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11.发明申请公开(公告)号：US20220235936A1
公开(公告)日：2022-07-28
申请号：US17610288
申请日：2020-05-12
摘要： A combustion chamber for a turbomachine including an annular casing delimiting an inner volume of the combustion chamber and provided with a chimney extending to the outside of the inner volume and delimiting a passage for a penetrating part, and a bushing mounted floating on the chimney, further includes: a main air collection chamber open to the upstream arranged facing the downstream portion of the chimney; and a through-opening of the annular casing, connecting the inner volume to the main air collection chamber. The air collected by the main air collection chamber is injected into the inner volume via the through-opening and can cool an annular casing zone downstream of the chimney.
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公开(公告)号：US11377970B2
公开(公告)日：2022-07-05
申请号：US16178768
申请日：2018-11-02
摘要： A system for directing cooling air into a gas turbine combustor is provided. The system comprises a transition duct coupled to a flow sleeve, where air to be used for combustor cooling and in the combustion process enters a bellmouth of the transition duct, passes through a plurality of struts within the bellmouth, and is distributed to a passage located between the combustion liner and flow sleeve.
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公开(公告)号：US20220196243A1
公开(公告)日：2022-06-23
申请号：US17610893
申请日：2020-05-14
IPC分类号： F23R3/50
摘要： A turbomachine has the upstream portion of the annular combustion chamber is fixed to the outer housing via individual pins with a swivel connection.
The swivel connection is established between the pin and a part of the outer housing.
The pin is slidable radially, or with a radial component, by a slide established between the pin and a tubular part of the outer annular shroud and/or the annular wall of the chamber bottom.-
公开(公告)号：US11280494B2
公开(公告)日：2022-03-22
申请号：US16412958
申请日：2019-05-15
摘要： An assembly for a combustion chamber of a turbomachine. The assembly comprises an annular shell extending along a longitudinal axis, the shell having an inner wall intended to be turned towards a furnace of the combustion chamber and an outer wall opposite the inner wall and a projecting element extending radially from an area of the outer wall. The shell has at least one deflector projecting from the outer wall and located downstream of the projecting element with respect to a direction of gas flow along the outer wall, oriented along the longitudinal axis. The deflector extends circumferentially. Perforations are provided axially between the projecting element and the or each deflector.
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公开(公告)号：US11143407B2
公开(公告)日：2021-10-12
申请号：US14895784
申请日：2014-06-11
摘要： A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow.
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公开(公告)号：US11079111B2
公开(公告)日：2021-08-03
申请号：US16397999
申请日：2019-04-29
发明人： German Verduzco , Michael Telfer , Drew Dominique , James Peffley , Taher Basrai , Rasoul Paydar
摘要： This disclosure provides an air tube for a combustor of a gas turbine engine. The air tube includes an inner tube and an outer tube to deliver discharged compressor air into a combustion chamber of the combustor. The air tube can include struts and fins that can improve the cooling performance of the air tube during operation of the gas turbine engine.
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公开(公告)号：US11073282B2
公开(公告)日：2021-07-27
申请号：US15686944
申请日：2017-08-25
申请人： Delavan Inc.
发明人： Jason A. Ryon , Lev A. Prociw
摘要： A heat transfer arrangement includes two or more heat transfer cells. The heat transfer cells together define a boundary between a higher temperature region and a lower temperature region. Each of the two or more heat transfer cells includes two or more walls defining a fluid tight cavity. One or more wick is fused to an inner surface of one or more of the walls to wick liquid from a lower temperature portion of the cavity to a higher temperature portion of the cavity. Combustors having heat transfer arrangements with heat transfer cells and methods of making heat transfer arrangements are also described.
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18.发明授权公开(公告)号：US11022307B2
公开(公告)日：2021-06-01
申请号：US15902171
申请日：2018-02-22
发明人： Jon E Sobanski , Steven D Porter
摘要： A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.
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19.发明授权公开(公告)号：US11009232B2
公开(公告)日：2021-05-18
申请号：US15695510
申请日：2017-09-05
发明人： Jost Imfeld , Paul Marlow , Oliver Konradt , Urs Benz
摘要： Combustor device having a twin-shell tubular casing including: an inner tubular member which extends roughly coaxial a longitudinal axis of the combustor device, delimits the combustion chamber and surrounds the burner; and an outer tubular housing which extends roughly coaxial outside of the inner tubular member. An intermediate supporting structure includes an outer annular supporting member, an inner annular supporting member, and a series of three or more oblong connecting beams angularly staggered about the longitudinal axis of combustor device in cantilever manner to stably connect the inner and outer annular supporting members.
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20.发明授权公开(公告)号：US11009231B2
公开(公告)日：2021-05-18
申请号：US15770573
申请日：2016-10-27
摘要： To improve air/fuel mixing at low speed, the invention concerns an aerodynamic injection system (30) for a combustion chamber (8) of an aircraft turbine engine, the system comprising a central body (70) comprising a first air circulation space (72) and a swirler (74) allowing air to penetrate into the first air circulation space (72), the hollow body (70) also comprising a fuel circuit (92, 93, 82) arranged at least partially around the first space (72), the circuit comprising a second annular space (82) for a fuel film to circulate and fuel supply structures (92, 93) communicating with the second space (82), the spaces (72, 82) opening into a third air and fuel mixing space (86). According to the invention, the system comprises fuel injection openings (90) that bring the fuel circuit into communication with the first space (72).
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