发明名称 |
Gas turbine engine variable bleed pivotal flow splitter |
摘要 |
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
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申请公布号 |
US5279109(A) |
申请公布日期 |
1994.01.18 |
申请号 |
US19930026250 |
申请日期 |
1993.03.04 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
LIU, HSIN-TUAN;HINES, WILLIAM R. |
分类号 |
F02C9/18;F02C7/05;F02C7/052;F04D27/02;F04D29/70;(IPC1-7):F02C6/18;F02G3/00 |
主分类号 |
F02C9/18 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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