Performance Modeling Technique of Turboshaft Engine Based on Flight Experimental Data

In order to realize the virtual predictive flight test of military turboshaft engines under installed condition, the steady-state performance calculation model of turboshaft engine was constructed by solving the least square solution of overdetermined nonlinear equations with penalty function method, using regression analysis to fit the curve of the component characteristics coupling factors, and optimizing the baseline steady state model. Then considering the volume effect, rotor dynamics of rotating parts, and heat transfer effect of high temperature parts, the component-based transient performance model of the turboshaft engine was developed, with the support of the acceleration and deceleration experimental data. This model was used to simulate the steady state and transient state under some engine working conditions in the flight envelope. Compared with the real installed test results, the results show that the steady-state prediction accuracy of engine parameters is less than 4.2% and the transition state prediction accuracy is less than 9.2%. The model can meet the technical requirements of virtual predictive flight test, and plays an important role in the design, experimental and service of turboshaft engines. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.