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公开(公告)号：US11313273B2
公开(公告)日：2022-04-26
申请号：US16794806
申请日：2020-02-19
发明人： Richard Ullyott , Anthony Jones , Andre Julien , Jean Thomassin
IPC分类号： F02B63/04 , B64D41/00 , F01C1/22 , F01C11/00 , F02B37/013 , F02B53/02 , F02C7/36 , B64D13/06 , F02B53/00
摘要： 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.
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公开(公告)号：US10968820B2
公开(公告)日：2021-04-06
申请号：US16574650
申请日：2019-09-18
发明人： Michael Gaul , Andre Julien , Bruno Villeneuve
IPC分类号： F02B53/12 , F01C1/22 , F02B19/10 , F02B53/10 , F02B53/02 , F02M53/02 , F02B55/14 , F02B53/00 , F02B55/08 , F02B19/12 , F02P19/02
摘要： 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.
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公开(公告)号：US10927791B2
公开(公告)日：2021-02-23
申请号：US16359152
申请日：2019-03-20
发明人： Andre Julien , Jean Thomassin , Maxime Courtois , Bruno Villeneuve , Richard Ullyott , Serge Dussault , Luc Dionne , Serge Lafortune , Anthony Jones , Behzad Hagshenas , David H. Menheere
IPC分类号： F02K1/38 , B64D41/00 , F01C1/22 , F02K5/00 , F02C5/00 , F02C7/14 , F02C7/18 , F02B63/04 , F02B63/06 , F02B67/04 , F01C21/18 , F01N3/05 , F01P5/02 , F01P11/10 , F02B53/02 , F02K1/82 , F02B53/00
摘要： 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.
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公开(公告)号：US10677154B2
公开(公告)日：2020-06-09
申请号：US16164148
申请日：2018-10-18
发明人： Sylvain Lamarre , Mike Fontaine , Andre Julien , Michael Gaul , Jean Thomassin , Lazar Mitrovic , Ilya Medvedev , Sergey Usikov , Andrey Zolotov
摘要： 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.
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公开(公告)号：US10544733B2
公开(公告)日：2020-01-28
申请号：US15672698
申请日：2017-08-09
发明人： Andre Julien
IPC分类号： F02B55/14 , F02B55/02 , F02B37/00 , F01C1/22 , F01C21/06 , F01C21/08 , F01C21/18 , F01C11/00 , F01C20/06 , F01C20/10 , F01C20/24 , F01C21/10 , F04C29/00
摘要： 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.
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公开(公告)号：US10527012B2
公开(公告)日：2020-01-07
申请号：US15666773
申请日：2017-08-02
发明人： Luc Dionne , Bruno Villeneuve , Andre Julien , Serge Dussault
摘要： 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.
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公开(公告)号：US10526961B2
公开(公告)日：2020-01-07
申请号：US15428303
申请日：2017-02-09
发明人： Serge Dussault , Andre Julien , Michael Lanktree , Edwin Schulz
IPC分类号： F02B55/14 , F02B53/00 , F01C11/00 , F01C20/18 , F02B55/02 , F02B55/08 , F02B53/08 , F01C1/22 , F01C21/08 , F01C21/00
摘要： 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.
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公开(公告)号：US10450952B2
公开(公告)日：2019-10-22
申请号：US15406989
申请日：2017-01-16
发明人： Andre Julien , Jean Thomassin , Serge Dussault
摘要： A turbofan engine assembly including an internal combustion engine in fluid communication between a compressor and a turbine, the internal combustion engine having an engine shaft, a bypass duct surrounding the internal combustion engine, and a fan drivingly engaged to the engine shaft via a gearbox, the gearbox configured to increase an output speed of the fan relative to an input speed of the engine shaft.
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公开(公告)号：US10428734B2
公开(公告)日：2019-10-01
申请号：US14864137
申请日：2015-09-24
发明人： Sylvain Lamarre , Mike Fontaine , Andre Julien , Michael Gaul , Jean Thomassin , Ilya B. Medvedev , Sergey Usikov , Andrey Zolotov
IPC分类号： F02C7/047 , F02C6/12 , F02C7/14 , F01C11/00 , F01C21/06 , F01C21/18 , F02B41/00 , F02C3/04 , F02C6/18 , F02C7/36 , F02B39/04 , F02C7/052 , F02B37/00 , F02B33/40 , F01C1/22
摘要： 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.
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公开(公告)号：US10371060B2
公开(公告)日：2019-08-06
申请号：US14864112
申请日：2015-09-24
发明人： Sylvain Lamarre , Andre Julien , Michael Gaul , Jean Thomassin , Ilya B. Medvedev , Sergey Usikov , Andrey Zolotov
摘要： A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section including a turbine shaft in driving engagement with the engine shaft, and a compressor, and a firewall. The compressor is located on one side of the firewall, and the turbine section and the engine core are located on the other side. The assembly may include a gearbox module with the turbine section and the engine core located on a same side of the gearbox module casing and the compressor located on the opposite side of the gearbox module casing, and with the firewall extending from the gearbox module casing. One or more rotatable accessory may be located on a same side of the firewall as the compressor. A method of reducing fire hazard in a compound engine assembly is also discussed.
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