Impact of Transonic Flow on HP Turbine Blade Tip Heat Transfer and Aerodynamics
A reviews of some recent progress towards underdtanding and prediction of HP turbine blade tip heat transfer and aerodyanmic loss charactistics is presnted. The paper is based on the experimental and numerical efforts made in the Osney Laboratory, University of Oxford. The focus is on the transonic ove tip flow behavor. Important implications of the transonic nature of the HP turbine blade overtip leakage (OTL) flow on heat transfer and loss generation mechanism are discussed. It is shown that in an engine realistic condition, a large portion of the flow within the tip gap can be transonic, which gives qualitative different OTL flow structures from the low speed. The over-tip choking sets a limiter for the OTL mass flow, and leads to a very different loss generation mechanism compared to the pressure-driven OTL consideration widely used in conventional tip designs. In addition, compared to heat transfer data found from low speed tests, qualitative differences are observed for a transonic blade tip (Peak heat transfer occurs in very different tip regions). The outcomes of these recent efforts highlight the need to incooperate the transonic aerothermal characteristics into HP blading designs and raise a cautionary note on the use of experimtnal data and compuatioonal capabilities purely derived from low speed testing and validation cases.
Q.Zhang L.He
Osney Laboratory, Department of Engineering Science University of Oxford United Kingdom
国际会议
The 3rd International Symposium on Jet Propulsion and Power Engineering(第三届喷气推进与动力工程国际会议 ISJPPE)
南京
英文
117-120
2010-09-13（万方平台首次上网日期，不代表论文的发表时间）