CPC F01D 7/02 (2013.01) [F05D 2220/32 (2013.01)] | 19 Claims |
1. A rotor assembly for a gas turbine engine, the rotor assembly comprising:
a disc mounted for rotation about an axis, the disc having a hub, a web extending radially outward from the hub, and a blade attachment at a radially outer diameter of the web;
a coverplate mounted to a forward or an aft facing side of the disc, the coverplate having a primary disc interface and an auxiliary disc interface, the primary disc interface including a radially inner diameter surface in tight fit engagement with a corresponding radially outer diameter surface of the disc, the auxiliary disc interface including a radially outer surface engageable with a surrounding radially inner abutment surface of the disc;
wherein under non-overspeed operating conditions, the radially outer surface of the auxiliary disc interface of the coverplate is spaced by a gap radially inwardly from the surrounding radially inner abutment surface of the disc, and wherein in the event of a rotor overspeed condition, the radially outer surface of the auxiliary disc interface of the coverplate moves outward under the centrifugal force against the surrounding radially inner abutment surface of the disc.
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