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1.发明公开公开(公告)号：US20240353105A1
公开(公告)日：2024-10-24
申请号：US18639359
申请日：2024-04-18
申请人： RTX Corporation
CPC分类号： F23R3/60 , F23R3/002 , F23R3/50 , F23R2900/00017
摘要： A gas turbine engine is provided having an axial centerline, a compressor section, a turbine section, and a combustor section. The turbine section has a turbine first vane assembly that includes an annular first vane inner radial support. The combustor section has an outer casing, an annular combustor, and a unitary inner diffuser structure. The annular combustor has an inner radial flange. The unitary inner diffuser structure includes a compressor discharge, an inner diffuser case, and a tangential onboard injector (TOBI) inseparably attached to one another. The unitary inner diffuser structure further includes an outer radial flange and a TOBI connection flange. The annular FV inner radial support, the combustor inner radial flange, and the TOBI connection flange are secured to one another.
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公开(公告)号：US20240247807A1
公开(公告)日：2024-07-25
申请号：US18585509
申请日：2024-02-23
发明人： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rample Rakeshkumar Rangrej , Saket Singh , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade
CPC分类号： F23R3/60 , F23R3/06 , B33Y80/00 , F23R2900/00012 , F23R2900/00017 , F23R2900/00018
摘要： A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
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公开(公告)号：US20240230100A9
公开(公告)日：2024-07-11
申请号：US18314565
申请日：2023-05-09
发明人： Ravindra Shankar Ganiger , Hiranya Nath , Michael A. Benjamin , Daniel D. Brown , Sibtosh Pal , Joseph Zelina
CPC分类号： F23R3/60 , F02C7/20 , F23R3/06 , F23R2900/00017 , F23R2900/03042
摘要： A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes operably direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.
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公开(公告)号：US12024474B2
公开(公告)日：2024-07-02
申请号：US17850430
申请日：2022-06-27
申请人： RTX CORPORATION
发明人： David C. Jarmon
IPC分类号： C04B35/80 , B28B1/00 , B28B11/12 , C04B35/01 , C04B35/565 , C04B35/571 , C04B35/573 , C04B35/622 , C04B35/634 , C04B35/638 , C04B35/64 , C04B35/76 , C04B35/83 , C04B37/00 , D03D25/00 , F01D5/00 , F01D9/00 , F01D11/00 , F01D25/00 , F01D25/24 , F01D25/28 , F01D25/30 , F02C7/28 , F02K1/82 , F23R3/00 , F23R3/28 , F23R3/60
CPC分类号： C04B35/80 , B28B1/001 , B28B1/002 , B28B11/12 , C04B35/01 , C04B35/565 , C04B35/571 , C04B35/573 , C04B35/62227 , C04B35/634 , C04B35/638 , C04B35/64 , C04B35/76 , C04B35/83 , C04B37/001 , D03D25/005 , F01D5/00 , F01D9/00 , F01D11/00 , F01D25/00 , F01D25/005 , F01D25/243 , F01D25/246 , F01D25/28 , F01D25/30 , F02C7/28 , F02K1/822 , F23R3/002 , F23R3/007 , F23R3/283 , F23R3/60 , C04B2235/48 , C04B2235/5208 , C04B2235/5244 , C04B2235/5248 , C04B2235/5252 , C04B2235/5256 , C04B2235/612 , C04B2235/614 , C04B2235/616 , C04B2237/38 , C04B2237/385 , C04B2237/60 , C04B2237/61 , C04B2237/80 , C04B2237/84 , F05D2220/323 , F05D2230/10 , F05D2230/314 , F05D2240/91 , F05D2260/30 , F05D2260/31 , F05D2300/6033 , F23M2900/05004 , Y02T50/60
摘要： A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.
