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公开(公告)号：US20240309811A1
公开(公告)日：2024-09-19
申请号：US18121503
申请日：2023-03-14
CPC分类号： F02C3/305 , F02C3/30 , F02C7/18 , F23R3/10 , F23R2900/03044
摘要： An assembly is provided for a turbine engine. This assembly includes a housing, a combustor and a steam system. The housing includes an air plenum. The combustor is disposed within the air plenum. The combustor includes a combustion chamber and a combustor wall between the combustion chamber and the air plenum. The steam system includes a steam injector arranged within the air plenum next to the combustor wall. The steam system is configured to inject steam out of the steam injector and into the air plenum to impinge against the combustor wall.
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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：US11927349B2
公开(公告)日：2024-03-12
申请号：US17812897
申请日：2022-07-15
发明人： Vijayaraj Sukumar , Perumallu Vukanti , Pradeep Naik , Ajoy Patra , Karthikeyan Sampath , Rimple Rangrej , Hiranya Nath , Krishnendu Chakraborty , Narasimhan S. Sahana , Saket Singh , Ravindra Shankar Ganiger
CPC分类号： F23R3/002 , F23R3/60 , F23R3/04 , F23R3/10 , F23R2900/00017 , F23R2900/03045
摘要： A deflector assembly for a combustor defining an operational fluid flow. The deflector assembly includes an upstream surface and a downstream surface opposite the upstream surface. One or more fastening mechanisms each extends through the deflector assembly. One or more cooling holes extend through the deflector assembly from the upstream surface to the downstream surface. The one or more cooling holes are located about the one or more fastening mechanisms to operably direct cooling air about the one or more fastening mechanisms at the downstream surface.
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公开(公告)号：US20240077026A1
公开(公告)日：2024-03-07
申请号：US18273090
申请日：2022-02-24
发明人： Ken UGAI , Tetsu KONISHI , Teruhiro MATSUMOTO
CPC分类号： F02C7/18 , F23R3/10 , F05D2260/201
摘要： A cylinder for combustion comprises a barrel having a cylindrical shape, and an air supply pipe. An insertion opening and a plurality of cooling flow paths are formed in the barrel. Collision region flow paths of the plurality of cooling flow paths each have a collision region circumvention flow path part intersecting with a collision gas axis extending in the direction of the flow of combustion gas moving toward a pipe center axis of the air supply pipe. The collision region circumvention flow path parts have an upstream-side direction component from the collision gas axis along the edge of the insertion opening, and have a downstream-side direction component from the collision gas axis along the edge of the insertion opening. No exit is formed in a portion of the collision region circumvention flow path parts within the range of specified angles about the pipe center axis.
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公开(公告)号：US11852345B2
公开(公告)日：2023-12-26
申请号：US17846412
申请日：2022-06-22
申请人： RTX Corporation
CPC分类号： F23R3/10 , C07K16/2863 , F01D9/041 , F04D29/545 , F23R3/005 , C07K2317/31 , C07K2317/622 , C07K2317/626 , F05D2230/60 , F05D2240/12 , F05D2240/35 , F05D2240/55
摘要： A hot fairing structure for a pre-diffuser includes a ring-strut-ring structure that comprises a multiple of hollow struts and a multiple of inlets to a respective diffusion passage, one of the multiple of inlets formed between each one of the multiple of hollow struts located between two diffusion passages.
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公开(公告)号：US11846425B2
公开(公告)日：2023-12-19
申请号：US18098793
申请日：2023-01-19
发明人： Lev A. Prociw , Jason A. Ryon , Jacob Greenfield
摘要： A pilot nozzle for a dual fuel turbine engine includes an inner air circuit, a gaseous fuel circuit radially outward from the inner air circuit, a liquid fuel circuit radially outward from the inner air circuit, an outer air circuit radially outward from the liquid fuel circuit and the gaseous fuel circuit, and a shroud radially outward from the outer air circuit. The shroud is configured to stabilize a pilot re-circulation zone downstream from outlets of the inner and outer air circuits and the liquid and gaseous fuel circuits.
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公开(公告)号：US11725821B2
公开(公告)日：2023-08-15
申请号：US17692273
申请日：2022-03-11
摘要： A fuel nozzle device (100) for injecting liquid fuel into a combustion chamber (52) of a gas turbine engine (10) includes an outer tube (101), a rear end wall (102) closing a base end of the outer tube, a tapered conical tube (104) defining a first air passage (112) therein, and a second air passage (114) having an annular cross section jointly with the outer tube, a fuel passage (108) axially passed through the rear end wall, and leading to a fuel ejection port (109) directed toward an inner circumferential surface of a base end of the conical tube, a first air introduction passage (111) passed through the outer tube to communicate with the first air passage, and a second air introduction passage (113) passed through the outer tube to communicate with the second air passage.
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公开(公告)号：US11619387B2
公开(公告)日：2023-04-04
申请号：US15221373
申请日：2016-07-27
摘要： A liner for a combustor includes a support member, an intermediate member, and a liner member. The intermediate member is positioned intermediate the support member and the liner member and has a plurality of protrusions and a plurality of recesses. The support member is coupled to the intermediate member at a tangent of each protrusion. Additionally, the liner member is comprised of a ceramic matrix composite material. The liner member is coupled to the intermediate member at a tangent of each recess.
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公开(公告)号：US11585275B2
公开(公告)日：2023-02-21
申请号：US17193390
申请日：2021-03-05
发明人： Jason A. Ryon , Lev A. Prociw , Gregory A. Zink , Joseph Samo
摘要： A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.
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公开(公告)号：US11543130B1
公开(公告)日：2023-01-03
申请号：US17360207
申请日：2021-06-28
申请人： Delavan Inc.
摘要： An injection system includes an inner nozzle body defining a first air path along a longitudinal axis. The first air path defines a converging-diverging section between an upstream portion of the first air path and an outlet orifice of the first air path. A main orifice is defined at a narrowest portion of the converging-diverging section. A fuel circuit wall is outboard of the inner nozzle body. A fuel path is defined between the fuel circuit wall and the inner nozzle body. An outer nozzle body outboard of the fuel circuit wall has a second air path defined through the inner nozzle body for communication of air from the outer nozzle body into the first air path, wherein the second air path meets the first air path at a second orifice in the first air path downstream of the main orifice of the inner nozzle body.
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