Pratt-Whitney Canada Corp

Julien, Andre

Chevrefils, Andre

Andre Julien

Jean Thomassin

Serge Dussault

Richard Ullyott

Bruno Villeneuve

Anthony C Jones

Mike Louis Fontaine

Edwin Schulz

Michael Gaul

Michael Lanktree

David Gagnon-Martin

Luc Dionne

David Harold Menheere

Sylvain Lamarre

Sebastien Bolduc

Pierre-Yves Legare

Stephane Berube

Serge Lafortune

Mark Cunningham

Lazar Mitrovic

Ilya Medvedev

Andrey Zolotov

Sergey Usikov

Behzad Hagshenas

Maxime Courtois

Daniel Van Den Ende

Sébastien Bolduc

Anthony Jones

Jade Bilodeau

Jean Dubreuil

Jean-Gabriel Gauvreau

Sebastien Bergeron

Eric LaTulipe

Renaud Besner

Eugene Gekht

Jason Nichols

Nigel Caldwell Davenport

Etienne Plamondon

Eric Latulipe

Xi Wang

Xiaoqin Wang

Andre Chevrefils

Mike L P Fontaine

Mark Huzzard Cunningham

Marie-Claude Vallieres

Daniel Van Den Hende

Gordon Saby

John Perera

Serge LaFortune

Stephane Bérubé

Jan Thomassin

Daniel Van De Ende

David Gagnon - Martin

Edwin Schultz

Ilya B Medvedev

A hybrid propulsion system includes a heat engine configured to drive a heat engine shaft. An electric motor is configured to drive an electric motor shaft. A transmission system includes at least one gearbox. The transmission system is configured to receive rotational input power from each of the heat engine shaft and the electric motor shaft and to convert the rotation input power to output power.

Architectures for hybrid-electric propulsion

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Auxiliary power unit with intercooler

A turbofan engine assembly including a compressor, an intermittent internal combustion engine having an inlet in fluid communication with an outlet of the compressor through at least one first passage of an intercooler, a turbine having an inlet in fluid communication with an outlet of the intermittent internal combustion engine, the turbine compounded with the intermittent internal combustion engine, a bypass duct surrounding the intermittent internal combustion engine, compressor and turbine, and a fan configured to propel air through the bypass duct and through an inlet of the compressor, wherein the intercooler is located in the bypass duct, the intercooler having at least one second passage in heat exchange relationship with the at least one first passage, the at least one second passage in fluid communication with the bypass duct.

Turbofan engine assembly with intercooler

A compound engine assembly for use as an auxiliary power unit for an aircraft and including an engine core with internal combustion engine(s), a compressor having an outlet in fluid communication with an engine core inlet, a bleed conduit in fluid communication with the compressor outlet through a bleed air valve, and a turbine section having an inlet in fluid communication with the engine core outlet and configured to compound power with the engine core. The turbine section may include a first stage turbine having an inlet in fluid communication with the engine core outlet and a second stage turbine having an inlet in fluid communication the first stage turbine outlet. A method of providing compressed air and electrical power to an aircraft is also discussed.

Compound engine assembly with bleed air

A method of operating a rotary engine including a rotor engaged to a shaft and rotationally received in a housing to define a plurality of working chambers of variable volume, including delivering a pilot quantity of fuel into a pilot cavity in successive communication with the working chambers, igniting the pilot quantity of fuel within the pilot cavity, and delivering a main quantity of fuel into the working chambers downstream of the successive communication of the pilot cavity with the working chambers, where at least one of the pilot quantity and the main quantity is varied between successive rotations of the shaft.

Method of operating an internal combustion engine

A rotary internal combustion engine including a rotor assembly where at least a first and a second of the combustion chambers have unequal theoretical volumetric ratios. Also, a rotary internal combustion engine including first and second rotor assemblies where at least one of the combustion chambers of the first rotor assembly and at least one of the combustion chambers of the second rotor assembly have unequal effective volumetric compression ratios and/or unequal effective volumetric expansion ratios.

