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The development of an improved mathematical model is reported, herein, for modeling the thermo-dynamic processes of triple spool mixed turbofan jet engines with an afterburner, at start conditions with special care for the verification. The T-s diagram and the main characteristics of the engines are determined by a concentrated parameter-distribution type method, implemented in the MATLAB environment. The governing equations are based on mass, energy balance and the real thermo-dynamic processes. A non-linear constraint optimization method is used, for identifying the unknown parameters. Temperature and component mass fraction dependent gas properties are calculated by iteration cycles in case of functional dependencies. A new and more accurate equation is derived and applied for determining the critical pressure at converging nozzle flow with consideration of the local material properties. The thermo-dynamic analyses are completed for NK-32 and NK-25 turbo jet engines. The plausibility of the method and the verification the new equation is provided.

Derivation and Application of a New Equation for Design and Analysis of Triple Spool Mixed Turbofan Jet Engines with Verification