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

Hamza Fawzy, Qun Zheng, Naseem Ahmad and Yuting Jiang
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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

Energies, 2020, vol. 13, issue 1, 1-23

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.

Keywords: swirl cooling; impingement cooling; compound cooling; blade leading edge; gas turbine (search for similar items in EconPapers)
JEL-codes: Q Q0 Q4 Q40 Q41 Q42 Q43 Q47 Q48 Q49 (search for similar items in EconPapers)
Date: 2020
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Citations: View citations in EconPapers (1)

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