-
公开(公告)号：US20240328622A1
公开(公告)日：2024-10-03
申请号：US18736704
申请日：2024-06-07
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
CPC classification number: F23R3/002 , F02C7/22 , F23R3/28 , F05D2220/323
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
-
公开(公告)号：US12104794B2
公开(公告)日：2024-10-01
申请号：US18226978
申请日：2023-07-27
Applicant: ROLLS-ROYCE plc
Inventor： Frederic Witham
CPC classification number: F23R3/283 , F23R3/002 , F23R2900/00005 , F23R2900/00012 , F23R2900/03042 , F23R2900/03043
Abstract: A combustor assembly for gas turbine engine, combustor assembly including: combustor wall including interior surface and combustor wall opening, wherein interior surface partially defines combustion chamber, wherein combustor wall opening extends between combustion chamber and its exterior; sealing element disposed partially within combustor wall opening and includes air inlet, air outlet and air passageway, wherein air outlet exits into combustion chamber and delivers flow of air received from exterior of combustion chamber via air inlet and air passageway to combustion chamber; and fuel nozzle coupled to sealing element and configured to deliver fuel into combustion chamber, wherein combustor wall further includes first bearing surface and sealing element further includes second bearing surface, wherein first bearing surface is concave and forms part of first spherical surface such that first and second bearing surfaces are configured to move relative to each other about central point of first spherical surface.
-
公开(公告)号：US20240309805A1
公开(公告)日：2024-09-19
申请号：US18673577
申请日：2024-05-24
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
CPC classification number: F02C3/22 , F02C7/22 , F23R3/002 , F23R3/286 , F05D2220/323 , F05D2240/35
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
-
公开(公告)号：US20240308924A1
公开(公告)日：2024-09-19
申请号：US18678649
申请日：2024-05-30
Applicant: RTX Corporation
Inventor： Olivier H. Sudre
IPC: C04B35/80 , C04B35/628 , C04B35/65 , C04B35/657 , F01D5/28 , F01D9/02 , F01D11/00 , F23R3/00
CPC classification number: C04B35/80 , C04B35/62863 , C04B35/62884 , C04B35/652 , C04B35/657 , F01D5/284 , F01D9/02 , F01D11/00 , F23R3/002 , C04B2235/3826 , C04B2235/5244 , C04B2235/5252 , C04B2235/614 , C04B2235/616 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2240/55 , F05D2300/20
Abstract: A method for making a ceramic matrix composite component includes densifying a fibrous preform of the component with a ceramic matrix to form an intermediate component; infiltrating a hole in the intermediate component with an infiltrate material comprising a solid and a metallic alloy whose reaction forms a carbide, silicide, boride or combination thereof, heating the infiltrate material to a temperature in excess of a melting point of the metallic alloy; and sequentially cooling regions of the hole starting from an interior end of the hole to the outer surface of the intermediate component to form a solidified through-thickness reinforcement element. The hole extends in a through-thickness direction and is open to an exterior surface of the intermediate component.
-
公开(公告)号：US20240302043A1
公开(公告)日：2024-09-12
申请号：US18270855
申请日：2021-10-12
Applicant: Siemens Energy Global GmbH & Co. KG
Inventor： Mikael Frejd , Johan Nilsson , Daniel Silfver
Abstract: A combustion section of a gas turbine includes an annular combustion chamber, a burner arrangement upstream of the combustion chamber, an annular compressor diffusor, and an annular combustion casing. The combustion casing has an outer section wall, an upstream section wall, and an inner section wall. The inner section wall extends along the rotor axis and is arranged between the burner arrangement and the compressor diffusor. A shielding is attached to the inner section wall at the side facing the rotor axis with a free space in-between at least. An outer diffusor wall of the compressor diffusor extends in axial direction up to the upstream half of the shielding.
