Numerical Analysis of Heat Transfer in a new Leading Edge Impingement Cooling Configuration
Leading edge of a gas turbine blade has the most critical heat-transfer area.The highest heat-transfer rates on the airfoil can always be found on the stagnation region of the leading edge.In order to further improve the gas turbine thermal efficiency the development of more advanced internal cooling configurations at leading edge is very necessary.As the state of the art leading edge cooling configuration a concave channel with multi inline jets has been widely used in the most blades.However,this kind of configuration can generate strong spent flow,which shifts the impingement from the stagnation point and weaken the impingement heat transfer.In order to solve this problem a new internal cooling configuration using double swirl chambers in gas turbine leading edge has been developed and introduced in this paper.The double swirl chambers cooling(DSC)technology is introduced by the authors and comprises a significant enhancement of heat transfer due to the generation of two anti-rotated swirls.In DSC-cooling,the reattachment of the swirl flows always occurs at the middle of the chamber,which results in a linear impingement effect.Compared with the reference standard impingement cooling configuration this new cooling system provides a much more uniform heat transfer distribution in the chamber axial direction and also provides much higher heat transfer rate.In this study,the influence of different geometrical parameters e.g.merging ratio of two cylinder channels,the jet inlet hole configurations and radius of blunt protuberances in DSC have been investigated numerically.The results show that in the DSC cooling system the jet inlet hole configurations have large influence on the thermal performance.The rectangular inlet holes,especially with higher aspect ratio,show much better heat transfer enhancement than the round inlet holes.However,as the price for it the total pressure drop is increased.Using blunt protuberances instead of sharp edges in the DSC cooling can improve the heat transfer enhancement and reduce the total pressure drop.
Impingement cooling Leading edge Double Swirl Chambers
Gang Lin Karsten Kusterer Dieter Bohn Takao Sugimoto Ryozo Tanaka Masahide Kazari
B&B-AGEMA GmbH,Aachen,D-52070,Germany RWTH Aachen University,Aachen,D-52062,Germany Kawasaki Heavy Industries,LTD.,Gas Turbine & Machinery Company,Akashi 673-8666,Japan Kawasaki Heavy Industries,LTD.,Technical Institute,Akashi 673-8666,Japan
国际会议
The 5th International Symposium on Jet Propulsion and Power Engineering(第五届喷气推进与动力工程国际会议)
北京
英文
1-9
2014-09-15（万方平台首次上网日期，不代表论文的发表时间）