Film-cooling and heat transfer characteristics of a gas turbine blade tip with a suction side rail was investigated in a stationary 3-blade rectilinear cascade. Mounted at the end of a blow-down facility the cascade operated at inlet and exit Mach numbers of 0.29 and 0.75, respectively. The rail was marginally offset from the suction side edge of the tip and extended from the leading to the trailing edge. A total of 17 film-cooling holes were placed along the near-tip pressure side surface and 3 on the near-tip leading edge surface with the objective of providing coolant to the tip. The tip surface itself did not carry any film-cooling holes. Relatively high blowing ratios of 2.0, 3.0, 4.0, and 4.5 and three tip gaps of 0.87%, 1.6%, and 2.3% of blade span made up the test matrix. Pressure sensitive paint (PSP) and Thermo-Chromic Liquid Crystal (TLC) were the experimental techniques employed to measure film-cooling effectiveness and heat transfer coefficient, respectively. Results indicated that when the tip gap was increased, film-cooling effectiveness on the tip surface decreased and heat transfer to the tip surface increased. On the other hand, when the blowing ratio was increased, film effectiveness increased but the effect on heat transfer coefficient was relatively small. The highest heat transfer coefficient levels were found atop the suction side rail, especially in the downstream two-thirds of its length whereas the lowest levels were found on the tip floor in the widest section of the blade.
Skip Nav Destination
ASME Turbo Expo 2014: Turbine Technical Conference and Exposition
June 16–20, 2014
Düsseldorf, Germany
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4572-1
PROCEEDINGS PAPER
Turbine Blade Tip Film-Cooling and Heat Transfer Measurements at High Blowing Ratios
Diganta Narzary,
Diganta Narzary
Texas A&M University, College Station, TX
Search for other works by this author on:
Kevin Liu,
Kevin Liu
Texas A&M University, College Station, TX
Search for other works by this author on:
Je-Chin Han,
Je-Chin Han
Texas A&M University, College Station, TX
Search for other works by this author on:
Shantanu Mhetras,
Shantanu Mhetras
Siemens Energy, Orlando, FL
Search for other works by this author on:
Kenneth Landis
Kenneth Landis
Florida Turbine Technologies, Inc., Jupiter, FL
Search for other works by this author on:
Diganta Narzary
Texas A&M University, College Station, TX
Kevin Liu
Texas A&M University, College Station, TX
Je-Chin Han
Texas A&M University, College Station, TX
Shantanu Mhetras
Siemens Energy, Orlando, FL
Kenneth Landis
Florida Turbine Technologies, Inc., Jupiter, FL
Paper No:
GT2014-25793, V05BT13A025; 10 pages
Published Online:
September 18, 2014
Citation
Narzary, D, Liu, K, Han, J, Mhetras, S, & Landis, K. "Turbine Blade Tip Film-Cooling and Heat Transfer Measurements at High Blowing Ratios." Proceedings of the ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. Volume 5B: Heat Transfer. Düsseldorf, Germany. June 16–20, 2014. V05BT13A025. ASME. https://doi.org/10.1115/GT2014-25793
Download citation file:
77
Views
Related Proceedings Papers
Related Articles
Aerothermodynamics of
a High-Pressure Turbine Blade With Very High Loading and Vortex
Generators
J. Turbomach (January,2012)
Effect of Unsteady Wake With Trailing Edge Coolant Ejection on Film Cooling Performance for a Gas Turbine Blade
J. Turbomach (July,1999)
Heat Transfer and Film Cooling of Blade Tips and Endwalls
J. Turbomach (July,2012)
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Survey of Trace Metals in Distillate Fuels
Manual on Requirements, Handling, and Quality Control of Gas Turbine Fuel
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential