Patent ID: 6325595
Filing Date: 2001-12-04
Classification: F01D,F04D

Abstract:
A compressor air bleed assembly for a gas turbine engine comprising:a compressor casing for surrounding a row of circumferentially spaced compressor blades extending from a rotatable shaft and defining a flowpath for receiving compressor airflow compressed by said blades;said casing including a bleed port disposed downstream of at least a row of said blades for receiving a portion of said compressed air as bleed airflow;a bleed duct extending away from said bleed port, said bleed duct having a first throat downstream of said port and a second throat downstream of said first throat;a first duct outlet in said duct leading to a first bleed air circuit, said first duct outlet for receiving a first portion of said bleed airflow, and said first duct outlet disposed between said first and second throats; anda second duct outlet in said duct leading to a second bleed air circuit, said second duct outlet for receiving a second portion of said bleed airflow, and said second duct outlet disposed downstream of said second throat.