Abstract: In order to evaluate the test data and build the adaptive model rapidly, an engine adaptive modelling method was proposed regarding to the turbofan engine in development stage. The method takes the engine test data as input and employs the aero-thermodynamic equations and engine matching constraint as governing equations to reconstruct the performance parameters of the engine components. The method for determining the core engine mass flow according to the flow capability of the throat of the guide vanes of the high-pressure turbine was presented. The load coefficient of the turbomachinery was taken as a medium to calculate their adaptive coefficients. The adaptive modelling of a small bypass ratio turbofan engine was conducted. Results show that the simulation results of the 17 parameters are consistent with their test data and the average time for the method to complete the adaptive calculation of a single state point is about 1.44ms. The adaptive coefficients of the main component characteristics are within 0.95 and 1.05. The adaptive coefficient of component characteristics calculated by this method can provide a basis for engine performance evaluation and fault diagnosis.

Key words: Development stage;Performance evaluation;Adaptive model;Adaptive coefficients;Component-level model

摘要： 为了实现研发阶段涡扇发动机整机试验数据的快速评估和模型自适应，提出一种发动机模型自适应方法。该方法以整机试验数据为输入，结合气动热力过程约束方程和发动机整机匹配约束条件，重构出各部件的性能参数。文中提出了按照高压涡轮导向器喉部流通能力确定核心机流量的方法，并以载荷系数为媒介实现叶轮机械部件参数修正计算，完成了小涵道比涡扇发动机的自适应建模计算。计算结果表明，17个测量参数与计算结果完全一致，该方法完成单个状态点自适应计算的平均时间约为1.44ms，主要部件特性的修正系数在0.95～1.05。采用该方法计算的部件特性参数自适应修正系数可为发动机性能调试和故障诊断提供依据。

关键词: 研发阶段;性能评估;自适应方法;自适应修正系数;部件级模型