Gas turbine combustor and operating method thereof

Abstract

A gas turbine combustor has a chamber supplied with fuel (50) and air (16) and a multi-burner (6) having a plurality of burners provided with an air hole plate (31) having a plurality of air holes (32), and fuel nozzles (25) for supplying fuel (50) to the air holes (32) in the air hole plate (31); the multi-burner (6) is made up of a center burner (33) disposed in the center and a plurality of outer burners (37) around the center burner (33), the outer burners (37) are divided into inner fuel nozzles (25) and outer fuel nozzles (25) to separately supply fuel through fuel systems (51 - 54), and the fuel (50) is supplied to the fuel nozzles (25) in the center burner (33) or to the fuel nozzles (25) in the center burner (33) and the inner fuel nozzles (25) in the outer burners (37) disposed around the center burner (33) in a partial load condition in which the load is lower than that of when all the fuel systems (51 - 54) are used to supply fuel (50).

Description

technical field

[0001] The present invention relates to a gas turbine combustor and a method for operating the gas turbine combustor. Background technique

[0002] From the viewpoint of environmental protection, gas turbines are required to further reduce NOx.

[0003] A premix combustor is mentioned as one means for reducing NOx in a gas turbine combustor, but in this case, there is concern about a backfire phenomenon in which flame enters the inside of the premixer.

[0004] Japanese Patent Application Laid-Open No. 2003-148734 discloses a gas turbine combustor comprising a fuel nozzle for supplying fuel to the combustion chamber and an air hole for supplying air located downstream of the fuel nozzle. The nozzle for fuel combustion in which the outlet hole and the air hole are arranged coaxially is constituted, and a gas turbine combustor having both backfire resistance and low NOx combustion is disclosed.

[0005] In addition, Japanese Patent Application Laid-Open No. 2...

Images