摘要
基于Denton的尾缘流动理论 ,发展了一种考虑冷气喷射的二维、可压涡轮叶栅尾缘混合损失模型 ,研究了涡轮叶栅尾缘损失的特征 ,定量评估了影响尾缘损失的各种参数。研究表明 ,冷气流量是影响尾缘损失的一个重要参数 ,对于主流马赫数为 1 1的典型情况 ,冷气流量从 0增大到 10 % ,损失增大 3 5倍。叶片尾缘基压变化对损失也具有明显的影响 ,其它影响损失的参数包括叶栅出口位置边界层动量厚度、冷气总压。
A two-dimensional, compressible flow model for loss created by mixing the flow behind the turbine cascade with coolant injection is presented, based on the theory developed by Denton. The principal mechanism and characteristics of loss caused by the flow mixing due to wake, coolant and base flow (base pressure) have been discussed in this paper. Calculation results show that the coolant flow mass, base pressure and boundary layer momentum thickness have a great effect on the trailing edge loss. This paper presents the quantitative analysis results to assess the effects of above parameters on the trailing edge loss.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2003年第3期199-202,共4页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金资助项目 (0 1C5 30 11)
关键词
尾缘损失
损失模型
叶栅
涡轮设计
Compressible flow
Computational fluid dynamics
Gas turbines
Machine design
Mathematical models
