Nearly half a century has elapsed since the advent of gas turbines. In cycle analysis, there are equations for deriving power or thrust from the specific heat, thermal efficiency, and various optimal (optimal reheating or increase in stress) pressure ratios of turbine exit pressures. However, there are no equations for the optimal pressure ratios of the fuel consumption rate with more complex relations. By using the parameter section simplified method system, the paper derives the simplified solution of the optimal pressure ratios; in addition, examples are cited in comparing the results of calculations and the precise solutions of the variable specific heat in order to have a correct evaluation of the extent of approximation and applications. ANNOTATION: Generalized Simplified Analytic Solution of Optimum Cycle Parameters for Land and Aircraft Gas Turbine Engines and its Applications-- Translation.