A Transient Performance Adaptation Method for Aero-Engine Based on Adaptation Factor Surface
Component-level model is widely used in various applications for aero-engine condition monitoring and diagnostics,and its accuracy relies on high-fidelity characteristic maps.However,characteristic maps often require extensive testing to determine and often differ from actual engine component performance due to test conditions,manufacturing assembly errors,engine degradation,etc.Inaccurate characteristic maps can lead to significant discrepancies between the model's performance predictions and the actual engine performance,especially during transient operation.Given that current adaptation methods mainly focus on steady-state operation and have a relatively narrow correction range,a novel transient performance adaptation method for aero-engine is proposed.It transforms the solution of transient performance adaptation factors into steady-state performance adaptation calculations and establishes the adaptation factor surfaces for extensive correction of the model's characteristic maps.The efficacy of the proposed method has been verified through simulations of two engines with different characteristic maps.The research results show that the proposed transient performance adaptation method can extensively adjust the component characteristic maps using adaptation factor surfaces,thus more closely mirroring the real characteristics of engine components.After adaptation,the model exhibits a significant reduction in prediction errors for both measured parameters and unmeasurable parameters,with the average relative error in measured parameters predictions falling from 8.34％to 0.20％.
万方数据
维普
