NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code

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NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code ( nasa-low-speed-centrifugal-compressor-3-d-viscous-code )

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Flo'4 at mid-pass5age ,...,rtt~FI flow a mid-passage Figure 9 Mcridion;l view of velocity vcctom from Moome's (1988) 3-D now * calculations of LSCC with 4% Up clearance and constant hcight vancless diffuser. shutdown for a scheduled one year rehabilitation on November 1, 1999, further investigation of the predicted shroud wall separation until after the shutdowii was not possible. We decided therefore, that the best time to effect any modifications to the compressor geometry would be during the facility shutdown. Two potential modifications to the low speed centrifugal com- pressor were considered; 1)reduce the impeller exit tip clearance, 2) increase the vaneless diffuser area contraction. Reduction of the im- peller tip clearance was considered appropriate since the low speed centrifugal compressor was initially designed with a uniform 4% exit1 tip clearance which, although not atypical of industry practice (see table 2 ), was on the high side. Before reducing the tip clearance, we asked industry for an opinion as to what level of tip clearance would be most representative of typical operating conditions. Based on in- dustry response, we reduced the tip clearance to a circumferentially uniform level from inlet to exit of 2% based on the impeller exit blade span by bonding balsa wood strips to the tip of the impeller. In-house CFD analysis, of the low speed centrifugal compressor with Figure to Merdlonal view of velocity vecrs from Moore's (1988) J-I) I0 calculations of LSCC with 4% Up clearance and modified vancless diffuser, iiS .. .I, fII ttt .. ,ttt~II1l~t, ..t. ,.,.ttr 1 ftt1 , 't'I'I Itt' z 1 V 5 0 40 0 nra 1 Rm/8)*11*-7 0 rrJL 30- r f 20 10 f 0 4J 0 SHROUD Preliminary Meagurement with Uncalibrated Probe 20 40 60 80 100 % IMMERSION Figure It Radial velocity distribution at impeller existtat2iao(n4%ticplearance). HUB

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