Patents by Inventor Fei Philip Lee
Fei Philip Lee 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: 10883719Abstract: A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; and a prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer including an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage. The fuel injector is arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element.Type: GrantFiled: April 5, 2019Date of Patent: January 5, 2021Assignee: Woodward, Inc.Inventor: Fei Philip Lee
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Patent number: 10711699Abstract: A torch igniter includes an auxiliary fuel injector; an ignition source; and an igniter body carrying the auxiliary fuel injector and the ignition source. The igniter body includes an auxiliary combustion chamber having a side wall extending axially from a first end wall to a second end wall. In some examples, at least a portion of the side wall includes a distributed pattern of cooling apertures, with each of the cooling apertures extending obliquely from an outer surface of the side wall to an inner surface of the side wall. In some examples, the second end wall defines a fluid outlet leading to an outlet tube in fluid communication with the primary combustion chamber, at least a portion of the outlet tube including a distributed pattern of dilution apertures.Type: GrantFiled: July 7, 2017Date of Patent: July 14, 2020Assignee: Woodward, Inc.Inventors: Bidhan Dam, Jimroy McCormack, Fei Philip Lee, Conor Riordan, Logan Oonk, Erik Pederson, Michael Stratton
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Patent number: 10704469Abstract: A torch igniter includes an auxiliary fuel injector; an ignition source; and an igniter body carrying the auxiliary fuel injector and the ignition source. The igniter body includes an auxiliary combustion chamber having a side wall extending axially from a first end wall to a second end wall, the side wall defining an interior cavity between the first and second end walls. The igniter body further includes a premixing cup residing within the interior cavity including a cylindrical wall radially surrounding the auxiliary fuel injector and an auxiliary air inlet, the cylindrical wall of the premixing cup protruding axially outward relative to the first end wall of the auxiliary combustion chamber through a portion of the interior cavity to delineate a premixing zone radially inward of the cylindrical wall and a recirculation zone radially outward of the cylindrical wall.Type: GrantFiled: July 7, 2017Date of Patent: July 7, 2020Assignee: Woodward, Inc.Inventors: Bidhan Dam, Jimroy McCormack, Fei Philip Lee, Conor Riordan, Logan Oonk, Erik Pederson, Michael Stratton
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Publication number: 20200141582Abstract: A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; and a prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer including an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage. The fuel injector is arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element.Type: ApplicationFiled: April 5, 2019Publication date: May 7, 2020Applicant: Woodward, Inc.Inventor: Fei Philip Lee
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Patent number: 10584639Abstract: A gas turbine combustor assembly includes a primary combustion chamber in fluid communication with a primary fuel injector and a primary air inlet. A torch igniter is carried by the primary combustion chamber, and includes an auxiliary combustion chamber housing comprising a mixing chamber and a throat region converging downstream of the mixing chamber. An air swirler including a plurality of swirl openings surrounding an outlet of an auxiliary fuel injector is coupled to the auxiliary combustion chamber proximate the mixing chamber. An ignition source projects into the mixing chamber of the auxiliary combustion chamber.Type: GrantFiled: August 18, 2015Date of Patent: March 10, 2020Assignee: Woodward, Inc.Inventors: Bidhan Dam, Jimroy McCormack, Erik Pederson, Fei Philip Lee, Paul Hicks
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Patent number: 10415832Abstract: A gas turbine combustor assembly has a fuel/air mixer assembly with a plurality of fuel/air mixer elements. Each fuel/air mixer element defines an air flow passage therethrough. A fuel injector is coupled to the fuel/air mixer assembly. The fuel injector has a tip portion with a plurality of fuel outlets arranged to direct fuel into the air flow passages of the air/fuel mixer elements. Each of the fuel/air mixer elements has at least one outlet arranged to supply fuel to the element.Type: GrantFiled: October 31, 2016Date of Patent: September 17, 2019Assignee: Woodward, Inc.Inventor: Fei Philip Lee
