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Optimization of A Swirl with Impingement Compound Cooling Unit for A Gas Turbine Blade Leading Edge

Author

Listed:
  • Hamza Fawzy

    (College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China)

  • Qun Zheng

    (College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China)

  • Naseem Ahmad

    (College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China)

  • Yuting Jiang

    (College of Power and Energy Engineering, Harbin Engineering University, Harbin 150001, China)

Abstract

In this article, a compound unit of swirl and impingement cooling techniques is designed to study the performance of flow and heat transfer using multi-conical nozzles in a leading-edge of a gas turbine blade. Reynolds Averaged Navier-Stokes equations and the Shear Stress Transport model are numerically solved under different nozzle Reynolds numbers and temperature ratios. Results indicated that the compound cooling unit could achieve a 99.7% increase in heat transfer enhancement by increasing the nozzle Reynolds number from 10,000 to 25,000 at a constant temperature ratio. Also, there is an 11% increase in the overall Nusselt number when the temperature ratio increases from 0.65 to 0.95 at identical nozzle Reynolds number. At 10,000 and 15,000 of nozzle Reynolds numbers, the compound cooling unit achieves 47.9% and 39.8% increases and 63.5% and 66.3% increases in the overall Nusselt number comparing with the available experimental swirl and impingement models, respectively. A correlation for the overall Nusselt number is derived as a function of nozzle Reynolds number and temperature ratio to optimize the results. The current study concluded that the extremely high zones and uniform distribution of heat transfer are perfectly achieved with regard to the characteristics of heat transfer of the compound cooling unit.

Suggested Citation

  • 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.
    • Handle: RePEc:gam:jeners:v:13:y:2020:i:1:p:210-:d:304328
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    References listed on IDEAS

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    1. Abdul Rehman & Bo Liu & Muhammad Afzaal Asghar, 2019. "Secondary Flow and Endwall Optimization of a Transonic Turbine," Energies, MDPI, vol. 12(21), pages 1-21, October.
    2. ZhiTan Liu & XiaoDong Ren & ZhiYuan Yan & HongFei Zhu & Tao Zhang & Wei Zhu & XueSong Li, 2019. "Effect of Inlet Air Heating on Gas Turbine Efficiency under Partial Load," Energies, MDPI, vol. 12(17), pages 1-11, August.
    3. Jianying Gong & Tieyu Gao & Junxiong Zeng & Jianqiang Hou & Zhen Li, 2019. "Effect of Actual Gas Turbine Operating Conditions on Mist/Steam Cooling Performance in a Ribbed Passage," Energies, MDPI, vol. 12(10), pages 1-17, May.
    4. Alessandro Rosini & Alessandro Palmieri & Damiano Lanzarotto & Renato Procopio & Andrea Bonfiglio, 2019. "A Model Predictive Control Design for Power Generation Heavy-Duty Gas Turbines," Energies, MDPI, vol. 12(11), pages 1-17, June.
    5. Aleksandra Dzido & Piotr Krawczyk & Michalina Kurkus-Gruszecka, 2019. "Numerical Analysis of Dry Ice Blasting Convergent-Divergent Supersonic Nozzle," Energies, MDPI, vol. 12(24), pages 1-14, December.
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    Cited by:

    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.

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