发明名称 |
ENGINE SURGE PREVENTION SYSTEM |
摘要 |
<p>A surge prevention system for a fan jet engine of an aircraft serves to manifest a signal whenever pressure distortions at the engine's inlet is calculated by judiciously located total pressure probes mounted downstream of the fan on the fan struts in the fan discharge duct. The engine's bleed valve is automatically opened to prevent surge and the fuel control's speed sensor is automatically reset to compensate for any loss of thrust. Safety switches are included to render the system inoperative whenever the aircraft is in the margin of stall and the reset feature is rendered inoperative for normal bleed open operating conditions.</p> |
申请公布号 |
GB8505820(D0) |
申请公布日期 |
1985.04.11 |
申请号 |
GB19850005820 |
申请日期 |
1985.03.06 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
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分类号 |
F02C9/18;F02C9/28;F02C9/52;F04D27/02 |
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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