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针对某燃气轮机透平第一级静叶的冷却结构与方式,采用Fluent软件数值计算了气膜冷却下的叶片外侧对流换热系数分布;归纳与分析了文献中的换热系数实验关联式,计算出叶片内侧前缘的射流冲击冷却、中弦区带横向流的射流冲击冷却及尾缘区的带柱肋楔形通道的强化换热系数分布;建立了叶片一维传热方程,编制叶片温度分布计算程序;将叶片外侧气膜冷却、内部强化对流冷却和叶片导热方程三者相互耦合计算出叶片表面的温度场分布。结果表明:第一级叶片表面温度基本维持在1200K以下,满足了叶片材料对温度的要求。
Aiming at the cooling structure and mode of the first stationary vane of a gas turbine turbine, the distribution of the convective heat transfer coefficient outside the blade under the film cooling was numerically calculated by Fluent software. The experimental correlation of the heat transfer coefficient in the literature was summarized and analyzed Jet impact cooling of the inner leading edge of the blade, impingement cooling of the jet in the middle chordal zone, and enhanced heat transfer coefficient distribution of the ribbed wedge channel in the trailing edge zone. A one-dimensional heat transfer equation of the blade was established and the temperature distribution of the blade The temperature field distribution on the blade surface is calculated by the coupling of the outer film cooling on the outer side of the blade, the internal convection cooling and the thermal conductivity equation of the blade. The results showed that the surface temperature of the first stage blade kept below 1200K, which satisfied the temperature requirement of the blade material.