公开(公告)号：US11867070B1

公开(公告)日：2024-01-09

申请号：US17876854

申请日：2022-07-29

Applicant: Pratt & Whitney Canada Corp.

Inventor： Damien Le Pape ,  Mark Cunningham

IPC: F01D21/00

CPC classification number: F01D21/003 ,  F05D2220/323 ,  F05D2260/30 ,  F05D2270/3011

Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.

公开(公告)号：US20250116229A1

公开(公告)日：2025-04-10

申请号：US18377180

申请日：2023-10-05

Applicant: Pratt & Whitney Canada Corp.

Inventor： Eray Akcayoz ,  Mark Cunningham ,  Roberto Marrano ,  Corentin Brette

IPC: F02C7/055 ,  F02C7/057

Abstract: A system is provided for an aircraft. This aircraft system includes an aircraft engine, an inlet guard and an actuation system. The aircraft engine has a flowpath projecting into the aircraft engine from an airflow inlet. The inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen, a second screen and a plurality of perforations. The first screen is adjacent and overlaps the second screen. The perforations project through the inlet guard and are formed by the first screen and the second screen. The actuation system is configured to move the first screen along the second screen. The movement of the first screen along the second screen changes a geometry of each of the perforations.

公开(公告)号：US20250115366A1

公开(公告)日：2025-04-10

申请号：US18377186

申请日：2023-10-05

Applicant: Pratt & Whitney Canada Corp.

Inventor： Mark Cunningham ,  Eray Akcayoz ,  Roberto Marrano ,  Corentin Brette

IPC: B64D33/02

Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine, a flowpath and an inlet guard. The gas turbine engine includes a compressor section. The flowpath projects longitudinally into the gas turbine engine from an airflow inlet and longitudinally through the compressor section. The inlet guard extends across the flowpath longitudinally upstream of the compressor section. The inlet guard extends circumferentially about an axis. The inlet guard includes a first screen and a second screen. The first screen includes a plurality of first perforations with a first perforation size. The second screen is circumferentially adjacent the first screen about the axis. The second screen includes a plurality of second perforations with a second perforation size that is different than the first perforation size.

公开(公告)号：US20240044288A1

公开(公告)日：2024-02-08

申请号：US17879406

申请日：2022-08-02

Applicant: Pratt & Whitney Canada Corp.

Inventor： Sid-Ali Meslioui ,  Mark Cunningham

IPC: F02C6/08 ,  F02C9/18

CPC classification number: F02C6/08 ,  F02C9/18 ,  F05D2220/323 ,  F05D2260/606

Abstract: A system is provided for a gas turbine engine. This engine system includes a flowpath wall, a takeoff conduit and a porous cover. The flowpath wall forms a peripheral boundary of an internal engine flowpath. The flowpath wall includes a takeoff port. The takeoff conduit includes an internal conduit passage fluidly coupled with the internal engine flowpath through the takeoff port. The takeoff conduit projects out from the flowpath wall. The porous cover for the internal conduit passage is disposed at the takeoff port.

公开(公告)号：US11719165B2

公开(公告)日：2023-08-08

申请号：US17453387

申请日：2021-11-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Damien Le Pape ,  Guorong Yan ,  Mark Cunningham ,  Philippe Beauchesne-Martel ,  Oleg Iskra ,  Richard Ivakitch

IPC: F02C7/32

CPC classification number: F02C7/32 ,  F05D2220/323

Abstract: An aircraft engine comprises an air inlet duct extending from an inlet through which air is configured to enter the aircraft engine, to an outlet within the aircraft engine. At least one strut has a leading edge and a trailing edge and extends across at least part of the air inlet duct. The at least one strut has a strut passage and a plurality of static pressure measurement taps spaced apart on the trailing edge and in fluid communication with the strut passage.

公开(公告)号：US10087839B2

公开(公告)日：2018-10-02

申请号：US15052214

申请日：2016-02-24

Applicant: Pratt & Whitney Canada Corp.

Inventor： Eugene Gekht ,  Francois Bisson ,  Mark Cunningham ,  Michel Desjardins ,  Guo Rong Yan

IPC: F02C7/042 ,  B64D33/02 ,  F02K3/02 ,  F02C7/04

Abstract: An air intake for efficiently channeling a flow of ambient air toward an air inlet of a turboprop or turboshaft gas turbine engine is disclosed. The air intake comprises an intake inlet for receiving the flow of air, an intake duct for channelling the flow of air, and an intake outlet for discharging the flow of air toward the air inlet of the gas turbine engine. The intake duct may be oriented toward a flow direction of the air pushed aft by a propeller coupled to the gas turbine engine.

