Patent ID: 8192149
Filing Date: 2012-06-05
Classification: F01D,F05D,Y02T,Y10T

Abstract:
1. A turbine or compressor stage for a turbojet, comprising: at least one rotor disk mounted inside a sectorized ring supported by a casing and comprising 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 and which comprises two annular walls, respectively inner and outer, connected together through a substantially radial wall, a substantially cylindrical heat shielding foil being interposed between the ring and the inner wall of the device, wherein the foil comprises at least one annular protuberance which is formed in a protruding manner on an outer surface of the foil and which extends on 360° around an axis of the foil, said annular protuberance having radial bearing means on the inner wall of the locking device.