EXPERIMENTS AND NUMERICAL SIMULATION ON INFLUENCE OF COOLING JETS TEMPERATURE WITH A TURBINE CASCADE

摘要：

Using a turbine cascade which has a single row of discrete film cooling holes on blades leading surface, a series of film cooled cascade experimental researches have been undertaken on a supersonic and transonic cascade wind tunnel test-bed.The test results showed that the influence of cooling jets temperature on flow loss is bigger and lower on flow angle.The numerical simulation of the experimental data has carried on. The results of numerical simulation are approximately consistent with the test data.

关键词： film cooling turbine cascade CFD

作者: Wang bin Zhou shan Wei gang

作者单位: China Gas Turbine Establishment, Chengdu 610500, China

会议类型: 国际会议

会议名称: 第一届喷气推进与动力工程国际会议(Proceedings of the 1st International Symposium on Jet Propulsion and Power Engineering)

会议地点: 昆明

会议语种:英文

页码: 300-304

在线出版日期: 2006-09-18（万方平台首次上网日期，不代表论文的发表时间）