Burner for a gas turbine
A technology of gas turbines and burners, which is applied in the directions of combustion chambers, combustion methods, combustion equipment, etc., can solve the problems of reducing the efficiency of gas turbines, etc.
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[0023] figure 1 One example of gas turbine engine 10 is shown in cross-section. Gas turbine engine 10 includes an inlet 12 , a compressor section 14 , a combustor section 16 , and a turbine section 18 in a flow sequence generally arranged in flow sequence and generally about and in the direction of a longitudinal or rotational axis 20 . Gas turbine engine 10 also includes a shaft 22 rotatable about an axis of rotation 20 and extending longitudinally through gas turbine engine 10 . Shaft 22 drivingly connects turbine section 18 to compressor section 14 .
[0024] In operation of gas turbine engine 10 , air 24 drawn through air inlet 12 is compressed by compressor section 14 and delivered to combustion section or combustor section 16 . As part of the compression process, the air temperature typically increases from ambient to about 400-400°C as the air pressure increases. The combustor section 16 includes a combustor plenum 26 , one or more combustion chambers 28 and at least...
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