Compressor cover for turbine engine having axial abutment

Details Compressor cover for turbine engine having axial abutment Compressor cover for turbine engine having axial abutment

F - Mech Eng,Light,Heat,Weapons

04

D

F04D 29/42 (2006.01) F02C 7/04 (2006.01)

Patent

CA 2726905

The invention relates to a centrifugal compressor of a turbine engine, said compressor including a cover having an upstream end and a downstream end (100b), including: - a casing (30) having an upstream edge and a downstream edge (34); - a blade wheel (20) rotatably mounted in said casing, said cover intended to cover the blades of the wheel so as to define an outer surface of a gas stream extending between the upstream and downstream edges of the casing while being attached to the upstream edge of the casing by the upstream end thereof as the downstream end thereof remains free. The invention is characterized in that the cover (100) also comprises an abutment (102) for limiting the axial movement of the downstream end (100b) relative to the downstream edge (34) of the casing when the compressor is operating.

L'invention concerne un compresseur centrifuge d'un turbomoteur, ledit compresseur comprenant un amont et une extrémité aval (100b) : - un carter (30) présentant un bord amont et un bord aval (34), - un rouet à pales (20) monté rotatif dans ledit carter, ledit couvercle étant destiné à couvrir les pales du rouet de façon à définir une surface extérieure d'une veine de gaz s'étendant entre les bords amont et aval du carter, tout en étant fixé au bord amont du carter par son extrémité amont tandis que son extrémité aval demeure libre. L'invention se caractérise par le fait que le couvercle (100) comporte en outre une butée (102) destinée à limiter le déplacement axial de l'extrémité aval (100b) par rapport au bord aval (34) du carter lors du fonctionnement du compresseur.

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