System and method for improving combustion stability in gas turbine

摘要

A compressor upstream of the combustor and a gas turbine engine with a turbine downstream of the combustor.The combustor also includes a combustor chamber, an oxyfuel pilot burner (104) centrally positioned at the end of the combustor chamber, and an air fuel premixed burner configured to at least partially mix the air and fuel.The air fuel premix burner surrounds the oxyfuel pilot burner 104 in an annular configuration.Diagram