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本文介绍的燃气涡轮特性计算方法可用来计算单级涡轮和多级涡轮特性。其中考虑了冷气掺混对涡轮特性的影响,非设计状态下亚音速和跨音速涡轮不同的损失特性,攻角变化的影响,落后角的变化以及多级涡轮特性级间的相互关系。文中提出了马赫数对损失修正的经验关系式。本文以双级涡轮特性计算方法为例进行介绍。用本方法计算了亚音、跨音、单级、双级、有冷却和无冷却五种涡轮的特性。在设计点,计算结果的精度在1％以内,与有试验特性的涡轮相比较,在设计点附近及常用工况内,计算结果与试验曲线吻合较好。
This article describes the gas turbine performance calculation method can be used to calculate single-stage turbine and multi-stage turbine characteristics. Considering the influence of air-conditioning mixing on turbine characteristics, the different loss characteristics of subsonic and transonic turbines in non-design conditions, the influence of the change of angle of attack, the variation of the backward angle and the inter-relationship among the characteristics of multi-stage turbines. In this paper, the empirical relationship between Mach number and loss correction is proposed. In this paper, two-stage turbine characteristics of the calculation method as an example to introduce. Using this method, the characteristics of subsonic, transonic, single-stage, two-stage, cooled and non-cooled turbines are calculated. The accuracy of the calculation results is less than 1% at the design point. Compared with the turbines with the test characteristics, the calculated results are in good agreement with the experimental curves near the design points and the common operating conditions.