Patents by Inventor Andre Julien

Andre Julien has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 9759128
    Abstract: A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.
    Type: Grant
    Filed: June 16, 2015
    Date of Patent: September 12, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andre Julien, Serge Dussault, Jade Bilodeau, Renaud Besner
  • Publication number: 20170226959
    Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.
    Type: Application
    Filed: August 3, 2016
    Publication date: August 10, 2017
    Inventors: Andre JULIEN, Jean THOMASSIN, Maxime COURTOIS, Bruno VILLENEUVE, Serge DUSSAULT, Richard ULLYOTT, Serge LAFORTUNE, Luc DIONNE, Anthony JONES, Behzad HAGSHENAS, David MENHEERE
  • Publication number: 20170218783
    Abstract: An inlet guide assembly for a turbine receiving a pulsed flow, including a duct having an internal volume, and an inlet port, first outlet nozzle and second outlet nozzle each communicating with the internal volume. The inlet port is configured to receive at least part of the pulsed flow. The first and second outlet nozzles each define a respective nozzle area communicating between the internal volume and a flow path of the turbine. The first and second outlet nozzles are spaced from one another with the first outlet nozzle located closer to the inlet port than the second outlet nozzle relative to a flow direction through the duct, the nozzle area of the first outlet nozzle being smaller than the nozzle area of the second outlet nozzle. A compound engine assembly and method of introducing a pulsed flow into a flow path of a turbine are also discussed.
    Type: Application
    Filed: January 29, 2016
    Publication date: August 3, 2017
    Inventors: Jean THOMASSIN, Marie-Claude VALLIERES, Mike FONTAINE, Andre JULIEN, John PERERA
  • Publication number: 20170074160
    Abstract: A method of controlling an air intake flow in a rotary engine having primary and secondary inlet ports, including positioning the secondary inlet port rearwardly of the primary inlet port and forwardly of the exhaust port along a direction of a revolution of the rotor, and controlling air intake flows communicating between an air source and the primary and secondary inlet ports. During engine start-up, a primary valve is closed to prevent the intake air flow between the primary inlet port and the air source and a secondary valve is opened to allow the intake air flow between the secondary inlet port and the air source. A rotary engine defining different compression ratios through actuation of a valve is also discussed.
    Type: Application
    Filed: November 29, 2016
    Publication date: March 16, 2017
    Inventors: Jean THOMASSIN, Andre JULIEN, Edwin SCHULZ, Michael LANKTREE
  • Publication number: 20170037775
    Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.
    Type: Application
    Filed: August 3, 2016
    Publication date: February 9, 2017
    Inventors: Anthony JONES, Andre JULIEN, David MENHEERE, Jean THOMASSIN, Richard ULLYOTT, Daniel VAN DEN ENDE
  • Publication number: 20170037776
    Abstract: An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine, a first heat exchanger in fluid communication with the liquid coolant system of the internal combustion engine, a second heat exchanger in fluid communication with the liquid coolant system of the generator, an exhaust duct in fluid communication with air passages of the heat exchangers, and a fan received in the exhaust duct and rotatable by the internal combustion engine for driving a cooling air flow through the air passages. The liquid coolant system of the engine may be distinct from fuel and lubricating systems of the auxiliary power unit. A method of cooling a generator and an internal combustion engine is also discussed.
    Type: Application
    Filed: August 3, 2016
    Publication date: February 9, 2017
    Inventors: Anthony JONES, Andre JULIEN, David MENHEERE, Jean THOMASSIN, Richard ULLYOTT
  • Publication number: 20170037756
    Abstract: A turboprop engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system, an air duct in fluid communication with an environment of the aircraft, a heat exchanger received within the air duct having coolant passages in fluid communication with the liquid coolant system and air passages air passages in fluid communication with the air duct, and an exhaust duct in fluid communication with an exhaust of the internal combustion engine. The exhaust duct has an outlet positioned within the air duct downstream of the heat exchanger and upstream of an outlet of the air duct, the outlet of the exhaust duct spaced inwardly from a peripheral wall of the air duct. In use, a flow of cooling air surrounds a flow of exhaust gases. A method of discharging air and exhaust gases in an turboprop engine assembly having an internal combustion engine is also discussed.
