With the help of a purpose-built computer program the separate and combined effects of the various aspects of internal combustion and non-perfect gas properties on the optimum performance of gas turbines are examined. The effects of variation of specific heat, addition of fuel mass, pressure losses and dissociation are elucidated. The numerical results have been extensively compared with closed-form analytical solutions and a linear perturbation analysis. The accuracy of a standard, approximate method for predicting gas turbine performance is assessed and its various limitations are identified. The newly established concept of optimum turbine entry temperature is further explored.
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