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Flowpath Cooling Concept The flowpath cooling is necessary for the thermally loaded elements reliable operation. According to [16], a special attention should be paid to the disc and blades cooling. It is very useful to apply the gas turbine cooling calculation experience. The turbine cooling system must satisfy the following requirements: In cooled parts the metal temperature must be kept under the limits that provide the design operating life. The cooled parts temperature gradients must be below the values that produce dangerous thermal stress or unacceptable deformations. Power spent for cooling must be considerably smaller than the additional power produced due to the cycle temperature increase. It is worth mentioning that in the Allam cycle the coolant flow is a part of the carbon dioxide flow at the recuperator outlet. So a part of the flow is supplied to the combustor, where its temperature is increased and the other part is spent on the turbine elements cooling. The cooling system design must consider a few sub-systems, turbine housing cooling, turbine rotor cooling, and especially vanes and blades cooling. Housing and Rotor Cooling The turbine housing cooling reduces its temperature and allows manufacturing from cheaper materials. In this turbine, the most temperature loaded is the internal housing, the non-cooled internal wall temperature in the first stage region may be up to the flow temperature of 1083 °C. In the proposed twin-wall structure, the gap between the walls is filled with carbon dioxide with parameters near to the last stage exit of 13 MPa and 850 °C. This flow surely can cool the internal housing. The turbine rotor and discs may be cooled in a way similar to gas turbines where the cooling air is supplied into the gap between the rotating shaft and the housing, the scheme is shown in Fig. 2. Deflector Blade root coupling Disc Blade Turbine housing Cooling CO2 supply channel Rotor FIGURE 2. Turbine rotor cooling with air blown through the blade root couplings As mentioned above the vanes and blades cooling needs a special attention. The gas turbine cooling systems where the gas temperature exceeded 1600 °C [17] shows that in this turbine may be applied convective cooling used in gas turbines in the 1980-1990s (Fig. 3). The cooling system efficiency θ=0.4 may be expected in this system. The heat transfer intensification technology also may be taken from the gas turbine practice. The traditional intensifiers are ribs, pins, and wave-shape channels. A prospective method is the application of asymmetric heat transfer intensifiers in radial cooling channels described in [18]. Figure 4 shows a few methods of heat transfer intensification in the blade cooling channels. 020018-4PDF Image | design approach for supercritical CO2 gas turbine
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