微型燃气轮机向心透平的性能试验  

Performance Test of Radial-inward Turbine in Microturbine

作　　者：邓清华[1] 倪平[1] 丰镇平[1] 

机构地区：[1]西安交通大学叶轮机械研究所,西安710049

出　　处：《动力工程》2008年第2期195-199,共5页Power Engineering

基　　金：国家863计划资助项目(2002AA503020);西安交通大学博士学位论文基金资助项目(DFXJTU2005-02)

摘　　要：对某向心透平进行了总体气动性能试验、导向器流动特性试验以及级环境下的数值模拟，分别对数值计算结果与试验结果作了对比，分析了导向器叶片出口气流落后角的影响因素及其损失状况．结果表明：无论是总体气动性能，还是导向器流动特性，数值计算结果与试验结果都吻合良好；导向器出口马赫数及相对尾缘厚度对其气流落后角有影响，当马赫数小于0．9时，气流落后角变化平缓，而马赫数高于0．9时气流落后角变化剧烈；导向器出口马赫数在0．9～1．2，速度系数在0．975以上，能量损失系数低于5%，有助于提高级效率．The general aerodynamic performance experiment for radial-inward turbine, and flow characteristic experiment for guide vanes, as well as the numerical simulation under stage conditions the same as that of experiment were performed. The comparisons between the numerical simulations and experimental results were conducted separately. The impact factors of exit flow lag angle and loss status of the guide vane were analyzed. It indicates that the results of numerical simulations are well agreed with that of experiment both for general aerodynamic performance and guide vane flow characteristics. The exit Math number and relative trailing edge thickness of guide vane have the influence on the exit flow lag angle. The lag angle changes smoothly with the Math number less than 0.9, but changes steeply with that exceeding 0.9. If the exit Maeh number of guide vane is within the range of 0. 9～ 1. 2, the velocity coefficient will be upward of 0. 975, the energy loss coefficient will be less than 5%, then the stage efficiency will be increased.

关 键 词：能源与动力工程 微型燃气轮机 向心透平 导向器 流动特性 试验 数值模拟 

分 类 号：TK479.11[动力工程及工程热物理—动力机械及工程]