Gas turbine engine variable bleed pivotal flow splitter or flap valve

摘要

A plurality of pivotal flow splitters 30 between compressor sections 22, 24 are provided to bleed off air flow and remove particles, particularly ice in the case of an aircraft fan-jet gas turbine engine, by pivoting the leading edge 31 of the splitter 30 into the compressor flow thereby using the total pressure of the flow to drive blood flows overboard and remove particles. In the preferred embodiment the pivotal flow splitter is integral with a booster variable bleed valve (VBV) door 30 and includes a booster bleed duct means 18 having a bellmouth shaped inducer type inlet 48 to enhance the capture of compressor flow and particle removal.