Burner for a gas combustor and a method of operating the burner thereof

Abstract

A burner for a gas combustor and a method of operating the burner are disclosed. The burner includes a front surface area divided into a plurality of subareas and inlets arranged on the front surface area such that each subarea is encircled by at least four inlets and such that during operation of the burner, a gas recirculation in the combustor is facilitated corresponding to each subarea.

Description

FIELD OF INVENTION[0001]The present invention relates to a gas combustor burner particularly arrangement of inlets in the burner which supplies combustible gas to the combustor and its operation for fuel staging.BACKGROUND OF INVENTION[0002]Gas turbines are used to convert heat energy to mechanical energy, for example in power plants. Gas turbines have combustion chambers in which a fuel is burned with air. The combustion chambers of gas turbine plants are supplied with liquid and / or gaseous fuel using burner consisting of one or more nozzle or inlets. The burner can also be used to carry air required for the combustion. For the optimal operation of the gas compressors, stable flames should be formed in the combustion chamber during combustion. Common techniques for flame stabilization include the formation of small eddies or recirculation zones in the combustion chamber. The temperature in the recirculation zone needs to be above a threshold especially at lower load conditions to s...

AI Technical Summary

Benefits of technology

The patent text describes a combustor design for a gas turbine that uses recirculating gas to maintain a stable temperature for combustion. The design includes inlets that create a gas recirculation in smaller subareas around the combustor, which can be staged to supply combustible gas for combustion. The recirculating gas helps to stabilize the flames and maintain the required temperature throughout different load ranges. This design also allows for the use of pre-mixed jet flames, which offer advantages over swirl stabilized systems. Overall, this combustor design improves the stability and efficiency of gas turbines.

Problems solved by technology

A flame will be inherently unstable if the energy release from the combustion is insufficient to raise the temperature to a level at which combustion is self sustaining under conditions of heat loss including radiation to and from the flame and under hot gas recirculation.

The ability to keep a sustainable temperature to maintain combustion at different loads especially at lower loads and simultaneously achieve emission targets is a great challenge in gas turbine operations.

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