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公开(公告)号：EP4407235A3
公开(公告)日：2024-09-11
申请号：EP24182682.5
申请日：2021-12-22
CPC分类号： F02C7/264 , F23R3/283 , F23R3/343 , F23R2900/0001920130101 , F05D2230/7220130101
摘要： A method comprising removing a hatch (150) from a high pressure engine case (18) to open a hatch opening and performing maintenance on a torch ignitor (10) that is inside the high pressure engine case by accessing the torch ignitor through the hatch opening.
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公开(公告)号：EP4019842B1
公开(公告)日：2024-07-03
申请号：EP21217134.2
申请日：2021-12-22
CPC分类号： F02C7/264 , F23R3/283 , F23R3/343 , F23R2900/0001920130101 , F05D2230/7220130101
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3.发明授权
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公开(公告)号：EP4015908B1
公开(公告)日：2024-02-14
申请号：EP21214511.4
申请日：2021-12-14
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公开(公告)号：EP3995740B1
公开(公告)日：2023-12-20
申请号：EP21192156.4
申请日：2021-08-19
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公开(公告)号：EP4148255A1
公开(公告)日：2023-03-15
申请号：EP22192754.4
申请日：2022-08-30
申请人： Rolls-Royce plc
摘要： An gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, together with a first electrical machine rotationally connected to the turbine module. The combustor module has a combustor volume V (cm 3 ). In use, at a full power condition, the gas turbine engine has a maximum corrected core flow Q (m 3 /sec), and a ratio T of: T = Maximum Corrected Core Flow = Q Combustor volume = V is in a range of between 450 and 2,500.
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公开(公告)号：EP4019839A2
公开(公告)日：2022-06-29
申请号：EP21216405.7
申请日：2021-12-21
摘要： A torch ignitor system for combustor of a gas turbine engine includes a torch ignitor (10), the torch ignitor (10) having a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends (102, 104) defining a flow direction through the combustion chamber, along the axis. The torch ignitor system also includes a cap (34) defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap (34) is configured to receive a fuel injector (45) and at least one glow plug (50), a tip (106) at a downstream end of the combustion chamber, and a passage (108) for pressurized oxygen containing gas passing through the cap (34) from an exterior of the combustion chamber and in fluid communication with the combustion chamber.
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公开(公告)号：EP3995740A1
公开(公告)日：2022-05-11
申请号：EP21192156.4
申请日：2021-08-19
摘要： An embodiment of a torch igniter (10; 110; 410) for a combustor (24) of a gas turbine engine comprises a combustion chamber (16) oriented about an axis (A-A), a cap defining an axially upstream end of the combustion chamber (16) and oriented about the axis, a tip defining an axially downstream end of the combustion chamber, a structural wall (36) coaxial with and surrounding the igniter wall (38), an outlet passage (40) defined by the igniter wall within the tip, and a cooling system. The cooling system comprises an air inlet (62) formed within the structural wall (36), a first flow path disposed between the structural wall and the igniter wall, and an aperture (680) extending through the igniter wall transverse to the flow direction. The aperture directly fluidly connects the first flow path to the combustion chamber.
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公开(公告)号：EP3120003B1
公开(公告)日：2021-04-28
申请号：EP15710776.4
申请日：2015-03-18
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公开(公告)号：EP3730766A1
公开(公告)日：2020-10-28
申请号：EP20169276.1
申请日：2020-04-14
摘要： A gas turbine engine (20) includes a compressor section (24), a combustor (56) fluidly connected to the compressor section (24) via a primary flowpath (C), a turbine section (28) fluidly connected to the combustor (56) via the primary flowpath (C), and a plurality of fuel injectors disposed within the combustor (56). The plurality of fuel injectors including at least one start fuel injector (82). Also included is a controller (80) having a memory and processor. The memory stores instructions configured to cause the at least one start fuel injector to pulse fuel through the start injector nozzle (82), thereby preventing stagnant fuel (130) in the start injector nozzle (82) from exceed a coking temperature threshold.
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