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Utilizing a diluent to lower combustion instabilities in a gas turbine engine

  • US 9,017,064 B2
  • Filed: 06/08/2010
  • Issued: 04/28/2015
  • Est. Priority Date: 06/08/2010
  • Status: Active Grant
First Claim
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1. A method of influencing combustion dynamics, comprising:

  • measuring pressure oscillations within a combustor; and

    controlling a non-fuel diluent flow that is delivered only to a fuel flow upstream of a pilot burner fuel outlet in response to the measured pressure oscillations,wherein the controlling occurs independent of control of a flow of fuel to an associated premix main burner,wherein the associated premix main burner is one of a plurality of premix main burners disposed in an annular array surrounding the pilot burner, andwherein the plurality of premix main burners and the pilot burner are disposed within the combustor and are effective to create a single combustion flame comprising a pilot flame formed by the pilot burner.

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