- 专利标题: HEATING SYSTEM FOR CONVERGENT-DIVERGENT SECONDARY NOZZLE
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申请号: US16105159申请日: 2018-08-20
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公开(公告)号: US20200378339A9公开(公告)日: 2020-12-03
- 发明人: Guillaume BODARD , Jeremy Paul Francisco GONZALEZ , Norman Bruno Andre JODET
- 申请人: SAFRAN AIRCRAFT ENGINES
- 申请人地址: FR Paris
- 专利权人: SAFRAN AIRCRAFT ENGINES
- 当前专利权人: SAFRAN AIRCRAFT ENGINES
- 当前专利权人地址: FR Paris
- 优先权: FR1757775 20170821; FR1757777 20170821
- 主分类号: F02K1/34
- IPC分类号: F02K1/34 ; F02K1/38 ; F02K1/48
摘要:
The invention proposes an assembly for a rear of a dual-flow turbomachine (10) having a longitudinal axis (X), comprising: a secondary nozzle (110) defined about the longitudinal axis (X), said secondary nozzle being configured to eject a mixture of the flows coming from a secondary vein (Vs) and a primary vein (Vp) of the turbomachine (10), the secondary nozzle being of convergent-divergent form with a neck (112) corresponding to a minimal cross-cross-section of the secondary nozzle (110), a heating system located on at least one portion of the internal circumference of the secondary nozzle longitudinally in the region of the neck and/or upstream from the neck (112).
公开/授权文献
- US10995702B2 Heating system for convergent-divergent secondary nozzle 公开/授权日:2021-05-04