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materialrrivedatthecompressionrlet.Ineachbatchof PSL seed solution produced, the seed particles were near-perfect spheres, varying by less than 0.1 percent of diameter. All tests were conducted with PSL particles no larger than 1.1 lam nor smaller than 0.8 _m. Figure 10 shows a typical particle size distribution acquired by the aerodynamic particle sizer at the inlet of the rotor. Further details of the instrumentation, laser anemometer system, and seeding system can be found in Hathaway et al. (1993) and Wasserbauer and Hathaway (1993). Test Procedure The research operating point (flow rate and rotor speed) se- lected for the data presented herein was the National Advisory Committee on Aeronautics (NACA) standard-day sea-level- corrected condition of 30.0 kg/sec and 1862 rpm, which is near the design point condition. Additional data were acquired at the same rotor speed but a lower flow rate (off-design condition) of 23.6 kg/sec (i.e., 78.7-percent rhd ). The corrected mass flow and rotor rotational speed were continually monitored and adjusted as required to maintain a constant operating point. As data were acquired, the results were corrected to account for any changes in plenum condi- tions due to changes in atmospheric conditions. Performance Measurements The plenum total temperature was calculated from the area average of measurements from 10 thermocouples located along the leading edge of an aerodynamically shaped horizontal strut that spanned the plenum. The plenum total pressure was meas- ured by a pitot probe located at approximately midspan of the strut leading edge; it was checked against the average of four static pressure taps equally spaced around the circumference of the plenum. Mass flow was determined from a calibration curve of actual bellmouth mass flow (based on integrated pres- sure probe surveys at the bellmouth throat) versus theoretical mass flow (based on the average of eight static pressure taps equally spaced around the circumference of the bell- mouth throat), together with the plenum total pressure and temperature. Spanwise surveys of total and static pressures, total tempera- ture, swirl (yaw) angle, and pitch angle were conducted at sur- vey stations 1 and 2 (upstream and downstream of the rotor, respectively), as shown in figure 5. All spanwise surveys were conducted with self-hulling-yaw five-hole pressure probes with attached thermocouples (see fig.7). At stations 1 and 2, meas- urements were acquired at approximately 20 spanwise loca- tions, and the endwall boundary layers were resolved to within 1-percent-of-span from the endwalls. Inner- and outer-wall static pressures were also measured at stations I and 2. The overall pressure ratio was calculated from the plenum total pressure and the energy-average of the spanwise distribu- tion of total pressure at survey station 2. Efficiency was calcu- lated from torque measurements since the small temperature rise of the LSCC impeller caused a significant uncertainty in temperature-based efficiency. For some surveys, efficiency cal- culations were based on the plenum total temperature and the mass-average of the spanwise distribution of total temperature at survey station 2. Details of the averaging procedures used for overall total pressure and total temperature, as well as the calculation of efficiency, are given in the subsequent Calcula- tions Procedures Laser Anemometer Laser anemometer r,O,z and Wn coordinates (see fig.3). The r,O,z coordinates are locations in the laboratory frame of reference, whereas the Wn coordinate is in the rotor frame of reference according to coor- dinates of a body-fitted measurement grid. The measurement grid used in this investigation divided the streamwise blade length into a series of quasi-orthogonal, channel planes. or near-normal, cross- section. Measurements measurement locations are specified in The circumferential measurement acquired mined by using two digital shaft angle encoders (one for each laser anemometer channel) to generate a fixed number of pulses for each rotor revolution. The encoders were frequency agile pulse generators whose frequency was digitally phase- locked to a multiple of the frequency of a once-per-revolution signal from the rotor. The encoder pulses were accumulated in a counter that was zeroed at the start of each rotor revolution. When a laser velocity measurement occurred, the concurrent encoder count was recorded along with the velocity data. The encoder count thus indicated the circumferential location of the measurement relative to the once-per-revolution timing mark on the impeller. Measurements that occurred anywhere be- tween two adjacent encoder counts were assigned to the same measurement window Wn. Here Wn denotes, in the rotor frame of reference, the circumferential measurement location in win- dow counts relative to the local blade suction surface. Further details of this process are described by Strazisar et al. (1989) and Wood, Strazisar, and Hathaway (1990). The width of a window defined the minimum spatial resolu- tion of the data in the circumferential direction. It was, there- fore, advantageous to select the smallest window width possible while maintaining a reasonable total number of win- dows. In the present investigation, the encoders were set to generate 20 000 pulses for each rotor revolution. The circum- ferential location of the center of each laser anemometer mea- surement window was therefore known to a resolution of 1000 windows across each of the 20 impeller blade channels. How- ever, to produce a data set that would be more manageable and meet the needs of most users, the data were routinely averaged across adjacent windows to produce a resolution of 200 meas- urement windows per blade channel. These velocity data were then passage-averaged (see Calculation Procedures) across the 20 blade channels to yield a single velocity profile that was location by the of laser each individual anemometer velocity was deter-PDF Image | Laser anemometer measurements of the three-dimensional rotor flow
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