Experimental data have shown that combustor temperature nonuniformities can lead to the excessive heating of first-stage rotor blades in turbines. This heating of the rotor blades can lead to thermal fatigue and degrade turbine performance. The results of recent studies have shown that variations in the circumferential location, or clocking, of the first-stage vane airfoils can be used to minimize the adverse effects of the hot streaks due to the hot fluid mixing with the cooler fluid contained in the vane wake. In addition, the effects of the hot streak/airfoil count ratio on the heating patterns of turbine airfoils have been quantified. In the present investigation, three-dimensional unsteady Navier–Stokes simulations have been performed for a single-stage high-pressure turbine geometry operating in high subsonic flow to study the effects of tip clearance on hot streak migration. Baseline simulations were initially performed without hot streaks to compare with the experimental data. Two simulations were then performed with a superimposed combustor hot streak; in the first the tip clearance was set at the experimental value, while in the second the rotor was allowed to scrape along the outer case (i.e., the limit as the tip clearance goes to zero). The predicted results for the baseline simulations show good agreement with the available experimental data. The simulations with the hot streak indicate that the tip clearance increases the radial spreading of the hot fluid, and increases the integrated rotor surface temperature compared to the case without tip clearance. [S0889-504X(00)02204-2]
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October 2000
Technical Papers
Effects of Tip Clearance on Hot Streak Migration in a High-Subsonic Single-Stage Turbine
Daniel J. Dorney,
Daniel J. Dorney
Virginia Commonwealth University, Department of Mechanical Engineering, Richmond, VA 23113
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Douglas L. Sondak
Douglas L. Sondak
Boston University, Office of Information Technology, Boston, MA 02215
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Daniel J. Dorney
Virginia Commonwealth University, Department of Mechanical Engineering, Richmond, VA 23113
Douglas L. Sondak
Boston University, Office of Information Technology, Boston, MA 02215
Contributed by the International Gas Turbine Institute and presented at the 45th International Gas Turbine and Aeroengine Congress and Exhibition, Munich, Germany, May 8–11, 2000. Manuscript recieved by the International Gas Turbine Institute February 2000. Paper No. 2000-GT-441. Review Chair: D. Ballal.
J. Turbomach. Oct 2000, 122(4): 613-620 (8 pages)
Published Online: February 1, 2000
Article history
Received:
February 1, 2000
Citation
Dorney, D. J., and Sondak, D. L. (February 1, 2000). "Effects of Tip Clearance on Hot Streak Migration in a High-Subsonic Single-Stage Turbine ." ASME. J. Turbomach. October 2000; 122(4): 613–620. https://doi.org/10.1115/1.1290399
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