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velocity ratio of 1.14. The blunt leading-edge case produced a peak velocity ratio of about 1.32 inthe same region. Blade Surface Loadings Loading diagrams for the radial rotor blade at the hub, midspan, and tip arepresentedinfigure17. Itisshownthatmostloadingisexertedinthe forward half of the blade. For the latter half of the blade where the flow is mostly in the axial direction, a small adverse loading occurs at the hub, and disappears by midspan. No Kutta condition is enforced by the DENTON code and the loading diagram at the tip section is slightly open at the trailing edge. CONCLUDING REMARKS Application of the DENTON code has been made to an experimental radial inflow turbine rotor. The rotor had 12 full blades thick enough to allow internal cooling passages and the trailing-edge ejection of coolant. It had unswept radial blades at the inducer inlet and large blockages resulting from the thick trailing edges. The rotor was also designed for a higher-than optimumworkfactorresultinginalarge,nonoptimumpositiveincidence. For this rotor, the fully three-dimensional DENTON code predicted an evolution of a passage vortex. Computed results also show highly twisted streamlines sug gesting that the quasi-three-dimensional analysis might not be valid for the flow through this radial turbine rotor passage. To get the solutions reported herein, it was necessary to use fine grid lines near the leading and trailing edges, to use cusps at the leading and trailing edges, and to extend the upstream computational domain beyond the rotor-inlet survey station of the experiment, which was very close to the leading edge. Since detailed flow measurements within the rotor blading itself are not available, the comparison of the computed results with the experimental data is limited to the data at rotor exit. The computed rotor-exit flow angles are generally underturned relative to the experimental values, especially near the hub region where the blockage at the trailing edge is very large. The computed radial distribution of the rotor-exit to turbine-inlet total pressure ratios are underpredicted for this exceptionally thick, highly loaded experimental rotor blade because of the errors inthe finite-difference approximations in the regions of the rapid flow adjustment and because of using the relatively coarser grids in the middle of the blade region where the flow passage is highly three-dimensional. Even with this extremely difficult geometry and flow field, the DENTON code predicted flow angles fairly well where trailing-edge blockage was not excessive. Certainly, itmust be used judiciously for such radial geometries. Additional experimental data are needed for more definitive assessment of the code. REFERENCES 1. Civinskas, K.C. and Povinelli, L.A., "Application of a Quasi-Three- Dimensional Inviscid Flow and Boundary Layer Analysis to the Hub-shroud Contouring of a Radial Turbine," AIAA Paper 84-1297, June 1984. 8PDF Image | 3-D Inviscid Analysis of Radial Turbine Flow
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