Turbine engine with induced pre-swirl at the compressor inlet

Details Turbine engine with induced pre-swirl at the compressor inlet Turbine engine with induced pre-swirl at the compressor inlet

1986-06-03

1988-01-19

Garrett, Robert E.

Rotary kinetic fluid motors or pumps

With means for re-entry of working fluid to blade set

Cross flow runner

415DIG1, 416 97R, F01D 112

Patent

active

047202351

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.

REFERENCES:
patent: 1970435 (1934-08-01), Shapp
patent: 2808197 (1957-10-01), Forgo
patent: 2944729 (1960-07-01), Foley et al.
patent: 3433015 (1969-03-01), Sneeden
patent: 4066552 (1978-01-01), Caine
patent: 4222703 (1980-09-01), Schaum et al.
patent: 4357914 (1982-11-01), Hauser
patent: 4403917 (1983-09-01), Laffitte et al.
patent: 4456428 (1984-06-01), Cuvillier
patent: 4462754 (1984-07-01), Schofield

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