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STALL PROTECTOR SYSTEM FOR A GAS TURBINE ENGINE

  • US 3,852,958 A
  • Filed: 09/28/1973
  • Issued: 12/10/1974
  • Est. Priority Date: 09/28/1973
  • Status: Expired due to Term
First Claim
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1. A stall protector system for a gas turbine engine of the type having a compressor, combustor, turbine and exhaust duct in serial flow relation comprises:

  • means for measuring compressor pressure and providing an electrical output signal corresponding to the actual compressor pressure measured;

    a differentiator for differentiating the output signal from the measuring means and providing an output signal indicative of the rate of change of compressor pressure;

    a slope detector for comparing the rate of change of compressor pressure with a reference rate signal indicative of the maximum rate at which the compressor pressure may be expected to decrease during normal operation;

    an integrator for providing a time integration of the compressor pressure rate when the actual rate of decrease of compressor pressure exceeds the reference rate;

    a pressure detector for comparing the actual change in compressor pressure from the integrator with a second reference signal corresponding to the minimum change in compressor pressure indicative of a compressor stall; and

    means for regulating the flow of fuel to the combustor when the actual change in compressor pressure exceeds the second reference signal.

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