CPC F01D 25/24 (2013.01) [F05D 2220/323 (2013.01); F05D 2220/76 (2013.01); F05D 2230/60 (2013.01); F05D 2300/133 (2013.01); F05D 2300/17 (2013.01)] | 19 Claims |
1. An aircraft engine, comprising:
a casing extending circumferentially around a central axis;
a support flange secured to the casing and extending circumferentially around the central axis, the support flange having an inner flange face facing the central axis and an outer flange face facing away from the central axis, the support flange including a first material, the support flange defining a flange recess and a flange protrusion axially offset from the flange recess, the flange recess located radially inwardly of the outer flange face, the flange protrusion protruding radially outwardly from the outer flange face;
a component drivingly engaged by a shaft of the aircraft engine, the component having a connecting section extending around the central axis, the connecting section having a connecting face facing away from the central axis, the inner flange face in abutment against the connecting face; and
a retaining ring extending circumferentially around the central axis, the retaining ring in abutment against the outer flange face of the support flange, the retaining ring including a second material having a coefficient of thermal expansion being less than that of the first material of the support flange, the retaining ring having a ring protrusion received within the flange recess, the retaining ring having a ring recess axially offset from the ring protrusion and receiving the flange protrusion, the support flange having a sloped recess face in abutment against a sloped protrusion face of the ring protrusion.
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