This paper studies the effect of transonic flow velocity on local film cooling effectiveness distribution of turbine vane suction side, experimentally. A conduction-free Pressure Sensitive Paint (PSP) method is used to determine the local film cooling effectiveness. Tests were performed in a five-vane annular cascade at Texas A&M Turbomachinery laboratory blow-down flow loop facility. The exit Mach numbers are controlled to be 0.7, 0.9, and 1.1, from subsonic to transonic flow conditions. Three foreign gases N2, CO2 and Argon/SF6 mixture are selected to study the effects of three coolant-to-mainstream density ratios, 1.0, 1.5, and 2.0 on film cooling. Four averaged coolant blowing ratios in the range, 0.7, 1.0, 1.3 and 1.6 are investigated. The test vane features 3 rows of radial-angle cylindrical holes around the leading edge, and 2 rows of compound-angle shaped holes on the suction side. Results suggest that the PSP technique is capable of producing clear and detailed film cooling effectiveness contours at transonic condition. The effects of coolant to mainstream blowing ratio, density ratio, and exit Mach number on the vane suction-surface film cooling distribution are obtained, and the consequence results are presented and explained in this investigation.
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ASME Turbo Expo 2015: Turbine Technical Conference and Exposition
June 15–19, 2015
Montreal, Quebec, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5672-7
PROCEEDINGS PAPER
Film Cooling Effectiveness of Transonic Turbine Vane Suction Side With Compound-Angle Shaped Hole Configuration
Shang-Feng Yang,
Shang-Feng Yang
Texas A&M University, College Station, TX
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Je-Chin Han,
Je-Chin Han
Texas A&M University, College Station, TX
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Alexander MirzaMoghadam,
Alexander MirzaMoghadam
Honeywell Aerospace, Phoenix, AZ
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Ardeshir Riahi
Ardeshir Riahi
Honeywell Aerospace, Phoenix, AZ
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Shang-Feng Yang
Texas A&M University, College Station, TX
Je-Chin Han
Texas A&M University, College Station, TX
Alexander MirzaMoghadam
Honeywell Aerospace, Phoenix, AZ
Ardeshir Riahi
Honeywell Aerospace, Phoenix, AZ
Paper No:
GT2015-42184, V05BT12A005; 12 pages
Published Online:
August 12, 2015
Citation
Yang, S, Han, J, MirzaMoghadam, A, & Riahi, A. "Film Cooling Effectiveness of Transonic Turbine Vane Suction Side With Compound-Angle Shaped Hole Configuration." Proceedings of the ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. Volume 5B: Heat Transfer. Montreal, Quebec, Canada. June 15–19, 2015. V05BT12A005. ASME. https://doi.org/10.1115/GT2015-42184
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