公开(公告)号：US11053811B2

公开(公告)日：2021-07-06

申请号：US16663498

申请日：2019-10-25

Applicant: Raytheon Technologies Corporation

Inventor： William G. Sheridan

IPC: F01D15/12 ,  F02K3/06 ,  F01D25/16 ,  F16H57/08 ,  F16H1/28

Abstract: A gear system for a geared turbofan engine is disclosed. The gear system includes a sun gear driven by a low spool shaft. The sun gear defines a sun gear diameter. A rotating carrier drives a fan. The carrier defines an outer carrier diameter and an inner carrier diameter. A non-rotating ring gear is also included. The ring gear defines a ring gear diameter and the ring gear diameter is smaller than the outer carrier diameter. A set of planet gears are mounted on corresponding rolling element bearing assemblies. Each roller element bearing assembly is supported within the carrier within a space defined between the carrier outer diameter and the carrier inner diameter. Each of the sun gear, ring gear and planet gears are substantially centered along a gearbox centerline transverse to an engine longitudinal axis and the gear system provides a speed reduction ratio between an input to the sun gear and an output from the carrier between 3:1 and 5:1. A method of creating a gear system for a geared turbofan engine and a geared turbofan system are also disclosed.

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：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：US20230042974A1

公开(公告)日：2023-02-09

申请号：US17969179

申请日：2022-10-19

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D25/24 ,  F02K3/06 ,  F16H1/28 ,  F02C3/107 ,  F01D5/02 ,  F01D5/12 ,  F01D17/10 ,  F04D29/32

Abstract: A gas turbine engine includes, among other things, a propulsor section including a propulsor hub, the hub including a hub diameter supporting a plurality of propulsor blades. A compressor section includes a first compressor and a second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture interconnects the first turbine and the propulsor hub. The geared architecture includes a gear volume. A compressor inlet passage is disposed annularly about the geared architecture.

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：US11459957B2

公开(公告)日：2022-10-04

申请号：US17527549

申请日：2021-11-16

Applicant: Raytheon Technologies Corporation

Inventor： William G. Sheridan

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F16H1/20 ,  F16H57/04

Abstract: A gas turbine engine comprises a fan drive turbine driving a shaft. The shaft engages a gear reduction. The gear reduction drives a fan rotor at a speed that is less than the speed of the fan drive turbine. The gear reduction is a non-epicyclic gear reduction.

公开(公告)号：US11384657B2

公开(公告)日：2022-07-12

申请号：US16940538

申请日：2020-07-28

Applicant: Raytheon Technologies Corporation

Inventor： William G. Sheridan

IPC: F01D21/04 ,  F02C7/36 ,  F02C7/06 ,  F01D5/02 ,  F02K3/06 ,  F01D25/16 ,  F01D21/02 ,  F01D21/00

Abstract: A turbine engine has a fan and a low pressure compressor that rotate at a common speed and in a common direction. A fan drive turbine drives a gear reduction to, in turn, drive the low pressure compressor and the fan at a speed which is slower than a speed of the fan drive turbine. A combustor intermediate the low pressure compressor and the fan drive turbine and a thrust bearing mount the fan drive turbine, the thrust bearing being aft of a location of the combustor. A shear section in a drive connection connecting the fan drive turbine to the gear reduction is weaker than other portions of the drive connection. The shear section is aft of the thrust bearing.

公开(公告)号：US11339726B2

公开(公告)日：2022-05-24

申请号：US16936791

申请日：2020-07-23

Applicant: Raytheon Technologies Corporation

Inventor： Michael E. McCune ,  William G. Sheridan

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

Abstract: A method of assembling an epicyclic gear train includes the steps of providing a carrier having a central axis that includes spaced apart side walls and circumferentially spaced connecting structure defining spaced apart apertures provided at an outer circumference of the carrier, gear pockets provided between the side walls and extending to the apertures, and a central opening in at least one of the side walls, 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, inserting a sun gear through the central opening after the step of inserting the plurality of intermediate gears through the central opening, moving the plurality of intermediate gears radially inwardly to engage the sun gear, and placing a ring gear on an outer periphery of the intermediate gears to engage the intermediate gears after the step of moving the plurality of intermediate gears radially inwardly.

公开(公告)号：US11280267B2

公开(公告)日：2022-03-22

申请号：US17007166

申请日：2020-08-31

Applicant: Raytheon Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F02C7/06 ,  F02K1/09 ,  F02C3/107 ,  F02K3/04 ,  F01D5/02 ,  F01D9/06 ,  F01D17/10 ,  F02C3/06 ,  F02C3/10 ,  F04D29/32 ,  F01D5/06 ,  F02C3/04 ,  F02C7/28 ,  F02C9/18 ,  F02K1/06 ,  F02K3/06 ,  F04D29/38 ,  F16H1/28

Abstract: A gas turbine engine according to the present disclosure includes, among other things, a fan section having a plurality of fan blades, the plurality of fan blades having a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath, and a core engine including a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section.

公开(公告)号：US20220003172A1

公开(公告)日：2022-01-06

申请号：US17480503

申请日：2021-09-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： William G. Sheridan ,  John R. Otto

IPC: F02C7/36 ,  F02C7/06 ,  F02C7/20

Abstract: A gas turbine engine includes a fan, a fan shaft coupled with the fan and arranged along an engine central axis, and a frame supporting the fan shaft. The frame defines a lateral frame stiffness (LFS). A non-rotatable flexible coupling and a rotatable flexible coupling support an epicyclic gear system. The couplings are subject to a Motion II of cantilever beam free end motion with respect to the engine central axis. The non-rotatable and the rotatable flexible couplings each have a stiffness of a common stiffness type under a common type of motion. The common stiffness type is a Stiffness B and the common type of motion is the Motion II. The Stiffness B of the rotatable flexible coupling is greater than the stiffness B of the non-rotatable flexible coupling, and a ratio of LFS/Stiffness B of the non-rotatable flexible coupling is in a range of 10-40.