Patent ID: 6397576
Filing Date: 2002-06-04
Classification: F01D,F02C,F23C,F23D,F23R

Abstract:
A gas turbine engine, said gas turbine engine comprising:a gas turbine engine flow duct; a compressor having a housing which encloses a compressor flow duct having a plurality of flow duct areas, each providing a different compression ratio, said compressor having an inlet and an outlet and a plurality of outlet taps each communicating with a respective area of said plurality of flow duct areas; a turbine mounted downstream of said compressor and having an inlet and an outlet; a heat exchanger having a first inlet and a second inlet and a first outlet and a second outlet; said compressor inlet being connected to said heat exchanger first outlet; said heat exchanger first inlet being connected to said turbine outlet; said heat exchanger second inlet being connected to said compressor outlet; a heated fluid source provided upstream of said turbine; a fuel source connected to said heated fluid source; said heat exchanger second outlet being connected to said heated fluid source; a combustion air supplying means for said gas turbine engine flow duct; an outlet tap switching means having a plurality of positions and selectively opening to the atmosphere one outlet tap of said plurality of outlet taps and disconnecting the rest of said outlet taps of said plurality of outlet taps from the atmosphere in each position of said switching means; and a switching means control for selecting one of said plurality of positions of said switching means.