Recent Advances in the Study of Film Cooling on the Gas Turbine Blade

Abstract:

The development of a new generation of high performance gas turbine engines requires gas turbines to be operated at very high inlet temperatures, which are much higher than the allowable metal temperatures. Consequently, this necessitates the need for advanced cooling techniques. Among the numerous cooling technologies, the film cooling technology has superior advantages and relatively favorable application prospect. The recent research progress of film cooling techniques for gas turbine blade is reviewed and basic principle of film cooling is also illustrated. Progress on rotor blade and stationary blade of film cooling are introduced. Film cooling development of leading-edge was also generalized. Effect of various factor on cooling effectiveness and effect of the shape of the injection holes on plate film cooling are discussed. In addition, with respect to progress of discharge coefficient is presented. In the last, the future development trend and future investigation direction of film cooling are prospected.

• Periodical: Advanced Materials Research (Volumes 971-973)
• Pages: 143-147
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.971-973.143
• Online since: June 2014
• Authors: Ping Dai*, Shuang Xiu Li
• Keywords: Discharge Coefficient, Film Cooling, Gas Turbine Blade, Heat Transfer Coefficient

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