A103 ANALYSIS ON EXIT TEMPERATURE PROFILE OF DLN COMBUSTOR FOR 110 MW HEAVY-DUTY GAS TURBINE(Gas Turbine-1)

概要

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Low pressure experiments were performed to better understand the effects of the dilution zone parameters in a DLN combustor on the exit temperature profile. The results show that the temperature uniformity deviates significantly from the design radial profile at full load. Enlargement of the dilution hole size reduces the pattern factor more than the profile factor, but results in a temperature increase near the wall on both sides because of the small circumferential spacing of the dilution holes. Reducing the dilution hole diameter in the lower part of the liner slightly increased the temperature at the blade root. The tests show that the mainstream flow suitably divided is the primary consideration for designing the dilution holes. The main jet holes should be the B holes, not the A holes which do not effectively change the heat flux distribution. A 12% reduction of the pilot fuel ratio made the temperature profile reasonably agree with the design.
一般社団法人日本機械学会の論文
2009-11-16