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Test Rotor Instrumentation The test impeller (see fig. 2) is a backswept impeller with a design tip speed of | 53 m/sec. The impeller is followed by a able at stations upstream and downstream of the rotor (see vaneless diffuser that generates an axisymmetric outflow boundary condition, which is desirable for CFD analysis of an isolated blade row. The original vaneless diffuser was modified to eliminate a region of reverse flow that occurred on the back wall of the diffuser (Hathaway, Wood, and Wasserbauer (1992)). This modification ensured that there would be no backfiow at stations downstream of the impeller. The impeller has 20 full blades with a backsweep of 55 °. The inlet diameter is 0.870 m and the inlet blade height is 0.218 m. The exit diam- eter is 1.524 m and the exit blade height is 0.141 m. The clear- ance between the impeller blade tip and the shroud is a con- stant 2.54 mm from the impeller inlet to the impeller exit. This clearance is 1.8 percent of the blade height at the exit of the impeller. The blade surfaces are composed of straight-line ele- ments from hub to tip. This feature allowed the laser anemom- eter optical axis to be directed parallel to the blade surface, thereby facilitating laser anemometer measurement of veloci- ties close to the blade surfaces. The impeller surface finish is 64 gin. rms and the fillet radii are 9.525 mm. Blade coordinates at the design speed operating condition are given in table I for six blade sections (surfaces of revolu- tion) from hub to tip (i.e., blade section six is the physical blade tip). The nomenclature used in table I is shown in fig- ure 3. The origin of all blade geometry z-coordinates is at the intersection of the blade leading edge with the hub. The blade surface coordinates provided in table I are given at 75 points for each blade section and include definition of the blade lead- ing and trailing edges. Figure 4 shows profiles of three actual (as inspected) blade tips: one for the LSCC and two from high-speed impellers scaled to the same dimensions. Flow Path A meridional view of the LSCC flow path, which includes the locations of the aerodynamic probe survey stations and the vaneless diffuser hub and shroud contractions, is shown in fig- ure 5; the coordinates of the hub and shroud contours are pro- vided in table II. The origin of both the blade and the flow path z-coordinates is at the intersection of the blade leading edge with the hub flow path. Figure 6 shows the spanwise and streamwise locations at which laser anemometer data were acquired, with arrows de- noting the locations where such measurements were made at both design and off-design conditions. The station numbers are the streamwise indices of a body-fitted measurement grid that was used to position the laser measurement point within the impeller. The measurement grid used in this investigation divided the streamwise blade length into a series of quasi- orthogonal, or near-normal, cross-channel planes. fig. 5). Five-hole probes with self-nulling yaw capability (fig. 7) were used for all standard pneumatic probe surveys. These probes were calibrated in a steady flow duct in which the pressure and temperature could be accurately controlled. During calibration, the probe pitch angle was varied over a range of Mach numbers, and the results were used together with the five-hole probe measurements acquired in the com- pressor to extract total and static pressures and the pitch angle. Before a probe was installed in the compressor test rig, a check on the pitch and swirl aerodynamic zero angle was performed in a calibration jet. Surface static pressure taps.--Static pressure taps were provided along the shroud and rotor blade surfaces. Those on the rotor surface (see fig. 8) measured the rotor blade pressure distribution and provided the opportunity for ammonia--ozalid flow visualization. They were located along quasi-orthogonal measurement planes at nominally 5, 20, 50, 80, 93, and 97 per- cent of blade span from the hub. The quasi-orthogonal mea- surement planes were located at approximately 2.5, 5, 15, 30, 50, 70, 90, 95, and 98 percent of meridional distance. Table III gives the r,z coordinates of the center of each static pressure tap on the rotor blade surfaces. The r,z coordinates of the cen- ters of each shroud static pressure tap are given in table IV. Laser anemometer system .--The laser anemometer system used for the present investigation was a two-component laser fringe anemometer operating in on-axis backscatter mode. An argon-ion laser produced the 514.5-nm (green) and 488-nm (blue) wavelengths for the two orthogonai fringe systems. Fre- quency shifting was used in both fringe systems to provide di- rectional sensitivity for all velocity measurements. Because of the size of the compressor, a relatively long focal length of 733 mm was needed. The final focusing lens aperture was 155 mm. Beam expansion (3.75x) enhanced the system signal-to-noise ratio. The fringe spacing was 8.2 nm for the blue component and 8.6 nm for the green component. Optical access to the flow field was provided by three 3-mm-thick glass windows that conformed to the flow path in both the circumferential and streamwise directions (see fig. 9). The windows covered the inlet, knee, and exit regions of the impeller and the inlet of the vaneless diffuser. The window mounting frames prevented laser anemometer measurements from being made in four areas: ahead of station !8; between stations 95 and ! 10; between stations 135 and 156; and down- stream of station 188 (see fig. 6). Polystyrene latex (PSL) spheres, used as seed particles, were introduced into the flow stream via four spray nozzles located in the plenum. During the development of the seeding system, an aerodynamic particle sizer was used to ensure that the seed- ing system could deliver mono-disperse particles and that the liquid carrier was fully evaporated by the time the seed Pneumatic probes.--Spanwise probe traverses were avail-PDF Image | Laser anemometer measurements of the three-dimensional rotor flow
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