Detailed film cooling effectiveness distributions are measured on the leading edge of a rotating gas turbine blade with two rows (pressure-side row and suction-side row from the stagnation line) of holes aligned to the radial axis using the pressure sensitive paint (PSP) technique. Film cooling effectiveness distributions are obtained by comparing the difference of the measured oxygen concentration distributions with air and nitrogen as film cooling gas respectively and by applying the mass transfer analogy. Measurements are conducted on the first-stage rotor blade of a three-stage axial turbine at (positive off-design), (design), and (negative off-design), respectively. The effect of three blowing ratios is also studied. The blade Reynolds number based on the axial chord length and the exit velocity is 200,000 and the total to exit pressure ratio was 1.12 for the first-stage rotor blade. The corresponding rotor blade inlet and outlet Mach numbers are 0.1 and 0.3, respectively. The film cooling effectiveness distributions are presented along with discussions on the influence of rotational speed (off design incidence angle), blowing ratio, and upstream nozzle wakes around the leading edge region. Results show that rotation has a significant impact on the leading edge film cooling distributions with the average film cooling effectiveness in the leading edge region decreasing with an increase in the rotational speed (negative incidence angle).
Skip Nav Destination
e-mail: jc-han@tamu.edu
Article navigation
September 2006
This article was originally published in
Journal of Heat Transfer
Research Papers
Film Cooling Effectiveness on the Leading Edge Region of a Rotating Turbine Blade With Two Rows of Film Cooling Holes Using Pressure Sensitive Paint
Jaeyong Ahn,
Jaeyong Ahn
Department of Mechanical Engineering,
Texas A&M University
, College Station, TX 77843-3123
Search for other works by this author on:
M. T. Schobeiri,
M. T. Schobeiri
Department of Mechanical Engineering,
Texas A&M University
, College Station, TX 77843-3123
Search for other works by this author on:
Je-Chin Han,
Je-Chin Han
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:
Hee-Koo Moon
Hee-Koo Moon
Solar Turbines Incorporated
, 2200 Pacific Highway, San Diego, CA 92101
Search for other works by this author on:
Jaeyong Ahn
Department of Mechanical Engineering,
Texas A&M University
, College Station, TX 77843-3123
M. T. Schobeiri
Department of Mechanical Engineering,
Texas A&M University
, College Station, TX 77843-3123
Je-Chin Han
Department of Mechanical Engineering,
Texas A&M University
, College Station, TX 77843-3123e-mail: jc-han@tamu.edu
Hee-Koo Moon
Solar Turbines Incorporated
, 2200 Pacific Highway, San Diego, CA 92101J. Heat Transfer. Sep 2006, 128(9): 879-888 (10 pages)
Published Online: April 22, 2006
Article history
Received:
October 30, 2005
Revised:
April 22, 2006
Citation
Ahn, J., Schobeiri, M. T., Han, J., and Moon, H. (April 22, 2006). "Film Cooling Effectiveness on the Leading Edge Region of a Rotating Turbine Blade With Two Rows of Film Cooling Holes Using Pressure Sensitive Paint." ASME. J. Heat Transfer. September 2006; 128(9): 879–888. https://doi.org/10.1115/1.2241945
Download citation file:
Get Email Alerts
Cited By
Estimation of thermal emission from mixture of CO2 and H2O gases and fly-ash particles
J. Heat Mass Transfer
Non-Classical Heat Transfer and Recent Progress
J. Heat Mass Transfer
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)
Prediction of Film Cooling and Heat Transfer on a Rotating Blade Platform With Stator-Rotor Purge and Discrete Film-Hole Flows in a 1 - 1 2 Turbine Stage
J. Turbomach (October,2009)
Turbine Nozzle Endwall Film Cooling Study Using Pressure-Sensitive Paint
J. Turbomach (October,2001)
Related Proceedings Papers
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
A Simple Carburetor
Case Studies in Fluid Mechanics with Sensitivities to Governing Variables