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公开(公告)号：US11873992B2
公开(公告)日：2024-01-16
申请号：US18070039
申请日：2022-11-28
发明人： Masayoshi Kobayashi , Takeo Oda , Takeo Nishiura , Tomoko Tsuru , Takaya Hamamoto , Takeshi Takagi , Osamu Hisamatsu , Hirotaka Kurashima
摘要： A combustor liner used for a gas turbine combustor and forming a combustion chamber includes: an outer side wall made of metal; a panel attached to an inner side of the outer side wall and made of a ceramic matrix composite material, the panel including a panel body facing the combustion chamber, and a connection piece rising from an exterior surface of the panel body at a side portion of the panel body and protruding in a lateral direction; and a connection unit configured to connect the panel to the outer side wall, the connection unit including an elastic member configured to bias at least one of the outer side wall and the connection piece, and a fixation member made of metal and configured to fix at least one of the connection piece and the elastic member to the outer side wall.
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公开(公告)号：US20240011636A1
公开(公告)日：2024-01-11
申请号：US18349275
申请日：2023-07-10
申请人： ROLLS-ROYCE plc
发明人： Lloyd D. MORSON , Julien DIGOUDE
摘要： A combustor casing component for a gas turbine engine which is manufactured as a single-piece. The combustor casing component has a combustor outer casing portion, an outlet guide vane outer case portion, a pre-diffuser portion, a plurality of outlet guide vanes, and an outlet guide vane inner case portion.
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公开(公告)号：US20230417412A1
公开(公告)日：2023-12-28
申请号：US18309262
申请日：2023-04-28
发明人： Michael Alan Stieg , Gregory Scott Phelphs , Jeffrey Douglas Johnson , Chad Holden Sutton , Robert Andrew Stowers , Darrell Glenn Senile
CPC分类号： F23R3/002 , F23R3/60 , F23R3/007 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018
摘要： A combustor assembly for a gas turbine engine includes a dome having a forward surface and an inner surface. The forward surface and the inner surface of the dome at least partially define a slot. The combustor assembly also includes a liner at least partially defining a combustion chamber and extending between an aft end and a forward end. The forward end of the liner is positioned within the slot of the dome. The forward end of the liner includes an axial interface surface and a radial interface surface. The axial interface surface defines a radial gap with the inner surface of the dome and the radial interface surface defines an axial gap with the forward surface of the dome. At least one of the radial gap or the axial gap is less than about 0.150 inches during operating conditions of the combustor assembly to prevent an undesirable airflow.
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公开(公告)号：US20230366545A1
公开(公告)日：2023-11-16
申请号：US17931646
申请日：2022-09-13
CPC分类号： F23R3/002 , F23R3/60 , F02C7/00 , F23R2900/03043 , F05D2220/32 , F05D2240/35
摘要： A combustor includes a skeleton mesh structure having a plurality of structural elements configured to mesh together to form the skeleton mesh structure. The combustor also includes an inner liner and an outer liner mounted to the skeleton mesh structure to define a combustion chamber. The inner liner includes a plurality of inner planks mounted to an inner side of the inner liner and a plurality of outer planks mounted to an outer side of the inner liner. The outer liner includes a plurality of inner planks mounted to an inner side of the outer liner and a plurality of outer planks mounted to the outer side of the outer liner.
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公开(公告)号：US11802512B2
公开(公告)日：2023-10-31
申请号：US17919463
申请日：2021-04-13
发明人： Jacques Marcel Arthur Bunel , William Louis Rodolphe Dousse , Dan-Ranjiv Joory , Benjamin Frantz Karl Villenave
CPC分类号： F02C7/266 , F23R3/002 , F23R3/50 , F23R3/60 , F05D2220/323 , F05D2240/35 , F05D2260/99
摘要： The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).
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公开(公告)号：US11725822B2
公开(公告)日：2023-08-15
申请号：US16423953
申请日：2019-05-28
发明人： Romain Nicolas Lunel , Damien Bonnefoi , Christophe Pieussergues , Luc Namer , Dominique Raulin , Dan Ranjiv Joory , Benjamin Frantz Karl Villenave
CPC分类号： F23R3/60 , F02C3/06 , F02C7/20 , F02C7/22 , F02C9/16 , F23R3/26 , F23R3/28 , F05D2220/323 , F05D2260/30
摘要： The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).
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