COMPRESSOR SHROUD REVERSE BLEED HOLES

摘要

A gas turbine engine compressor includes a rotor defining a central axis of rotation and a plurality of blades which project into an annular compressor gas flow passage, and a shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips. Bleed holes extend through the shroud adjacent the blade tips, each of the bleed holes having an inlet end disposed in the shroud radially inner surface and an outlet end disposed in a shroud radially outer surface. Bleed air removed from the annular gas flow passage flows through the bleed holes from the inlet to the outlet ends. The outlet end of each bleed hole is located circumferentially upstream of the inlet end relative to a direction of rotational flow in the annular gas flow passage driven by a direction of rotation of the rotor.

主权项

1. A compressor for a gas turbine engine comprising:
a rotor having hub defining a central axis of rotation and a plurality of blades radially extending from the hub to project into an annular gas flow passage of said compressor, each of said blades having a remote blade tip and a leading edge defined between opposed pressure and suction surfaces, said rotor being rotatable about said axis of rotation; an annular shroud circumferentially surrounding the rotor and having a radially inner surface adjacent to the blade tips, the inner surface of the shroud facing said annular gas flow passage; and a plurality of bleed holes extending through said shroud adjacent said blade tips, the bleed holes providing gas flow communication between said annular gas flow passage and a region outside the shroud, each of said bleed holes having an inlet end disposed in the radially inner surface of the shroud adjacent the blade tips to communicate with the annular gas flow passage, each of said bleed holes having an outlet end disposed in a radially outer surface of the shroud, bleed air removed from the annular gas flow passage by the bleed holes flowing from the inlet end to the outlet end of the bleed holes, the outlet end of each of said bleed holes being located circumferentially upstream of the inlet end thereof relative to a direction of rotational flow in the annular gas flow passage driven by a direction of rotation of the rotor.