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公开(公告)号：US11988387B2
公开(公告)日：2024-05-21
申请号：US18014326
申请日：2021-07-02
摘要： Annular combustion chamber for an aircraft turbomachine, said chamber having two coaxial annular walls, an inner annular wall and an outer annular wall, respectively, which are connected upstream by an annular bottom wall of the chamber, wherein an injection device passes through an axis and comprises an air injection system and a frustoconical bowl which is flared downstream and has air passage openings, the chamber further having an annular deflector placed downstream of the bottom wall substantially parallel to the latter; and wherein the air injection system, the bottom wall, the deflector and the bowl are integrally formed.
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公开(公告)号：US20240142104A1
公开(公告)日：2024-05-02
申请号：US17773082
申请日：2020-10-02
摘要： A combustion chamber of a gas turbine, wherein downstream of the combustion chamber an expansion turbine with a turbine inlet is arranged. The combustion chamber has an annular design with a component, which has a chamber wall and an end wall arranged next to the turbine inlet and a corner as connection of the chamber wall and the end wall. To increase the cooling performance the component further has an air guidance piece arranged at a distance from the chamber wall with a cooling channel in-between. Further, the corner is fluid tight, wherein the distance of the air guidance piece to the end wall is at least 0.5-times and at most 2-times the lowest width of the cooling channel.
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公开(公告)号：US11920789B2
公开(公告)日：2024-03-05
申请号：US17167165
申请日：2021-02-04
CPC分类号： F23R3/002 , F23R3/007 , F23R3/50 , F23R3/60 , F23R2900/00014
摘要： A combustor assembly for a gas turbine engine includes an outer liner that at least partially defines a combustion chamber. The outer liner extends between an aft end and a forward end generally along an axial direction within an outer casing of the gas turbine engine. The outer liner includes an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The combustor assembly includes a radial damper assembly disposed against the outer liner at a plurality of circumferential points.
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公开(公告)号：US20240053016A1
公开(公告)日：2024-02-15
申请号：US18254485
申请日：2021-11-26
申请人： SAFRAN CERAMICS
CPC分类号： F23R3/50 , F23R3/60 , F23R3/007 , F23R3/54 , F23R2900/00017
摘要： A combustion module for a turbomachine is provided and includes an annular casing extending about a longitudinal axis; an annular combustion chamber located inside the casing and comprising coaxial annular walls connected to one another by an annular chamber dome, the walls and the chamber dome consisting of at least two annular envelopes, which are made of a ceramic-matrix composite material. The module can include anti-disengagement devices to keep the annular edges pressing axially against one another and fuel injectors borne by the casing and engaged in apertures of one of the envelopes.
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公开(公告)号：US11898494B2
公开(公告)日：2024-02-13
申请号：US17502502
申请日：2021-10-15
摘要： A gas turbine engine is provided having a combustion section with a liner extending between a forward end and an aft end. A structural member is positioned in or around at least a portion of the combustion section. Additionally, a piston ring holder is provided attached to the structural member at a first end and positioned proximate to the aft end of the liner at a second end. The piston ring holder is a bimetallic member including a first portion formed of a first material and a second portion formed of a second material. A coefficient of thermal expansion of the first material is different than a coefficient of thermal expansion of the second material.
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6.发明授权公开(公告)号：US11846420B2
公开(公告)日：2023-12-19
申请号：US17610288
申请日：2020-05-12
CPC分类号： F23R3/06 , F23R3/002 , F23R3/50 , F02C7/266 , F23R2900/03042
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：US11808456B2
公开(公告)日：2023-11-07
申请号：US17431254
申请日：2020-02-19
CPC分类号： F23R3/283 , F02C3/00 , F23R3/50 , F23R3/60 , F05D2220/32 , F05D2230/60 , F05D2240/35 , F23R2900/00017
摘要： A combustion chamber includes a bottom wall having at least one opening, at least one sleeve mounted upstream of the bottom wall and fixed to the bottom wall, a closing ring defining an annular groove with the sleeve and fixed to the sleeve, and at least one air and fuel injection system having an axis, mounted in the opening of the bottom wall. The injection system has an annular flange extending radially with respect to the axis and is mounted in the groove with radial clearance. A baffle is situated downstream of the bottom wall and is fixed to the sleeve and/or to the bottom wall.
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公开(公告)号：US11781753B2
公开(公告)日：2023-10-10
申请号：US17809629
申请日：2022-06-29
CPC分类号： F23R3/60 , F23M5/04 , F23R3/002 , F23R3/50 , F23R2900/00014 , F23R2900/00017 , F23R2900/03044
摘要： A combustor for a gas turbine includes a dome, and a deflector connected to the dome to define a baffle cavity therebetween, the deflector having a deflector cold side adjacent to the baffle cavity and a deflector hot side adjacent to a combustion chamber. At least one dome-deflector connecting member connects the dome and the deflector to each other. The dome-deflector connecting member forms a flexible joint between the dome and the deflector.
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公开(公告)号：US20230304665A1
公开(公告)日：2023-09-28
申请号：US18302346
申请日：2023-04-18
发明人： Ajoy Patra , Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , R Narasimha Chiranthan , Manampathy G. Giridharan , Michael A. Benjamin , Clayton S. Cooper
CPC分类号： F23R3/286 , F02C7/264 , F23D14/64 , F23R3/045 , F23R3/50 , F05D2240/35 , F05D2260/99 , F23D2207/00
摘要： A method of supplying a first fuel and air mixture and a second fuel and air mixture to a combustor. The combustor having a combustion chamber, a dome wall at least partially defining the combustion chamber, at least one fuel cup provided in the dome wall, and at least one ignition tube having an outlet exhausting to the combustion chamber. The method comprising supplying a first flow of compressed air to only the at least one ignition tube, igniting the first fuel and air mixture, supplying the first ignited fuel and air mixture of the combustion chamber, and supplying a second flow of fuel and a second flow of compressed air to the at least one fuel cup.
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公开(公告)号：US20220275941A1
公开(公告)日：2022-09-01
申请号：US17630284
申请日：2020-07-27
摘要： A combustion chamber for an aircraft turbomachine includes an annular chamber end wall structure, an annular row of main injection systems mounted in the chamber end wall structure and configured to deliver a sheet of fuel, including a central recirculation region and a corner recirculation region around the central recirculation region, and secondary injection systems each configured to inject an additional flow of air and fuel directly into a corresponding corner recirculation region.
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