发明申请
US20120134788A1 LOW PRESSURE TURBINE FOR AN AIRCRAFT TURBOMACHINE, COMPRISING A SEGMENTED NOZZLE WITH AN IMPROVED DESIGN
有权
用于飞机涡轮机的低压涡轮机，包括具有改进设计的分段喷嘴
- 专利标题： LOW PRESSURE TURBINE FOR AN AIRCRAFT TURBOMACHINE, COMPRISING A SEGMENTED NOZZLE WITH AN IMPROVED DESIGN
- 专利标题（中）： 用于飞机涡轮机的低压涡轮机，包括具有改进设计的分段喷嘴
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申请号： US13300981申请日： 2011-11-21
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公开(公告)号： US20120134788A1公开(公告)日： 2012-05-31
- 发明人: Jean-Claude Christian TAILLANT , Alain Dominique Gendraud
- 申请人： Jean-Claude Christian TAILLANT , Alain Dominique Gendraud
- 申请人地址： FR Paris
- 专利权人： SNECMA
- 当前专利权人： SNECMA
- 当前专利权人地址： FR Paris
- 优先权： FR1059946 20101130
- 主分类号： F04D29/58
- IPC分类号： F04D29/58
摘要：
The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).
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