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.

航空发动机快速成功启动以确保安全飞行是至关重要的前提，但是发动机启动过程是非常复杂的非平衡，非线性空气热力学过程。本文将理论模型与实验数据相结合，建立了直升机涡轮轴发动机的启动过程模型。首先，基于阶段叠加法，通过典型零件的特征，设计点参数和零件结构，大致估算了压缩机和涡轮的低速零件的特征。然后，充分考虑燃烧效率的变化，燃烧室的影响以及涡轮机的热惯性，在组件法的基础上，开发了直升机涡轮轴发动机的启动过程模型，并将上述空闲状态建模方法成功地应用于启动过程。仿真表明，该模型符合实时性和准确性要求，并且很好地模拟了启动过程。最后，基于模型对启动过程进行了性能分析，表明该模型为发动机启动控制系统的设计提供了通用平台和工程参考价值。