This paper studies the effect of shock wave on turbine vane suction side film cooling using a conduction-free Pressure Sensitive Paint (PSP) technique. Tests were performed in a five-vane annular cascade with a blow-down flow loop facility. The exit Mach numbers are controlled to be 0.7, 1.1, and 1.3, from subsonic to transonic flow conditions. Two foreign gases N2 and CO2 are selected to study the effects of two coolant-to-mainstream density ratios, 1.0 and 1.5, on film cooling. Four averaged coolant blowing ratios in the range, 0.4 to 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 is an accurate technique capable of producing clear and detailed film cooling effectiveness contours at transonic flow conditions. At lower blowing ratio, film cooling effectiveness decreases with increasing exit Mach number. On the other hand, an opposite trend is observed at high blowing ratio. In transonic flow, the rapid rise in pressure caused by shock benefits film-cooling by deflecting the coolant jet toward the vane surface at higher blowing ratio. Results show that denser coolant performs better, typically at higher blowing ratio in transonic flow. Results also show that the optimum momentum flux ratio decreases with density ratio at subsonic condition. In transonic flow, however, the trend is reversed and the peak effectiveness values plateau over a long range of momentum flux ratio.
Skip Nav Destination
ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition
June 6–10, 2011
Vancouver, British Columbia, Canada
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5465-5
PROCEEDINGS PAPER
Influence of Shock Wave on Turbine Vane Suction Side Film Cooling With Compound-Angle Shaped Holes
D. P. Narzary,
D. P. Narzary
Texas A&M University, College Station, TX
Search for other works by this author on:
J. C. Han,
J. C. Han
Texas A&M University, College Station, TX
Search for other works by this author on:
A. V. Mirzamoghadam,
A. V. Mirzamoghadam
Honeywell International, Phoenix, AZ
Search for other works by this author on:
A. Riahi
A. Riahi
Honeywell International, Phoenix, AZ
Search for other works by this author on:
K. Liu
Texas A&M University, College Station, TX
D. P. Narzary
Texas A&M University, College Station, TX
J. C. Han
Texas A&M University, College Station, TX
A. V. Mirzamoghadam
Honeywell International, Phoenix, AZ
A. Riahi
Honeywell International, Phoenix, AZ
Paper No:
GT2011-45927, pp. 447-457; 11 pages
Published Online:
May 3, 2012
Citation
Liu, K, Narzary, DP, Han, JC, Mirzamoghadam, AV, & Riahi, A. "Influence of Shock Wave on Turbine Vane Suction Side Film Cooling With Compound-Angle Shaped Holes." Proceedings of the ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. Volume 5: Heat Transfer, Parts A and B. Vancouver, British Columbia, Canada. June 6–10, 2011. pp. 447-457. ASME. https://doi.org/10.1115/GT2011-45927
Download citation file:
46
Views
0
Citations
Related Proceedings Papers
Related Articles
Transonic Aerodynamic Losses Due to Turbine Airfoil, Suction Surface Film Cooling
J. Turbomach (April,2000)
Related Chapters
Thermodynamic Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Studies Performed
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
The Special Characteristics of Closed-Cycle Gas Turbines
Closed-Cycle Gas Turbines: Operating Experience and Future Potential