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Laser Anemometer Measurements of the Three-Dimensional Rotor Flow Field in the NASA Low-Speed Centrifugal Compressor Michael D. Hathaway Vehicle Propulsion Directorate U.S. Army Research Laboratory Lewis Research Center Cleveland, Ohio Randall M. Chriss, Anthony J. Strazisar, and Jerry R. Wood National Aeronautics and Space Administration Lewis Research Center Cleveland, A laser fringe anemometer low-speed centrifugal compressor (LSCC) rotor flow field. Measurements of the three-dimensional velocity field were ac- quired at several measurement planes upstream, within, and downstream of the rotor. Most of the data were collected at the design flow rate; a few selected additional measurements were made at a lower flow rate. The experimental configuration consisted of a backswept impeller followed by a vaneless diffuser. The rotor was de- signed for axial inlet flow, so there were no inlet guide vanes. This rotor-only configuration enabled the laser anemometer data to be compared with results from numerical flow analysis codes that assume the flow is steady in the reference frame of the rotor. In addition, the large size and low speed of the compressor generated large viscous regions, thus enabling near-wall details to be measured with laser anemometry. The resulting data provide an experimental data base with which to compare the results from three-dimensional viscous analysis codes. The laser anemometer surveys were conducted along axisymmetric surfaces of revolution that were constructed by a computational fluid dynamics (CFD) grid-generation routine so as to be approximately orthogonal to the casing and hub flow paths. Data were acquired at nominally 20 survey planes upstream, within, and downstream of the rotor. Within each survey plane, data were acquired, nominally, at 15 spanwise locations in intervals of 5-percent-of-span from the shroud. At each survey point within a measurement plane, the axial, ra- dial, and relative tangential velocity components were resolved at 1000 points across the rotor blade pitch. However, for pre- sentation purposes and to provide more manageable data sets, the results were routinely averaged to a resolution of 200 points across a rotor pitch. The laser anemometer survey data at fixed span locations are presented in the form of blade-to- blade plots of axial, radial, and relative tangential velocity, all normalized by the rotor exit tip speed. In addition, for all mea- surement planes there are wire-frame and contour plots of Ohio throughflow velocity and vector plots of secondary velocity, all normalized by the rotor exit tip speed. Spanwise pneumatic probe surveys of the total and static pressures, the total temperature, and the flow yaw and pitch angles were also performed at stations upstream and down- stream of the rotor. These probe survey data were used to cal- culate overall compressor performance. Both the survey data and performance data are included herein in tabular form and can be used to set boundary conditions for computational codes. Detailed descriptions of the blade and flow path geometry, as well as a complete set of the laser anemometer survey data, are available on magnetic medium upon request. Introduction Centrifugal compressors traditionally have not performed as well as their axial flow counterparts, partly because of our in- ability to predict their inherently complex three-dimensional viscous flow fields. With the development of three-dimen- sional Navier-Stokes codes for turbomachinery flow-field analysis, it became possible to predict such viscous flow fields. However, detailed experimental measurements with which to assess the limitations of the computational analyses are largely lacking. Several previous investigators have measured flow fields within unshrouded centrifugal compressor impellers. Eckardt's laser anemometer measurements in a radial-outflow impeller (1976) provided the first experimental evidence that in high- speed impellers a "wake" of low momentum fluid develops. At the impeller exit, the wake appears near the suction surface- shroud corner of the blade passage. However, Krain (1988), Krain and Hoffman (1989), Ahmed and Elder (1990), Sipos (1991), and Rohne and Banzhaf (1991) acquired laser an- emometer measurements in backswept impellers which indi- cated that, at the impeller exit, the wake appears near the shroud at midpitch. Summary was used to survey the NASAPDF Image | Laser anemometer measurements of the three-dimensional rotor flow
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