Rolls-royce Corporation

John Hoptroff

Peter Broadhead

Alan Robert Maguire

Peter Avery

A cooling system for a gas turbine engine (FIG.) comprises a pre-swirl arrangement, preferably including a pre-swirl chamber, for providing cooling air to a turbine blade disc, and a ventilation arrangement for providing ventilation air to a rotating component of the gas turbine engine. The cooling system includes an air bypass arrangement, which preferably includes first, second and third air bypass duct portions, for conveying ventilation air away from the pre-swirl arrangement.

Cooling system for a gas turbine engine

A retaining arrangement for joining together two components such as a rim coverplateand a rotor discin a gas turbine engine. The arrangement comprising a channelformed by respective formationson the discand coverplate, which channellocates one or more annular ring memberwhich prevents relative axial movement therebetween. Engageable abutment formationsare provided respectively on the discand coverplate, to prevent relative pivotal movement.

Retaining arrangement

A gas turbine engine rotor disc (20) is provided with a plurality of cooling air supply passages (32) which are generally radially extending but are inclined in the downstream direction. Each passage (32) has a cross-sectional configuration which renders the ends (34) of the passages (32) less likely than normal to act as the site of hoop-stress induced cracks.

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Derby, United Kingdom

John Hoptroff