公开(公告)号：US11767885B2

公开(公告)日：2023-09-26

申请号：US17320306

申请日：2021-05-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Mark Shields ,  David Menheere ,  Dennis Kim

IPC: F16D3/60

CPC classification number: F16D3/60 ,  Y10T403/1624 ,  Y10T403/61

Abstract: A coupling has: a first coupler rotatable about an axis and defining first connections distributed about the axis; a second coupler defining second connections distributed about the axis, the second connections offset from the first connections; and segments distributed about the axis and extending radially from the first connections to the second connections, a segment of the segments having a first end engaging a first connection of the first connections and a second end engaging a second connection of the second connections, the first end circumferentially offset from the second end, a face of the segment abutting against a face of the first coupler when the segment is inserted into the first connection in a first orientation such that a penetration depth of the segment into the first connection in the first orientation is less than the penetration depth in a second orientation opposite the first orientation.

公开(公告)号：US11698024B1

公开(公告)日：2023-07-11

申请号：US17662673

申请日：2022-05-10

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David Menheere

IPC: F02C7/047

CPC classification number: F02C7/047

Abstract: An inlet guide vane assembly for an aircraft engine includes an array of inlet guide vanes having radially inner ends at a radially inner shroud, radially outer ends at a radially outer shroud, and airfoils extending therebetween. An internal passage extends radially through the airfoil from a vane air inlet at the radially inner end to a vane air outlet at the radially outer end. The vane air inlet is in fluid communication with an inner plenum, disposed radially inwardly of the inlet guide vane and in fluid communication with an anti-icing air source. The vane air outlet in fluid communication with an outer plenum, disposed radially outwardly of the inlet guide vane and having an exhaust port. A vane anti-icing pathway is defined in a radially-outward direction from the inner plenum, through the internal passage of the vane, and into the outer plenum.

公开(公告)号：US11572837B2

公开(公告)日：2023-02-07

申请号：US17155500

申请日：2021-01-22

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Daniel Alecu ,  David Menheere

IPC: F02C7/28 ,  F01D9/06 ,  F01D25/12 ,  F01D25/18 ,  F02C6/08 ,  F02C7/18 ,  F02C3/04 ,  F02C7/06 ,  F02C9/16

Abstract: Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.

公开(公告)号：US11529705B1

公开(公告)日：2022-12-20

申请号：US17337023

申请日：2021-06-02

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David Menheere

IPC: B23P19/04 ,  F02C7/36

Abstract: A tool for installing segments of a coupling having male and female couplers drivingly engaged to one another by the segments, the tool has: a coupler-engaging section engageable to the a female coupler of the couplers for radially supporting the tool relative to the female coupler about a rotation axis of the coupling; and a peripheral wall secured to the coupler-engaging section and extending circumferentially around the rotation axis, a diameter (D2) of the peripheral wall selected to allow insertion of the segments between the female coupler and the peripheral wall, the peripheral wall defining an abutting surface against which radially inner ends of the segments abut during insertion of the segments between the female coupler and the peripheral wall.

公开(公告)号：US11384687B2

公开(公告)日：2022-07-12

申请号：US16451548

申请日：2019-06-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David Menheere ,  Richard Kostka ,  Steven Strecker

IPC: F02C7/047 ,  F01D25/02 ,  B64D33/02 ,  F02C6/08

Abstract: An anti-icing system for a gas turbine engine comprises a closed circuit containing a phase-change fluid, at least one heating component for boiling the phase-change fluid, the anti-icing system configured so that the phase-change fluid partially vaporizes to a vapour state when boiled by the at least one heating component. The closed circuit has an anti-icing cavity adapted to be in heat exchange with an anti-icing surface of the gas turbine engine for the phase-change fluid to release heat to the anti-icing surface and condense. A feed conduit(s) has an outlet end in fluid communication with the anti-icing cavity to feed the phase-change fluid in vapour state from heating by the at least one heating component to the anti-icing cavity, and at least one return conduit having an outlet end in fluid communication with the anti-icing cavity to direct condensed phase-change fluid from the anti-icing cavity to the at least one heating component. A method for heating an anti-icing surface of an aircraft is also provided.

