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Heat transfer and film cooling effectiveness on the squealer tip of a turbine blade

Author

Listed:
  • Park, Jun Su
  • Lee, Dong Hyun
  • Rhee, Dong-Ho
  • Kang, Shin Hyung
  • Cho, Hyung Hee

Abstract

Detailed heat/mass transfer coefficients and film-cooling effectiveness were measured on the tip and inner rim surfaces of a blade with a squealer rim. The test blade was a two-dimensional version of a modern first-stage gas turbine rotor blade with a squealer rim. The experimental apparatus was equipped with a linear cascade of three blades, and the axial chord length (Cx) was 237 mm with a turning angle of 126°, the mainstream Reynolds number based on the axial chord and inlet velocity was 1.5 × 105. In addition, three different types of blade tip surfaces were equipped with a single row of film-cooling holes along the camber line, near the pressure and suction-side rim. The blowing ratio was fixed at 1.5. High heat transfer rates were observed near the leading edge on the tip surface due to reattached flow. Furthermore, heat transfer on both inner side surfaces was higher than that on the tip surface. High film cooling effectiveness was observed in the middle region (0.1 < X/Cx < 0.6) due to stagnation of the film cooling. Ultimately, a proper cooling system is suggested to reduce the thermal load and enhance the film cooling effectiveness in the squealer tip.

Suggested Citation

  • Park, Jun Su & Lee, Dong Hyun & Rhee, Dong-Ho & Kang, Shin Hyung & Cho, Hyung Hee, 2014. "Heat transfer and film cooling effectiveness on the squealer tip of a turbine blade," Energy, Elsevier, vol. 72(C), pages 331-343.
    • Handle: RePEc:eee:energy:v:72:y:2014:i:c:p:331-343
    DOI: 10.1016/j.energy.2014.05.041
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    Cited by:

    1. Zou, Zhengping & Shao, Fei & Li, Yiran & Zhang, Weihao & Berglund, Albin, 2017. "Dominant flow structure in the squealer tip gap and its impact on turbine aerodynamic performance," Energy, Elsevier, vol. 138(C), pages 167-184.
    2. Li, Haiwang & Wang, Meng & You, Ruquan & Liu, Song, 2023. "Thermal radiation correction formula of the scaling criteria for film cooling of turbine blades," Energy, Elsevier, vol. 282(C).
    3. Wang, Meng & Li, Haiwang & You, Ruquan & Kong, Weidi & Tao, Zhi, 2024. "Experimental research on high-temperature radiation characteristics of film-cooled plate of gas turbines," Energy, Elsevier, vol. 303(C).
    4. Sciubba, Enrico, 2015. "Air-cooled gas turbine cycles – Part 1: An analytical method for the preliminary assessment of blade cooling flow rates," Energy, Elsevier, vol. 83(C), pages 104-114.
    5. Rulik, Sebastian & Wróblewski, Włodzimierz & Nowak, Grzegorz & Szwedowicz, Jarosław, 2015. "Heat transfer intensification using acoustic waves in a cavity," Energy, Elsevier, vol. 87(C), pages 21-30.
    6. Zhang, Fan & Liu, Cunliang & Ye, Lin & Ran, Yuan & Zhou, Tianliang & Yan, Haonan, 2024. "Study on the film superposition method for dense multirow film Hole layouts," Energy, Elsevier, vol. 293(C).
    7. Ye, Xuemin & Li, Pengmin & Li, Chunxi & Ding, Xueliang, 2015. "Numerical investigation of blade tip grooving effect on performance and dynamics of an axial flow fan," Energy, Elsevier, vol. 82(C), pages 556-569.

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