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B.3 Recommendations and Trouble-Shooting The faster fluid property subroutines should be used for stage design unless time is not a concern. Running RGRC on the NIST subroutines can take a few days. The best approach is to use the Gong subroutines for RGRC and then develop the performance map in RGRCMS with the NIST subroutines. RGRC will return a warning when the code operates out of the range of agreement between Gong’s subroutines and NIST values. The user should realize that this usually only occurs at very low mass flow rates, when the compressor is stalled anyway. A few data points outside the range of applicability will not be a problem if they occur within the range of choke and surge. There are common problems that arise in the use of RGRC and an inexperienced user may not have the compressor design intuition to develop a solution. These common problems, and their typical solutions, are listed here. Oftentimes, a designer will find that the solution to one problem is the cause of another. Below are some issues commonly encountered and some suggestions for new users to find solutions. Problem: Velocity at the diffuser outlet (V4) is too small. Solution: This problem will arise if the diffuser pressure recovery is too high. If the diffuser area ratio is very high, then the velocity at the outlet will necessarily be low. Lowering the diffuser area ratio will alleviate this problem. The velocity at the outlet must be maintained above some minimum, especially for multi-stage machines. If the outlet velocity from the first stage is very small, then the second stage is likely to stall. Problem: The stall margin for the operating point is too small. Solution: Stall will usually occur at the impeller outlet due to excessively large flow angles. This will result in incidence stall at the diffuser inlet as well. To eliminate this problem, the axial height of the blades at the impeller outlet will have to be decreased. One could also increase the number of blades at the outlet, increase the blade thickness, or divide the compressor into stages. If the diffuser stalls before the impeller stalls, the axial height of the blades can be increased, but the diffuser angle may have to be changed. Decreasing the axial height of the blades will have penalties in the losses however, and will reduce the margin to choking. Another option for avoiding stall is to design the system with an increased flow velocity at the impeller inlet. 139PDF Image | Supercritical Carbon Dioxide Cycle Analysis
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