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:'. LASERVELOCIMETRSYSTEM PROES 20 -. BLADES " . CLEARANCE J PROSE LOCATIONS f, SHROUDSTATICS SPINNER HUB SPINNER A,: ROTARTYABLE Z.SLIDE AVC LASER ""X.SLIOE Figure 6 Rotating frame toLad pressure and touateampcraturc rakes. distribution along the pressure tubing isused to correct the measured pressures for the centrifugal head effects due to the fluid in the pres- sure tubing between the static pressure measurement location and the ESP pressure sensor port • Ianddition to the aiove its-rumentation, windows are provided Primary measurement Pressure Calculated measurement Velocity Mnss now rate Pressurroatio Nominal value Percent uncertainty SHROUDDIFFUSEVRANE STATICPRESSURE PASSAGSETATICS STAT, PRESSURE TAP LOCATIONS. TYPICAL 10PLANES 23 DIFFUSERP VANES SHROUADNDNUBDIFFUSER VANEPASSAGSETATICS AK SURVEY DIFFUSEVRANESTATICS over the impeller inlet, knee, and .xit r.gions to allow for optical accesstotheflowfield(figure5).Theexitwindowcoversthe Pitch 0.4 Perent uncertainty 0.25 0,3 0.042 (iue.j extPoslton rotor uailing edge, the vaneless space, and the diffuser throat region. Laser anemometry and flow visualization are therefore possible. The ammonia-ozalid flow visualization technique will be used in both th impeller and diffuser. Fluorescing oil, liquid crystal sheets, and tufts will also be used in the diffuser. .1 6 Nominal value 100 m/see 30 k/,oc 1.13 MERIDIONAL ROTOR SECTION , . " WINDOWS Y-SUODE Figure 5 Low-spccd centrifugacolmpressor instrumentation. MEASUREMENT • TOTAL PRESSURAEND TEMPERATURE SPUORINVETYS MEASUREMENT UNCERTAINTIES Uncertainties determined for each of the primary and calculated measurements are listed in table 4. In addition to providing uncer- tainty estimates for measured and calculated parameters, indications of the repeatability and circumferential uniformity ofthe flow field which can be expected from the low speed centrifugal compressor are provided. The repeatibility of the data provides assessment of how well flow conditions can be matched from test to test. The degree of circumferential uniformity of the flowfield is important since most steady-flow CFD codes require axisymmetric boundary conditions. The normalized velocity profiles shown in figures 7 and 8 were acquired at four different circumferential locations over a one month period. These results therefore provide an indication of the repeatability of the measurements as well as the degree of circum- ferential uniformity in the impeller inlet and exit flow field. Tblc 4 Measurement uncertainties (95 %confidence interval). Temperature Swirl angle 288 "K 70 dog 1133ccmglmle 03.05 r 101325 N/ n 0.034 1.4PDF Image | NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code
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