公开(公告)号：US10697365B2

公开(公告)日：2020-06-30

申请号：US16168045

申请日：2018-10-23

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean Thomassin ,  Nigel Davenport ,  Eugene Gekht

IPC: F02B19/10 ,  F02B55/08 ,  F02B53/10 ,  F01C21/06 ,  F01C21/10 ,  F01C21/18 ,  F01C1/22 ,  F02B19/12 ,  F02B53/02 ,  F02B53/12 ,  F01C11/00 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/08 ,  F04C29/00

Abstract: A rotary engine having an insert in a peripheral wall of the stator body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the stator body and having a tip communicating with the cavity at a location spaced apart from the insert. The subchamber has a volume corresponding to from 5% to 25% of a sum of the minimum volume and the volume of the subchamber. A method of injecting heavy fuel into a Wankel engine is also discussed.

公开(公告)号：US11773785B2

公开(公告)日：2023-10-03

申请号：US18096071

申请日：2023-01-12

Applicant: Pratt & Whitney Canada Corp.

Inventor： Keith Morgan ,  Robert Peluso ,  Ghislain Plante ,  Eugene Gekht ,  Eric Durocher ,  Jean Dubreuil

IPC: F02C7/32 ,  F02C3/14 ,  F02C6/20 ,  F02C3/04 ,  F02C3/067 ,  F02C3/113 ,  F02C7/36 ,  F01D1/26 ,  F04D25/02

CPC classification number: F02C7/32 ,  F01D1/26 ,  F02C3/04 ,  F02C3/067 ,  F02C3/113 ,  F02C3/145 ,  F02C6/206 ,  F02C7/36 ,  F04D25/024 ,  F05D2220/32 ,  F05D2250/38 ,  F05D2260/40 ,  Y02T50/60

Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

公开(公告)号：US10578012B2

公开(公告)日：2020-03-03

申请号：US15908987

申请日：2018-03-01

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean Thomassin ,  Nigel Davenport ,  Eugene Gekht

IPC: F02B53/10 ,  F02B53/12 ,  F02B55/08 ,  F02B19/10 ,  F01C1/22 ,  F01C21/06 ,  F01C21/10 ,  F01C21/18 ,  F02B19/12 ,  F02B53/02 ,  F02B19/16 ,  F01C11/00 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/08 ,  F04C29/00

Abstract: A non-Wankel rotary engine having an insert in the peripheral wall of the outer body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface bordering the cavity, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the housing and having a tip communicating with the cavity at a location spaced apart from the insert.

公开(公告)号：US10247092B2

公开(公告)日：2019-04-02

申请号：US14816245

申请日：2015-08-03

Applicant: Pratt & Whitney Canada Corp.

Inventor： Eugene Gekht ,  Bruno Villeneuve ,  Mike Fontaine ,  David Gagnon-Martin

IPC: F02B55/10 ,  F02B53/00 ,  F02B53/12 ,  F02B53/10 ,  F01C1/22 ,  F01C21/06

Abstract: A rotary internal combustion engine having an insert opening defined in a hot area of one of the walls of the stator body and in communication with its internal cavity. A cooling jacket is received in and lines the insert opening. An insert is sealingly received in the cooling jacket and made of a material having a greater heat resistance than that of the wall. The cooling jacket extends between the insert and the wall along most of the length of the insert to prevent direct contact between the insert and the wall. A cooling gallery surrounds the cooling jacket and the insert, and is defined at least in part by the cooling jacket such that a coolant circulated therein contacts the cooling jacket. The cooling jacket is located between the cooling gallery and the insert.

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：US11555453B2

公开(公告)日：2023-01-17

申请号：US17368317

申请日：2021-07-06

Applicant: Pratt & Whitney Canada Corp.

