公开(公告)号：US10030581B2

公开(公告)日：2018-07-24

申请号：US15052189

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 ,  F02C7/04 ,  F02C6/20

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 air intake may comprise a scroll portion and a strutted portion configured to receive the flow of air from the intake duct and channel the flow of air toward the intake outlet. The strutted portion may comprise one or more vanes for interacting with the flow of air. 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：US10436149B2

公开(公告)日：2019-10-08

申请号：US15249847

申请日：2016-08-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Francois Bisson

IPC: F02K1/48 ,  F02K3/06

Abstract: An exhaust mixer for a gas turbine engine has a lobe cross-over offset. The proposed geometric feature leads to improved exhaust performance and potential weight reduction.

公开(公告)号：US11066996B2

公开(公告)日：2021-07-20

申请号：US16202827

申请日：2018-11-28

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Roberto Marrano ,  Francois Bisson

IPC: F02C7/052 ,  F02K3/02 ,  F02C7/04

Abstract: There is disclosed an inertial particle separator communicating with an engine inlet. The inertial particle separator has: a main duct body; a bypass duct; and a splitter defined by an intersection of the main duct and the bypass duct. The main duct and the bypass duct having particular geometric characteristics. A method of separating particles via inertia in an aircraft engine inlet is also provided.

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：US10765980B2

公开(公告)日：2020-09-08

申请号：US16359163

申请日：2019-03-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Francois Bisson ,  Mark Cunningham

IPC: B01D45/06 ,  B64D33/02 ,  F02C7/052

Abstract: An inertial particle separator for an aircraft engine inlet, including inlet, intermediate and bypass ducts. The intermediate duct extends generally transversally from the inlet duct to the engine inlet, and communicates with the inlet duct adjacent its downstream end. The bypass duct extends downstream from the inlet duct and intermediate duct, and defines an outlet communicating with the environment of the engine. A wall of the intermediate duct intersects a wall of the inlet duct on an engine side of the wall of the inlet duct. The engine side of the wall of the inlet duct defines an engine-side inlet air flow line of the inertial particle separator. A wall of the bypass duct intersects the wall of the intermediate duct closer to a central axis of the engine than an extension of the engine-side inlet air flow line into the bypass duct.

公开(公告)号：US10245540B2

公开(公告)日：2019-04-02

申请号：US15401237

申请日：2017-01-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Francois Bisson ,  Mark Cunningham

IPC: B01D45/06 ,  B64D33/02 ,  F02C7/052

Abstract: An inertial particle separator for an aircraft engine inlet, including inlet, intermediate and bypass ducts. The intermediate duct extends generally transversally from the inlet duct to the engine inlet, and communicates with the inlet duct adjacent its downstream end. The bypass duct extends downstream from the inlet duct and intermediate duct, and defines an outlet communicating with the environment of the engine. A wall of the intermediate duct intersects a wall of the inlet duct on an engine side of the wall of the inlet duct. The engine side of the wall of the inlet duct defines an engine-side inlet air flow line of the inertial particle separator. A wall of the bypass duct intersects the wall of the intermediate duct closer to a central axis of the engine than an extension of the engine-side inlet air flow line into the bypass duct.