This study investigates the influence of incidence on convective heat transfer to highly curved surfaces of a film-cooled turbine rotor blade. A computational study of free-stream inviscid aerodynamics without cooling at various incidences is followed by well-documented measured heat transfer data sets. The heat transfer experiments are discussed for cases with and without film cooling, performed under realistic gas turbine flow conditions in the short-duration heat transfer facility of the von Karman Institute for Fluid Dynamics. The precise location of the stagnation point and the iso-Mach number contours in the passage for each incidence (−10, 0, 10, +15 deg) are presented for a nominal exit Mach number of 0.94. The free-stream mass flow rate was kept constant for each experiment at different incidence levels. Three rows of compound angled discrete cooling holes are located near the leading edge in a showerhead configuration. Two rows of staggered discrete cooling holes are located on the suction side and a single row of cooling holes is located on the pressure side. The short-duration measurements of quantitative wall heat fluxes on nearly isothermal blade surfaces both in the presence and absence of coolant ejection are presented. The study indicated that the change of the position of the stagnation point strongly altered the aerodynamic behavior and convective heat transfer to the blade in approximately the first 30 percent of both the pressure side and the suction side in the presence and absence of film cooling. The immediate vicinity of the stagnation point was not significantly affected by changing incidence without cooling. Transitional behavior both on the suction surface and on the pressure surface was significantly influenced by the changes in approaching flow direction. Flow separation associated with incidence variations was also observed. Extremely low levels of the convective heat transfer coefficients were experienced near the regions where small separation bubbles are located.
Skip Nav Destination
Article navigation
July 1991
Research Papers
Effect of Incidence on Wall Heating Rates and Aerodynamics on a Film-Cooled Transonic Turbine Blade
C. Camci,
C. Camci
The Pennsylvania State University, Aerospace Engineering Department, University Park, PA 16802
Search for other works by this author on:
T. Arts
T. Arts
The von Karman Institute for Fluid Dynamics, Turbomachinery Department, Rhode Saint Genese, Belgium
Search for other works by this author on:
C. Camci
The Pennsylvania State University, Aerospace Engineering Department, University Park, PA 16802
T. Arts
The von Karman Institute for Fluid Dynamics, Turbomachinery Department, Rhode Saint Genese, Belgium
J. Turbomach. Jul 1991, 113(3): 493-501 (9 pages)
Published Online: July 1, 1991
Article history
Received:
January 11, 1990
Online:
June 9, 2008
Citation
Camci, C., and Arts, T. (July 1, 1991). "Effect of Incidence on Wall Heating Rates and Aerodynamics on a Film-Cooled Transonic Turbine Blade." ASME. J. Turbomach. July 1991; 113(3): 493–501. https://doi.org/10.1115/1.2927901
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
Aerothermodynamics of
a High-Pressure Turbine Blade With Very High Loading and Vortex
Generators
J. Turbomach (January,2012)
Aerothermal Investigations of Tip Leakage Flow in Axial Flow Turbines—Part III: TIP Cooling
J. Turbomach (January,2009)
An Experimental and Numerical Investigation of Near Cooling Hole Heat Fluxes on a Film-Cooled Turbine Blade
J. Turbomach (January,1989)
Heat Transfer and Film Cooling of Blade Tips and Endwalls
J. Turbomach (July,2012)
Related Chapters
The Special Characteristics of Closed-Cycle Gas Turbines
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential