Patents by Inventor John Hu
John Hu 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: 11401867Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the heater rod extending from the base along an axis and terminating in a rod end, a peripheral wall extending circumferentially around the rod end and having a distal end directed away from the base, a gap between the peripheral wall and the heater rod, the rod end being axially retracted relative the distal end of the peripheral wall.Type: GrantFiled: March 29, 2019Date of Patent: August 2, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Patent number: 11402100Abstract: A ring assembly for holding a double-skin combustor liner has an inner skin of ceramic matrix composite and an outer skin. The assembly comprises an annular end body, a first projecting portion projecting relative to the annular end body at least partially in an axial direction, the first projecting portion configured for supporting the inner skin, a second projecting portion projecting relative to the annular end body at least partially in the axial direction, the second projecting portion configured for supporting the outer skin. The first and second projecting portions are radially spaced apart to provide a radial spacing between the inner skin and the outer skin. An expansion joint is between the ring assembly and the inner skin configured to permit motion resulting from a variation in thermal expansion between the inner skin and the ring assembly.Type: GrantFiled: November 15, 2018Date of Patent: August 2, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Tin-Cheung John Hu, Nassim Bedrani
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Patent number: 11391213Abstract: There is disclosed a method of servicing a gas turbine engine having a spark plug igniter connected to a spark plug igniter socket of the engine, the method including: removing the spark plug from the spark plug igniter socket of the gas turbine engine; inserting a glow plug igniter having a base configured for matingly engaging the spark plug igniter socket; and securing the glow plug igniter to the gas turbine engine.Type: GrantFiled: March 29, 2019Date of Patent: July 19, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Publication number: 20220212609Abstract: The application proposes a bracket, a bracket assembly, a device arranged on vehicle roof and a vehicle, which are applied in the field of automobile technology. The bracket comprises: a first bracket body mounted to the top of the vehicle; and a connecting body comprising: a first connecting piece arranged on the left side of the first bracket body and mounted with a first image sensor, and a second connecting piece arranged on the right side of the first bracket body and mounted with a second image sensor, wherein the first connecting piece and the second connecting piece are arranged above A pillars of the vehicle.Type: ApplicationFiled: January 14, 2021Publication date: July 7, 2022Inventors: William LI, Samir AGRAWAL, Jianyong ZHANG, Waylon CHEN, John HU, Yunyue CAI, Xiaoning GONG, Shaoqing REN, Ted LI, Gordon CAO, Jiong CHEN, Matt SAMSON, Devin ZHANG, Yunfeng DONG, Taylor CHENG, Nicole GUO
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Publication number: 20220145803Abstract: A method of servicing a gas turbine engine having an igniter socket, the method comprising: inserting a glow plug into the igniter socket of the gas turbine engine until a rod end of a glow plug heater rod of the glow plug is exposed to a combustion chamber of the gas turbine engine; and blocking a gap between the glow plug heater rod and an aperture defined in a combustor liner of the gas turbine engine to block fluid communication between the combustion chamber and an environment outside the combustion chamber via the aperture.Type: ApplicationFiled: January 26, 2022Publication date: May 12, 2022Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
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Patent number: 11286861Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis to a rod end distal from the base, the glow plug heater rod sized such that that the rod end is exposed to a combustion chamber of the gas turbine engine when the base is connected to the casing.Type: GrantFiled: March 29, 2019Date of Patent: March 29, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Patent number: 11268447Abstract: There is disclosed an igniter for a gas turbine engine including: a base including a securing assembly configured to be matingly connected to a casing of the gas turbine engine, a glow plug heater rod extending from the base along an axis and terminating in a rod end, a combustor liner plug extending circumferentially around the heater rod, the combustor liner plug being sized and configured to extend inside an aperture in a combustor liner of the gas turbine engine when the base is connected to the casing between the heater rod and a periphery of the aperture.Type: GrantFiled: March 29, 2019Date of Patent: March 8, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Patent number: 11268486Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the sleeve having an inner surface spaced from the glow plug heater rod to provide a gap between the inner surface and the glow plug heater rod, the gap extending radially relative to said axis.Type: GrantFiled: March 29, 2019Date of Patent: March 8, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Freer, Kian Mccaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Patent number: 11255271Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.Type: GrantFiled: March 29, 2019Date of Patent: February 22, 2022Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Patent number: 11054136Abstract: An interface for double-skin combustor liner comprises an annular ceramic matrix composite (CMC) body. The annular body extends from a first side to a second side, the first and second sides each having an annular inner joint groove configured to receive a CMC combustor skin and an annular outer joint groove configured to receive a metal combustor skin. The outer joint groove is radially outward of the inner joint groove. A combustor and an gas turbine engine with the interface are also provided.Type: GrantFiled: November 30, 2018Date of Patent: July 6, 2021Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Tin-Cheung John Hu, Robert Sze
