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公开(公告)号：EP4198280A1
公开(公告)日：2023-06-21
申请号：EP22158636.5
申请日：2022-02-24
摘要： A turbine engine (10) comprising a compressor section (12), a combustion section (14) having a combustor (120), and a turbine section (14) in serial flow arrangement. The combustor (120) having a combustion chamber (126), at least one fuel injector (122), at least one compressed air passage (124), and at least one igniter (140, 142). The at least one igniter (140, 142) is provided within a portion of the at least one fuel injector (122) or the at least one compressed air passage (124).
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公开(公告)号：EP4202307A1
公开(公告)日：2023-06-28
申请号：EP22161672.5
申请日：2022-03-11
发明人： HAN, Fei , SAMARASINGHE, Ramal Janith , NAIK, Pradeep , VENKATESAN, Krishnakumar , BUCARO, Michel , PATRA, Ajoy , GIRIDHARAN, Manampathy
IPC分类号： F23R3/28
摘要： A turbine engine (10) having a compressor section (12), a combustion section (14) and a turbine section (16) in serial flow arrangement. The turbine engine (10) further having a combustor (80), provided within the combustion section (14), defining a combustion chamber (86) and having at least one fuel injector (76). The fuel injector (140) having a fuel channel (120), a first set of fuel orifices (122), and a flow restrictor (124) located within the fuel channel (120) and having a second set of fuel orifices (126).
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公开(公告)号：EP4198397A1
公开(公告)日：2023-06-21
申请号：EP22164988.2
申请日：2022-03-29
IPC分类号： F23R3/14
摘要： A turbine engine (10) can include a compressor section (12), a combustion section (14, 29), and a turbine section (16) in serial flow arrangement. The combustion section (14, 29) can include a combustor (30) with a combustion chamber (98), a compressed air passage (110) fluidly coupled to the combustion chamber (98), and a swirler (124, 224). At least one acoustic resonator (150, 152, 250, 252) can be provided in the combustor (30).
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公开(公告)号：EP4202302A1
公开(公告)日：2023-06-28
申请号：EP22184746.0
申请日：2022-07-13
发明人： BUCARO, Michael , PATRA, Ajoy , NAIK, Pradeep , VUKANTI, Perumallu , CHIRANTHAN, R Narasimha , COOPER, Clayton , BENJAMIN, Michael , VISE, Steven , GIRIDHARAN, Manampathy , VENKATESAN, Krishnakumar
摘要： An engine (10) can utilize a combustor (36) to combust fuel to drive the engine (10). A fuel nozzle assembly (100) can supply fuel to the combustor (36) for combustion or ignition of the fuel. The fuel nozzle assembly (100) can include a swirler (104) and a fuel nozzle (102) to supply a mixture of fuel and air for combustion. The fuel nozzle can include both a primary fuel passage (108) and secondary fuel passage (110), and an additional air passage (106) to provide for greater flame control, fuel provision, or local fuel and air mixing prior to combustion.
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公开(公告)号：EP4198395A1
公开(公告)日：2023-06-21
申请号：EP22163562.6
申请日：2022-03-22
IPC分类号： F23R3/00
摘要： A turbine engine (10) comprises a compressor section (12), a combustion section (14) and a turbine section (16) in serial flow arrangement, with the combustion section (14) having a combustor (30) defining a longitudinal axis (LA). The combustor (30) comprises a combustor liner (94) at least partially defining a combustion chamber (98), a fuel passage (122) fluidly coupled to the combustion chamber (98), a compressed air passage (110) fluidly coupling the compressor section (12) to the combustion chamber (98), a dome plate (142) separating the combustion chamber (98) from the compressed air passage (110) and having a set of apertures (146, 246, 346) fluidly coupled to the compressed air passage (110), and a set of resonator cavities (150, 250, 250a, 250b, 350, 350a-f) proximate the dome plate (142) and fluidly coupled to the set of apertures (146, 246, 346).
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