Experiments were performed to study the effect of film hole row location on local film effectiveness distribution of a turbine blade model with air or CO2 film injection. Tests were performed on a five-blade linear cascade at the chord Reynolds number of 3.0 × 105 at the cascade inlet. A combination of turbulence grid and unsteady wake was used to create a higher free-stream turbulence level. The test blade had three rows of film holes in the leading edge region and two rows each on the pressure and suction surfaces. Film hole row locations were set by leaving the film holes at that row location open and covering the remaining rows. In addition, the additive nature of film cooling on the turbine blade model was examined by comparing the measured film effectiveness with the predicted effectiveness from the superposition method. Results show that injection from a different film hole row location provides a different effectiveness distribution on pressure and suction surfaces depending on local mainstream velocity and blade curvature. In most cases, the superposition method holds downstream of the last film hole row.
Skip Nav Destination
Article navigation
Research Papers
Effect of Film Hole Row Location on Film Effectiveness on a Gas Turbine Blade
H. Wanda Jiang,
H. Wanda Jiang
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
Search for other works by this author on:
J.-C. Han
J.-C. Han
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
Search for other works by this author on:
H. Wanda Jiang
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
J.-C. Han
Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123
J. Heat Transfer. May 1996, 118(2): 327-333 (7 pages)
Published Online: May 1, 1996
Article history
Received:
August 1, 1994
Revised:
February 1, 1996
Online:
December 5, 2007
Connected Content
A companion article has been published:
Unsteady Boundary Layers on a Flat Plate Disturbed by Periodic Wakes: Part II—Measurements of Unsteady Boundary Layers and Discussion
Citation
Jiang, H. W., and Han, J. (May 1, 1996). "Effect of Film Hole Row Location on Film Effectiveness on a Gas Turbine Blade." ASME. J. Heat Transfer. May 1996; 118(2): 327–333. https://doi.org/10.1115/1.2825848
Download citation file:
Get Email Alerts
Cited By
On Prof. Roop Mahajan's 80th Birthday
J. Heat Mass Transfer
Thermal Hydraulic Performance and Characteristics of a Microchannel Heat Exchanger: Experimental and Numerical Investigations
J. Heat Mass Transfer (February 2025)
Related Articles
Combined Effect of Grid Turbulence and Unsteady Wake on Film Effectiveness and Heat Transfer Coefficient of a Gas Turbine Blade With Air and CO 2 Film Injection
J. Turbomach (July,1997)
Effect of Unsteady Wake on Detailed Heat Transfer Coefficient and Film Effectiveness Distributions for a Gas Turbine Blade
J. Turbomach (October,1998)
Unsteady Wake Over a Linear Turbine Blade Cascade With Air and CO 2 Film Injection: Part II—Effect on Film Effectiveness and Heat Transfer Distributions
J. Turbomach (October,1994)
Turbine Separation Control Using Pulsed Vortex Generator Jets
J. Turbomach (April,2001)
Related Proceedings Papers
Related Chapters
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Thermodynamic Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential