HYBRID COMPRESSOR BLEED AIR FOR AIRCRAFT USE

摘要

A gas turbine engine comprises at least two compressor rotors, including a first lower pressure compressor rotor and a second higher pressure compressor rotor. At least two corresponding air taps include a low tap for tapping low pressure compressor air from a location downstream of a first stage of the lower pressure compressor rotor, and upstream of a first stage of the higher pressure compressor rotor, and a high tap to tap air downstream of the first stage of the higher pressure compressor rotor. an air handling system selectively communicates both the low tap and the high tap to an air use destination. Air is selectively supplied from the low tap to the air handling system at a high power operation and from the high tap to the air handling system at a low power operation.

主权项

1. A gas turbine engine comprising:
at least two compressor rotors, including a first lower pressure compressor rotor and a second higher pressure compressor rotor; at least two corresponding air taps, including: a low tap for tapping low pressure compressor air from a location downstream of a first stage of the lower pressure compressor rotor, and upstream of a first stage of the higher pressure compressor rotor; and a high tap to tap air downstream of said first stage of said higher pressure compressor rotor; an air handling system to selectively communicate both said low tap and said high tap to an air use destination; andwherein air is selectively supplied from the low tap to the air handling system at a high power operation and from said high tap to the air handling system at a low power operation.