Calculations were performed to simulate the tip flow and heat transfer on the GE-E3 first-stage turbine, which represents a modern gas turbine blade geometry. Cases considered were a smooth tip, 2 percent recess, and 3 percent recess. In addition, a two-dimensional cavity problem was calculated. Good agreement with experimental results was obtained for the cavity calculations, demonstrating that the k–ω turbulence model used is capable of representing flows of the present type. In the rotor calculations, two dominant flow structures were shown to exist within the recess. Also areas of large heat transfer rate were identified on the blade tip and the mechanisms of heat transfer enhancement were discussed. No significant difference in adiabatic efficiency was observed for the three tip treatments investigated.

Issue Section:
Research Papers
Topics:
Heat transfer, Rotors, Flow (Dynamics), Blades, Cavities, Turbulence, Gas turbines, Geometry, Turbines
1.
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2.
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3.
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5.
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7.
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8.
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11.
Menter, F. R., 1993, “Zonal Two-Equation k–ω Turbulence Models for Aerodynamic Flows,” Paper No. AIAA-93-2906.
12.
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Chyu
 
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13.
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14.
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18.
Yang, T. T., and Diller, T. E., 1995, “Heat Transfer and Flow for a Grooved Turbine Blade Tip in a Transonic Cascade,” ASME Paper No. 95-WA/HT-29.
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