Turbine engine with induced pre-swirl at the compressor inlet
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United States of America Patent
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-
Jan 19, 1988
Issued Date -
N/A
app pub date -
Jun 3, 1986
filing date -
Apr 24, 1985
priority date (Note) -
Expired
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Abstract
A jet flap construction for the compressor of an aircraft gas turbine engine provided with a bleed for bleeding air interstage of the compressor and communicating with the hollowed-out struts in the airflow path to the compressor. The hollow struts are each provided with one or more rows of discrete openings extending from the shroud to the hub on the strut to form an aligned series of jets for discharging the pressurized bleed air and forming a jet flap, thereby providing pre-swirl at the compressor inlet.
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