IDEAS home Printed from https://ideas.repec.org/a/gam/jeners/v18y2025i3p540-d1576098.html
   My bibliography  Save this article

Recent Advances in Cooling Technology for the Leading Edge of Gas Turbine Blades

Author

Listed:
  • Shixing Zhu

    (Tianjin Key Laboratory for Advanced Mechatronic System Design and Intelligent Control, School of Mechanical Engineering, Tianjin University of Technology, Tianjin 300384, China
    National Demonstration Center for Experimental Mechanical and Electrical Engineering Education, Tianjin University of Technology, Tianjin 300384, China)

  • Yan Li

    (Tianjin Key Laboratory for Advanced Mechatronic System Design and Intelligent Control, School of Mechanical Engineering, Tianjin University of Technology, Tianjin 300384, China
    National Demonstration Center for Experimental Mechanical and Electrical Engineering Education, Tianjin University of Technology, Tianjin 300384, China)

  • Junyang Yan

    (Tianjin Key Laboratory for Advanced Mechatronic System Design and Intelligent Control, School of Mechanical Engineering, Tianjin University of Technology, Tianjin 300384, China
    National Demonstration Center for Experimental Mechanical and Electrical Engineering Education, Tianjin University of Technology, Tianjin 300384, China)

  • Chao Zhang

    (Tianjin Key Laboratory for Advanced Mechatronic System Design and Intelligent Control, School of Mechanical Engineering, Tianjin University of Technology, Tianjin 300384, China
    National Demonstration Center for Experimental Mechanical and Electrical Engineering Education, Tianjin University of Technology, Tianjin 300384, China)

Abstract

As the inlet temperature of the gas turbine exceeds the high temperature limit of the blade materials, efficient leading edge cooling technologies are crucial for the further development of gas turbines. Therefore, this paper reviews the research progress on external cooling technology, internal cooling technology, and composite cooling technology for gas turbine rotating blade leading edge cooling. It focuses on the impact of the geometric shape, arrangement, and flow parameters of film cooling holes on external cooling performance, the influence of jet hole design, configuration, crossflow, ribs on internal cooling efficiency, and the characteristics and influencing factors of composite cooling technologies are also discussed. Among the most promising composite cooling techniques, the impingement jet film composite cooling technology and swirl film composite cooling technology stand out. For impingement jet film composite cooling technology, this paper explores the effects of blowing ratio, nozzle parameters, jet hole characteristics, and flow field parameters on the overall cooling performance of the rotating blade leading edge. Impingement jet film composite cooling technology has been shown to significantly improve the cooling performance of the leading edge compared to traditional single cooling techniques. For applications requiring large area cooling or maintaining film integrity, swirl film composite cooling technology not only enhances heat transfer efficiency but also improves the uniformity of heat transfer. The design of swirl nozzles, coolant flow rate, Reynolds number, and jet temperature all have significant effects on the heat transfer efficiency of swirl film composite cooling. To further advance the development of gas turbine rotating blade leading edge cooling technologies, it is recommended to focus on the study of film composite cooling techniques, particularly investigating the effects of various parameters of impingement, swirl on composite cooling performance.

Suggested Citation

  • Shixing Zhu & Yan Li & Junyang Yan & Chao Zhang, 2025. "Recent Advances in Cooling Technology for the Leading Edge of Gas Turbine Blades," Energies, MDPI, vol. 18(3), pages 1-21, January.
    • Handle: RePEc:gam:jeners:v:18:y:2025:i:3:p:540-:d:1576098
    as

    Download full text from publisher

    File URL: https://www.mdpi.com/1996-1073/18/3/540/pdf
    Download Restriction: no
    File URL: https://www.mdpi.com/1996-1073/18/3/540/
    Download Restriction: no
    ---><---

    References listed on IDEAS

    as
    1. Hamza Fawzy & Qun Zheng & Naseem Ahmad & Yuting Jiang, 2020. "Optimization of A Swirl with Impingement Compound Cooling Unit for A Gas Turbine Blade Leading Edge," Energies, MDPI, vol. 13(1), pages 1-23, January.
    Full references (including those not matched with items on IDEAS)

    Citations

    Citations are extracted by the CitEc Project, subscribe to its RSS feed for this item.
    as


    Cited by:

    1. Anton Pulin & Ivan Talabira & Denis Konin & Kirill Alisov & Mikhail Kanakin & Mikhail Laptev & Evgenii Komlev & Viktor Barskov & Anatoliy Popovich & Kirill Starikov, 2025. "Investigation of the Influence of Gyroid Lattice Dimensions on Cooling," Energies, MDPI, vol. 18(17), pages 1-25, August.

    Most related items

    These are the items that most often cite the same works as this one and are cited by the same works as this one.
    1. Liaqat Hussain & Muhammad Mahabat Khan & Manzar Masud & Fawad Ahmed & Zabdur Rehman & Łukasz Amanowicz & Krzysztof Rajski, 2021. "Heat Transfer Augmentation through Different Jet Impingement Techniques: A State-of-the-Art Review," Energies, MDPI, vol. 14(20), pages 1-40, October.

    More about this item

    Keywords

    ;
    ;
    ;
    ;
    ;

    Statistics

    Access and download statistics

    Corrections

    All material on this site has been provided by the respective publishers and authors. You can help correct errors and omissions. When requesting a correction, please mention this item's handle: RePEc:gam:jeners:v:18:y:2025:i:3:p:540-:d:1576098. See general information about how to correct material in RePEc.

    If you have authored this item and are not yet registered with RePEc, we encourage you to do it here. This allows to link your profile to this item. It also allows you to accept potential citations to this item that we are uncertain about.

    If CitEc recognized a bibliographic reference but did not link an item in RePEc to it, you can help with this form .

    If you know of missing items citing this one, you can help us creating those links by adding the relevant references in the same way as above, for each refering item. If you are a registered author of this item, you may also want to check the "citations" tab in your RePEc Author Service profile, as there may be some citations waiting for confirmation.

    For technical questions regarding this item, or to correct its authors, title, abstract, bibliographic or download information, contact: MDPI Indexing Manager (email available below). General contact details of provider: https://www.mdpi.com .

    Please note that corrections may take a couple of weeks to filter through the various RePEc services.

    IDEAS is a RePEc service. RePEc uses bibliographic data supplied by the respective publishers.