Aerodynamic Design of High End Wall Angle Turbine Stages-Part II: Experimental Verification
Aerodynamic Design of High End Wall Angle Turbine Stages-Part II: Experimental Verification
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高端壁角式涡轮级气动设计第二部分：实验验证
DOI：
10.1115/1.4023906
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发表时间：
2014
期刊：
影响因子：
--
通讯作者：
Cranstone A
中科院分区：
文献类型：
--
作者：
Cranstone A
本文介绍了一种具有极高端壁倾角的涡轮级的实验研究。最初的涡轮设计并没有达到令人满意的性能，设计预测和试验结果之间的差异可以追溯到后吸力面上的一个大的分离区域。为了提高计算流体力学(CFD)与实验的一致性，发现有必要对所采用的湍流模型进行修改。然后使用修改后的CFD程序重新设计叶片，并对所做的更改进行了描述。经测试，重新设计的叶片的性能与预测结果吻合得更好。最后，将重新设计的级的流场和性能与设计成相同负荷的类似涡轮进行了比较，后者位于中等端壁角度的环隙内。对于非常高的端壁角度设计，估计级效率至少降低了2.4%。
An experimental investigation of a turbine stage featuring very high end wall angles is presented. The initial turbine design did not achieve a satisfactory performance and the difference between the design predictions and the test results was traced to a large separated region on the rear suction-surface. To improve the agreement between computational fluid dynamics (CFD) and experiment, it was found necessary to modify the turbulence modeling employed. The modified CFD code was then used to redesign the vane, and the changes made are described. When tested, the performance of the redesigned vane was found to have much closer agreement with the predictions than the initial vane. Finally, the flowfield and performance of the redesigned stage are compared to a similar turbine, designed to perform the same duty, which lies in an annulus of moderate end wall angles. A reduction in stage efficiency of at least 2.4% was estimated for the very high end wall angle design.