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actual fluid, but which can be more closely approximated by an ideal gas model. These key parameters were selected from turbomachinery similarity principles and non-ideal gas properties. This method of analysis adjusts the density, temperature, and other properties of the surrogate fluid so that the volumetric flow rate and adiabatic head produce inlet and exit flow angles that are identical to those in the supercritical fluid. This results in a design that has the correct flow passage dimensions and velocity vectors for the same shaft rpm. In addition, the loss models for the near ideal gas (in the surrogate fluid) are applied and used to predict the isentropic efficiency for the supercritical fluid. This method introduces many approximations but provides a way to use existing loss models and design tools such as the NASA CCODP code (Galvas, 1973) to develop the detailed design of the turbomachinery and to predict its performance. The development of this capability is extremely important and was performed early in the program, because these tools were needed to develop the detailed design so that the wheels could be manufactured. The method has been successfully applied to both supercritical CO2 compressors and turbines. At the same time, Sandia has been developing its own code to predict supercritical CO2 compressor and turbine performance. In spite of the very different approaches taken by these two methods, they produce similar results. Table 5.1 summarizes the main design features of the main compressor. The first column describes the property, the second gives the variable name and units, and the last column provides the value. The small size of the compressor wheel is further exhibited by the height of the blade at the exit of the compressor, (only 1.7 mm), in spite of the fact that the compressor is pumping 3.53 kg/s or 13 tons per hour of CO2 and operates at about 50 kW or 70 horse power. At Sandia, we have developed a simple, but fundamental mean-line flow analysis code to model the compressor performance. This code is implemented in Excel, and uses enthalpy based sets of equations coupled to the NIST REFPROP data base to model the flow at the compressor inlet and outlet. The method closely follows the approach described in Japikse (Japikse, 1996 & 1997) and requires a non- linear solution to 19 simultaneous equations. The loss models use a combination of methods described by Jiang (Jiang, 2006) and Oh (Oh, 1997). The loss models currently account for inlet and outlet flow deviation, disk friction, clearance effects and other effects. The Sandia compressor model is still being developed and more effort needs to be applied to the implementation of the loss models and improved models for the diffuser. 53PDF Image | Operation and Analysis of a Supercritical CO2 Brayton Cycle
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