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CHAetal., DevelopmentofaSupercriticalCO2BraytonEnergyConversionSystemCoupledwithaSodiumCooledFastReactor Fig. 6. Design Point of Turbine in the Diagram of the Specific Diameter and Specific Speed Table 7. One-dimensional Design Data of Turbine Average density Stage pressure difference Stage head Rotational speed Diameter Volume flow rate Specific speed Specific diameter Stage Unit kg/m3 MPa m rpm ft ft3/s - - 4 Stages 97.4 3.04 3178 3600 5.3 2928.9 188.8 0.98 4 3 Stages 97.4 4.05 4237 3600 5.6 2928.9 152.2 1.12 3 conditions between the two compressors. Since compressor 1 is operated near the critical point, the properties inside it varied greatly. 3.2 Design of Supercritical CO2 Turbine The S- CO2 turbine was conceptually designed by using a similar process and methodology to that applied to the compressor design. Table 7 shows the major design factors that were used to perform the conceptual design of the turbine for the S-CO2 Brayton cycle coupled to the KALIMER-600 reactor. A one-dimensional design code, named TURB1D, was developed to analyze the performance of the S- CO2 turbine at an operation point. The design code for the S-CO2 turbine was developed on the basis of references [5,13,14]. In addition to the losses associated with the blades, secondary losses also exist, including those due to leakage of fluid flow between the tips of the blades and the casing of the turbine. In the code, secondary loss due to leakage between the tips and the casing was assumed to be 5%. Preliminary performance analysis of the turbine was conducted for the S-CO2 Brayton cycle coupled to the KALIMER-600 reactor. A sensitivity analysis for the performance parameters was conducted by using the TURB1D code. The off-design performance and sensitivity analysis for the turbine was conducted by using the TURB1D code, which was modified slightly to evaluate the sensitivity of the parameters. For the calculation, the inlet condition was given as Pinlet=20 MPa, Tinlet=550 oC and the outlet condition as Poutlet=7.4 MPa, respectively. The permissible blade stress was assumed to be 300 MPa. Figure 7 shows an efficiency change according to the stage number and the hub diameter of the turbine. By increasing the stage number, the efficiency of the turbine tends to increase and approach a constant value. Hun diameter efficiency tends to increase linearly. However, since an increment of the hub diameter results in a cost increase for the turbine due to volume enlargement, the hub diameter should be determined at a proper size to optimize its efficiency. Figure 8 shows the blade angle variation for the stage 1032 NUCLEAR ENGINEERING AND TECHNOLOGY, VOL.41 NO.8 OCTOBER 2009PDF Image | DEVELOPMENT OF A SUPERCRITICAL CO2 BRAYTON ENERGY CONVERSION
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