发明名称 |
Dual valve apparatus for aircraft engine ice protection and related methods |
摘要 |
A thermal anti-ice system in an aircraft. A controlled valve receives air from a compressor bleed port of an engine of the aircraft. A self-regulating valve is fluidly connected between the controlled valve and an inlet of the engine. A first pressure sensor senses pressure between the valves. A second pressure sensor senses pressure between the self-regulating valve and the inlet. The system can be used to de-ice aircraft inlet lip skins made of composite materials that have comparatively lower design temperatures than other comparable materials.
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申请公布号 |
US7959109(B2) |
申请公布日期 |
2011.06.14 |
申请号 |
US20080167164 |
申请日期 |
2008.07.02 |
申请人 |
THE BOEING COMPANY |
发明人 |
DASILVA OLUBUSOLA ANTHONY;CONN HEATH ALAN;LANGHOFER ERIK MARC;EL-GABALAWY HOSAM EL DIN;DIRUSSO JOSEPH M. |
分类号 |
B64D15/04 |
主分类号 |
B64D15/04 |
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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