| 摘要 |
#CMT# #/CMT# The device has a cylindrical shell (148) made of sheet iron, and with an upstream end fixed to an exhaust case. The shell has a downstream end supported on an annular stiffener of a trim of the case in a sealed manner. The downstream end has slits (156) parallel to an axis of the case and delimits longitudinal blades (158) between them. The blades are supported on the stiffener and are freely deformable in radial direction under an effect of differential thermal dilatation between the case and the trim. #CMT#USE : #/CMT# Used in a turbomachine such as jet engine or turbo-prop of an aircraft, for ventilating an exhaust case of the turbomachine (all claimed). #CMT#ADVANTAGE : #/CMT# The blades are freely deformable in radial direction under the effect of differential thermal dilatation between the case and the trim, thus preserving the sealing between the shell and the stiffener without generating high constraints in the stiffener, and hence increasing the life duration of the stiffener. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows an axial sectional partial schematic view of an exhaust case. 148 : Cylindrical shell 150 : Upstream cylindrical part 152 : Downstream cylindrical part 154 : Conical part 156 : Slits 158 : Blades. |