    Type: Application
    Filed: August 3, 2016
    Publication date: February 9, 2017
    Inventors: Andre JULIEN, Jean THOMASSIN, Serge DUSSAULT
  • Publication number: 20170036775
    Abstract: 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.
    Type: Application
    Filed: August 3, 2016
    Publication date: February 9, 2017
    Inventors: Anthony JONES, Andre JULIEN, David MENHEERE, Jean THOMASSIN, Richard ULLYOTT, Daniel VAN DEN HENDE
  • Publication number: 20170036773
    Abstract: There is described herein methods and systems for selective use of an auxiliary power source inflight in order to reduce fuel consumption of an aircraft.
    Type: Application
    Filed: July 18, 2016
    Publication date: February 9, 2017
    Inventors: Anthony JONES, Andre JULIEN, David MENHEERE, Jean THOMASSIN, Richard ULLYOTT, Daniel VAN DEN HENDE
  • Publication number: 20170037774
    Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine, a turbine having an inlet in fluid communication with an outlet of the engine, the turbine compounded with the engine, a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with the aircraft, the compressor rotatable independently of the turbine, an electric motor drivingly engaged to the compressor, and a transfer generator drivingly engaged to the engine, the transfer generator and the electric motor being electrically connected to allow power transfer therebetween. The compressor or an additional compressor may be in fluid communication with the inlet of the engine. A method of operating an auxiliary power unit of an aircraft is also discussed.
    Type: Application
    Filed: August 3, 2016
    Publication date: February 9, 2017
    Inventors: Anthony JONES, Andre JULIEN, David MENHEERE, Jean THOMASSIN, Richard ULLYOTT, Daniel VAN DEN HENDE
  • Patent number: 9540992
    Abstract: A method and apparatus for controlling an air input in a rotary engine, including selectively controlling a plurality of inlet ports communicating with an internal combustion cavity of the engine, the ports located serially downstream of the exhaust port relative direction of a revolution of a rotor of the engine. The inlet ports are controlled to alter air intake at various engine operational stages, such as start up, idle, etc., to allow for varying operational requirements to be met. For example: when a power demand on the engine lower than a predetermined threshold, control may be effected by opening a primary inlet port and closing a secondary inlet port; and, when the power demand exceeds the predetermined threshold, control may be effected by opening the primary inlet port and opening the secondary inlet port, the secondary inlet port being located such as to be in communication with the exhaust port throughout portions of the revolution of the engine to purge exhaust gases of the engine.
    Type: Grant
    Filed: January 10, 2014
    Date of Patent: January 10, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jean Thomassin, Andre Julien, Edwin Schulz, Michael Lanktree
  • Publication number: 20160376022
    Abstract: An auxiliary power unit for an aircraft, having an engine core, a compressor having an outlet in fluid communication with the engine core inlet, a turbine section in fluid communication with the engine core outlet, and an excess air duct having a first end in fluid communication with the compressor outlet and a second end in fluid communication with a turbine inlet of the turbine section. The excess air duct defines a flow path between the compressor outlet and the turbine section separate from the engine core. The auxiliary power unit may include a generator in driving engagement with 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.
    Type: Application
    Filed: June 25, 2015
    Publication date: December 29, 2016
    Inventors: Richard ULLYOTT, Anthony JONES, Andre JULIEN, Jean THOMASSIN
  • Publication number: 20160376023
    Abstract: A compound engine assembly for use as an aircraft auxiliary power unit, having an engine core including internal combustion engine(s) in driving engagement with an engine shaft, a generator having a generator shaft directly engaged to the engine shaft such as to be rotatable at a same speed, a compressor having an outlet in communication with the engine core inlet, and a turbine section having an inlet in 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 communication with the engine core outlet, and a second stage turbine having an inlet in communication with the first stage turbine outlet. A method of providing electrical power to an aircraft is also discussed.
    Type: Application
    Filed: June 25, 2015
    Publication date: December 29, 2016
    Inventors: Richard ULLYOTT, Anthony JONES, Andre JULIEN, Jean THOMASSIN
  • Publication number: 20160376021
    Abstract: 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.
