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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：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：US11841141B2
公开(公告)日：2023-12-12
申请号：US17072465
申请日：2020-10-16
CPC分类号： F23R3/54 , F02C3/145 , F02C7/18 , F23R3/06 , F23R3/46 , F01D9/023 , F05D2220/323 , F05D2240/35 , F23R3/50 , F23R2900/00017
摘要： An apparatus and method for a reverse flow combustor, the reverse flow combustor including a straight portion, a dilution portion and a curved portion. The reverse flow combustor receives a flow of fuel that is ignited and mixed with cooling air to form a flow of combustion gases. The flow of combustion gases travels through the reverse flow combustor to a turbine section of an engine.
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公开(公告)号：US11761631B2
公开(公告)日：2023-09-19
申请号：US17806576
申请日：2022-06-13
CPC分类号： F23R3/002 , F23R3/007 , F23R3/50 , F23R2900/00017 , F23R2900/03043
摘要： A dome structure for a combustor of a gas turbine includes a frame structure extending circumferentially about a combustor centerline axis, and a plurality of integrated dome-deflector plate members mounted to the frame structure. Each of the plurality of integrated dome-deflector plate members includes a dome wall, a deflector wall, and a plurality of side walls connecting the dome wall and the deflector wall to each other. A cavity is defined by the dome wall, the deflector wall, and the plurality of side walls.
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公开(公告)号：US20180363509A1
公开(公告)日：2018-12-20
申请号：US15624070
申请日：2017-06-15
CPC分类号： F01D25/28 , F01D9/04 , F01D25/005 , F05D2240/11 , F05D2240/35 , F05D2250/184 , F05D2250/61 , F05D2260/52 , F05D2300/10 , F05D2300/6012 , F05D2300/6033 , F05D2300/611 , F23R3/007 , F23R3/60 , F23R2900/00005 , F23R2900/00017
摘要： A turbine component assembly is disclosed, including a first component, a second component, and a circumferentially oriented flat spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The circumferentially oriented flat spring is disposed on and directly contacting the second component and directly contacting and supporting the first component as a compliant contact interface between the first component and the second component. The circumferentially oriented flat spring provides a radial spring compliance between the first component and the second component.
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公开(公告)号：US20180306113A1
公开(公告)日：2018-10-25
申请号：US15491047
申请日：2017-04-19
发明人： Jeffrey T. Morton , San Quach
CPC分类号： F23R3/002 , F23R3/06 , F23R3/50 , F23R2900/00017 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： A combustor section of a turbine engine includes a first liner panel including a first end rail. The first end rail includes a protruding heat transfer feature. A second liner panel includes a second end rail disposed proximate the first end rail. The second end rail includes a recess matching the protruding heat transfer feature of the first end rail. A turbine engine and a method of assembling a combustor assembly of a gas turbine engine are also disclosed.
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公开(公告)号：US20180299133A1
公开(公告)日：2018-10-18
申请号：US15485278
申请日：2017-04-12
发明人： Stephen K. Kramer
CPC分类号： F23R3/60 , F23M5/04 , F23M5/085 , F23M2900/05004 , F23R3/002 , F23R3/007 , F23R3/06 , F23R2900/00012 , F23R2900/00017 , F23R2900/03044
摘要： Combustors of gas turbine engines having a combustor shell having a first end and a second end opposite the first end, a first securing element positioned at the first end of the combustor shell, a second securing element positioned at the second end of the combustor shell, a plurality of high temperature material panels fixedly secured by the first securing element at the first end and the second securing element at the second, wherein a panel gap is formed between edges of adjacent high temperature material panels of the plurality of high temperature material panels, and a seal divider extending from the first end to the second end and positioned on the combustor shell and arranged to seal the panel gap between adjacent first and second high temperature material panels.
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10.发明申请公开(公告)号：US20180231255A1
公开(公告)日：2018-08-16
申请号：US15894407
申请日：2018-02-12
发明人： Christoph GAUPP , Urs BENZ , Michael MAURER
CPC分类号： F23R3/286 , F23C2900/07002 , F23D2900/00008 , F23R3/343 , F23R2900/00001 , F23R2900/00017
摘要： A burner assembly for a combustor is provided with a pilot burner extending along a longitudinal axis and a premix burner surrounding the pilot burner; the pilot burner being integral with the premix burner.
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