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out that station 3 is very close to the leading edge of the rotor blade and station4is2.8cmdownstreamfromthetrailingedge. Inthiscase,even though the velocity field converged, examination of results indicated that the results were not correct. Because the upstream boundary was very close to the leading edge and the rotor-inlet absolute flow angle at station 3 was specified and fixed, both flow direction and velocity rapidly changed around the leading edge, especially on the suction side. This rapid change in direction and mag nitude evidently caused errors Inthe finite-difference approximations, which are manifested as stagnation pressure changes in the flow. When this situation is expected, users should check the ratios of the computed pressure to ideal pressure obtained from an isentropic process. These computed to ideal pressure ratiosatallgridpointsareavailableasapartofoutput. Ifthesepressure ratios are far from unity, close scrutiny of results isneeded. Further dis cussions on the entropy and total pressure changes in the time marching scheme can be found in reference 6. Three actions were taken to correct the situation. First, the pitchwise spacing of grid lines was packed near the blade surfaces in addition to the streamwise grid packing around the leading and trailing edges, following the suggestions made by Denton and Singh inreference 5. Second, the upstream region of the computational domain was extended beyond station 3 by using a larger number of grids and variable streamwise spacing. Third, cusps were used at the leading and trailing edges to reduce the changes in entropy and total pressure due to the errors in finite-differencing scheme around these regions. The results presented in this paper were obtained with these changes. RESULTS Flow Angle Figure 7 shows the calculated absolute flow angle distribution on the cross-channel surface at station 4. To compare with experimental data, these flow angles were circumferentially mass averaged at each grid location between hub and shroud. The radial distribution of these averaged absolute flow angles are then compared with the experimental data in figure 8. Figure 8(a) shows a comparison of the computed rotor exit flow angles with the experimental data. Two computed cases are those with the blunt and rounded leading edges shown in figure 6. Both cases used cusps at the trailing edges and the experimental operating conditions presented intable I. The computed rotor-exit flow angles are underturned relative to the experimental data, particularly near the hub. This large deviation of the computed flow angles near the hub from the experimental data could be anticipated. In the actual experiment, a flow separation off the trailing edge and a development of strong wakes could be anticipated due to the large trailing-edge blockage (78.7percentatthehub). Obviously,theseeffectsarenotincludedinthe inviscid analysis, and the flow is diffused without separation in the calcula tion. The case with rounded leading edges shows a flatter distribution than the result of the blunt leading-edge case. Figure 8(6) shows the effect of 20 reduction in the rotor-inlet absolute flow angle towards optimum incident angle of this rotor design. This is shown usingthebluntleading-edgecase; Withthereducedinletflowanglethe rotor-exit flow angles are overturned relative to the experimental values in 5PDF Image | 3-D Inviscid Analysis of Radial Turbine Flow
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