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

Bo Hu, Xuesong Li, Yanxia Fu, Chunwei Gu, Xiaodong Ren and Jiaxing Lu
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Bo Hu: Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China
Xuesong Li: Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China
Yanxia Fu: School of Energy and Power Engineering, Jiangsu University, Zhenjiang 212013, China
Chunwei Gu: Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China
Xiaodong Ren: Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China
Jiaxing Lu: Department of Energy and Power Engineering, Tsinghua University, Beijing 100084, China

Energies, 2019, vol. 12, issue 15, 1-15

Abstract: 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.

Keywords: gas turbine; disk cavity; axial thrust; disk frictional losses; heat transfer (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: 2019
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