论文部分内容阅读
基于大涵道比涡扇发动机部件级模型,从减少单次流路计算耗时和降低单步流路计算次数两方面研究提高模型实时性的方法。测试并分析了发动机各模块单步计算耗时,通过建立气体热力属性插值表,使模型单次流路计算耗时减少80%,在3.3GHz Intel CPU平台下模型单次流路计算耗时0.02ms,在168MHz STM32F407硬件平台下耗时1.55ms。研究了不同收敛残差对模型流路计算次数及仿真精度的影响。仿真结果表明:相比Newton-Raphson法,Broyden法流路计算次数更少;将迭代求解残差由0.0001调整至0.001或0.005,模型流路计算次数显著减少,低压转速仿真偏差在0.2%以内。
Based on the large-bypass ratio turbofan engine component model, this paper studies how to improve the real-time performance of the model by reducing the time-consuming calculation of single-pass flow and reducing the calculation of single-pass flow. Test and analyze the single-step calculation time-consuming of each module of the engine. By establishing the interpolation table of the thermal properties of the gas, the calculation time of the model single-channel is reduced by 80%. Under the 3.3GHz Intel CPU platform, the calculation time of the single-channel model is 0.02 ms, consuming 1.55ms under 168MHz STM32F407 hardware platform. The effects of different convergence residuals on the calculation times and simulation accuracy of the model flow path are studied. Simulation results show that, compared with Newton-Raphson method, Broyden method has fewer computation times; the iterative solution residual error is adjusted from 0.0001 to 0.001 or 0.005, the computation times of model flow paths are significantly reduced, and the simulation deviation of low-pressure rotation speed is less than 0.2%.