In order to solve the problem that the calculation result of mathematical model and the measured data of the whole machine deviate greatly due to the conditional simplification in the modeling process and engine component difference, an engine model correction method based on Quantum-behaved Particle Swarm Optimization(QPSO) is proposed. And the engine model calculation results are compared with the measured data of the whole machine performance. The results show that using the QPSO to modify the engine model can significantly improve the accuracy of the model. Before the correction, comparing the performance calculation result of the engine model with the measured data, the maximum error reaches 4.84%. After the correction, the accuracy of the model is greatly improved, and the maximum error is only 0.966%. The correction effect is good.

No abstract

The mathematical model of turbofan engine is established and simulation calculation is carried out in this paper. An engine component model is established by means of the gas flow path of the engine. Then, according to the common working conditions, common working equations are established and the N+1 residual method is used to solve the nonlinear equations. The general model of an engine is established based on the design point parameters, and the specific performance parameters of the intermediate state are calculated under standard atmospheric conditions. The simulation results are compared with the measured performance data of the engine, which shows that: there are errors between the calculated value of the model and the measured value of the engine. The maximum error is 2.85%, which meets the requirement of model error less than 3% in general engineering.

In order to solve the problem that the temperature of the compressor outlet air in turbofan engine is not measurable, a method of calculating the static temperature of the compressor outlet air based on the total temperature of the compressor outlet air in the engine bench test data is proposed, according to the principle of aerothermodynamics. And a Simulink model is established. The total temperature, total pressure and design point flow at the compressor outlet of the engine are brought into the Simulink model to calculate. The results show that the static temperature of the compressor outlet at the design point is Ts = 0.9873T*. According to the inverse relationship between temperature ratio function and N2 speed, the linear interpolation is carried out. The relationship between static temperature of compressor outlet and total temperature is T = (1 − 0.0127* N 2)T*.