Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image TechniqueReport as inadecuate




Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique - Download this document for free, or read online. Document in PDF available to download.

International Journal of Rotating Machinery - Volume 7 2001, Issue 6, Pages 415-424



Schlumberger SPT Center, Rosharon, Texas, USA

Mechanical Engineering Department, Louisiana State University, Baton Rouge, Louisiana, USA

Marcus C. Easterling Chair, Department of Mechanical Engineering, Texas A&M University, College Station, Texas, USA

GE Aircraft Engines, Cincinnati, Ohio, USA

Mechanical Engineering Dept., Louisiana State University, Baton Rouge 70803, LA, USA

Revised 10 July 2001

Copyright © 2001 Hindawi Publishing Corporation. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

Detailed heat transfer coefficient and film effectiveness distributions over a gas turbine blade with film cooling are obtained using a transient liquid crystal image technique. The test blade has three rows of film holes on the leading edge and two rows each on the pressure and suction surfaces. A transient liquid crystal technique maps the entire blade midspan region, and helps provide detailed measurements, particularly near the film hole. Tests were performed on a five-blade linear cascade in a low-speed wind tunnel. The mainstream Reynolds number based on cascade exit velocity is 5.3×105. Two different coolants air and Co2 were used to simulate coolant density effect. Coolant blowing ratio was varied between 0.8 and 1.2 for air injection and 0.4–1.2for Co2 injection. Results show that film injection promotes earlier laminar-turbulent boundary layer transition on the suction surface and also enhances local heat transfer coefficients up to 80% downstream of injection. An increase in coolant blowing ratio produces higher heat transfer coefficients for both coolants. This effect is stronger immediately downstream of injection holes. Film effectiveness is highestat a blowing ratio of 0.8 for air injection and at a blowingratio of 1.2 for Co2 injection. Such detailed results will help provide insight into the film cooling phenomena on a gas turbine blade.





Author: Hui Du, Srinath V. Ekkad, Je-Chin Han, and C. Pang Lee

Source: https://www.hindawi.com/



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