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2. THE ALLAM CYCLE COUNTER-PRESSURE GAS TURBINE As mentioned above the Allam cycle gas turbine inlet pressure of 20 – 40 MPa corresponds to USC steam turbines. Therefore, the R-100-300 steam turbine fabricated in 1968 by Kharkov turbo-generator plant for the 30 MPa inlet pressure may be taken for a prototype. An axial section of the power turbine developed for the Allam cycle is given in Fig. 4. The turbine flowpath is of a loop scheme, which remarkably reduces the thrust bearing 1 axial load and also reduces the size of the internal housing 2 made of nickel alloy. With the reasons described in chapter 2 above, the first rotor disc is taken as to fit the first stage blades height above 40 mm. FIGURE 4. Turbine axial section for the Allam cycle on super-critical carbon dioxide The first stage calculation results at the root diameter 0.9 m are the blade height = 45 mm and chord that gives the relative height According to the data [5] at this relative height, airfoil dimensions [6] and Mach number the energy loss coefficients are 5% for vanes and 6.5% for blades. According to the authors data the endwall ribbing reduces the loss coefficients for 15 %, which makes the values 4.25 % and 5.52 % respectively. Thus, the first stage internal relative efficiency is The downstream stages efficiency values except the last 12-th stage are surely higher and in the stage before the last, the efficiency is as high as 90.1%. These flowpath efficiency values are pretty high, so the number of stages may be reduced by the root diameter linear increase from 0.9 m in the first stage to 1.2 m in the last one. As the results, the number of stages located in the internal housing 2 dropped down to nine and five of them in the turbine left part (Fig. 3) and the remaining four are moved to the turbine right part and are fixed in the external housing 3. Further calculations of the turbine shown in Fig. 4 give its internal relative efficiency value of 85.7%. This efficiency evaluation took into consideration the 2% of carbon dioxide labyrinth losses and 1% at the 180° flow turn after the internal housing 2 exit. This analysis did not consider the rotor and blades cooling systems. Here the main goal was to apply the steam turbine typical flowpath layout solutions. On the other side, the considered 1150 0С temperature is typical for available industrial gas turbines where the initial gas temperatures are already above 1600 0С. Therefore, the second turbine version is shown in Fig. 5 retains the first version housing and layout, but this version flowpath is assembled of cooled gas turbine [7] stages with all blades dimensions retained. 020026-5PDF Image | Supercritical CO2 gas turbines for high-power generation
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