Rotary internal combustion engine with unequal volumetric ratios

An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.

Aircraft heating assembly with liquid cooled internal combustion engine and heating element using waste heat

A method of combusting fuel, e.g. heavy fuel, in a rotary engine, including injecting a main quantity of fuel directly into a combustion chamber to form a first fuel-air mixture having a first air-fuel equivalence ratio &#x3bb; higher than 1, injecting a pilot quantity of fuel into a pilot subchamber to form a second fuel-air mixture having a second air-fuel equivalence ratio &#x3bb; smaller than the first air-fuel equivalence ratio, igniting the second fuel-air mixture within the pilot subchamber, using the ignited second fuel-air mixture from the pilot subchamber to ignite the first fuel-air mixture, and injecting a supplemental quantity of fuel directly into the combustion chamber after igniting the first fuel-air mixture, upstream of an exhaust port of the rotary engine with respect to a direction of rotation of the rotor. A rotary engine with interburner fuel injector is also discussed.

Rotary engine and method of combusting fuel

A compound engine system includes a rotary engine with rotating chambers, a compressor section in successive communication with the rotating chambers, and a turbine section in successive communication with the rotating chambers. The turbine section has an output shaft. The output shaft and the engine shaft are drivingly engaged to each other and wherein the turbine section has a power output corresponding to from 20% to 35% of a total power output of the compound engine system. A method of compounding power in a compound engine system is also discussed.

Compound engine system with rotary engine

A method of operating an engine assembly receiving fuel, including admitting atmospheric air at a temperature Tthrough an inlet of a compressor having a pressure ratio of PR, compressing the air in the compressor, cooling the compressed air from the compressor through an intercooler to cool the air from a temperature Tto a temperature T, delivering the cooled compressed air from the intercooler to an inlet of an intermittent internal combustion engine having an effective volumetric compression ratio r, and further compressing the air in the intermittent internal combustion engine before igniting the fuel, where An engine assembly is also discussed.

Engine assembly with intercooler

There is disclosed an engine assembly for an aircraft, including: a combustion engine including a coolant circuit in heat exchange relationship with a heat sink, the heat sink including a heat exchanger and at least one component, the at least one component having a main function that differs from thermal exchange. A method of operating the system is also disclosed.

Engine assembly with heat management system

An engine assembly includes an engine compartment containing an internal combustion engine and a cooler compartment adjacent the engine compartment containing a heat exchanger. The engine and cooler compartments have an opening defined therebetween. A forced air system is operable to drive an airflow. A method for cooling the engine and its compartment is disclosed.

Engine assembly with engine and cooler compartments

There is disclosed a method of operating an engine assembly, including: driving a load with an internal combustion engine and an output of a turbine section, the turbine section driven by combustion gases from an exhaust the internal combustion engine; and injecting fuel upstream of the turbine section and downstream of the exhaust of the internal combustion engine. An engine assembly having a secondary injector for injecting fuel upstream of the turbine section and downstream of the combustion engine is also disclosed.

Compounded internal combustion engine

A rotary engine includes an insert having a pilot subchamber defined therein and communicating with the internal cavity of the engine. A pilot fuel injector has a tip in communication with the pilot subchamber. An ignition element extends into an element cavity defined through the insert adjacent the pilot subchamber. The element cavity is in communication with the pilot subchamber through a communication opening defined in the insert between the element cavity and the pilot subchamber. The communication opening is smaller than a portion of the ignition element adjacent the communication opening such as to prevent the portion of the ignition element from completely passing through the communication opening upon breaking off of the portion of the ignition element from a remainder of the ignition element. An outer body for a rotary engine and a method of combusting fuel in a rotary engine are also provided.

Method of combusting fuel in a rotary internal combustion engine with pilot subchamber and ignition element

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Ste-Julie, Canada

Andre Julien