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Patent number: 10408454Abstract: A gas turbine combustor assembly includes a fuel injector, a dome stator around the fuel injector, and a dome sleeve coupled to the dome stator. The dome sleeve defines an air inlet opening with the dome stator, and is carried to move with respect to the dome stator to change a flow area of the air inlet opening. The dome sleeve also defines a nozzle sloping downstream from the air inlet opening toward an outlet of the combustor assembly. The sloping nozzle defines an annular pinch gap adjacent an outlet of the fuel injector, and is coupled to move with the dome sleeve to change a flow area through the pinch gap.Type: GrantFiled: June 18, 2013Date of Patent: September 10, 2019Assignee: Woodward, Inc.Inventors: Fei Philip Lee, Hukam Chand Mongia, Kathleen M. Tacina, Chi-Ming Lee, Daniel L. Bulzan
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Patent number: 10267524Abstract: A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; and a prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer including an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage. The fuel injector is arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element.Type: GrantFiled: September 16, 2015Date of Patent: April 23, 2019Assignee: Woodward, Inc.Inventor: Fei Philip Lee
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Publication number: 20190010873Abstract: A torch igniter includes an auxiliary fuel injector; an ignition source; and an igniter body carrying the auxiliary fuel injector and the ignition source. The igniter body includes an auxiliary combustion chamber having a side wall extending axially from a first end wall to a second end wall. In some examples, at least a portion of the side wall includes a distributed pattern of cooling apertures, with each of the cooling apertures extending obliquely from an outer surface of the side wall to an inner surface of the side wall. In some examples, the second end wall defines a fluid outlet leading to an outlet tube in fluid communication with the primary combustion chamber, at least a portion of the outlet tube including a distributed pattern of dilution apertures.Type: ApplicationFiled: July 7, 2017Publication date: January 10, 2019Inventors: Bidhan Dam, Jimroy McCormack, Fei Philip Lee, Conor Riordan, Logan Oonk, Erik Pederson, Michael Stratton
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Publication number: 20190010872Abstract: A torch igniter includes an auxiliary fuel injector; an ignition source; and an igniter body carrying the auxiliary fuel injector and the ignition source. The igniter body includes an auxiliary combustion chamber having a side wall extending axially from a first end wall to a second end wall, the side wall defining an interior cavity between the first and second end walls. The igniter body further includes a premixing cup residing within the interior cavity including a cylindrical wall radially surrounding the auxiliary fuel injector and an auxiliary air inlet, the cylindrical wall of the premixing cup protruding axially outward relative to the first end wall of the auxiliary combustion chamber through a portion of the interior cavity to delineate a premixing zone radially inward of the cylindrical wall and a recirculation zone radially outward of the cylindrical wall.Type: ApplicationFiled: July 7, 2017Publication date: January 10, 2019Inventors: Bidhan Dam, Jimroy McCormack, Fei Philip Lee, Conor Riordan, Logan Oonk, Erik Pederson, Michael Stratton
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Patent number: 10006637Abstract: In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage therethrough having an outlet in a first plane. A second fuel/air mixer assembly comprises a second fuel injector and a plurality of second mixer elements, and each second mixer element defines an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.Type: GrantFiled: January 20, 2017Date of Patent: June 26, 2018Assignee: Woodward, Inc.Inventor: Fei Philip Lee
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Publication number: 20170328570Abstract: In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage therethrough having an outlet in a first plane. A second fuel/air mixer assembly comprises a second fuel injector and a plurality of second mixer elements, and each second mixer element defines an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.Type: ApplicationFiled: January 20, 2017Publication date: November 16, 2017Inventor: Fei Philip Lee
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Publication number: 20170299184Abstract: A gas turbine combustor assembly has a fuel/air mixer assembly with a plurality of fuel/air mixer elements. Each fuel/air mixer element defines an air flow passage therethrough. A fuel injector is coupled to the fuel/air mixer assembly. The fuel injector has a tip portion with a plurality of fuel outlets arranged to direct fuel into the air flow passages of the air/fuel mixer elements. Each of the fuel/air mixer elements has at least one outlet arranged to supply fuel to the element.Type: ApplicationFiled: October 31, 2016Publication date: October 19, 2017Inventor: Fei Philip Lee
