The method for designing dynamic models for single-flow jet turbine engines from the aerodynamic design and mechanical structure design stages.

Abstract

The invention relates to a method for designing a dynamic model for a single-flow turbojet engine from the aerodynamic design and mechanical design stages. The method includes constructing a hybrid 0D–2D model, in which the compressor and turbine are modeled using a curve or through-flow solver, while the combustion chamber and nozzle are modeled using a 0D model; a method for solving the problem of coordinating the entire engine modules based on mass balance, energy balance, and shaft power balance equations to determine the aerodynamic parameter anchor point; a 0D dynamic model for the entire engine designed with compressor and turbine characteristic maps obtained from aerodynamic simulation (CFD) results, nozzle cross-section and shaft inertia obtained from aerodynamic and mechanical design data; and the 0D dynamic model calibrated using the aforementioned aerodynamic anchor point.

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