Vane pressure side heat transfer is studied numerically using large eddy simulation (LES) on an aft-loaded vane with a large leading edge over a range of turbulence conditions. Numerical simulations are performed in a linear cascade at exit chord Reynolds number of Re = 5.1 × 105 at low (Tu ≈ 0.7%), moderate (Tu ≈ 7.9%), and high (Tu ≈ 12.4%) freestream turbulence with varying length scales as prescribed by the experimental measurements of Varty and Ames (2016, “Experimental Heat Transfer Distributions Over an Aft Loaded Vane With a Large Leading Edge at Very High Turbulence Levels,” ASME Paper No. IMECE2016-67029). Heat transfer predictions on the vane pressure side are in a very good agreement with the experimental measurements and the heat transfer augmentation due to the freestream turbulence is well captured. At Tu ≈ 12.4%, freestream turbulence enhances the Stanton number on the pressure surface without boundary layer transition to turbulence by a maximum of about 50% relative to the low freestream turbulence case. Higher freestream turbulence generates elongated structures and high-velocity streaks wrapped around the leading edge that contain significant energy. Amplification of the velocity streaks is observed further downstream with max rms of 0.3 near the trailing edge but no transition to turbulence or formation of turbulence spots is observed on the pressure side. The heat transfer augmentation at the higher freestream turbulence is primarily due to the initial amplification of the low-frequency velocity perturbations inside the boundary layer that persist along the entire chord of the airfoil. Stanton numbers appear to scale with the streamwise velocity fluctuations inside the boundary layer.
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April 2019
Research-Article
Large Eddy Simulation of the Laminar Heat Transfer Augmentation on the Pressure Side of a Turbine Vane Under Freestream Turbulence
Yousef Kanani,
Yousef Kanani
Materials and Aerospace
Engineering Department,
Illinois Institute of Technology Mechanical,
Chicago, IL 60616
e-mail: ykanani@hawk.iit.edu
Engineering Department,
Illinois Institute of Technology Mechanical,
Chicago, IL 60616
e-mail: ykanani@hawk.iit.edu
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Sumanta Acharya,
Sumanta Acharya
Materials and Aerospace
Engineering Department,
Illinois Institute of Technology Mechanical,
Chicago, IL 60616
e-mail: sacharya1@iit.edu
Engineering Department,
Illinois Institute of Technology Mechanical,
Chicago, IL 60616
e-mail: sacharya1@iit.edu
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Forrest Ames
Forrest Ames
Mechanical Engineering Department,
University of North Dakota,
Grand Forks, ND 58202
e-mail: forrest.ames@engr.und.edu
University of North Dakota,
Grand Forks, ND 58202
e-mail: forrest.ames@engr.und.edu
Search for other works by this author on:
Yousef Kanani
Materials and Aerospace
Engineering Department,
Illinois Institute of Technology Mechanical,
Chicago, IL 60616
e-mail: ykanani@hawk.iit.edu
Engineering Department,
Illinois Institute of Technology Mechanical,
Chicago, IL 60616
e-mail: ykanani@hawk.iit.edu
Sumanta Acharya
Materials and Aerospace
Engineering Department,
Illinois Institute of Technology Mechanical,
Chicago, IL 60616
e-mail: sacharya1@iit.edu
Engineering Department,
Illinois Institute of Technology Mechanical,
Chicago, IL 60616
e-mail: sacharya1@iit.edu
Forrest Ames
Mechanical Engineering Department,
University of North Dakota,
Grand Forks, ND 58202
e-mail: forrest.ames@engr.und.edu
University of North Dakota,
Grand Forks, ND 58202
e-mail: forrest.ames@engr.und.edu
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received September 5, 2018; final manuscript received September 24, 2018; published online January 21, 2019. Editor: Kenneth Hall.
J. Turbomach. Apr 2019, 141(4): 041004 (12 pages)
Published Online: January 21, 2019
Article history
Received:
September 5, 2018
Revised:
September 24, 2018
Citation
Kanani, Y., Acharya, S., and Ames, F. (January 21, 2019). "Large Eddy Simulation of the Laminar Heat Transfer Augmentation on the Pressure Side of a Turbine Vane Under Freestream Turbulence." ASME. J. Turbomach. April 2019; 141(4): 041004. https://doi.org/10.1115/1.4041599
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