- Patent Title: Injection system for a turbine engine annular combustion chamber
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Application No.: US17049442Application Date: 2019-04-10
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Publication No.: US11268699B2Publication Date: 2022-03-08
- Inventor: Sébastien Alain Christophe Bourgois , Romain Nicolas Lunel , Haris Musaefendic
- Applicant: SAFRAN AIRCRAFT ENGINES
- Applicant Address: FR Paris
- Assignee: SAFRAN AIRCRAFT ENGINES
- Current Assignee: SAFRAN AIRCRAFT ENGINES
- Current Assignee Address: FR Paris
- Agency: Christensen O'Connor Johnson Kindness PLLC
- Priority: FR1853573 20180424
- International Application: PCT/FR2019/050839 WO 20190410
- International Announcement: WO2019/207230 WO 20191031
- Main IPC: F23R3/00
- IPC: F23R3/00 ; F23R3/14 ; F02C7/22 ; F23R3/28

Abstract:
An injection system for a turbine engine annular combustion chamber includes a support configured to support and to center a fuel injector head. The support includes a frustoconical surface connected at its downstream end of smallest diameter to an upstream end of a cylindrical surface. The system further includes a bowl configured to mix air and fuel arranged downstream of the support and at least one axial swirl inducer extending at least in part around the support. Each swirl inducer includes vanes delimiting between them substantially axial channels for the passage of an air flow. The channels open at their upstream ends on said frustoconical surface.
Public/Granted literature
- US20210262665A1 INJECTION SYSTEM FOR A TURBINE ENGINE ANNULAR COMBUSTION CHAMBER Public/Granted day:2021-08-26
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