Gas turbine engine variable bleed pivotal flow splitter

Details Gas turbine engine variable bleed pivotal flow splitter Gas turbine engine variable bleed pivotal flow splitter

1993-03-04

1994-01-18

Bertsch, Richard A.

Power plants

Combustion products used as motive fluid

60 39092, F02C 618, F02G 300

Patent

active

052791092

ABSTRACT:
The present invention provides a gas turbine engine with a circumferentially disposed plurality of pivotal flow splitters between compressor sections to bleed off flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine engine, by pivoting the leading edge of the splitter into the compressor flow thereby using the total pressure Q of the flow to drive bleed flows overboard and remove particles. In the preferred embodiment the pivotal flow splitter is integral with a booster variable bleed valve (VBV) door, and includes a booster bleed duct means having a bellmouth shaped inducer type inlet to enhance the capture of compressor flow and particle removal

REFERENCES:
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patent: 3979903 (1976-09-01), Hull, Jr. et al.
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patent: 5044153 (1991-09-01), Mouton
patent: 5119625 (1992-06-01), Glowacki
patent: 5123240 (1992-06-01), Frost et al.
"Energy Efficient Engine Preliminary Design and Integration Studies", Final Report by General Electric, Sep., 1978 pp. 153,155,158,159, and 161.

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