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Patent number: 10865761Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a fuel receiver adjacent the heater rod, the fuel receiver including a portion located closest to the heater rod, the rod end protruding axially relative to the axis from the fuel receiver portion located closest to the heater rod.Type: GrantFiled: March 29, 2019Date of Patent: December 15, 2020Assignee: PRATT & WHITNEY CANADA CORPInventors: Richard Freer, Kian McCaldon, Tin-Cheung John Hu, Michel Bousquet, André Fortin
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Publication number: 20200355369Abstract: Wall assemblies for a combustor of a gas turbine engine are disclosed. A wall assembly comprises an outer shell made of a metallic material, adjacent first and second inner panels mounted to the outer shell via an insert and a damper disposed between the outer shell and at least one of the first and second inner panels. The first and second inner panels may be spaced apart from the outer shell to define a double-wall configuration with the outer shell. The first and second inner panels may be made of a composite material. The insert may be made from substantially the same or other type of composite material.Type: ApplicationFiled: December 16, 2019Publication date: November 12, 2020Inventor: Tin-Cheung John HU
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Patent number: 10816200Abstract: The build-up of carbon deposition on the front face of a combustor heat shield is discouraged by jetting air out from the front face of the heat shield with sufficient momentum to push approaching fuel droplets or rich fuel-air mixture way from the heat shield.Type: GrantFiled: November 8, 2016Date of Patent: October 27, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Tin Cheung John Hu, Robert Sze, Honza Stastny
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Patent number: 10788209Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.Type: GrantFiled: August 5, 2015Date of Patent: September 29, 2020Assignee: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu
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Publication number: 20200200387Abstract: A combustor for a gas turbine engine comprises a combustor chamber defined at least partially by an outer combustor skin and an inner combustor skin. A plurality of stand-off devices have a body including a first end and a second end, the second end of the body retained in an opening in the outer combustor skin, the first end spaced apart from the second end and abutting the inner combustor skin to space the inner combustor skin apart from the outer combustor skin.Type: ApplicationFiled: June 21, 2019Publication date: June 25, 2020Inventors: Tin-Cheung John HU, Oleg MORENKO
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Publication number: 20200173661Abstract: An interface for double-skin combustor liner comprises an annular ceramic matrix composite (CMC) body. The annular body extends from a first side to a second side, the first and second sides each having an annular inner joint groove configured to receive a CMC combustor skin and an annular outer joint groove configured to receive a metal combustor skin. The outer joint groove is radially outward of the inner joint groove. A combustor and an gas turbine engine with the interface are also provided.Type: ApplicationFiled: November 30, 2018Publication date: June 4, 2020Inventors: Tin-Cheung John HU, Robert SZE
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Publication number: 20200158344Abstract: A ring assembly for holding a double-skin combustor liner has an inner skin of ceramic matrix composite and an outer skin. The assembly comprises an annular end body, a first projecting portion projecting relative to the annular end body at least partially in an axial direction, the first projecting portion configured for supporting the inner skin, a second projecting portion projecting relative to the annular end body at least partially in the axial direction, the second projecting portion configured for supporting the outer skin. The first and second projecting portions are radially spaced apart to provide a radial spacing between the inner skin and the outer skin. An expansion joint is between the ring assembly and the inner skin configured to permit motion resulting from a variation in thermal expansion between the inner skin and the ring assembly.Type: ApplicationFiled: November 15, 2018Publication date: May 21, 2020Inventors: Tin-Cheung John HU, Nassim BEDRANI
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Publication number: 20200080529Abstract: There is disclosed an igniter for a gas turbine engine including: a base, a glow plug heater rod, the glow plug heater rod extending from the base along an axis and terminating in a rod end, a sleeve extending circumferentially around the glow plug heater rod along at least a portion of a length of the glow plug heater rod, the sleeve having an inner surface spaced from the glow plug heater rod to provide a gap between the inner surface and the glow plug heater rod, the gap extending radially relative to said axis.Type: ApplicationFiled: March 29, 2019Publication date: March 12, 2020Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
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Publication number: 20200080491Abstract: There is disclosed a method of servicing a gas turbine engine having a spark plug igniter connected to a spark plug igniter socket of the engine, the method including: removing the spark plug from the spark plug igniter socket of the gas turbine engine; inserting a glow plug igniter having a base configured for matingly engaging the spark plug igniter socket; and securing the glow plug igniter to the gas turbine engine.Type: ApplicationFiled: March 29, 2019Publication date: March 12, 2020Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN
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Publication number: 20200080482Abstract: There is disclosed an igniter for a gas turbine engine including: a base; a glow plug heater rod extending from the base along an axis and terminating in a rod end; and a structure having open porosity disposed adjacent the glow plug heater rod. A method of operating the igniter and a gas turbine engine having such an igniter are also disclosed.Type: ApplicationFiled: March 29, 2019Publication date: March 12, 2020Inventors: Richard FREER, Kian MCCALDON, Tin-Cheung John HU, Michel BOUSQUET, André FORTIN