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THREE-DIMENSIONAL INVISCID ANALYSIS OF RADIAL TURBINE FLOW AND A LIMITED COMPARISON WITH EXPERIMENTAL DATA Y.K. Choo National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio 44135 and K.C. Civinskas Propulsion Directorate U.S. Army Aviation Research and Technology Activity (AVSCOM) Lewis Research Center Cleveland, Ohio 44135 SUMMARY The three-dimensional inviscid DENTON code was used to analyze flow through a radial-inflow turbine rotor. Experimental data from the rotor are compared with analytical results obtained by using the code. The experimental data available for comparison are the radial distributions of circumferentially averaged values of absolute flow angle and total pressure downstream of the rotor exit. The computed rotor-exit flow angles are generally underturned relative to the experimental Values, which reflect the boundary-layer separa tion at the trailing edge and the development of wakes downstream of the rotor. The experimental rotor was designed for a higher-than-optimum work factor of 1.126 resulting in a nonoptimum positive incidence and causing a region of rapid flow adjustment and large velocity gradients. For this experimental rotor, the computed radial distribution of rotor-exit to turbine-inlet total pressure ratios are underpredicted due to the errors in the finite-difference approximations in the regions of rapid flow adjustment and due to using the relatively coarser grids in the middle of the blade region where the flow pas sage is highly three-dimensional. Additional results obtained from the three dimensional inviscid computation are also presented, but without comparison due to the lack of experimental data. These include quasi-secondary velocity vectors on cross-channel surfaces, velocity components on the meridional and blade-to-blade surfaces, and blade surface loading diagrams. Computed results show the evolution of a passage vortex and large streamline deviations from the computational streamwise grid lines. Experience gained from applying the code to a radial turbine geometry is also discussed. INTRODUCTION The radial-inflow turbine continues to be a candidate configuration for many small size applications ranging from ground transportation to space power. The rotor passages are highly three-dimensional and have low aspect ratios compared with axial turbines. Typical geometries, which turn flow through 900 of deflection in the meridional plane while simultaneously turning the flow in the blade-to-blade plane naturally induce large three-dimensional secondary flowsevenintheabsenceofviscouseffects. Eventhoughquasi-three dimensional techniques can provide valuable guidance for design analysis ofPDF Image | 3-D Inviscid Analysis of Radial Turbine Flow
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