• Effects of Coolant Density Ratio on Film Cooling Performance on a Vane - Submitted for Presentation at the 2003 ASME Turbo Conference in Atlanta, June 2003
• The Effects of High Turbulence and Turbine Vane Film Cooling on the Dispersion of a Simulated Hot Streak - Submitted for Presentation at the 2003 ASME Turbo Conference in Atlanta, June 2003
• Computational Predictions of Endwall Film-Cooling for a First Stage Vane - Submitted for Presentation at the 2003 ASME Turbo Conference in Atlanta, June 2003
• Effects of Hot Streaks on Adiabatic Effectiveness for a Film Cooled Turbine Vane - Submitted for Approval for Conference Presentation at IGTI 2004, Vienna
• The Effects of the Vane and Mainstream Turbulence Level on Hot Streak Attenuation - Submitted for Approval for Conference Presentation at IGTI 2004, Vienna

Performing Member Contact:

David G. Bogard, Professor

University of Texas, Austin
Department of Mechanical Engineering
1 University Station C2200
Austin, TX 78712-0292
512-471-3128/FAX 512-471-8727
dbogard@mail.utexas.edu

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University of Texas, Austin

Experience

Aero/thermal studies turbine engine turbine sections. A wide range of studies have been completed in the area of turbine airfoil film cooling. Experimental studies include vane and blade leading edges, vane pressure and suction sides, and full coverage configurations. Special facilities are used to incorporate realistic airfoil geometries and high mainstream turbulence. Measurements include adiabatic effectiveness, heat transfer coefficients, thermal fields, and velocity fields for two-dimensional and three-dimensional regions. Computational studies have focused on the development of the TEXTAN CFD code for rapid analysis of the thermal fields associated with turbine airfoils.

Interest

Recent areas of interest include studies of conjugate heat transfer using models constructed of high conductivity materials. We are also involved in studies of roughness effects and partial hole blockage effects on film cooling performance.

Facility Information

The primary facilities for gas turbine aero/thermal research are two wind tunnels that have been specially modified to incorporate models of turbine vanes and blades. Large scale models are used in both facilities to good spatial resolution of the flow and thermal fields on the scale of the cooling holes used in film cooling. These facilities incorporate secondary flow systems that are cryogenically cooled to allow coolant flows to be cooled to an absolute temperature that is a factor of two smaller than the mainstream temperature. This enables film cooling studies using realistic density ratios for the coolant. The wind tunnels also incorporate free stream turbulence generators that allow mainstream turbulence as high as 20% to be used in experiments. One of the wind tunnels also incorporates a hot streak generator that allows a simulated hot streak to be positioned at varying pitch positions relative to the test vane.

Essentially adiabatic test models are used in conjunction with IR camera surface temperature measurement to obtain adiabatic effectiveness distributions. Heat transfer coefficient measurements are accomplished with constant heat flux surface foils. Velocity field measurements are made with a three-component laser Doppler velocimeter system which was specially designed for near wall measurements around the vane leading edge. Thermal field measurements are made using a miniature thermocouple rake manufactured in our lab.