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Development Trend of Cooling Technology for Turbine Blades at Super-High Temperature of above 2000 K

Author

Listed:
  • Liang Xu

    (State Key Laboratory for Manufacturing Systems Engineering, Xi’an Jiaotong University, Xi’an 710049, China)

  • Zineng Sun

    (State Key Laboratory for Manufacturing Systems Engineering, Xi’an Jiaotong University, Xi’an 710049, China)

  • Qicheng Ruan

    (State Key Laboratory for Manufacturing Systems Engineering, Xi’an Jiaotong University, Xi’an 710049, China)

  • Lei Xi

    (State Key Laboratory for Manufacturing Systems Engineering, Xi’an Jiaotong University, Xi’an 710049, China)

  • Jianmin Gao

    (State Key Laboratory for Manufacturing Systems Engineering, Xi’an Jiaotong University, Xi’an 710049, China)

  • Yunlong Li

    (State Key Laboratory for Manufacturing Systems Engineering, Xi’an Jiaotong University, Xi’an 710049, China)

Abstract

Aeroengines and heavy-duty gas turbines are the core power equipment in the field of national defense and energy. Their research and development (R&D) level and manufacturing level represent the status of a country’s heavy industry in the world. The common cooling technologies of turbine blades including impingement cooling, film cooling, effusion cooling, layer cooling, pin fin cooling, and rough ribs were introduced in this paper. With the continuous improvement of the efficiency and performance of aeroengines and gas turbines, the turbine inlet temperature increases gradually every year; turbine blades will be exposed to higher gas temperatures in the future as gas temperatures break 2000 K. In order to ensure the safe operation of turbine blades under severe super-high temperature working conditions, cooling technology must be developed emphatically. This paper first reviews the research status of turbine blade cooling technology and points out future research focuses. The development trends of next-generation turbine blade cooling technology for above 2000 K temperature are summarized from several aspects: the innovative excavation of high-efficiency composite cooling configuration, multi-objective cooperative cooling structure and optimization design based on 3D printing, composite cooling structure design and optimization based on an artificial intelligence algorithm, tapping the cooling potential of new cooling media and heat pipes, integrated thermal protection with new thermal insulators, and the application of low-resistance and high-efficiency surface dimple cooling. The summary of this paper can provide a reference for the researchers of turbine blade cooling technology.

Suggested Citation

  • Liang Xu & Zineng Sun & Qicheng Ruan & Lei Xi & Jianmin Gao & Yunlong Li, 2023. "Development Trend of Cooling Technology for Turbine Blades at Super-High Temperature of above 2000 K," Energies, MDPI, vol. 16(2), pages 1-19, January.
    • Handle: RePEc:gam:jeners:v:16:y:2023:i:2:p:668-:d:1026763
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    References listed on IDEAS

    as
    1. Wei Zhang & Huiren Zhu & Guangchao Li, 2020. "Experimental Study of Heat Transfer on the Internal Surfaces of a Double-Wall Structure with Pin Fin Array," Energies, MDPI, vol. 13(24), pages 1-17, December.
    2. Liang Xu & Qicheng Ruan & Qingyun Shen & Lei Xi & Jianmin Gao & Yunlong Li, 2021. "Optimization Design of Lattice Structures in Internal Cooling Channel with Variable Aspect Ratio of Gas Turbine Blade," Energies, MDPI, vol. 14(13), pages 1-27, July.
    3. Sandip Dutta & Inderjot Kaur & Prashant Singh, 2022. "Review of Film Cooling in Gas Turbines with an Emphasis on Additive Manufacturing-Based Design Evolutions," Energies, MDPI, vol. 15(19), pages 1-35, September.
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    Cited by:

    1. Chen, Zhimin & Chen, Xuejiao & Yang, XuFei & Yu, Bo & Wang, Bohong & Zhu, Jianqin & Chen, Yujie & Cai, Weihua, 2024. "Numerical study on cooling characteristics of turbine blade based on laminated cooling configuration with clapboards," Energy, Elsevier, vol. 299(C).

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