发明名称 Fast acting aircraft engine bleed air check valve
摘要 <p>An engine air supply system includes an air source, which is a gas turbine engine in one example. A component, such as an environmental control system component, is interconnected to the air source by a conduit (24) that includes a supply flow direction (B). A check valve (20) is arranged in the conduit. The check valve includes first and second hemi-elliptical valve portions (32, 34) moveable in the supply flow direction from a closed position (C) to an open position (O). The closed position is arranged at an acute angle (A) relative to the supply flow direction. The first and second valve portions are non-planar and arranged approximately 90 degrees apart when in the closed position (C). The first and second valve portions move toward one another from the closed position to the open position (O). Each of the first and second valve portions moves approximately 30-40 degrees from the open position to the closed position in response to a stall condition, which significantly reduces the response time and forces generated by the first and second valve portions when closing. </p>
申请公布号 EP1988315(A3) 申请公布日期 2011.03.02
申请号 EP20080251395 申请日期 2008.04.10
申请人 HAMILTON SUNDSTRAND CORPORATION 发明人 ELDER, JAMES;ADAMS, JOSHUA
分类号 F16K15/03;F16K24/04 主分类号 F16K15/03
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