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Experimental investigation of the bending clearance on the aerodynamic performance in turbine blade tip region

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  • Shuai, Jiang
  • Jianyang, Yu
  • Hongwu, Wang
  • Fu, Chen
  • Shaowen, Chen
  • Yanping, Song

Abstract

The bending clearance design method is applied for the aerodynamic optimization by using the Kriging model and Genetic Algorithm. To validate the effects of the clearance shape and the deformation coefficient on the TLF suppression, the baseline case and other four modified cases have been experimentally and numerically investigated in a low speed wind tunnel linear cascade. The measured data and numerical results demonstrates that the modified cases increase the pressure inside the clearance, impedes the tip leakage flow (TLF), and its deceleration effect on leakage fluid inside the bending clearance gradually increased with the increasing deformation coefficient. In addition, the presence of the blocking vortex (BV) exerts a brake on the tip leakage vortex (TLV) and divides it into two parts. The TLV development is interrupted in front of the midstream under the blocking effect, but the UPV scale is enlarged. Compared with the baseline case, the application of bending clearance is proved to reduce the aerodynamic loss and leakage with relative reduction of 9.7% and 28.8%, furthermore, the optimal configuration has better aerodynamic performance with relative reduction of 16.3% and 31%. Both of the aerodynamic loss and leakage continue to decline with the increase of λ, but no significant performance improvement will be achieved when λ exceeds 6 mm.

Suggested Citation

  • Shuai, Jiang & Jianyang, Yu & Hongwu, Wang & Fu, Chen & Shaowen, Chen & Yanping, Song, 2020. "Experimental investigation of the bending clearance on the aerodynamic performance in turbine blade tip region," Energy, Elsevier, vol. 197(C).
    • Handle: RePEc:eee:energy:v:197:y:2020:i:c:s0360544220303418
    DOI: 10.1016/j.energy.2020.117234
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    References listed on IDEAS

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    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. Gao, Jie & Zheng, Qun & Xu, Tianbang & Dong, Ping, 2015. "Inlet conditions effect on tip leakage vortex breakdown in unshrouded axial turbines," Energy, Elsevier, vol. 91(C), pages 255-263.
    3. Cho, Soo-Yong & Cho, Chong-Hyun & Choi, Sang-Kyu, 2017. "An experimental study of partial admission losses with various blade tip clearances using a linear cascade," Energy, Elsevier, vol. 122(C), pages 627-637.
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    Cited by:

    1. Nakhchi, M.E. & Naung, S. Win & Rahmati, M., 2022. "Influence of blade vibrations on aerodynamic performance of axial compressor in gas turbine: Direct numerical simulation," Energy, Elsevier, vol. 242(C).

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