Inventor： Keith Morgan ,  Robert Peluso ,  Ghislain Plante ,  Eugene Gekht ,  Eric Durocher ,  Jean Dubreuil

IPC: F02C7/32 ,  F02C3/14 ,  F02C6/20 ,  F02C3/04 ,  F02C3/067 ,  F02C3/113 ,  F02C7/36 ,  F01D1/26 ,  F04D25/02

Abstract: A gas turbine engine has a first spool having a low pressure compressor section disposed forward of an air inlet along a direction of travel of the engine, and a low pressure turbine section disposed forward of the low pressure compressor section and drivingly engaged thereto. A second spool has a high pressure compressor section disposed forward of the low pressure compressor section, and a high pressure turbine section disposed forward of the high pressure compressor section and drivingly engaged thereto. The high pressure turbine section is disposed aft of the low pressure turbine section. An output drive shaft drivingly engages the low pressure turbine section and extends forwardly therefrom to drive a rotatable load. A method of operating a gas turbine engine is also discussed.

公开(公告)号：US10465519B2

公开(公告)日：2019-11-05

申请号：US14056488

申请日：2013-10-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Guy Bouchard ,  Eugene Gekht ,  Danny Mills

IPC: F01D5/06 ,  F01D25/24 ,  F04D29/32 ,  F01D5/02 ,  F01D11/00

Abstract: A rotor disk assembly comprises a first rotor disk with a plurality of circumferentially distributed first throughbores. A second rotor disk comprises a connection portion projecting at least partially axially, a plurality of circumferentially distributed second throughbores being provided in the connection portion in cooperative distribution relative to the first rotor disk for the first and second throughbores to be in register with one another in the rotor disk assembly. Connector bolts each have an elongated body with a flange between its ends, a head at its first end and a removable head at its second end, the head at the first end spaced apart from the flange for the connector bolt to be secured to one of the rotor disks at a respective throughbore, the removable head at the second end being spaced apart from the flange for the second end to project. An anti-rotation feature is between each said connector bolt and at least one of the rotor disks to prevent rotation of the connector bolts when the removable head is installed on the second end in the rotor disk assembly.

公开(公告)号：US10125676B2

公开(公告)日：2018-11-13

申请号：US14706457

申请日：2015-05-07

Applicant: Pratt & Whitney Canada Corp.

Inventor： Jean Thomassin ,  Nigel Davenport ,  Eugene Gekht

IPC: F02B19/10 ,  F02B55/08 ,  F01C1/22 ,  F01C21/06 ,  F01C21/10 ,  F01C21/18 ,  F02B53/10 ,  F02B19/12 ,  F02B53/02 ,  F02B53/12 ,  F01C11/00 ,  F01C20/06 ,  F01C20/10 ,  F01C20/24 ,  F01C21/08 ,  F04C29/00

Abstract: A rotary engine having an insert in a peripheral wall of the stator body, the insert being made of a material having a greater heat resistance than that of the peripheral wall, having a subchamber defined therein and having an inner surface, the subchamber communicating with the cavity through at least one opening defined in the inner surface and having a shape forming a reduced cross-section adjacent the opening, a pilot fuel injector having a tip received in the subchamber, an ignition element having a tip received in the subchamber, and a main fuel injector extending through the stator body and having a tip communicating with the cavity at a location spaced apart from the insert. The subchamber has a volume corresponding to from 5% to 25% of a sum of the minimum volume and the volume of the subchamber. A method of injecting heavy fuel into a Wankel engine is also discussed.

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：US09726040B2

公开(公告)日：2017-08-08

申请号：US14670848

申请日：2015-03-27

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Eugene Gekht ,  Pierre-Yves Legare ,  Thomas Francis Haslam-Jones

IPC: F01D25/18 ,  F01D25/16 ,  F16N7/36

CPC classification number: F01D25/18 ,  F01D25/164 ,  F05D2250/15 ,  F05D2260/98 ,  F16N7/363

Abstract: A fluid delivery assembly for delivering fluid to a component in a gas turbine engine includes a rotating shaft having a central bore and at least one fluid exhaust in communication with the central bore for centrifugally expelling fluid, and a delivery scoop disposed around the rotating shaft and spaced apart from the rotating shaft by an annular gap. The delivery scoop includes an annular body having at least one impingement surface facing the at least one fluid exhaust and configured to scoop the fluid expelled by the at least one fluid exhaust. The impingement surface has at least one outlet for delivering the scooped fluid to the component. A method of delivering pressurised fluid in a fluid system is also presented.