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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| Format: | Article |
| Language: | English |
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Wiley
2001-01-01
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| Series: | International Journal of Rotating Machinery |
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| Online Access: | http://dx.doi.org/10.1155/S1023621X01000367 |
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| _version_ | 1832545370537721856 |
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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. |
| format | Article |
| id | doaj-art-5ed97cd673724133b0211e30cde743d1 |
| institution | Kabale University |
| issn | 1023-621X |
| language | English |
| publishDate | 2001-01-01 |
| publisher | Wiley |
| record_format | Article |
| 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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