公开(公告)号：US20230139607A1

公开(公告)日：2023-05-04

申请号：US17452883

申请日：2021-10-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David PYRA ,  Guy LEFEBVRE ,  Gerard THERIAULT

IPC: F16B39/10 ,  F02C7/20

Abstract: A locking tab washer for rotatably locking a bolt fastened to a component in an aircraft engine has a body with an opening and at least four locking tabs positioned about the opening and circumferentially spaced apart from one another at integer multiples of a common angle relative to the center of the opening. The locking tabs are bendable towards to rotatably lock the bolt. The locking tab washer also has a retaining feature positioned about the opening and operable to rotatably retain the locking tab washer to the component.

公开(公告)号：US20220275761A1

公开(公告)日：2022-09-01

申请号：US17663698

申请日：2022-05-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy LEFEBVRE

IPC: F02C7/32

Abstract: A through-flow gas turbine engine includes a core comprising multiple spools rotatable about a center axis. An accessory gearbox (AGB) is drivingly engaged to the core and disposed aft of the outlet. A reduction gearbox (RGB) is drivingly engaged to the core and disposed forward of the inlet. The RGB has an RGB output to provide rotational output to a rotatable load. An electric motor is drivingly engaged to the rotatable load. An electric generator is configured to provide electrical power to the electric motor. the electric motor and the electric generator are disposed axially adjacent one another, and axially between the outlet and the AGB.

公开(公告)号：US20220106892A1

公开(公告)日：2022-04-07

申请号：US17062005

申请日：2020-10-02

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy LEFEBVRE ,  Remy SYNNOTT

IPC: F01D25/18 ,  F02C7/06

Abstract: A gas turbine engine has a housing exposed to a high temperature environment. The housing has a circumferential wall extending around the engine centerline and circumscribing an oil cavity. The wall has a sealing interface at an inner diameter thereof, the sealing interface having a central axis offset from the engine centerline. A boss is formed on the wall on the offset side relative to the engine centerline and a probe is mounted to the boss. The probe projects into the oil cavity. The oil in the oil cavity thermally shields the probe from the high temperature environment.

公开(公告)号：US20210355881A1

公开(公告)日：2021-11-18

申请号：US16897776

申请日：2020-06-10

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy LEFEBVRE

IPC: F02C7/32 ,  F02C6/14 ,  F02C7/268

Abstract: A through-flow gas turbine engine includes a core comprising multiple spools rotatable about a center axis. An accessory gearbox (AGB) is drivingly engaged to the core and disposed aft of the outlet. A reduction gearbox (RGB) is drivingly engaged to the core and disposed forward of the inlet. The RGB has an RGB output to provide rotational output to a rotatable load. An electric motor is drivingly engaged to the rotatable load. An electric generator is configured to provide electrical power to the electric motor. One of the electric motor and the electric generator is disposed axially between the outlet and the AGB and the other of the electric motor and the electric generator is disposed axially between the inlet and the RGB.

公开(公告)号：US20210355870A1

公开(公告)日：2021-11-18

申请号：US16875470

申请日：2020-05-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy LEFEBVRE

IPC: F02C6/20

Abstract: A twin-engine system includes a gas turbine engine comprising a core and a first output shaft drivable by the core. An electric engine has an electric motor configured to drive a second output shaft. A reduction gear box (RGB) has an RGB input drivingly engaged to both the first output shaft and the second output shaft. The RGB has an RGB output to provide rotational output to a rotatable load.

公开(公告)号：US20190120170A1

公开(公告)日：2019-04-25

申请号：US16219189

申请日：2018-12-13

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eric DUROCHER ,  Guy LEFEBVRE

IPC: F02K1/48 ,  B21D53/92

CPC classification number: F02K1/48 ,  B21D53/92 ,  Y10T29/49323

Abstract: A mixer of a bypass turbine aeroengine according to one embodiment, includes circumferential inner and outer flow surfaces in a wavy configuration to form a plurality of lobes of the mixer. The mixer has an upstream end portion of sheet metal with a first thickness and a downstream end portion of sheet metal with a second thickness less than the first thickness.