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Publication number: 20170074518Abstract: A turbine combustor assembly includes a fuel/air mixer assembly having a plurality of fuel/air mixer elements and a fuel injector coupled to the fuel/air mixer assembly. Each of the fuel/air mixer elements includes: a fuel/air mixer body having an internal cavity extending axially between an air inlet and an air outlet; and a prefilmer residing within an interior cavity of the fuel/air mixer body, the prefilmer including an axial inner air flow passage extending coaxially with an axial centerline of the internal cavity of the fuel/air mixer body and a radial fuel injection port into the air flow passage. The fuel injector is arranged to direct fuel into a plurality of the fuel/air mixer elements via the fuel injection port of the prefilmer of each fuel/air mixer element.Type: ApplicationFiled: September 16, 2015Publication date: March 16, 2017Inventor: Fei Philip Lee
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Patent number: 9587833Abstract: In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage therethrough having an outlet in a first plane. A second fuel/air mixer assembly comprises a second fuel injector and a plurality of second mixer elements, and each second mixer element defines an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.Type: GrantFiled: January 29, 2014Date of Patent: March 7, 2017Assignee: Woodward, Inc.Inventor: Fei Philip Lee
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Patent number: 9482433Abstract: A gas turbine combustor assembly has a fuel/air mixer assembly with a plurality of fuel/air mixer elements. Each fuel/air mixer element defines an air flow passage therethrough. A fuel injector is coupled to the fuel/air mixer assembly. The fuel injector has a tip portion with a plurality of fuel outlets arranged to direct fuel into the air flow passages of the air/fuel mixer elements. Each of the fuel/air mixer elements has at least one outlet arranged to supply fuel to the element.Type: GrantFiled: November 11, 2013Date of Patent: November 1, 2016Assignee: Woodward, Inc.Inventor: Fei Philip Lee
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Publication number: 20160138807Abstract: A gas turbine combustor assembly includes a fuel injector, a dome stator around the fuel injector, and a dome sleeve coupled to the dome stator. The dome sleeve defines an air inlet opening with the dome stator, and is carried to move with respect to the dome stator to change a flow area of the air inlet opening. The dome sleeve also defines a nozzle sloping downstream from the air inlet opening toward an outlet of the combustor assembly. The sloping nozzle defines an annular pinch gap adjacent an outlet of the fuel injector, and is coupled to move with the dome sleeve to change a flow area through the pinch gap.Type: ApplicationFiled: June 18, 2013Publication date: May 19, 2016Inventors: Hukam Chand Mongia, Chi-Ming Lee, Daniel L. Bulzan, Fei Philip Lee, Kathleen M. Tacina
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Patent number: 9291139Abstract: The disclosure provides a fuel injection nozzle. The fuel injection nozzle includes a nozzle body, with the nozzle body defining a central bore. A fuel atomizer is disposed in the central bore. The fuel atomizer defines a spill-return bore and a swirl chamber. The swirl chamber is in fluid communication with the central bore. The spill-return bore includes a return swirler approximate the swirl chamber. An air supply pump is coupled to the fuel atomizer and is in fluid communication with the spill-return bore. The air supply pump is configured to selectively inject air into the swirl chamber through the spill-return bore.Type: GrantFiled: August 27, 2008Date of Patent: March 22, 2016Assignee: Woodward, Inc.Inventors: Paul G. Hicks, Fei Philip Lee
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Publication number: 20160047318Abstract: A gas turbine combustor assembly includes a primary combustion chamber in fluid communication with a primary fuel injector and a primary air inlet. A torch igniter is carried by the primary combustion chamber, and includes an auxiliary combustion chamber housing comprising a mixing chamber and a throat region converging downstream of the mixing chamber. An air swirler including a plurality of swirl openings surrounding an outlet of an auxiliary fuel injector is coupled to the auxiliary combustion chamber proximate the mixing chamber. An ignition source projects into the mixing chamber of the auxiliary combustion chamber.Type: ApplicationFiled: August 18, 2015Publication date: February 18, 2016Inventors: Bidhan Dam, Jimroy McCormack, Erik Pederson, Fei Philip Lee
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Publication number: 20150211742Abstract: In some aspects, a gas turbine combustor assembly is arranged around a longitudinal axis. The gas turbine combustor comprises a first fuel/air mixer assembly, the mixer assembly comprising a first fuel injector and a plurality of first mixer elements, each mixer element defining an air flow passage therethrough having an outlet in a first plane. A second fuel/air mixer assembly comprises a second fuel injector and a plurality of second mixer elements, and each second mixer element defines an air flow passage therethrough having an outlet in a second plane, longitudinally offset from the first plane.Type: ApplicationFiled: January 29, 2014Publication date: July 30, 2015Applicant: Woodward, Inc.Inventor: Fei Philip Lee