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Gas turbine engine having two outlet fuel premix nozzles for a secondary fuel stage
Gas turbine engine having two outlet fuel premix nozzles for a secondary fuel stage
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机译：具有用于辅助燃料级的两个出口燃料预混喷嘴的燃气涡轮发动机
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摘要
Gas turbine engine combustor secondary fuel stage (14). The combustor has a main combustion zone upstream of the secondary fuel stage for igniting the working gas. The secondary fuel stage has a nozzle (18) with two outlets (20, 22) directed to have a circumferential component for injecting an air-fuel mixture into the combustor. The nozzle is such that the peak temperature of the working gas at a location downstream of the secondary fuel stage is lower than the peak temperature of the working gas when the air-fuel mixture is injected into the combustor by one outlet nozzle. Effective for drawing air-fuel mixture by the working gas.
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