Affiliation:
1. Department of Mechanical & Aerospace Engineering, Carleton University, Ottawa, ON K1S 5B6, Canada
Abstract
Midspan measurements were made in a transonic wind tunnel for three high pressure turbine blade cascades at design incidence. The baseline profile is the midspan section of a high pressure turbine blade of fairly recent design. It is considered mid-loaded. To gain a better understanding of blade loading limits and the influence of loading distributions, the profile of the baseline airfoil was modified to create two new airfoils having aft-loaded and front-loaded pressure distributions. Tests were performed for exit Mach numbers between 0.6 and 1.2. In addition, measurements were made for an extended range of Reynolds numbers for constant Mach numbers of 0.6, 0.85, 0.95, and 1.05. At the design exit Mach number of 1.05, the aft-loaded airfoil showed a reduction of almost 20% in the total pressure losses compared with the baseline airfoil. However, it was also found that for Mach numbers higher than the design value the performance of the aft-loaded blade deteriorated rapidly. The front-loaded airfoil showed generally inferior performance compared with the baseline airfoil.
Reference20 articles.
1. Mayle, R. E.
, 1991, “The Role of Laminar-Turbulent Transition in Gas Turbine Engines,” ASME J. Turbomach., 113, pp. 509–537.
2. Abu-Ghannam, B. J., and Shaw, R., 1980, “Natural Transition of Boundary Layers—The Effects of Turbulence, Pressure Gradient and Flow History,” J. Mech. Eng. Sci., 22, pp. 213–228.
3. Sharma, O. P., Wells, R. A., Schlinker, R. H., and Bailey, D. A., 1982, “Boundary Layer Development on Turbine Airfoil Suction Surfaces,” ASME J. Eng., 104, pp. 698–706.
4. Gostelow, J. P., 1989, “Adverse Pressure Gradient Effects on Boundary Layer Transition in a Turbulent Free Stream,” Proc. 9th Int. Symp. On Air Breathing Engines, AIAA, Washington, DC, 2, pp. 1299–1306.
5. Gostelow, J. P., and Blunden, A. R., 1989, “Investigations of Boundary Layer Transition in an Adverse Pressure Gradient,” ASME J. Turbomach., 111, pp. 366–375.
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