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Problem: Choke occurs too soon. Solution: Choke is likely to occur at the vaned diffuser inlet. At this location, the flow must not encounter an excessive area reduction, or the velocity will approach the critical velocity. To solve this problem, the vaneless space could be made longer or wider. Widening of the vaneless space could be accomplished by increasing the clearance or the axial blade height. Increasing the input variable R3/R2 will increase the pressure recovery of the vaneless space, decreasing the flow velocity and avoiding choke. The problem can be avoided by increasing the diffuser area ratio also. By increasing the area ratio, pressure recovery is improved. Thus, the code will not design the impeller quite as large and flow velocities will be reduced as a result. Problem: The operating range at high speeds is small or non-existent. Solution: This problem can occur due to impeller or diffuser dimensions. Decreasing the diffuser area ratio or increasing the backsweep angle will expand the operating range. Typically, backsweep angle will only achieve so much. Beyond a certain point, compressor performance is not changed significantly. Experience has shown this angle to be about 50 degrees for most designs. Problem: The efficiency is unappealingly low. Solution: The compressor could be divided into multiple stages or the backsweep of the impeller could be decreased. Decreasing the backsweep angle will typically result in rapidly shrinking operating range. It is often best to attempt a design that will give an acceptable operating range and then tweak parameters to achieve a decent efficiency without compromising the operating range much. Efficiency will depend strongly on the size of the impeller and flow velocity. Problem: A multi-stage design has an extremely narrow operating range Solution: Usually the problem is caused by surge in the second or subsequent stage. This is due to off-design losses in the first stage magnifying the effects of reduced flow velocity in the down-stream stages. Second and subsequent stages should be designed with special consideration for the margin to stall. Usually, improving on a stage design will have a direct effect on the entire compressor’s operation. In other words, if the second stage is improved such that it has a higher stall margin alone, the multi-stage compressor will be less likely to exhibit stall in the second stage. Inevitably, the operating range of the multi-stage compressor will be narrower than that of any one stage. The designer must make a trade-off between operating range and total compressor efficiency. 140PDF Image | Supercritical Carbon Dioxide Cycle Analysis
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