IGTC-32 Cooling Performance of an Advanced Liner Element For Gas Turbine Combustors(Session B-4 HEAT TRANSFER IN GAS TURBINE COMPONENTS)

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概要

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• Recent trends in the gas turbine have been toward high pressure ratio, high temperature engine cycles. The liner cooling system have been required to improve cooling effectiveness with less cooling air flow, minimizing thermal stresses. The system features ; (1) Structural separation of inner and outer walls, and (2) Cooling air passed in the direction counter to hot gas flow, through the channel with the twisted tape as a turhurence promoter. The purpose of this study is to obtain the data for design. Data were obtained from experiments arranged separately for measuring heat transfer in the twisted tape channels to investigate the influence of the gap between twisted tape edge and channel wall and in the film cooling after issue of the cooling air into combustion chamber. The data were then combined to estimate the compounded effect of the combined system, and the results a model representing the combined system.

• 公益社団法人日本ガスタービン学会の論文
• 1991-10-00

著者

• Obata M.

  Frontier Aircraft Basic Research Center (FARC), Research Engineering Department, Power Plant System Group, Mizuho Office

関連論文

• IGTC-32 Cooling Performance of an Advanced Liner Element For Gas Turbine Combustors(Session B-4 HEAT TRANSFER IN GAS TURBINE COMPONENTS)

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