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US 9,017,064 B2Granted
Utilizing a diluent to lower combustion instabilities in a gas turbine engine
AssigneeSiemens Energy, Inc.
InventorSamer P. Wasif
Life of this patent
Estimating the term…
Abstract
A method of influencing combustion dynamics, including measuring a combustion dynamics parameter, and controlling a diluent flow (26) delivered to a fuel flow (32) upstream of a pilot burner fuel outlet (40) in response to the measured combustion dynamics parameter.
Claims19
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, and
- wherein 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.
3 more elements
A method of influencing combustion dynamics in a gas turbine engine, comprising:
- monitoring a combustor for a combustion dynamics parameter associated with pressure oscillations;
- and
- adjusting a pilot flame parameter in response to the combustion dynamics parameter by controlling a non-fuel diluent flow into a fuel flow and delivering a combined flow only to a pilot flame through a pilot burner fuel outlet, wherein the controlling of the non-fuel diluent flow 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, and
- wherein 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.
2 more elements
A method of influencing combustion dynamics in a combustor of a gas turbine engine, the combustor including premix main burners disposed in an annular array around a diffusion pilot burner, the method comprising:
- monitoring a pressure-oscillation related combustion dynamics parameter, and
- controlling a flow of a diluent delivered to a fuel flow dedicated to a pilot burner but not to a fuel flow dedicated to the premix main burners in response to the combustion dynamics parameter,
- wherein the controlling occurs independent of control of a flow of fuel to the premix main burners and a control of a flow of fuel to the pilot burner,
- wherein the diluent contributes no energy to a pilot flame associated with the pilot burner, and
- wherein the premix main burners are disposed in an annular array surrounding the pilot burner and are effective to create a single combustion flame comprising a pilot flame formed by the pilot burner.
2 more elements
Dependencies are inferred from the claim text.