发明名称 |
TRANSIENT GAS TURBINE ENGINE BLEED CONTROL |
摘要 |
<p>Flexibility in the control of the compressor bleed valve is of the type utilized in a twin spool axial flow engine for preventing compressor surge is manifested by electronically summing an approximated rate of change of burner pressure that has a first order time constant introduced to actual burner pressure and a burner pressure limit that is scheduled as a function of corrected high pressure compressor speed and the altitude of the aircraft. The signal may be treated by a hysteresis circuit to stabilize the bleed valve.</p> |
申请公布号 |
EP0187114(B1) |
申请公布日期 |
1990.06.20 |
申请号 |
EP19850630179 |
申请日期 |
1985.10.31 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
KENISON, DAVID FRANCIS;LYNN, DAVID GOWER |
分类号 |
F02C9/18;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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