In order to further study the effects of the target channel shape on the cooling performance of the double swirl cooling (DSC), five double swirl channels formed by two overlapping elliptic cylinders with different length ratio between the vertical semi-axis and the horizontal semi-axis are applied. Numerical studies are carried out under three Reynolds numbers. The flow characteristics and heat transfer performance of five DSC cases are compared with the benchmark impingement cooling case. The flow losses, cross-flow development, generated vortices, and velocity distributions inside target channels are illustrated, analyzed, and compared. The spanwise averaged Nusselt number, Nusselt number distributions, and thermal performance are discussed and compared. Results indicate that the largest length ratio between the vertical semi-axis and the horizontal semi-axis of the target channel yields the lowest flow loss, largest overall averaged Nusselt number, and best thermal performance. With the decrease in the length ratio, the heat transfer distribution on the target surface becomes more uniform. The maximum enhancement of overall averaged Nusselt number and thermal performance in DSC is about 30% and 33%, respectively.
Skip Nav Destination
Article navigation
July 2019
Research-Article
Effects of Target Channel Shapes on Double Swirl Cooling Performance at Gas Turbine Blade Leading Edge
Junfei Zhou,
Junfei Zhou
Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Search for other works by this author on:
Xinjun Wang,
Xinjun Wang
Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
e-mail: xjwang@xjtu.edu.cn
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
e-mail: xjwang@xjtu.edu.cn
Search for other works by this author on:
Jun Li,
Jun Li
Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Search for other works by this author on:
Weitao Hou
Weitao Hou
Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Search for other works by this author on:
Junfei Zhou
Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Xinjun Wang
Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
e-mail: xjwang@xjtu.edu.cn
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
e-mail: xjwang@xjtu.edu.cn
Jun Li
Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Weitao Hou
Institute of Turbomachinery,
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
Shaanxi Engineering Laboratory of
Turbomachinery and Power Equipment,
Xi'an Jiaotong University,
Xi'an 710049, China
1Corresponding author.
Manuscript received July 5, 2018; final manuscript received December 14, 2018; published online January 11, 2019. Assoc. Editor: Riccardo Da Soghe.
J. Eng. Gas Turbines Power. Jul 2019, 141(7): 071004 (15 pages)
Published Online: January 11, 2019
Article history
Received:
July 5, 2018
Revised:
December 14, 2018
Citation
Zhou, J., Wang, X., Li, J., and Hou, W. (January 11, 2019). "Effects of Target Channel Shapes on Double Swirl Cooling Performance at Gas Turbine Blade Leading Edge." ASME. J. Eng. Gas Turbines Power. July 2019; 141(7): 071004. https://doi.org/10.1115/1.4042311
Download citation file:
Get Email Alerts
Shape Optimization of an Industrial Aeroengine Combustor to reduce Thermoacoustic Instability
J. Eng. Gas Turbines Power
Dynamic Response of A Pivot-Mounted Squeeze Film Damper: Measurements and Predictions
J. Eng. Gas Turbines Power
Review of The Impact Of Hydrogen-Containing Fuels On Gas Turbine Hot-Section Materials
J. Eng. Gas Turbines Power
Effects of Lattice Orientation Angle On Tpms-Based Transpiration Cooling
J. Eng. Gas Turbines Power
Related Articles
Enhancement of Impingement Cooling in a High Cross Flow Channel Using Shaped Impingement Cooling Holes
J. Turbomach (April,2010)
Flow Visualization of Axisymmetric Impinging Jet on a Concave Surface
J. Heat Transfer (August,2018)
Statistical Properties of Round, Square, and Elliptic Jets at Low and Moderate Reynolds Numbers
J. Fluids Eng (October,2017)
Experimental Investigation on the Heat Transfer of a Leading Edge Impingement Cooling System for Low Pressure Turbine Vanes
J. Heat Transfer (December,2010)
Related Chapters
Vortex-Induced Vibration
Flow Induced Vibration of Power and Process Plant Components: A Practical Workbook
Cavitating Structures at Inception in Turbulent Shear Flow
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Application of Conjugate Heat Transfer Models in External and Internal Flows
Applications of Mathematical Heat Transfer and Fluid Flow Models in Engineering and Medicine