An Infrared Technique for Evaluating Turbine Airfoil Cooling Designs

Journal of Turbomachinery - Tập 122 Số 1 - Trang 170-177 - 2000
Patrick C. Sweeney1, James F. Rhodes2
1Rolls-Royce Allison, Indianapolis, IN 46206
2Allison Advanced Development Company, Indianapolis, IN 46206

Tóm tắt

An experimental approach is used to evaluate turbine airfoil cooling designs for advanced gas turbine engine applications by incorporating double-wall film-cooled design features into large-scale flat plate specimens. An infrared (IR) imaging system is used to make detailed, two-dimensional steady-state measurements of flat plate surface temperature with spatial resolution on the order of 0.4 mm. The technique employs a cooled zinc selenide window transparent to infrared radiation and calibrates the IR temperature readings to reference thermocouples embedded in each specimen, yielding a surface temperature measurement accuracy of ±4°C. With minimal thermocouple installation required, the flat plate/IR approach is cost effective, essentially nonintrusive, and produces abundant results quickly. Design concepts can proceed from art to part to data in a manner consistent with aggressive development schedules. The infrared technique is demonstrated here by considering the effect of film hole injection angle for a staggered array of film cooling holes integrated with a highly effective internal cooling pattern. Heated free stream air and room temperature cooling air are used to produce a nominal temperature ratio of 2 over a range of blowing ratios from 0.7 to 1.5. Results were obtained at hole angles of 90 and 30 deg for two different hole spacings and are presented in terms of overall cooling effectiveness. [S0889-504X(00)01901-2]

Từ khóa


Tài liệu tham khảo

Moon, H. K., and Glezer, B., 1996, “Application of Advanced Experimental Techniques in the Development of a Cooled Turbine Nozzle,” ASME Paper No. 96-GT-233.

Scherer, V., Wittig, S., Morad, K., and Mikhael, N., 1991, “Jets in a Crossflow: Effects of Hole Spacing to Diameter Ratio on the Spatial Distribution of Heat Transfer,” ASME Paper No. 91-GT-356.

Martiny, M., Schulz, A., and Wittig, S., 1995, “Full-Coverage Film Cooling Investigations: Adiabatic Wall Temperatures and Flow Visualization,” ASME Paper No. 95-WA/HT-4.

Wittig, S., Schulz, A., Gritsch, M., and Thole, K. A., 1996, “Transonic Film-Cooling Investigations: Effects of Hole Shapes and Orientations,” ASME Paper No. 96-GT-222.

Martiny, M., Schulz, A., Wittig, S., and Dilzer, M., 1997, “Influence of a Mixing-Jet on Film Cooling,” ASME Paper No. 97-GT-247.

Sen, B., Schmidt, D. L., and Bogard, D. G., 1996, “Film Cooling With Compound Angle Holes: Heat Transfer,” ASME J. Turbomach., 118, pp. 800–806.

Schmidt, D. L., Sen, B., and Bogard, D. G., 1996, “Film Cooling With Compound Angle Holes: Adiabatic Effectiveness,” ASME J. Turbomach., 118, pp. 807–813.

Schmidt, D. L., Sen, B., and Bogard, D. G., 1996, “Effects of Surface Roughness on Film Cooling,” ASME Paper No. 96-GT-299.

Schmidt, D. L., and Bogard, D. G., 1996, “Effects of Free-Stream Turbulence and Surface Roughness on Film Cooling,” ASME Paper No. 96-GT-462.

Reilly, R. S., 1996, “Advanced Film Cooling Rig Development and Test Results,” NASA Contractor Report #204136, Aug., limited distribution.

Martiny, M., Schulz, A., and Wittig, S., 1997, “Mathematical Model Describing the Coupled Heat Transfer in Effusion Cooled Combustor Walls,” ASME Paper No. 97-GT-329.

Ballal, D. R., and Lefebvre, A. H., 1972, “A Proposed Method for Calculating Film-Cooled Wall Temperatures in Gas Turbine Combustion Chambers,” ASME Paper No. 72-WA/HT-24.

Ballal, D. R., and Lefebvre, A. H., 1973, “Film-Cooling Effectiveness in the Near Slot Region,” ASME J. Heat Transfer, 95, pp. 265–266.

Stollery, J. L., and El-Ehwany, A. A. M., 1967, “On the Use of a Boundary Layer Model for Correlating Film-Cooling Data,” Int. J. Heat Mass Transf., 10, pp. 101–105.

Dieck, R. H., 1992, Measurement Uncertainty Methods and Applications, Instrument Society of America, pp. 91–112.

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Journal of Turbomachinery

Tập 122 Số 1

170-177

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