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Axial Thrust, Disk Frictional Losses, and Heat Transfer in a Gas Turbine Disk Cavity

by 1,2, 1, 3, 1, 1,* and 1,4,*
1
Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China
2
Department of Mechanical Engineering, University of Duisburg-Essen, 47057 Duisburg, Germany
3
School of Energy and Power Engineering, Jiangsu University, Zhenjiang 212013, China
4
Key Laboratory of Fluid and Power Machinery, Xihua University, Ministry of Education, Chengdu 610039, China
*
Authors to whom correspondence should be addressed.
Energies 2019, 12(15), 2917; https://doi.org/10.3390/en12152917
Received: 26 June 2019 / Revised: 23 July 2019 / Accepted: 26 July 2019 / Published: 29 July 2019
The gas turbine is a kind of high-power and high-performance energy machine. Currently, it is a hot issue to improve the efficiency of the gas turbines by reducing the amount of secondary air used in the disk cavity. The precondition is to understand the effects of the through-flow rate on the axial thrust, the disk frictional losses, and the characteristics of heat transfer under various experimental conditions. In this paper, experiments are conducted to analyze the characteristics of flow and heat transfer. To ensure the safe operation of the gas turbine, the pressure distribution and the axial thrust are measured for various experimental conditions. The axial thrust coefficient is found to decrease as the rotational speed and the through-flow rate increases. By torque measurements, the amounts of the moment coefficient drop as the rotational speed increases while increase with through-flow rate. In order to better analyze the temperature field within the cavity, both the local and the average Nusselt number are investigated with the help of thermochromic liquid crystal technique. Four correlations for the local Nusselt number are determined according to the amounts of a through-flow coefficient. The results in this study can help the designers to better design the secondary air system in a gas turbine. View Full-Text
Keywords: gas turbine; disk cavity; axial thrust; disk frictional losses; heat transfer gas turbine; disk cavity; axial thrust; disk frictional losses; heat transfer
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MDPI and ACS Style

Hu, B.; Li, X.; Fu, Y.; Gu, C.; Ren, X.; Lu, J. Axial Thrust, Disk Frictional Losses, and Heat Transfer in a Gas Turbine Disk Cavity. Energies 2019, 12, 2917.

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