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research-article

Film Cooling Effectiveness Comparison on Full-Scale Turbine Vane Endwalls Using PSP Technique

[+] 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

Andrew F Chen

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

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

Salam Azad

Siemens Energy, Inc., Orlando, FL, USA
salam.azad@siemens.com

Ching-Pang Lee

Siemens Energy, Inc., Orlando, FL, USA
ching-pang.lee@siemens.com

1Corresponding author.

ASME doi:10.1115/1.4038278 History: Received September 19, 2017; Revised October 04, 2017

Abstract

Turbine vane endwalls are highly susceptible to intensive heat load due to their large exposed area and complex flow field especially for the first-stage of the vane. Therefore, a suitable film cooling design that properly distributes the given amount of coolant is critical to keep the vane endwall from failure at the same time to maintain a good balance between manufacturing cost, performance, and durability. This work is focused on film cooling effectiveness evaluation on full-scale heavy duty turbine vane endwall and the performance comparison with different film cooling pattern designs in the literature. The area of interest of this study is on the inner endwall (hub) of turbine vane. Tests were performed in a three-vane annular sector cascade under the mainstream Reynolds number 350,000; the related inlet Mach number is 0.09 and the freestream turbulence intensity is 12%. Two variables, coolant-to-mainstream mass flow ratios (MFR = 2%, 3%, 4%) and density ratios (DR = 1.0, 1.5) are investigated. The conduction-error free Pressure-sensitive paint (PSP) technique is utilized to evaluate the local flow behavior as well as the film cooling performance. The presented results are expected to provide the gas turbine engine designer a direct comparison between two film-hole configurations on a full-scale vane endwall under the same amount of coolant usage.

Siemens AG
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