Patent ID: 8490409

Claim:
A bleed air system for directing bleed air from a compressor section of a gas turbine engine, the bleed air system comprising: a cylindrical adaptor in fluid communication with the compressor section, the adaptor having an inner surface; a cylindrical conduit defined by an outer cylindrical wall having two opposed open ends for permitting fluid passage therethrough, the outer cylindrical wall having a pair of adjacent annular flanges extending radially outwardly in proximity of a respective one of the open ends, the pair of annular flanges defining a circumferential groove between opposed annular side walls thereof and being circumscribed by the cylindrical adaptor; and a non-elastomeric ring received in the circumferential groove, the ring having two opposed annular walls located adjacent a respective one of the two side walls of the flanges, the ring having a radial thickness greater than a depth of the groove such that an outer peripheral portion of the ring protrudes radially from the groove around an entire circumference thereof, the outer peripheral portion having an outer peripheral surface abutting the inner surface of the adaptor and maintaining the adaptor spaced apart from the conduit in proximity of the ring while sealing the conduit within the adaptor, the outer peripheral surface having a curved profile extending between the opposed annular walls along a longitudinal direction configured to provide continuous abutment of the outer peripheral surface on the inner surface irrespective of angular displacement of the cylindrical adaptor relative to the cylindrical conduit, the ring being spaced apart from an inner circumferential surface defining a bottom of the groove along at least a portion of the circumference of the groove such as to create a radial gap permitting relative movement between the ring and the cylindrical conduit.