Invention Grant
- Patent Title: Turbine or compressor stage for a turbojet
- Patent Title (中): 用于涡轮喷气发动机的涡轮机或压缩机级
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Application No.: US12266813Application Date: 2008-11-07
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Publication No.: US08192149B2Publication Date: 2012-06-05
- Inventor: David Audeon , David Da Silva
- Applicant: David Audeon , David Da Silva
- Applicant Address: FR Paris
- Assignee: SNECMA
- Current Assignee: SNECMA
- Current Assignee Address: FR Paris
- Agency: Oblon, Spivak, McClelland, Maier & Neustadt, L.L.P.
- Priority: FR0707939 20071113
- Main IPC: F01D5/20
- IPC: F01D5/20 ; F01D9/00

Abstract:
A turbojet turbine or compressor stage is disclosed. The stage includes at least one rotor disk mounted inside a sectorized ring supported by a casing and including a circumferential flange radially clamped on an annular rail of the casing by a substantially C-shaped cross-section annular locking device which is axially engaged on the casing rail and on the flange of the ring. A substantially cylindrical heat shielding foil is interposed between the ring and the device. The foil or the device includes at least one extra thickness which respectively bears on the device, or the foil, to radially immobilize this foil.
Public/Granted literature
- US20090123273A1 TURBINE OR COMPRESSOR STAGE FOR A TURBOJET Public/Granted day:2009-05-14
Information query
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