Patents by Inventor Sergey USIKOV
Sergey USIKOV 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).
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Patent number: 10677154Abstract: 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: GrantFiled: October 18, 2018Date of Patent: June 9, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Sylvain Lamarre, Mike Fontaine, Andre Julien, Michael Gaul, Jean Thomassin, Lazar Mitrovic, Ilya Medvedev, Sergey Usikov, Andrey Zolotov
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Patent number: 10533500Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, the compressor and the engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and the engine core. The mount cage includes a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and engine core being located outside of the axial space.Type: GrantFiled: September 24, 2015Date of Patent: January 14, 2020Assignee: Pratt & Whitney Canada Corp.Inventors: Sylvain Lamarre, Mike Fontaine, Andre Julien, Michael Gaul, Jean Thomassin, Lazar Mitrovic, Ilya B. Medvedev, Sergey Usikov, Andrey Zolotov
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Patent number: 10533492Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, compressor and engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and exhaust pipe(s). The struts are separated from the hot zone by at least one firewall. The mount cage may include a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and exhaust pipe(s) being located outside of the axial space.Type: GrantFiled: February 18, 2016Date of Patent: January 14, 2020Assignee: Pratt & Whitney Canada Corp.Inventors: Sylvain Lamarre, Mike Fontaine, Andre Julien, Michael Gaul, Jean Thomassin, Lazar Mitrovic, Ilya B. Medvedev, Sergey Usikov, Andrey Zolotov
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Patent number: 10428734Abstract: 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: GrantFiled: September 24, 2015Date of Patent: October 1, 2019Assignee: Pratt & Whitney Canada Corp.Inventors: Sylvain Lamarre, Mike Fontaine, Andre Julien, Michael Gaul, Jean Thomassin, Ilya B. Medvedev, Sergey Usikov, Andrey Zolotov
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Patent number: 10408123Abstract: 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: GrantFiled: September 24, 2015Date of Patent: September 10, 2019Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Sylvain Lamarre, Mike Fontaine, Andre Julien, Michael Gaul, Jean Thomassin, Lazar Mitrovic, Ilya B. Medvedev, Sergey Usikov, Andrey Zolotov
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Patent number: 10371060Abstract: 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.Type: GrantFiled: September 24, 2015Date of Patent: August 6, 2019Assignee: Pratt & Whitney Canada Corp.Inventors: Sylvain Lamarre, Andre Julien, Michael Gaul, Jean Thomassin, Ilya B. Medvedev, Sergey Usikov, Andrey Zolotov
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Publication number: 20190112973Abstract: 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: ApplicationFiled: October 18, 2018Publication date: April 18, 2019Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Lazar MITROVIC, Ilya MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
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Publication number: 20160245174Abstract: 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: ApplicationFiled: September 24, 2015Publication date: August 25, 2016Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
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Publication number: 20160245171Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, compressor and engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and exhaust pipe(s). The struts are separated from the hot zone by at least one firewall. The mount cage may include a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and exhaust pipe(s) being located outside of the axial space.Type: ApplicationFiled: February 18, 2016Publication date: August 25, 2016Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Lazar MITROVIC, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
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Publication number: 20160245156Abstract: 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: ApplicationFiled: September 24, 2015Publication date: August 25, 2016Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Lazar MITROVIC, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
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Publication number: 20160245185Abstract: 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.Type: ApplicationFiled: September 24, 2015Publication date: August 25, 2016Inventors: Sylvain LAMARRE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
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Publication number: 20160245162Abstract: 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: ApplicationFiled: September 24, 2015Publication date: August 25, 2016Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Lazar MITROVIC, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV
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Publication number: 20160245170Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, the compressor and the engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and the engine core. The mount cage includes a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and engine core being located outside of the axial space.Type: ApplicationFiled: September 24, 2015Publication date: August 25, 2016Inventors: Sylvain LAMARRE, Mike FONTAINE, Andre JULIEN, Michael GAUL, Jean THOMASSIN, Lazar MITROVIC, Ilya B. MEDVEDEV, Sergey USIKOV, Andrey ZOLOTOV