Patent ID: 10495111

Abstract:
A compressor stage of a gas turbine engine is provided. The compressor stage has a circumferential row of static vanes and a radially outer casing. Each vane has a radially outer and forwardly projecting front tenon which on build of the compressor stage is received into a first recess of the casing. Each vane also has a radially outer and rearwardly projecting rear tenon which on build of the compressor stage is received into a second recess of the casing. Each vane further has a baulking tab adjacent one of the front and the rear tenons. The casing has a respective baulking land adjacent the recess into which the other of the front and the rear tenons is received. The baulking tab and the baulking land are configured such that if the vane is attempted to be installed in the stage back-to-front, the baulking tab interferes with the baulking land to prevent completion of the build of the compressor stage.