Patent ID: 8337146
Filing Date: 2012-12-25
Classification: F01D,F04D,F05D

Abstract:
1. A compressor for a gas turbine engine, comprising a shroud surrounding a rotor having a plurality of radially extending blades mounted for rotation about a central axis of the engine, each blade having leading and trailing edges and a tip, said shroud having an inner surface surrounding the tip of the blades, a plurality of axially spaced-apart circumferential grooves defined in said inner surface of the shroud adjacent said tips, at least some of the grooves being disposed axially between the leading and trailing edges of the blades, and a plurality of circumferentially spaced-apart recessed baffles projecting from a bottom surface of each groove to a distance less than a full height of the groove, wherein each recessed baffle has a substantially flat top surface bounded in a circumferential direction by a pair of fillets merging with the bottom surface of the grooves.