公开(公告)号：US09879591B2

公开(公告)日：2018-01-30

申请号：US14806883

申请日：2015-07-23

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean Thomassin ,  Sebastien Bolduc ,  Bruno Villeneuve ,  Stephane Berube ,  Mike Fontaine ,  David Gagnon-Martin ,  Andre Julien ,  Mark Cunningham ,  Serge Lafortune ,  Pierre-Yves Legare

IPC: F02B29/04 ,  F02C6/12 ,  F02C7/047 ,  F02C7/052 ,  F02C7/055 ,  F02C7/14 ,  F02C7/36 ,  F02B37/12 ,  F02B53/08 ,  F02B53/14 ,  F01C11/00 ,  F02B39/04 ,  F01C21/18 ,  F02M31/04 ,  F02M31/10 ,  F01C1/22

CPC classification number: F02B29/0406 ,  F01C1/22 ,  F01C11/008 ,  F01C21/18 ,  F02B29/0412 ,  F02B33/40 ,  F02B37/12 ,  F02B39/04 ,  F02B53/08 ,  F02B53/14 ,  F02C6/12 ,  F02C7/047 ,  F02C7/052 ,  F02C7/055 ,  F02C7/14 ,  F02C7/36 ,  F02M31/042 ,  F02M31/10 ,  F02M31/107 ,  F05D2250/312 ,  F05D2260/40311 ,  F05D2260/98 ,  Y02T10/126 ,  Y02T10/17 ,  Y02T50/675

Abstract: An intake assembly for a compressor providing compressed air to an internal combustion engine core, including an air conduit having at least one heat exchanger extending thereacross, an intake plenum for the compressor, a first intake conduit connected to the air conduit upstream of the heat exchanger(s), a second intake conduit connected to the air conduit downstream of the heat exchanger(s), and a selector valve configurable between a first configuration to allow a fluid communication between the intake plenum and the air conduit through the first intake conduit and a second configuration to prevent the fluid communication through the first intake conduit. Fluid communication between the intake plenum and the air conduit through the second intake conduit is allowed at least when the selector valve is in the second configuration. An engine assembly and method of supplying air to a compressor are also discussed.

公开(公告)号：US20250051029A1

公开(公告)日：2025-02-13

申请号：US18233127

申请日：2023-08-11

Applicant: Pratt & Whitney Canada Corp.

Inventor： Trevor T. Ricci ,  Frank Paoletti ,  Mark Cunningham

IPC: B64D35/08 ,  F02C7/36 ,  F02C9/28

Abstract: A method of operation is provided during which rotation of a propulsor rotor of an aircraft is driven using mechanical power output from a powerplant. The powerplant includes a heat engine and an electric machine. The heat engine provides a first portion of the mechanical power. The electric machine provides a second portion of the mechanical power. An operational temperature of the heat engine is regulated by controlling the first portion of the mechanical power generated by the heat engine and the second portion of the mechanical power generated by the electric machine.

公开(公告)号：US20240141832A1

公开(公告)日：2024-05-02

申请号：US17977722

申请日：2022-10-31

Applicant: Pratt & Whitney Canada Corp.

Inventor： Mark Cunningham ,  Eray Akcayoz ,  Raja Ramamurthy ,  Roberto Marrano

IPC: F02C7/042 ,  F02C9/20

CPC classification number: F02C7/042 ,  F02C9/20 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2270/60

Abstract: An air intake for an aircraft propulsion system includes an air inlet duct and a flow control device. The air inlet duct includes an interior surface and an intake inlet. The interior surface extends from the intake inlet. The interior surface forms and surrounds an inlet flow passage through the air inlet duct. The intake inlet includes a top side, a bottom side, a first lateral side, and a second lateral side. Each of the first lateral side and the second lateral side extend between and to the top side and the bottom side. The flow control device is disposed inside the air inlet duct at the first lateral side. The flow control device is configured to form an asymmetrical shape of the intake inlet at the first lateral side relative to the second lateral side.

公开(公告)号：US11952962B1

公开(公告)日：2024-04-09

申请号：US18162269

申请日：2023-01-31

Applicant: Pratt & Whitney Canada Corp.

Inventor： Eray Akcayoz ,  Mark Cunningham

IPC: F02K1/40

CPC classification number: F02K1/40 ,  F05D2220/323 ,  F05D2250/51 ,  F05D2250/52 ,  F05D2250/71 ,  F05D2250/73

Abstract: An exhaust duct of an aircraft engine includes an annular inlet conduit having an inlet central axis, and at least two outlet conduits in flow communication with the inlet conduit. The at least two outlet conduits are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.