Compressor Stall Warning System.
DEPARTMENT OF THE NAVY WASHINGTON D C
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This patent describes a compressor stall warning system for jet aircraft gas turbine engines. The turbine inlet temperature and the compressor rotor speed are monitored and signals representative of the ratio of these two functions and the inlet temperature itself are produced. If the turbine inlet temperature increases while the compressor rotor speed decreases their ratio would increase rapidly. When either this ratio or the turbine inlet temperature alone increase beyond predetermined thresholds, a signal is furnished to the aircraft pilot warning him of impending aircraft engine stall. Author
- Flight Control and Instrumentation