Importance

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Abstract

A gas turbine engine comprises a compressor, an inner casing and a turbine arranged to drive the compressor via a shaft. The compressor comprises a rotor and a stage of compressor outlet guide vanes. The stage of vanes comprises a plurality of vanes extending radially between inner and outer annular walls. The rotor has a stub shaft and the shaft is joined to the stub shaft at a welded joint. The inner casing surrounds the shaft and stub shaft to define an annular chamber and an annular bleed duct is defined between the upstream end of the wall of the stage of vanes and the downstream end of the compressor rotor. The upstream end of the wall of the stage of vanes has a concave surface between its radially inner and radially outer ends to produce a counter clockwise flow of air over the welded joint.

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First Claim