公开(公告)号：US11181010B2

公开(公告)日：2021-11-23

申请号：US16460067

申请日：2019-07-02

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Richard Kostka ,  David Menheere

IPC: F01D25/18 ,  F16H57/04 ,  F02C7/32 ,  F02C7/06 ,  F16H57/027 ,  B64D33/00 ,  F16N39/00 ,  B01D45/12 ,  F16H57/02

Abstract: The aircraft engine can have an air-oil separator having an air-oil mixture inlet, an oil outlet, an air outlet, and a pressure relief path provided fluidly in parallel with the air-oil separator, between the air-oil mixture inlet and the air outlet, the pressure relief path can have a pressure relief valve for evacuating air-oil mixture to the exhaust duct in the event of excess pressure in the auxiliary gearbox.

公开(公告)号：US11073082B2

公开(公告)日：2021-07-27

申请号：US16683552

申请日：2019-11-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Richard Ivakitch ,  David Menheere ,  Paul Stone

IPC: F02C7/047

Abstract: A fan blade anti-icing system comprises a fan hub and a fan blade extending radially outwardly from the fan hub. The fan blade has a base and an airfoil extending radially outwardly from the fan base. The airfoil having a leading edge, a trailing edge, a convex side surface between the leading and trailing edge and a concave side surface between the leading and trailing edge. The fan blade further has a radial passage extending from a blade air inlet in the blade base in communication with a source of heated air, and a rearwardly directed passage in communication with the radial passage and having a blade air outlet forward of the trailing edge and oriented tangentially to the convex side surface or concave side surface of the airfoil.

公开(公告)号：US11060457B2

公开(公告)日：2021-07-13

申请号：US15367450

申请日：2016-12-02

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David Menheere ,  Daniel Alecu

IPC: F02C7/18 ,  F02C7/14 ,  F28D15/02 ,  B64D33/08 ,  F02K3/06

Abstract: A cooling system for a gas turbine engine comprising a closed circuit containing a change-phase fluid, the closed circuit having at least one cooling exchanger configured to be exposed to a flow of cooling air for the change-phase fluid to release heat to the cooling air. A plurality of heat exchangers in are heat exchange relation with the change-phase fluid in the closed circuit, the plurality including at least a first heat exchanger configured to receive a first coolant from a first engine system for the change-phase fluid to absorb heat from the first coolant, and a second heat exchanger configured to receive a second coolant from a second engine system for the change-phase fluid to absorb heat from the second coolant. The system is configured so that the fluid at least partially vaporizes when absorbing heat from at least one of the first coolant and the second coolant and at least partially condenses when releasing heat to the cooling air. A method for cooling engine systems of a gas turbine engine is also provided.

公开(公告)号：US10934930B2

公开(公告)日：2021-03-02

申请号：US16284381

申请日：2019-02-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony Jones ,  Andre Julien ,  David Menheere ,  Jean Thomassin ,  Richard Ullyott ,  Daniel Van Den Ende

IPC: F02B53/14 ,  B64D41/00 ,  F02B33/40 ,  F02B37/10 ,  F02B37/24 ,  F02B39/10 ,  F02B39/12 ,  F02B61/06 ,  F02B63/04 ,  F02C6/12 ,  F02C7/32 ,  F02C7/36 ,  F02B53/00

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

公开(公告)号：US10724429B2

公开(公告)日：2020-07-28

申请号：US16227141

申请日：2018-12-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Anthony Jones ,  Andre Julien ,  David Menheere ,  Jean Thomassin ,  Richard Ullyott ,  Daniel Van Den Ende

IPC: F02B53/14 ,  B64D41/00 ,  F02B53/04 ,  F02B63/04

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.