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Gas turbine engine controls for minimizing combustion dynamics and emissions

  • US 8,504,276 B2
  • Filed: 02/28/2008
  • Issued: 08/06/2013
  • Est. Priority Date: 02/28/2008
  • Status: Active Grant
First Claim
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1. A method of controlling a gas turbine engine having a compressor, at least one combustor, a turbine, and a control system comprising:

  • measuring a compressor inlet temperature;

    calculating a turbine reference temperature as a function of at least compressor discharge pressure, exhaust pressure, and pressure across the combustor;

    selecting a baseline fuel schedule for a fuel circuit corresponding to the turbine reference temperature;

    determining whether a baseline fuel split corresponds to the turbine reference temperature;

    determining a bias parameter so as to increase or decrease the baseline fuel split wherein the bias parameter is a percentage change in fuel split that varies as a function of the measured compressor inlet temperature for a given turbine reference temperature; and

    ,adjusting the fuel flow for the fuel circuit to a sum of the baseline fuel split and the bias parameter.

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