Patent ID: 6109868
Filing Date: 2000-08-29
Classification: F01D,F04D,Y02T

Abstract:
A compressor for a gas turbine engine, said compressor comprising:a stator comprising a plurality of stator vanes assemblies, each said assembly comprising a stator vane and a stator vane platform, said stator further comprising a stator casing supporting said stator vane assemblies, said stator casing comprising a first portion and a second portion, an annular slot extending substantially around said stator casing and positioned between said stator casing first portion and said stator casing second portion, said stator vane platforms forming a smoothed and rounded entrance corner and a portion of a first wall of said annular slot, a partition extending into said annular slot and configured to reduce circumferential airflow to said annular slot; anda rotor comprising a plurality of rotor blades configured to rotate with respect to said stator vanes.