摘要
高性能小发双级模拟涡轮在总性能试验阶段获得的气动性能参数达到并超过了设计指标．为更详细地研究涡轮气动参数在流场中的分布及二次流的影响，进一步掌握涡轮内部流动机理，验证涡轮气动设计思想，进行了双级模拟涡轮出口扇形段流场测试工作、测试结果表明：双级模拟涡轮二次损失较小，出口参数分布合理，较好的完成了设计意图。
This paper deals with the aerodynamic behavior of a high performance two-stage small turbine. Based on some new design skills, tills model turbine reached an advanced level with an efficiency of 0.90 at design point, that is one percent higher than the predicted design Value. Since the axial gab is too small to install traversing and probes between stators and rotors, detailed measurement was performed only on the downstream section of the two-stage turbine. Radial and circumferential traversing presented a detailed exit flow picture of the two-stage turbine, which was very helpful in the identification and understanding of the major sources of loss. The purpose of the experiment research with conventional measurement instrument is to assess the design method.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2001年第4期447-449,共3页
Journal of Engineering Thermophysics
关键词
热力学
流场分析
涡轮
气动性能
high performance small turbine
modular test
flow field investigation
