Research on dynamic modeling and performance analysis of helicopter turboshaft engine's start-up process

Abstract

It is a vital precondition that the aeroengine start-up quickly and successfully to ensure a safe flight, but the engine start-up process is a very complex non-equilibrium, non-linear aerothermodynamics process. This paper establishes a start-up process model of helicopter turboshaft engine by combining theoretical modeling with experimental data. Firstly, based on the stage-stacking method, the characteristics of low-speed components of compressor and turbine are approximately estimated with the characteristics of typical components, design point parameters and component structure. Then in full consideration of the change of combustion efficiency, the impact of the combustion chamber and turbine's thermal inertia, a helicopter turboshaft engine's start-up process model is developed on the basis of component method, and the above-idle state modeling method is successfully applied to the start-up process. The simulation shows that the model is in conformity with real-time and accuracy requirements, and simulates the start-up process quite well. Finally, the performance analysis of the start-up process is carried out based on the model, which shows that the model provides a general platform and engineering reference value for the design of the engine start-up control system.