公开(公告)号：US20170328303A1

公开(公告)日：2017-11-16

申请号：US15655102

申请日：2017-07-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Franco DI PAOLA ,  Guy LEFEBVRE ,  Patrick L'ESPERANCE ,  Gabriel EMARD-PARENT

IPC: F02K1/38 ,  F02C7/18

CPC classification number: F02K1/386 ,  F02C7/18

Abstract: An ejector/mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of lobes. A support member interconnects the lobes, and includes an annular blade located radially inwardly of the bight of the lobes. The lobes extend radially inwardly downstream relative to the annular wall and the support member includes an annular blade and has spaced apart joint surfaces spaced apart to coincide with the joint surfaces of a respective lobes. The spaced-apart joint surfaces of the support member being profiled to mate with the corresponding joint surface of the lobes.

公开(公告)号：US20170198604A1

公开(公告)日：2017-07-13

申请号：US15372873

申请日：2016-12-08

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy LEFEBVRE ,  Remy SYNNOTT

IPC: F01D25/12 ,  F01D25/30 ,  F02C7/18 ,  F01D25/24 ,  F01D25/14

CPC classification number: F01D25/12 ,  F01D9/042 ,  F01D21/045 ,  F01D25/145 ,  F01D25/24 ,  F01D25/246 ,  F01D25/26 ,  F01D25/30 ,  F02C7/18 ,  F05D2220/32 ,  F05D2240/11 ,  F05D2240/35 ,  Y02T50/671

Abstract: A case assembly for a turbine section has a structural outer case structurally connected to a gas generator upstream of the outer case and to an exhaust case downstream of the outer case. The assembly further comprises a containment ring mounted within the outer case and surrounding a plurality of axially spaced-apart turbine stages. An inner surface of the containment ring defines a plurality of shroud receiving portions. An annular plenum is defined between the outer case and the containment ring. The plenum has an inlet connected to a source of pressurized coolant. Outlets are circumferentially and axially distributed and defined through the containment ring. The outlets provides flow communication between the annular plenum and the plurality of axially spaced-apart turbine stages.

公开(公告)号：US20240011415A1

公开(公告)日：2024-01-11

申请号：US17858293

申请日：2022-07-06

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy LEFEBVRE ,  Remy SYNNOTT

IPC: F01D25/16

CPC classification number: F01D25/162 ,  F05D2220/323 ,  F05D2260/96 ,  F05D2260/39 ,  F01D9/026

Abstract: The damper segment can be assembled between adjacent segments of a pressurized gas pipe of an aircraft engine. The damper segment can have a proximal end, a distal end, a rigid tube at the proximal end, a damper tube extending between the rigid tube and the distal end, the damper tube being made of a metal mesh, a proximal catch structurally connecting a proximal end of the damper tube to the rigid tube, and a distal catch structurally connected between a distal end of the damper tube and the distal end, the damper tube having an unsupported length extending between the distal catch and the proximal catch, the rigid tube having a liner portion projecting into the distal segment, the liner portion extending internally relative the damper tube.

公开(公告)号：US20230193774A1

公开(公告)日：2023-06-22

申请号：US17644630

申请日：2021-12-16

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Ian MACFARLANE ,  Eric DUROCHER ,  Guy LEFEBVRE

IPC: F01D11/02 ,  F02C7/28

CPC classification number: F01D11/02 ,  F02C7/28 ,  F05D2220/323 ,  F05D2240/55

Abstract: A labyrinth seal assembly comprising: an outer seal having a radially inner cavity surface, and an axial cavity surface inward of the radially inner cavity surface; a floating seal received by the outer seal so as to be movable in a radial direction relative to the outer seal, the floating seal having a radially outer seal surface spaced inwardly from the radially inner cavity surface, a radially inner surface inward of the radially outer seal surface, and an axial seal surface bearing against the axial cavity surface; and an inner seal received by the floating seal, the inner seal having a radially outer surface spaced inwardly from the radially inner surface, a first one of the radially outer surface and the radially inner surface defining one tooth projecting toward a second one of the radially outer surface and the radially inner surface to inward of the axial seal surface.