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Next: Future Directions Up: INFLUENCE OF 3D HOT Previous: Numerical Results

Conclusions

Previous numerical and experimental studies, assuming adiabatic airfoil and end wall surfaces, have shown that combustor hot streaks can cause significant temperature increases along the pressure surface of first-stage turbine rotors. In the current investigation, the combined effects of combustor hot streaks and airfoil heat transfer have been studied. The predicted results indicate that full-impingement of the hot streak on the first-stage stator results in low levels of heat transfer on the second-stage stator. Relatively high heat transfer on the first-stage rotor is localized to the leading edge and hub vortex and tip leakage flow regions. It is expected that alignment of the hot streak with the mid-passage of the first-stage stator would result in significant pressure-surface heat transfer on the first-stage rotor. These are the areas of the rotor which have been shown experimentally to endure the greatest thermal stresses.



Karen L. Gundy-Burlet
Wed Apr 9 15:13:00 PDT 1997