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research-article

Turbine Vane Endwall Film Cooling Comparison From Five Film-Hole Design Patterns And Three Upstream Injection Angles

[+] Author and Article Information
Chao-Cheng Shiau

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX, 77843-3123, USA
joeshiau@tamu.edu

Izzet Sahin

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX, 77843-3123, USA
izzetsahin@tamu.edu

Nian Wang

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX, 77843-3123, USA
wangnian@tamu.edu

Dr. Je-Chin Han

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX, 77843-3123, USA
jc-han@tamu.edu

Hongzhou Xu

Solar Turbines Incorporated, 2200 Pacific Highway, San Diego, CA 92186
xu_hongzhou@solarturbines.com

Michael Fox

Solar Turbines Incorporated, 2200 Pacific Highway, San Diego, CA 92186
mikefox@solarturbines.com

1Corresponding author.

ASME doi:10.1115/1.4042057 History: Received July 03, 2018; Revised November 15, 2018

Abstract

The effects of upstream injection angle on film cooling effectiveness of a turbine vane endwall with various endwall film-hole designs were examined by applying PSP measurement technique. As the leakage flow from the slot between the combustor and the turbine vane is not considered an active source to protect the vane endwall in certain engine designs, discrete cylindrical holes are implemented near the slot to create an additional controllable upstream film to cool the vane endwall. Three potential injection angles were studied: 30o, 40o, and 50o. To explore the optimum endwall cooling design, five different film-hole patterns were tested: axial row, cross row, cluster, mid-chord row, and downstream row. Experiments were conducted in a four-passage linear cascade facility in a blowdown wind tunnel at the exit isentropic Mach number of 0.5 corresponding to inlet Reynolds number of 380,000 based on turbine vane axial chord length. A freestream turbulence intensity of 19% with an integral length scale of 1.7 cm was generated at the cascade inlet plane. Detailed film cooling effectiveness for each design was analyzed and compared at the design operation conditions (coolant mass flow ratio 1% and density ratio 1.5). The results are presented in terms of high-fidelity film effectiveness contours and laterally (spanwise) averaged effectiveness. This paper will provide the gas turbine designers valuable information on how to select the best endwall cooling pattern with minimum cooling air consumption over a range of upstream injection angle.

Copyright (c) 2018 by ASME
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