Pratt-whitney Canada Corp

Pratt & Whitney Canada Ccorp.

Eugene Gekht

Jean Thomassin

David Gagnon-Martin

Nigel Caldwell Davenport

Sebastien Bolduc

Mike Louis Fontaine

Eric Durocher

Keith Morgan

Jean Dubreuil

Ghislain Plante

Robert Peluso

Danny Mills

Thomas Francis Haslam-Jones

Franco Di Paola

Bruno Villeneuve

Michel Desjardins

Mark Cunningham

Guy Bouchard

Francois Bisson

Pierre-Yves Légaré

Guo Rong Yan

Guy Lefebvre

Andre Julien

Philippe Beauchesne-Martel

Serge Dussault

Edwin Schulz

Valerio Valentini

Pierre-Yves Legare

Michael Lanktree

Francois Doyon

Alain C Martel

Stephen Mah

Patrice Remy

André Julien

Martin Jutras

François Doyon

André Denis Leblanc

Terrence Lucas

Michel Labbé

Andre Leblanc

Yusuf V Akgun

Nigel Davenport

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.

Reverse-flow gas turbine engine

A gas turbine engine has a first spool having a low pressure compressor section in fluid communication with an air inlet, the low pressure compressor section including a first plurality of variable guide vanes therein, and a low pressure turbine section drivingly engaged to the low pressure compressor section. A second spool has a high pressure compressor section in fluid communication with the low pressure compressor section to receive pressurized air therefrom, the high pressure compressor section including a second plurality of variable guide vanes at an entry thereof, and a high pressure turbine section drivingly engaged to the high pressure compressor section, the high pressure turbine section disposed upstream of the low pressure turbine section and in fluid communication therewith. An output drive shaft drivingly engages the low pressure turbine section and is adapted to drivingly engage a rotatable load of the gas turbine engine.

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.

Rotary internal combustion engine with pilot subchamber

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.

A rotary engine including a rotor sealingly received within an internal cavity of an outer body to define a plurality of combustion chambers having a variable volume, a pilot subchamber located in a wall of the outer body, the pilot subchamber in fluid communication with the internal cavity via at least two spaced apart transfer holes defining a flow restriction between the pilot subchamber and the internal cavity, a pilot fuel injector in fluid communication with the pilot subchamber, an ignition element configured for igniting fuel in the pilot subchamber, and a main fuel injector extending through the stator body and communicating with the cavity at a location spaced apart from the pilot subchamber. A method of combusting fuel in a rotary engine is also discussed.

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.

Fastening system for rotor hubs

In one aspect, described is a rotor for a Wankel engine comprising two circumferentially spaced apart apex seals at each of the apex portions with each apex seal protruding axially from both end faces, and each apex seal having a first biasing member biasing the apex seal radially outwardly away from the peripheral face of the body, and a second biasing member biasing the apex seal axially outwardly away from a respective one of the end faces, the two apex seals of a same one of the apex portions being biased by the respective second biasing member in opposite axial directions from one another.

Apex seal arrangement for rotary internal combustion engine

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.

Rotary internal combustion engine with cooled insert

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.

Air intake for turboprop engine

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.

Air intake with scroll portion and strutted portion for gas turbine engine

A rotor for a rotary internal combustion engine with a first face seal biased axially outwardly away from the first end face has opposed curled ends abutting a first end seal of a respective one of the adjacent apex portions, and a second face seal biased axially outwardly away from the second end face has opposed curled ends abutting a second end seal of a respective one of the adjacent apex portions. A rotary internal combustion engine and a method of sealing chambers of a Wankel engine are also discussed.

Apex and face seals with rotary internal combustion engine

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Brossard, Canada

Eugene Gekht