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公开(公告)号：US20220128008A1
公开(公告)日：2022-04-28
申请号：US17077954
申请日：2020-10-22
发明人： Joseph CIRTWILL , Jian-Ming ZHOU , Kian MCCALDON
摘要： A method of purging fuel injectors of a gas turbine engine, the fuel injectors fluidly connected to a fuel manifold and having primary and secondary fuel passages fluidly connectable to the fuel manifold, the method includes: selectively fluidly disconnecting one or more of the primary and secondary fuel passages from the fuel manifold; and purging the one or more of the primary and secondary fuel passages by injecting a purging fluid into the one or more of the primary and secondary fuel passages while bypassing the fuel manifold. A fuel injector having two fuel passages, a flow divider valve, and a purging valve is disclosed.
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公开(公告)号：US20200080491A1
公开(公告)日：2020-03-12
申请号：US16369991
申请日：2019-03-29
IPC分类号： F02C7/266
摘要： 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.
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公开(公告)号：US20200080486A1
公开(公告)日：2020-03-12
申请号：US16369644
申请日：2019-03-29
摘要： 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 sleeve extending at least partially axially along the heater rod, the sleeve having an inner surface facing and spaced apart from the rod, the inner surface defining a pocket adjacent to the heater rod and having a radial depth relative to the axis.
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4.发明公开公开(公告)号：US20230340910A1
公开(公告)日：2023-10-26
申请号：US18216954
申请日：2023-06-30
发明人： James Robert JARVO , Cedric SAINTIGNAN , Joseph Daniel Maxim CIRTWILL , Kian MCCALDON , Marc-Andre TREMBLAY , David WADDLETON
IPC分类号： F02C7/30 , F02C7/236 , F02C7/232 , F02C7/22 , F02C9/32 , F02C9/42 , F02C7/228 , F02C6/00 , F02C6/16
CPC分类号： F02C7/30 , F02C6/00 , F02C6/16 , F02C7/222 , F02C7/228 , F02C7/232 , F02C7/236 , F02C9/32 , F02C9/42
摘要： Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.
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公开(公告)号：US20220145803A1
公开(公告)日：2022-05-12
申请号：US17584483
申请日：2022-01-26
摘要： 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.
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公开(公告)号：US20200080492A1
公开(公告)日：2020-03-12
申请号：US16370021
申请日：2019-03-29
摘要： 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, 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 igniter having a ventilation path extending from an inlet to an outlet, the inlet fluidly connectable to a spacing located between a casing and a combustor liner of the gas turbine engine, the outlet extending circumferentially around the glow plug heater rod and oriented axially relative to the axis, the outlet fluidly connectable to a combustion chamber of the gas turbine engine delimited by the combustor liner.
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7.发明申请公开(公告)号：US20230083847A1
公开(公告)日：2023-03-16
申请号：US17989247
申请日：2022-11-17
发明人： James Robert JARVO , Cédric SAINTIGNAN , Joseph Daniel Maxim CIRTWILL , Kian MCCALDON , Marc-Andre TREMBLAY , David WADDLETON
摘要： Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.
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公开(公告)号：US20210025332A1
公开(公告)日：2021-01-28
申请号：US16671446
申请日：2019-11-01
摘要： A fuel delivery system for an aircraft engine includes a first fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a first set of fuel nozzles, a second fuel manifold operable to deliver fuel to a combustor of the aircraft engine via a second set of fuel nozzles, and a valve in a fuel nozzle of the second set of fuel nozzles, the valve operable to block fuel flow from the second fuel manifold to the fuel nozzle when the aircraft engine is operated in a standby mode. An aircraft gas turbine engine and a method of operating an aircraft engine are also disclosed.
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公开(公告)号：US20200080529A1
公开(公告)日：2020-03-12
申请号：US16369661
申请日：2019-03-29
摘要： 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.
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公开(公告)号：US20200080483A1
公开(公告)日：2020-03-12
申请号：US16369660
申请日：2019-03-29
IPC分类号： F02C7/264
摘要： 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 plurality of fins disposed circumferentially around the glow plug heater rod, the fins extending axially along at least a portion of the glow plug heater rod. A gas turbine engine including such an igniter is further disclosed.
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