An experimental investigation to obtain detailed film cooling effectiveness distributions on a cooled turbine blade platform within a linear cascade has been completed. The Reynolds number of the freestream flow is , and the platform has a labyrinthlike seal upstream of the blades to model a realistic stator-rotor seal configuration. An additional coolant is supplied to the downstream half of the platform via discrete film cooling holes. The coolant flow rate through the upstream seal varies from 0.5% to 2.0% of the mainstream flow, while the blowing ratio of the coolant through the discrete holes varies from 0.5 to 2.0 (based on the mainstream velocity at the exit of the cascade). Detailed film cooling effectiveness distributions are obtained using the pressure sensitive paint (PSP) technique under a wide range of coolant flow conditions and various freestream turbulence levels (0.75% or 13.4%). The PSP technique clearly shows how adversely the coolant is affected by the passage induced flow. With only purge flow from the upstream seal, the coolant flow rate must exceed 1.5% of the mainstream flow in order to adequately cover the entire passage. However, if discrete film holes are used on the downstream half of the passage, the platform can be protected while using less coolant (i.e., the seal flow rate can be reduced).
Skip Nav Destination
e-mail: jc-han@tamu.edu
Article navigation
July 2008
Research Papers
Film Cooling Effectiveness Distributions on a Turbine Blade Cascade Platform With Stator-Rotor Purge and Discrete Film Hole Flows
Lesley M. Wright,
Lesley M. Wright
Department of Aerospace and Mechanical Engineering,
The University of Arizona
, Tucson, AZ 85721-0119
Search for other works by this author on:
Je-Chin Han
Je-Chin Han
Distinguished Professor and Marcus Easterling Endowed Chair
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering,
e-mail: jc-han@tamu.edu
Texas A&M University
, College Station, TX 77843-3123
Search for other works by this author on:
Lesley M. Wright
Department of Aerospace and Mechanical Engineering,
The University of Arizona
, Tucson, AZ 85721-0119
Je-Chin Han
Distinguished Professor and Marcus Easterling Endowed Chair
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering,
Texas A&M University
, College Station, TX 77843-3123e-mail: jc-han@tamu.edu
J. Turbomach. Jul 2008, 130(3): 031015 (10 pages)
Published Online: May 5, 2008
Article history
Received:
February 10, 2007
Revised:
February 28, 2007
Published:
May 5, 2008
Citation
Wright, L. M., Blake, S. A., and Han, J. (May 5, 2008). "Film Cooling Effectiveness Distributions on a Turbine Blade Cascade Platform With Stator-Rotor Purge and Discrete Film Hole Flows." ASME. J. Turbomach. July 2008; 130(3): 031015. https://doi.org/10.1115/1.2777186
Download citation file:
Get Email Alerts
The Cooling Effect of Combustor Exit Louver Scheme on a Transonic Nozzle Guide Vane Endwall
J. Turbomach (July 2025)
Aerodynamic Performance Evaluation of Subsonic Compressor Cascade Blade With Leading-Edge Damage
J. Turbomach (July 2025)
Thermohydraulic Performance and Flow Structures of Diamond Pyramid Arrays
J. Turbomach (July 2025)
Related Articles
Film-Cooling Effectiveness on a Rotating Turbine Platform Using Pressure Sensitive Paint Technique
J. Turbomach (October,2010)
Turbine Blade Platform Film Cooling With Typical Stator-Rotor Purge Flow and Discrete-Hole Film Cooling
J. Turbomach (October,2009)
Film Cooling Effect of Rotor-Stator Purge Flow on Endwall Heat/Mass Transfer
J. Turbomach (July,2012)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Introduction
Turbine Aerodynamics: Axial-Flow and Radial-Flow Turbine Design and Analysis
Introduction
Consensus on Operating Practices for Control of Water and Steam Chemistry in Combined Cycle and Cogeneration