发明名称 |
TRANSIENT GAS TURBINE ENGINE BLEED CONTROL SYSTEM |
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 |
IL76568(A) |
申请公布日期 |
1991.01.31 |
申请号 |
IL19850076568 |
申请日期 |
1985.10.04 |
申请人 |
UNITED TECHNOLOGIES CORP. |
发明人 |
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分类号 |
F02C9/18;F04D27/02;(IPC1-7):F02C9/52 |
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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