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ITTA A A,~ ttI t 1~ f t A At t t ,~R/Rtip- 1.258 70.21 14 m/s F19tirc 12 Meridioitil view of vctouiy vctbors predicted by the E~awol 3-D vilCoul ntow Calculation or the LSCC with 11 lip Clearane thc reduced tip clearance was then initiated using the Dawes and Flah crxde3 to determine if a further modification to increase the vancles diffus~er area contraction was necessary. At the same time the low sped centrifugal compressor was reinstalld in the facility and test- ing was initiated with the reduced tip clearance impeller. Hereafter, all references to the low speed centrifugal compressor will be for-U the reduced tip clearance impeller. Figure 12~ snows a meidional view of velocity vectors at mid- pitch predicted by the Dawes code. The Dawes code was run20 with a 107 streamwise by 41 spanwise by 21 pitchwise grid with 3 control volumes in the clearance gap. The Dawes solution predicts bepteen to pcredic the meanuhdroed rad al lit Aprof isonte beptioen toe opcr onodhteashroud randihallc.t Apomaisothe impeller exit survey station, STA. 2a, is shown in figure 13 . The experimental results clearly do not indicate separation on either the hub or shroud surfaces as is predicted by the Dawes code. Since the Dawes code prediction showed that the hub separation began very close to the experimental survey station and that the shroud separation was confined to a thin layer, it seemed reasonable toIm expect that the survey probe might not be able to detect the separation rein.As aresult, it was decided to add a new aerodynamic survey location, STA. 2b, near the point at which the hub wall separation was predicted to reach it's maximum thickness (I e., at fl/Il 12S.In addition, flow tufts were taped to the laser window 80 40ii Vr (m/5) 01-"----- 0 -20 -4%0 20 R/t 1.6 9 SHROUD HUB Cd 112 7 , 1AI ci CFD, me/a CFD, men/an EXPERIMENT 40 60 eso 80 100 Ipllr exit saiaveotdtution 2(%ti lat~c) RR .6 L _PDF Image | NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code
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