-
Patent Agency Ranking
公开(公告)号：US20240295323A1
公开(公告)日：2024-09-05
申请号：US18660388
申请日：2024-05-10
Applicant: General Electric Company
Inventor： Michael A. Benjamin , Manampathy G. Giridharan
Abstract: A gas turbine engine includes a hydrogen fuel delivery assembly configured to deliver a hydrogen fuel flow, a compressor section configured to compress air flowing therethrough to provide a compressed air flow, and a combustor including a combustion chamber having a burner length and a burner dome height. The combustion chamber is configured to combust a mixture of the hydrogen fuel flow and the compressed air flow. The combustion chamber can be characterized by a combustor size rating between one inch and seven inches. In more detail, the combustion chamber can be characterized by the combustor size rating between one inch and seven inches at a core air flow parameter between two and one half kN and sixty kN, in which the combustor size rating is a function of the core air flow parameter.
-
公开(公告)号：US12078351B2
公开(公告)日：2024-09-03
申请号：US18258356
申请日：2021-12-20
Applicant: SAFRAN HELICOPTER ENGINES
IPC: F23R3/00
CPC classification number: F23R3/005 , F23R3/002 , F23R2900/03043
Abstract: A double wall for an aircraft gas turbine combustion chamber comprising an internal wall which is configured to be in contact with the combustion reaction, and an external wall which is at a distance from the internal wall, comprising a plurality of openings so as to allow the circulation of cooling air streams, outside the external wall, which cool the internal wall. The internal wall being free of perforations to prevent any circulation of a cooling air stream towards the centre of the combustion chamber. The the internal wall comprises a plurality of members projecting towards the external wall, each projecting member comprising a foot portion and a cylindrical head portion with a circular cross-section, the head portion extending into an opening with a circular cross-section so as to define a calibrated cross-sectional area between the projecting member and the opening, through which area a cooling air stream can flow.
-
公开(公告)号：US20240263793A1
公开(公告)日：2024-08-08
申请号：US18346591
申请日：2023-07-03
Applicant: Pratt & Whitney Canada Corp.
Inventor： Tin Cheung John Hu
Abstract: A combustor includes a liner defining a combustion chamber and receiving a fuel and air mixing body. The mixing body has a central fuel supply, and radial distribution passages communicating fuel from the central fuel supply radially outwardly relative to a central axis of the central fuel supply and to mixing passages. The radial distribution passages have injection ports in the mixing passages. The mixing passages extend from a rear face of the mixing body to an inner face facing into the combustion chamber. Air inlets in the mixing body communicate air into the mixing passages, and there is cellular material in the mixing passages at a location at which the fuel is injected into the mixing passages. A gas turbine engine is also disclosed.
-
公开(公告)号：US12038175B2
公开(公告)日：2024-07-16
申请号：US17984159
申请日：2022-11-09
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Timothy S. Snyder , James B. Hoke
Abstract: A combustor may comprise an outer combustor panel and an inner combustor panel radially inward of the outer combustor panel. A bulkhead panel may extend radially between the outer combustor panel and the inner combustor panel. An outer spacer may be located between an outer flange of the bulkhead panel and the outer combustor panel. An inner spacer may be located between an inner flange of the bulkhead panel and the inner combustor panel.
-
公开(公告)号：US20240230093A1
公开(公告)日：2024-07-11
申请号：US18401579
申请日：2023-12-31
Applicant: GE Infrastructure Technology LLC
Inventor： Michael John Hughes , Jonathan Dwight Berry , Homayoon Feiz
Abstract: A combustor for a gas turbine engine includes a head end section containing a fuel nozzle assembly and a liner extending downstream from the head end section to an aft frame and defining a combustion chamber therein. First injectors, disposed at a first axial location, directs a first fuel/air mixture through the liner. Second injectors, disposed at a second downstream axial location, direct a second fuel/air mixture through the liner. A compressor discharge casing, which at least partially surrounds the combustor, defines a plenum from which a first air supply is directed only to the first injectors, a second air supply is directed only to the second injectors, and a third air supply is directed only to the head end section. The second air supply is greater than each of the first air supply and the third air supply.
-
-
-
-
-
-
-
-
-
Search Results
2387
records
(took 0.024 seconds)