    Type: Application
    Filed: June 25, 2015
    Publication date: December 29, 2016
    Inventors: Richard ULLYOTT, Anthony JONES, Andre JULIEN, Jean THOMASSIN
  • Publication number: 20160376981
    Abstract: 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.
    Type: Application
    Filed: June 25, 2015
    Publication date: December 29, 2016
    Inventors: Richard ULLYOTT, Anthony JONES, Andre JULIEN, Jean THOMASSIN
  • Publication number: 20160369693
    Abstract: A compound engine assembly with at least one rotary internal combustion engine, an impulse turbine, and an exhaust pipe for each internal combustion engine providing fluid communication between the exhaust port of the respective internal combustion engine and the flow path of the turbine. Each exhaust pipe terminates in a nozzle. For each exhaust pipe, a ratio Vp/Vd between the pipe volume Vp and the displacement volume Vd of the respective internal combustion engine is at most 1.5. A minimum value of a cross-sectional area of each exhaust pipe is defined at the nozzle. In one embodiment, a ratio An/Ae between the minimum cross-sectional area An and the cross-sectional area Ae of the exhaust port of the respective internal combustion engine is at least 0.2. A method of compounding at least one rotary engine is also discussed.
    Type: Application
    Filed: June 16, 2015
    Publication date: December 22, 2016
    Inventors: Andre JULIEN, Serge DUSSAULT, Jade BILODEAU, Renaud BESNER
  • Publication number: 20160245162
    Abstract: A compound engine assembly with an inlet duct, a compressor, an engine core including at least one internal combustion engine, and a turbine section including a turbine shaft configured to compound power with the engine shaft. The turbine section may include a first stage turbine and a second stage turbine. The turbine shaft and the engine shaft are parallel to each other. The turbine shaft, the engine shaft and at least part of the inlet duct are all radially offset from one another. A method of driving a rotatable load of an aircraft is also discussed.
    Type: Application
    Filed: September 24, 2015
    Publication date: August 25, 2016
    Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Lazar MITROVIC, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
  • Publication number: 20160245156
    Abstract: An engine assembly including an engine core with at least one internal combustion engine, a first casing, a turbine module including a second casing located outside of the first casing, and a compressor module including a third casing located outside of the first and second casings. The turbine shaft extends into the first casing, is rotationally supported by a bearings all contained within the first casing, and is free of rotational support within the second casing. The first casing may be a gearbox module casing through which the turbine shaft is in driving engagement with the engine shaft. A method of driving a rotatable load of an aircraft, and an engine assembly with a rotary engine core, a gearbox module with a first casing, and a second module including a second casing located outside of the first casing and detachably connected to the first casing are also discussed.
    Type: Application
    Filed: September 24, 2015
    Publication date: August 25, 2016
    Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Lazar MITROVIC, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
  • Publication number: 20160245174
    Abstract: A compound engine assembly with an inlet duct having an inlet surrounded by an inlet lip including at least one conduit extending therethrough, a compressor, an engine core including at least one internal combustion engine, a turbine section having a turbine shaft in driving engagement with the engine shaft, and an exhaust conduit providing a fluid communication between the outlet of the turbine section and the conduit(s) of the inlet lip. An exhaust duct and ant exhaust conduit providing a fluid communication between the outlet of the turbine section and the exhaust duct may also be provided. The internal combustion engine(s) may be rotary engine(s). A method of driving a rotatable load of an aircraft is also discussed.
    Type: Application
    Filed: September 24, 2015
    Publication date: August 25, 2016
    Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
  • Publication number: 20160245165
    Abstract: A rotary engine including an insert in one of the walls of the outer body. The insert has a pilot subchamber defined therein communicating with the internal cavity and includes a subchamber wall surrounding the pilot subchamber. A main fuel injector is in communication with the internal cavity at a location spaced apart from the insert. A pilot fuel injector is in communication with the pilot subchamber. A heating element extends within the subchamber wall completely outside of the pilot subchamber, in heat transfer communication with the subchamber wall. An outer body for a rotary engine and a method of combusting fuel in a rotary engine are also provided.
    Type: Application
    Filed: May 2, 2016
    Publication date: August 25, 2016
    Inventors: Michael GAUL, Andre JULIEN, Bruno VILLENEUVE