公开(公告)号：US11971174B2

公开(公告)日：2024-04-30

申请号：US17610893

申请日：2020-05-14

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Dan-Ranjiv Joory ,  Jacques Marcel Arthur Bunel ,  Benjamin Frantz Karl Villenave

IPC: F23R3/50

CPC classification number: F23R3/50 ,  F23R2900/00017

Abstract: 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：US11802512B2

公开(公告)日：2023-10-31

申请号：US17919463

申请日：2021-04-13

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jacques Marcel Arthur Bunel ,  William Louis Rodolphe Dousse ,  Dan-Ranjiv Joory ,  Benjamin Frantz Karl Villenave

IPC: F23R3/60 ,  F02C7/266 ,  F23R3/00 ,  F23R3/50

CPC classification number: F02C7/266 ,  F23R3/002 ,  F23R3/50 ,  F23R3/60 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2260/99

Abstract: The invention relates to a combustion chamber for a gas turbine engine, in which two openings extend through a metal wall (58) and a wall made of a refractory material (16). A device (76) guides a spark plug (48) in said two orifices, the guiding device comprising a metal flange (80) and a floating ring (82), the flange being shrunk onto or welded to the metal wall (58).

公开(公告)号：US11614234B2

公开(公告)日：2023-03-28

申请号：US16476776

申请日：2018-01-04

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jacques Marcel Arthur Bunel ,  Dan-Ranjiv Joory ,  Patrice André Commaret ,  Romain Nicolas Lunel

IPC: F23R3/00 ,  F23R3/60

Abstract: A combustion chamber for a turbine engine, in particular for an aircraft turbojet engine or turboprop engine. The combustion chamber includes a radially outer annular shroud, a radially inner annular shroud coaxial with the radially outer shroud, and an end wall connecting the radially outer shroud and the radially inner shroud. The combustion chamber further includes a first annular sealing member coaxial with said radially inner and outer shrouds. The first annular sealing member is radially interposed between the end wall and the radially outer shroud.

公开(公告)号：US11248793B2

公开(公告)日：2022-02-15

申请号：US16976354

申请日：2019-02-28

Applicant: Safran Aircraft Engines

Inventor： Jacques Marcel Arthur Bunel ,  Dan-Ranjiv Joory

IPC: F23R3/00 ,  F23R3/28 ,  F02C7/232

Abstract: A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.

公开(公告)号：US20210140639A1

公开(公告)日：2021-05-13

申请号：US16976354

申请日：2019-02-28

Applicant: Safran Aircraft Engines

Inventor： Jacques Marcel Arthur Bunel ,  Dan-Ranjiv Joory

IPC: F23R3/28 ,  F02C7/232 ,  F23R3/00

Abstract: A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.