Volume 41 Issue 4
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HAN Feng, PU Haotian, CHEN Jiaona, et al. Effects of Reynolds number and density ratio on the leading edge film cooling of twisted turbine blade[J]. Journal of Aerospace Power, 2026, 41（4）：20240417 doi: 10.13224/j.cnki.jasp.20240417
Citation: HAN Feng, PU Haotian, CHEN Jiaona, et al. Effects of Reynolds number and density ratio on the leading edge film cooling of twisted turbine blade[J]. Journal of Aerospace Power, 2026, 41（4）：20240417 doi: 10.13224/j.cnki.jasp.20240417
shu

Effects of Reynolds number and density ratio on the leading edge film cooling of twisted turbine blade

doi: 10.13224/j.cnki.jasp.20240417
  • 1.

    College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

  • 2.

    Integrated Energy Institute，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

  • Received Date: 2024-06-26
    Available Online: 2026-01-14
    Abstract

  • In view of the vulnerability of the turbine blade leading edge to ablation, numerical simulation study was conducted to study the effects of mainstream Reynolds number, coolant-to-mainstream density ratio and blowing ratio on the film cooling characteristics of the leading edge of a rotating twisted turbine blade. The mainstream Reynolds numbers were 44200, 55200 and 71800, respectively. According to the turbine inlet mainstream speeds and velocity triangles corresponding to the three different Reynolds numbers while the rotational number was kept constant (0.001 8), 400 r/min, 500 r/min and 650 r/min turbine speeds at zero angle of attack were obtained for three different Reynolds numbers. N2 and CO2 were used as coolants to achieve coolant-to-mainstream density ratios of 1.04 and 1.56, respectively. Results showed that when the density ratio and blowing ratio were the same, the film covering area and cooling effectiveness of the twisted blade leading edge increased with the increase of Reynolds number. Regardless of the density ratio, when the blowing ratio was the same, the film cooling effectiveness on the pressure surface was higher than that on the suction surface under the three Reynolds numbers. For the N2 case, the average film cooling effectiveness increased with the increase of Reynolds number at −5.5<X/D<0.5. For the CO2 case, the average film cooling effectiveness increased with the increase of Reynolds number at −3.75<X/D<0.5. Under constant blowing ratio, the average film cooling effectiveness of the two types of coolant increased with the increase of Reynolds number. The average spanwise film cooling effectiveness of the whole leading edge increased with the blow ratio increases. When the blowing ratio was the same, the average film cooling effectiveness provided by the higher density coolant CO2 was higher than that of the lower density coolant N2.

     

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