Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique

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...

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Main Authors: Hui Du, Srinath V. Ekkad, Je-Chin Han, C. Pang Lee
Format: Article
Language:English
Published: Wiley 2001-01-01
Series:International Journal of Rotating Machinery
Subjects:
Online Access:http://dx.doi.org/10.1155/S1023621X01000367
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author Hui Du
Srinath V. Ekkad
Je-Chin Han
C. Pang Lee
author_facet Hui Du
Srinath V. Ekkad
Je-Chin Han
C. Pang Lee
author_sort Hui Du
collection DOAJ
description 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 0.4–1.2 for 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 highest at a blowing ratio of 0.8 for air injection and at a blowing ratio of 1.2 for Co2 injection. Such detailed results will help provide insight into the film cooling phenomena on a gas turbine blade.
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series International Journal of Rotating Machinery
spelling doaj-art-5ed97cd673724133b0211e30cde743d12025-02-03T07:25:59ZengWileyInternational Journal of Rotating Machinery1023-621X2001-01-017641542410.1155/S1023621X01000367Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image TechniqueHui Du0Srinath V. Ekkad1Je-Chin Han2C. Pang Lee3Schlumberger SPT Center, Rosharon, Texas, USAMechanical Engineering Department, Louisiana State University, Baton Rouge, Louisiana, USAMarcus C. Easterling Chair, Department of Mechanical Engineering, Texas A&M University, College Station, Texas, USAGE Aircraft Engines, Cincinnati, Ohio, USADetailed 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 0.4–1.2 for 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 highest at a blowing ratio of 0.8 for air injection and at a blowing ratio of 1.2 for Co2 injection. Such detailed results will help provide insight into the film cooling phenomena on a gas turbine blade.http://dx.doi.org/10.1155/S1023621X01000367Turbine bladeFilm coolingHeat transferFilm effectiveness.
spellingShingle Hui Du
Srinath V. Ekkad
Je-Chin Han
C. Pang Lee
Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique
International Journal of Rotating Machinery
Turbine blade
Film cooling
Heat transfer
Film effectiveness.
title Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique
title_full Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique
title_fullStr Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique
title_full_unstemmed Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique
title_short Detailed Film Cooling Measurements over a Gas Turbine Blade Using a Transient Liquid Crystal Image Technique
title_sort detailed film cooling measurements over a gas turbine blade using a transient liquid crystal image technique
topic Turbine blade
Film cooling
Heat transfer
Film effectiveness.
url http://dx.doi.org/10.1155/S1023621X01000367
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AT jechinhan detailedfilmcoolingmeasurementsoveragasturbinebladeusingatransientliquidcrystalimagetechnique
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