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.1983) have reported measurements of flows in centrifugal compres- sors which have shed light on many aspects of centrifugal compres- sor flow physics. Most of these investigations however, have lacked the detailed measurements required to assess the ability of three- dimensional viscous codes to accurately model the fundamental flow physics. Furthermore, none of the investigations yielded detailed in- formation within viscous regions (i e.,blade boundary layers). The NASA Low Speed Centrifugal Compressor (LSCC) was de- signed and built in order to obtain the detailed measurements which are required to assess hree-dimensional viscous codes and to de- velop more sophisticated models of the various physical phenomena occurring in centrifugal compressors. This paper describes the major components and instrumentation of the low speed centrifugal corn- pressor facility. Experimental investigations of inlet and exit flow uniformity, measurement repeatability and overall performance are also presented which demonstrate the high quality of the data which may be expected from this facility. The significance of synergism between computational fluid dynamic (CFD) analyses and experi- mentation throughout the development of the low speed centrifugal compressor facility is demonstrated. FACILITY Figure Idepicts the major elements of the low speed centrifugal compressor facility. Air is drawn in from a filtered vent in the roof past a bank of steam pipes and louvers designed to control the air temperature to within ± 1 *F for mass flows up to 45 kg/s. The flow then enters the facility room and is then drawn into the plenum through a bank of flow straighteners which are contained between two mesh screens. The air passes through a'specially designed bellmouth with a 10:1 area contraction. The turbulence levels at the bellmouth exit are expected to be less than I percent, and will be measured in the near future along with the impeller inlet turbulence profile. The flow then enters the compressor and exits through a specially designed throttle valve at the entrance to the collector. The throttle valve consists of two concentric rings with overlapping holes drilled in each ring which slide relative to each other to produce a throttle. This throttle valve design was chosen to minimize circumferential asymmetry in the exit static pressure distribution such as is typically found in scroll-type collectors. The bellmouth, inlet transition piece, and shroud flow path were machined together to minimize any boundary layer disturbance due to a step in the flow path. Altitude exhaust capability of 660 mm-Hg (26 in-Hg) of vacuum enables mass flow rates up to 45 kg/sec. A 1.115 MW (1500-hp) electric motor and gear reducer drives the facility to a maximum speed of 2400 rpm. A complete description of the facility is provided by Wood et al. (1983). TEST COMPRESSOR During the design of the low speed compressor several condi- tions were imposed. First, the design should reflect the geometric and dynamic parameters that were deemed to be representative of modern compressors and second, the blade lean should not be so severe that laser access would be precluded. The design parameters for the low speed centrifugal compressor are given in table I while table 2 shows a comparison of some low speed centrifugal compres- sor stage parameters with those from several high speed centrifugal VOLUTE COLLECTOR - COMPRESSOR ASSEMBLY I/ -AIR STRAIGHTENER BELLMOUTH- 7 / / TRANSITION PIECE --BELLMOUTH INLET I • , 2'Tin ,.- SLIP-RING ASSEMBLIES r-MOTOR 2.4 m BEOPLATE- BEDPLTE/-/- /1 L MOO STND SPEED EXHAUST DRIVE FLEXIBLE SEAL \PLENUM-,/ / BLOWER I MW PESR AE/ - VRAL PRESSURE RAKE LOCAION ---- /ALTITUDE MOTOR STAND I VARIABLE SHROUD-- , THROTTLE / VALVE I,/ / / // SENSOR t / -TORQUE GEARI BOX// COUPLING Figure I Low speed centrifugal compressor facility. 2 /PDF Image | NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code
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