GAS TURBINE ENGINE COMPRESSOR Russian patent published in 2002 - IPC

FIELD: mechanical engineering; gas turbine engines of aircraft and ground applications. SUBSTANCE: protective lip is made in compressor of gas turbine engine with wearing coating of inner surface of stator working ring. This lip is made integral with working ring from side of compressor input out of the zone possible contact with working blade. Δ1 = 0,1...0,3δ, Δ2 = 0,6...2δ, where δ is radial clearance between peripheral end face of compressor working blade feather and inner surface of wearing coating of working ring; Δ1 is height of projection of wearing coating or working ring into compressor passage; Δ2 is depth of sinking of wearing coating into working ring. EFFECT: increased efficiency of engine owing to decreased erosive wear of compressor working ring. 2 dwg