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Gas turbine combustor with annular flow sleeves for dividing airflow upstream of premixing passages
Gas turbine combustor with annular flow sleeves for dividing airflow upstream of premixing passages
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机译：带有环形导流套筒的燃气轮机燃烧室，用于在预混合通道上游分配气流
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摘要
A gas turbine combustor includes a plurality of fuel nozzles, a premixing plate, and a plurality of annular flow sleeves. The plurality of annular flow sleeves includes an inner annular flow sleeve and an outer annular flow sleeve. The plurality of annular flow sleeves is formed to divide an airflow passage into a plurality of flow passages including an inner and an outer circumferential flow passages. The airflow passage is formed around the plurality of fuel nozzles. The airflow passage extends from an upstream side of the plurality of fuel nozzles to fuel injecting ports of the fuel nozzles. The plurality of annular flow sleeves rectifies a flow of air in each of the flow passages and guiding the flow of air to the fuel injecting ports of the fuel nozzles.
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