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Numerical Investigations of the Influence of Unsteady Vane Trailing Edge Shock Wave on Film Cooling Effectiveness of Rotor Blade Leading Edge

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Abstract

Unsteady numerical simulations of a high-load transonic turbine stage have been carried out to study the influences of vane trailing edge outer-extending shockwave on rotor blade leading edge film cooling performance. The turbine stage used in this paper is composed of a vane section and a rotor one which are both near the root section of a transonic high-load turbine stage. The Mach number is 0.94 at vane outlet, and the relative Mach number is above 1.10 at rotor outlet. Various positions and oblique angles of film cooling holes were investigated in this research. Results show that the cooling efficiency on the blade surface of rotor near leading edge is significantly affected by vane trailing edge outer-extending shockwave in some cases. In the cases that film holes are close to leading edge, cooling performance suffers more from the sweeping vane trailing edge outer-extending shockwave. In addition, coolant flow ejected from oblique film holes is harder to separate from the blade surface of rotor, and can cover more blade area even under the effects of sweeping vane trailing edge shockwave. As a result, oblique film holes can provide better film cooling performance than vertical film holes do near the leading edge on turbine blade which is swept by shockwaves.

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Acknowledgments

The authors thank all the professors at Engine Dynamics Research Center of Harbin Institute of Technology for their support, encouragement, constructive suggestions and assistances. The author would also like to thank the support of the National Natural Science Foundation of China (NSFC), Grant No. 51421063.

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Authors and Affiliations

  1. Engine Aerodynamics Research Centre Harbin Institute of Technology, Harbin, 150001, China

    Yufeng Wang, Le Cai, Songtao Wang & Xun Zhou

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  1. Yufeng Wang
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  2. Le Cai
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  3. Songtao Wang
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  4. Xun Zhou
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Correspondence to Yufeng Wang.

Additional information

This research is supported by National Natural Science Foundation of China, Grant No. 51421063.

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Wang, Y., Cai, L., Wang, S. et al. Numerical Investigations of the Influence of Unsteady Vane Trailing Edge Shock Wave on Film Cooling Effectiveness of Rotor Blade Leading Edge. J. Therm. Sci. 27, 135–145 (2018). https://doi.org/10.1007/s11630-018-0994-3

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  • DOI: https://doi.org/10.1007/s11630-018-0994-3

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