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DistrtbutloGs/ NASA LOW-SPEED CENTRIFUGAL COMPRESSOR Av. 11"ty Codes AND FUNDAMENTAL FLOW PHYSICS RESEARCH tind/or Speco1al a FOR 3-D VISCOUS CODE ASSESSMENT last M.D. Hathaway Propulsion Directorate U.S. Army Aviation Systems Command Cleveland, Ohio 44135 ABSTRACT A low speed centrifugal compressor facility recently built by the NASA Lewis Research Center is described. The purpose of this facility is to obtain detailed flow field measurements for computa- tional fluid dynamic code assessment and flow physics modelling in support of Arr.y and NASA efforts to advance small gas turbine en- gine technology. The facility is heavily instrumented with pressure and temperature probes, both in the stationary and rotating frames of reference, and has provisions for flow visualization and laser ye- locimetry. The facility will accommodate rotational speeds to 2400 rpm and is rated at pressures to 1.25 atm. The initial compressor stage being tested isg.eometrically and dynamically representative of modern high-performance centrifugal compressor stages with the exception of Mach number levels. Preliminary experimental inves- tigations of inlet and exit flow uniformity and measurement repeata- bility are presented. These results demonstrate the high quality of the data which may be expected from this facility. The significance of synergism between computational fluid dynamic analyses and exper- imentation throughout the development of the low speed centrifugal compressor facility is demonstrated. NOMENCLATURE b = Impeller exit blade height, cm 2 fs r t z * D H = Ideal head rise, m N = Q = R = U = w = Z = Subscripts 0 rotational speed, rad/sec Volumetric flow rate, ma/scC radius, cm rotor blade speed, m/sec Relative velocity, m/sec axial coordinate, cm = Impeller exit tip diameter, cm Centrifugal compressors are widely used in a variety of appli- cations because of their ability to achieve high pressure ratios in a relatively short axial distance and due to their rugged construction. Centrifugal compressors are characterized by long blade channels which have complex in- and out-of-plane turns with high curva- ture. Due to the complex turning of the flow and rotational forces, strong secondary flows are produced. These secondary flows, along with separated flow regions, lead to strong cross-flow velocity com- ponents which transport fluid with low momentum and high total- pressure loss into the main stream. Attempts to model the com- plex three-dimensional nature of the flow in centrifugal compressors have generally met with little success, although recently a number of investigators have produced numerical computations which show great promise (e g., Moore and Moore, 1989, 1990, Hah et al., 1988, 1989, Dawes, 1988). Designers of centrifugal turbomachines have therefore had to rely heavily on empiricism. As a result, centrifu- gal compressors tend to have lower efficiencies than their axial-flow counterparts. For significant improvements in the aerodynamic per- formance of centrifugal compressors to be realized a more detailed understanding of the fundamental flow physics is required. Syner- gism between experiments and computational analyses will undoubt- edly play a key role in developing this understanding. With the advent of more powerful computers and further de- velopment of three-dimensional Navier-Stokes codes, the numeri- cal prediction of centrifugal compressor flow fields has greatly im- proved. However, assessment of the ability of these predictions to accurately model the fundamental physics of centrifugal com- pressor flow fields is largely lacking. Krain and Hoffman (1989), Eckart (1976), Joslyn et al. (1990), Young et al. (1987), Japiske and Karon (1989), Hayami et al., (1984), Johnson and Moore (1980, plenum = impeller inlet survey station J.R. Wood NASA Lewis Research Center Cleveland, Ohio 44135 C.A. Wasserbauer Sverdrup Technology, ie. Lewis Research Center Group Cleveland Ohio 44135 = impeller exit survey station = free stream = radial direction = Impeller tip . = axialdirection INTRODUCTIONPDF Image | NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code
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