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Three-dimensional vane and blade geometries, which were optimized for pressure distribution while meeting all design constraints, were obtained using a steady, inviscid flow solver. The results were then validated with a viscous flow solver. Endwall contouring of the vane and blade platforms was examined as a mechanism to increase efficiency, reduce circumferential flow distortion, and potentially increase structural strength. Endwall contouring as applied to the blade platform can be seen in Figure 2.1.3. Both two-dimensional and three-dimensional models were used to analyze the stress levels in the rotor using end wall contouring. Unexpected high hoop stress developed around the troughs and under the platform. Attempts to add mass under the rim resulted in an increase in bore stress, and did not relieve the stress on the upper surface of the platform. End wall contouring as a method of reducing bore stress was abandoned. Figure 2.1.3 Sample endwall contouring of blade platform The primary focus of the aerodynamic team turned to aerothermal analysis of the high pressure turbine stage including the effect of tip clearance, and more detailed transient analyses of both vane and blade for cold-day start-up and standard-day load-shed emergency shutdown conditions. The primary objective of the aerothermal analysis was to provide temperature and convective heat transfer coefficient boundary conditions for the structural analysis of the shroud. Earlier analyses of the turbine had been run without tip clearance since this greatly reduces the computational complexity of the problem. However, modeling of the tip flow is critical to an accurate assessment of the heat transfer to the shroud. In order to accurately resolve the flow in this region, an additional computational sector must be added to the model and the grids near the tip must be significantly refined. Because of this increase in the model size the run time increased to approximately 10 days with the model running in parallel on four processors. As in previous analyses, cases with both adiabatic and constant wall temperature boundary conditions were run to derive the local values of the convective heat transfer coefficient 22PDF Image | ADVANCED MICROTURBINE SYSTEMS Final Report for Tasks 1 Through 4 and Task 6
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