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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 69 Parameters for the thermodynamic analysis The turbofan has an internal Brayton cycle system responsible to generate the propulsive power in both the core and fan sides. It is convenient to analyze this system and obtain the thermodynamic states in each stage of the engine. There are several adopted assumptions, • no transmission losses, • ideal diffuser and nozzles, • no pressure losses in combustion chamber, • fuel mass flow neglected, • the properties of air are considered valid for the working fluid during the entire cycle. The figures of merit of the turbine and compressor (or fan) are the polytropic efficiencies, defined as eTR = Actual turbine work for a differential pressure change, Ideal turbine work for a differential change eCM = Ideal compressor work for a differential pressure change , Actual compressor work for a differential pressure change (4-13) (4-14) (4-15) for the turbine and the compressor respectively. It can be demonstrated that the isentropic efficiency of both components is function of the polytropic efficiency for an ideal gas, (4-16) (4-17) γ−1eTR 1−Π γ η = TR , TR γ−1 1−Π γ TR γ−1 Πγ−1 η=CM , CM γ−1 eCM Πγ −1 CM for the turbine and the compressor respectively. The total pressure ratio Π corresponds to the ratio of the total or stagnation pressures in both components, Π = Total pressure leaving the component . (4-18) Total pressure entering the component Expressions (4-16) and (4-17) are used to obtain the isentropic efficiencies of the turbine and compressor respectively. Similarly, the combustion efficiency is defined as ηCC = Energy transfered to the cycle. (4-19) Energy from the fuel The values of the figures of merit for the compressor, turbine and combustion chamber are presented in Table 4-3 and correspond, according to Mattingly [9], to a level of technology 4, i.e., engines produced since the year 2005. As mentioned in Table 4-1, the cruise thrust rating is done at 10670 m and the air properties have to be corrected for these conditions. The air properties are calculated according to the International Standard Atmosphere (ISA) models. The temperature decreases with a constant gradient, Master of Science Thesis κ = −6.5 · 10−3 K/m. (4-20) J.S. Bahamonde Noriega

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