Bleed system for a compressor stage of a turbine engine and corresponding component for use in a turbine engine

摘要

The present invention relates to a bleed system for use in a gas turbine engine. The bleed system comprises a plurality of blades 10 with each of the blades 10 having an airfoil member 14 and a platform structure 16. The bleed system further has at least one interblade passage 12 formed by adjacent ones of the airfoil members 14 and an inner endwall 18 formed by the platform structures 16. A bleed hole 30 is located in the at least one interblade passage 12 for extracting a portion of a fluid passing therethrough. The bleed positioning within the stator passage, both axially and circumferentially, is selected for optimum balance of static pressure and tangential velocity.