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公开(公告)号：EP4424877A3
公开(公告)日：2024-11-13
申请号：EP24153625.9
申请日：2024-01-24
发明人： OTA, Hiroyuki
IPC分类号： C25B1/23 , C25B3/26 , C25B5/00 , C25B15/08 , B01J19/24 , C07C1/02 , C10G2/00 , C10L1/04 , F23R3/28 , H02K7/18
摘要： A synthetic fuel manufacturing system according to an embodiment includes: a carbon dioxide electrolysis unit that discharges cathode gas containing carbon monoxide gas and hydrogen gas; a booster that increases a pressure of the cathode gas; a synthetic fuel generation unit that generates a synthetic fuel by means of the cathode gas having the increased pressure; and a combustion section. The combustion section combusts anode gas containing carbon dioxide gas and oxygen gas, and off gas containing hydrocarbon gas, to generate highly concentrated gas having an increased concentration of the carbon dioxide gas. The carbon dioxide electrolysis unit electrolyzes the carbon dioxide gas contained in the highly concentrated gas discharged from the combustion section.
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公开(公告)号：EP4086517B1
公开(公告)日：2024-11-06
申请号：EP22166747.0
申请日：2022-04-05
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公开(公告)号：EP4414608A3
公开(公告)日：2024-10-23
申请号：EP24157190.0
申请日：2024-02-12
申请人： RTX Corporation
摘要： A system for an aerial vehicle includes a splash plate (132), a fuel nozzle (128) and a gas circuit (136). The splash plate (132) includes a splash plate surface (156, 160). The fuel nozzle (128) includes a nozzle orifice (150). The fuel nozzle (128) is configured to direct fuel out of the nozzle orifice (150) to impinge against the splash plate surface (156, 160). The gas circuit (136) includes a gas passage (166) and a gas outlet (174). At least a portion of the gas passage (166) is formed by and embedded within the splash plate (132). The gas passage (166) extends through the splash plate (132) to the gas outlet (174).
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公开(公告)号：EP4123224B1
公开(公告)日：2024-10-23
申请号：EP22183948.3
申请日：2022-07-08
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公开(公告)号：EP4417870A3
公开(公告)日：2024-10-16
申请号：EP24157315.3
申请日：2024-02-13
摘要： A system includes an engine case (102) for a gas turbine engine defined around a longitudinal axis. A plurality of access openings are defined through the engine case (102). A combustor (108) is housed in the space inside the engine case (102). The inner annular wall (110) of the combustor (108) includes a first rail on an upstream end thereof with a radially outward opening slot. The outer annular wall (112) of the combustor (108) includes a second rail on an upstream end thereof. A plurality of circumferentially spaced apart dome liners extending from the first rail to the second rail. Each dome liner extends tangentially in a direction oblique relative to a radius extending from the longitudinal axis. A plurality of multipoint fuel injector components are assembled across the first and second rails to from a combustor dome together with the dome liners.
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公开(公告)号：EP4431813A1
公开(公告)日：2024-09-18
申请号：EP24163518.4
申请日：2024-03-14
申请人： RTX Corporation
CPC分类号： F23R3/286 , F23R3/283 , F23R3/14 , F23R2900/0000220130101
摘要： An assembly is provided for a turbine engine (20). This assembly includes a fuel injector assembly (62), and the fuel injector assembly (62) includes a fuel passage (114), an air passage (160) and a steam passage (118). The fuel injector assembly (62) is configured to direct fuel out of the fuel passage (114) along an axis (72) into a volume (58) as a fuel flow. The fuel injector assembly (62) is configured to direct air out of the air passage (160) along the axis (72) into the volume (58) as an air flow, where the air flow circumscribes the fuel flow. The fuel injector assembly (62) is configured to direct steam out of the steam passage (118) along the axis (72) into the volume (58) as a steam flow, where the steam flow circumscribes the fuel flow and provides a radial buffer between the fuel flow and the air flow.
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公开(公告)号：EP4202308B1
公开(公告)日：2024-08-28
申请号：EP21216659.9
申请日：2021-12-21
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公开(公告)号：EP4411243A1
公开(公告)日：2024-08-07
申请号：EP24155603.4
申请日：2024-02-02
发明人： HU, Tin Cheung John
CPC分类号： F23R3/286 , F23R3/16 , F23R2900/0000220130101
摘要： An injector (38) for introducing hydrogen and air into a combustion chamber (26a) of a gas turbine engine (20) includes a convergent-divergent nozzle head (40), a fairing (42), a fuel nozzle (44), and an air nozzle (46). The convergent-divergent nozzle head (40) has in fluid communication in series a convergent section (40a), a throat (40b), and a divergent section (40c). The fairing (42) extends through the convergent section (40a) and through the throat (40b) to define an annular passage (48) between the fairing (42) and the convergent-divergent nozzle head (40) that has an outlet (48a) in the divergent section (40c). The fuel nozzle (44) has multiple feed conduits (44a) that open to the annular passage (48) for providing hydrogen fuel. The gas nozzle (46) is upstream of the convergent-divergent nozzle head (40) for providing gas into the annular passage (48).
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公开(公告)号：EP4411239A1
公开(公告)日：2024-08-07
申请号：EP24154531.8
申请日：2024-01-29
发明人： McCALDON, Kian
CPC分类号： F23R3/286 , F23R2900/0000220130101 , F23R3/12
摘要： A fuel mixture distribution system (35) for a turbine engine assembly (20) includes a combustor (26) that includes a wall (44) that defines a combustion chamber (46), a fuel mixture distributor that includes an air conduit (48) that defines a mixing chamber (52) that extends through the wall (44) along between an inlet (54) to an exit opening (56) to the combustion chamber (46), the air conduit shape is defined to achieve the desired mixing and prevent flashback at all operating conditions, and a fuel distributor (42; 58; 90; 98) extends into the mixing chamber (52) at a location upstream of the exit opening (56). The fuel distributor (42; 58; 90; 98) includes a plurality of fuel openings (68; 102; 112) where a fuel flow (38) is communicated and mixed with an airflow (40) passing through the mixing chamber (52).
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