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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2021, Vol. 42 ›› Issue (7): 124775-124775.doi: 10.7527/S1000-6893.2020.24775

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Research on film cooling performance of sister hole based on structural parameter analysis

WANG Jin1, SUN Jie1, ZHAO Zhanming1, ZHANG Bo1, REN Xiaodong2,3, XIE Gongnan4   

  1. 1. School of Energy and Environmental Engineering, Hebei University of Technology, Tianjin 300401, China;
    2. Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Tsinghua University, Beijing 100084, China;
    3. Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China;
    4. School of Marine Science and Technology, Northwestern Polytechnical University, Xi'an 710072, China
  • Received:2020-09-22 Revised:2020-10-15 Published:2020-12-25
  • Supported by:
    National Natural Science Foundation of China (51806118, 51806057)

Abstract: A three-factor and five-level orthogonal table is designed using the Taguchi method for the sister hole structure, with the compound angle, the inclination angle and the blowing ratio as factors and the average wall film cooling effectiveness as the evaluation index. The flow characteristics and the cooling effectiveness distribution under different conditions are analyzed with numerical calculations. Results show that the film cooling effectiveness of the sister holes is 165%-412.5% of that of conventional cylindrical holes at a high blowing ratio, and the film cooling effectiveness of the sister holes with a 10° compound angle is higher than that of the sister holes with a -10° compound angle. Parameterized results reveal that the hole structure with a blowing ratio of 0.5, a compound angle of 10° and an inclination angle of 35° exhibits the best cooling performance.

Key words: sister holes, film cooling effectiveness, Taguchi method, blowing ratio, compound angle

CLC Number: