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research-article

Large Eddy Simulation of the Laminar Heat Transfer Augmentation on the Pressure Side of a Turbine Vane Under Freestream Turbulence

[+] Author and Article Information
Yousef Kanani

Illinois Institute of Technology, Mechanical, Materials and Aerospace Engineering Dept., Chicago, IL, USA, 60616
ykanani@hawk.iit.edu

Dr. Sumanta Acharya

Illinois Institute of Technology, Mechanical, Materials and Aerospace Engineering Dept., Chicago, IL, USA, 60616
sacharya1@iit.edu

Forrest Ames

University of North Dakota, Mechanical Engineering Department Grand Forks, ND, USA 58202
forrest.ames@engr.und.edu

1Corresponding author.

ASME doi:10.1115/1.4041599 History: Received September 05, 2018; Revised September 24, 2018

Abstract

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 in the experimental measurements of Varty and Ames (2016). 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 maximum r.m.s 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.

Copyright (c) 2018 by ASME
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