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Turbine vane endwall heat transfer measurement and coolant migration mechanism considering film hole geometric deviation

Author

Listed:
  • Li, Zhiyu
  • Zhang, Kaiyuan
  • Bai, Bo
  • Li, Zhigang
  • Duan, Fei
  • Li, Jun

Abstract

Film cooling is essential for protecting nozzle guide vanes from severe thermal loads in modern gas turbines. In particular, the endwall cooling is critical due to strong secondary flows and complex heat transfer characteristics. The effectiveness of endwall film cooling is highly sensitive to the geometry of the film holes, where even slight deviations in diameter or injection angle can markedly affect the coolant–mainstream interaction and the overall aerothermal performance of the endwall. This paper presents a comprehensive analysis of the effects of film hole deviations on the endwall aerothermal performance considering two types of film hole geometric deviations (enlarged hole diameter and increased hole surface angle) at three coolant mass flow conditions. The transient infrared thermography is employed to capture the endwall heat transfer distributions, while complementary numerical simulations are conducted to provide detailed aerothermal characteristics and enable a thorough analysis of the underlying flow mechanisms. Both types of film-hole geometric deviations lead to a reduction in the endwall Nusselt number. The film hole with enlarged hole diameter also reduces the endwall thermal load, resulting in the area exhibiting a net heat flux reduction greater than 0.1 reaching 52.87 %. For the cases with enlarged hole diameter, the endwall film cooling effectiveness increases compared with the baseline case due to the weak kidney vortex with fast dissipation. Under a mass flow ratio of 1.0 %, the overall coverage area reaches a maximum of 40.2 %. For the cases with increased hole surface angle, the coolant tends to enter the mainstream rather than cooling the endwall. These results provide practical guidance indicating that enlarging the hole diameter enhances endwall cooling performance, whereas increasing the surface angle may compromise thermal protection despite expanding phantom coverage.

Suggested Citation

  • Li, Zhiyu & Zhang, Kaiyuan & Bai, Bo & Li, Zhigang & Duan, Fei & Li, Jun, 2025. "Turbine vane endwall heat transfer measurement and coolant migration mechanism considering film hole geometric deviation," Energy, Elsevier, vol. 339(C).
    • Handle: RePEc:eee:energy:v:339:y:2025:i:c:s0360544225046717
    DOI: 10.1016/j.energy.2025.139029
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    References listed on IDEAS

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