IGTC-50 Combustion Performance of Lean Premixed Type Combustors for a Hydrogen-Fueled Micro Gas Turbine(Session B-8 COMBUSTION III)
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概要
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Lean premixed combustion may reduce NO_x emission of gas turbines. Based on this idea, a micro gas turbine test combustor using a lean premixed swirling hydrogen flame was developed. The total pressure loss of the combustor, which influences engine performance of the micro gas turbine with a rather low pressure ratio, was restrained low by equipping a wide throat at the combustor inlet. Excellent performance concerning flame stability, heat release rate and NO_x emission was attained. The results enabled the test combustor to be designed to a practical combustor burning lean hydrogen-air premixture, and a prototype hydrogen combustor having the same structure as the test combustor was developed. The combustion test of the prototype combustor standing alone was conducted at atmospheric pressure. Good flame stability of the combustor and extremely low NO_x emissions of under 1ppm were confirmed.
著者
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Minakawa K.
Department Of Aerospace Engineering Tokyo Metropolitan Institute Of Technology
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Yuasa S.
Department of Aerospace Engineering, Tokyo Metropolitan Institute of Technology
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Shigeta M.
Department of Aerospace Engineering, Tokyo Metropolitan Institute of Technology
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Nishida K.
Department of Aerospace Engineering, Tokyo Metropolitan Institute of Technology
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Yuasa S.
Department Of Aerospace Engineering Tokyo Metropolitan Institute Of Technology
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Shigeta M.
Department Of Aerospace Engineering Tokyo Metropolitan Institute Of Technology
関連論文
- IGTC-50 Combustion Performance of Lean Premixed Type Combustors for a Hydrogen-Fueled Micro Gas Turbine(Session B-8 COMBUSTION III)
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