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40 '2 20 HU-- -MIDSPAN TIP I I (a)MERIDIONAL AND PLAN VIEW. (b) BLADE 'EACNAMBER LINE DISTRIBUTION FOR HUB. MIDSPAN, AND TIP. (c) BLADE NORMAL THICKNESS DISTRIBUTION FOR HUB, MIDSPAN. AND TIP. Figure 2 Configuration of low-speed centrifugal compressor initial stage design. THROTTLE 200 - VALVE INLET SO ROTOR DIFFUSER VANES (23) -20 BLADES 60 /-- TIP z- 3.0 2.0 DIFFUSER VANES 0-o 0-50 AXIAL DISTANCE, cm MERIDIONAL VIEW 5 SPAE 550\ 76 °' l- '/ -- 20 PLAN VIEW ~ EQUIVALENT DIFFUSER FOR AREA RATIO CALCULATION ~CALCULT'O Although the virtues of the various types of diffusers used on centrifugal compressors - pipe, wedge, cambered vane - are extolled by various proponents, the area of basic interest is the region where the flow transitions from the somewhat axisymmetric impeller exit flow with potential perturbations from the diffuser vanes to a nearly one-dimensional flow in the diffuser channel downstream of the throat. Data obtained from the diffuser of a 4:1 pressure ratio centrifugal stage designed for automotive applications indicated that after the initial rapid adjustment of the flow around the uncovered region of the diffuser upstream of the throat, the isobars became nearly orthogonal to the diffuser channel mid-line. This same tendency was observed for the diffuser of Stage 1 at flow rates away from diffuser choke. The wedge diffuser of the LSCC is similar to that for Stage 2 and was designed with a-throat area consistent with a pressure recovery coefficient from the impeller exit to the throat of 0.20. 'Rechoice of axial tip clearance reflected the previous expe- rience obtained with small stages, such as Stage I in table 2. The closest clearance tested with that stage was 3.9% of exit blade height which was 0.02 cm. Also, since centrifugal stages tend to "flower" (i e., deflect axially) significandy with rotational speed, the actual running clearance at part-speed conditions can be much more than the design value. For example, for Stage 2 the design clearance was 2.5%, but the clearance should be about 3.3% at 80% design speed - a speed that might be typical of a cruise condition - if the change in deflection with speed is considered. Stage 4 suffered even more axial deflection because of its higher design speed and even though it was tested at 2.4% clearance, the calculated value at 80% speed would be more like 6.1% clearance if active clearance control were not used. The choice of what clearance to use for the LSCC became a matter of selecting a low clearance representative of large machines or a rather large clearance more representative of small machines (and part speed conditions). Since it was anticipated that the duration of the test program would be long term, it was decided to provide for flexibility in varying tip clearance by selecting a large clearance for initial tests and reducing it for later tests. Obviously, adding material such as balsa wood to the impeller tips is preferable to machining a 1360 kg impeller. (a) ORTION END OF LEADING- EDGE ELLIPSE I I r-MISPA VANELESS 1S0SPACE 1G0. 650 ________________________________________ 20 40 60 80 100 MERIDIONAL DISTANCE. PERCENt 4 -j 1.0 (C) 0 20 40 60 80 100PDF Image | NASA Low-Speed Centrifugal Compressor for 3-D Viscous Code
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