Gas turbine overtemperature protection

作者: Gary A. Stone , Charles B. Redpath , Robert T. Legore , George A. White

DOI:

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摘要: Turbine gas temperature, which escalates during a compressor stall, is monitored 46, and compared to set point temperature 52. If the exceeded, valve 36 pulsed discharging fuel from line 24 reducing flow combustor. Open closed intervals are selected reduce flow, but avoid flameout. An additional second 42 operates in similar mode response an even higher temperature. Engine operation continues this protection until stall corrected by whatever means.

参考文章(4)
Hilbert Holzhauer, Christian Greune, Adolf Fehler, Control system for metering the fuel flow in gas turbine engines ,(1970)
Gene A. Meyer, Robert E. Peck, Pulse width modulated fuel metering system ,(1981)
Samuel E Arnett, Harry E Starr, Fuel control apparatus for an internal combustion engine ,(1956)