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STABILIZING A GAS TURBINE ENGINE VIA INCREMENTAL TUNING

  • US 20100300108A1
  • Filed: 05/24/2010
  • Published: 12/02/2010
  • Est. Priority Date: 05/26/2009
  • Status: Active Grant
First Claim
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1. A computerized method, implemented by a processing unit, for automatically tuning a combustor of a gas turbine engine, the method comprising:

  • monitoring one or more operating conditions of the gas turbine engine;

    determining whether the one or more operating conditions have overcome a threshold value; and

    when the threshold value is overcome, adjusting a fuel flow split by a predefined increment, wherein the fuel flow split governs a portion of a total fuel flow that is directed to each fuel nozzle of the combustor'"'"'s fuel circuit.

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