16H57/04 ,  F02C7/36 ,  F01M11/06 ,  F01M1/12 ,  F16N7/40

Abstract: A disclosed lubrication system for a turbofan engine includes a pump for driving lubricant through a lubrication circuit, at least one sensor generating a signal indicative of an engine operating condition and at least one valve for controlling a flow of lubricant through the lubrication circuit. A controller controls operation of the valve to vary the flow of lubricant based on the engine operating condition to maintain lubricant flow within predefined operating limits.