Design method for s-CO2 gas turbine power plants

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Design method for s-CO2 gas turbine power plants ( design-method-s-co2-gas-turbine-power-plants )

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4-1 Aircraft propulsion systems 73 and low pressure turbines. The leaving total enthalpy is obtained working equation (4-32), h09 =h04−W ̇2−13 −W ̇2−3. (4-33) fCR fCR The entropy leaving the core, s09, is obtained with its correspondent total pressure and enthalpy and it is used to obtain the enthalpy at point (9), h9 =h(P9,s09), (4-34) where P9 equals the environmental pressure. The velocity of the air leaving the core is again a function of the stagnation enthalpy at (09) and the enthalpy at (9), 􏰏 v9 = 2(h09 − h9). (4-35) The core velocity is shown in Table 4-2 and it is necessary to iterate the value of the total pressure P09 until the core velocity matches this value. The information of the core side analysis is shown in Figure 4-6. The propulsive power of the engine core is the difference of 00=02 0 Pressure Density Enthalpy Cycle 03 04 05=09 9 1000 800 600 400 200 0 6.8 7 7.2 7.4 s [kJ/kgK] 7.6 7.8 [bar] [◦ C] 0.24 -54.50 0.38 -22.80 19.12 566.60 19.12 941.90 0.42 231.56 0.24 157.79 Figure 4-6: Core T-s diagram of the Turbofan Trent 1000 engine. the kinetic energy of the air mass flow through the core and it can be calculated as a function Cycle points Environm. cond. (0) Fan inlet (02) Cm. outlet (03) Tr. inlet (04) PTh Tr. outlet (09) Nozzle outlet (9) Trb. power (gross) [kW] 73453.51 Comp. power [kW] 57389.97 Turb. Is. efficiency 0.94 Comp. Is. efficiency 0.84 Turb. pressure ratio 0.022 [kJ/kg] 218.79 250.56 867.15 1297.51 508.34 432.80 of the total enthalpies in the system, 􏰉v2 v2􏰊 W ̇ PR,CR = fCR 29 − 20 = fFN[(h05 − h9) − (h02 − h0)]. The turbine shaft power driving the compressor and the fan reads W ̇ 4-5 = fCR (h04 − h05) . Finally, the power of the compressor is W ̇ 2-3 = fCR (h03 − h02) . (4-36) (4-37) (4-38) Master of Science Thesis J.S. Bahamonde Noriega T [◦C]

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