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Stall could also be experienced by an extreme flow incidence at the diffuser, but experimental data determining where that flow angle lies for CO2 is not available. In practice, the first two conditions above are sufficiently limiting that severe negative incidence does not occur at the diffuser inlet. Choke occurs when the flow velocity at any point rises above the critical velocity or when losses in the impeller cause the density at the diffuser inlet to fall below the impeller inlet density. This occurs due to excessively high flow rates, since the impeller losses are calculated as pressure losses. The critical velocity database applies to CO2 and no other fluids have had databases created for them yet. The process of creating a critical velocity database is discussed in Appendix B. RGRC will output the location of choke or surge so that the user can design around the limiting conditions. In RGRCMS the output includes the stage number of the choke or surge also, so the user knows which stage design needs to be improved. 3.4 The Multi-Stage Code RGRCMS The multi-stage code reads in geometric parameters and first stage inlet conditions formed from output of the single stage code. The geometry data required by the multi-stage code is written by a subroutine called MULTISTAGE in RGRC. The multi-stage code assigns the geometrical parameters to vectors with an index identifying the stage number. The code then begins looping through the range of shaft speeds and mass flow rates. Within each combination of shaft speed and mass flow rate, the code proceeds through each stage. After calculating the first stage, the outlet conditions of the first stage are assigned as the inlet conditions of the second stage, with a form loss for the return channel in between. The losses expressed as additional work terms are progressively summed as the code steps through stages. Otherwise, the multi-stage code proceeds almost exactly as does the off-design portion of RGRC. It includes the exact same calculations for impeller and diffuser flows and the losses are calculated with exactly the same subroutines. Stage matching can be difficult and the designer must consider the effects of the return channel on downstream stages. Oftentimes, stall and choke will be a serious issue in downstream stages at mass flow rates that were well within the operating range of the stage when designed independently. This is due to the changing inlet conditions of the second stage as the first stage performance changes. Designing a multi-stage compressor with RGRCMS will inevitably be an iterative process. Multi-stage compressors are usually designed so that each stage has the same static pressure ratio at the design point. The form loss model of the return channel is really not sufficient to describe the effect of the return channel on the flow. The rotation of the fluid will still affect the second stage as the 72PDF Image | Supercritical Carbon Dioxide Cycle Analysis
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