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Application of the Source Term Method and Fan-Shaped Hole for Cooling Performance Improvement in a High-Pressure Turbine

Author

Listed:
  • Sangook Jun

    (Aeropropulsion Research Division, Korea Aerospace Research Institute, Daejeon 34133, Korea)

  • Dong-Ho Rhee

    (Aeropropulsion Research Division, Korea Aerospace Research Institute, Daejeon 34133, Korea)

  • Young Seok Kang

    (Aeropropulsion Research Division, Korea Aerospace Research Institute, Daejeon 34133, Korea)

  • Heeyoon Chung

    (Aeropropulsion Research Division, Korea Aerospace Research Institute, Daejeon 34133, Korea)

  • Jae-Hwan Kim

    (Aeropropulsion Research Division, Korea Aerospace Research Institute, Daejeon 34133, Korea)

Abstract

This study presents the arrangement design of the cooling hole and the application of a fan-shaped hole to improve the cooling performance of the high-pressure turbine. To this end, the first stage nozzle vane of the energy efficient engine (E3) was selected as the base model, and for efficient design, the source term method, called the injection region, was applied for producing the effect of the cooling flow when the RANS analysis was performed. At this time, because the cooling flow rate also changed when the location of the cooling hole changed, a neural network model was constructed to predict the cooling flow rate for the location of the cooling hole. Design optimization was performed to improve the film cooling effectiveness and the temperature uniformity on the vane surface using the streamwise location of the cooling hole as a design variable, and then the cooling performance was investigated by applying several fan-shaped holes instead of cylinder holes on the pressure side. As a result, the final design was obtained, which improved the film cooling effectiveness by 4.1%p and temperature uniformity by 0.7% compared with the base model.

Suggested Citation

  • Sangook Jun & Dong-Ho Rhee & Young Seok Kang & Heeyoon Chung & Jae-Hwan Kim, 2022. "Application of the Source Term Method and Fan-Shaped Hole for Cooling Performance Improvement in a High-Pressure Turbine," Energies, MDPI, vol. 15(19), pages 1-17, September.
    • Handle: RePEc:gam:jeners:v:15:y:2022:i:19:p:6943-:d:922409
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