Gas turbine combustor of the completely premixed combustion type

Power plants – Combustion products used as motive fluid – Combustion products generator

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60737, 60746, F23R 334

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active

053396359

ABSTRACT:
A gas turbine combustor of the pre-mixed combustion system in which the pre-mixed fuel and the air are combusted. The gas turbine combustor comprises main cylindrical nozzles provided in the end wall on the upstream side of a cylindrical combustion chamber, auxiliary nozzles formed to surround the main nozzles, a main pre-mixed gas supply for supplying a pre-mixed gas to the main nozzles, and an auxiliary pre-mixed gas supply for supplying a pre-mixed gas having an fuel/air ratio smaller than that of the main pre-mixed gas to the auxiliary nozzles, and wherein it is allowed to stably burn a lean pre-mixed gas having an fuel/air ratio of greater than 1 from a low-load condition through and up to a high-load condition of the gas turbine.

REFERENCES:
patent: 3919840 (1975-11-01), Markowski
patent: 3943705 (1976-03-01), DeCorso et al.
patent: 4237694 (1980-12-01), Wood et al.
patent: 4967561 (1990-11-01), Bruhwiler et al.
"The Aircraft Gas Turbine Engine and Its Operation", United Technologies, P&W Oper. Instr 200, 1974 p. 85.
Lefebvre, Arthur H. "Gas Turbine Combustion," McGraw-Hill, New York, 1983 pp. 4-7.

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