发明名称 Turbine or compressor stage of a jet engine
摘要 The stage has a rotor disk mounted inside a sectorized ring supported by a casing (116) and comprising a circumferential flange (132) radially clamped on an annular rail of the casing by a C-shaped cross-section annular locking device (138). The device is engaged on a casing rail (136) and on the flange, comprises a cylindrical heat shielding foil (146) interposed between the ring and an inner wall (142) of the device, where extra thickness of the foil and the inner wall are radially extended towards the device and the foil, respectively, and includes a radial bearing unit on the device.
申请公布号 EP2060751(A1) 申请公布日期 2009.05.20
申请号 EP20080168315 申请日期 2008.11.04
申请人 SNECMA 发明人 AUDEON, DAVID;DA SILVA, DAVID
分类号 F01D25/24;F01D11/08 主分类号 F01D25/24
代理机构 代理人
主权项
地址