应用特征线法求解航空发动机瞬态空气系统
Solving transient second air system in engine by characteristics method
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摘要: 用特征线法求解瞬态航空发动机空气系统的连续方程和动量方程,单独迭代求解能量方程.计算了空气系统内流体的压力、质量流量、温度随时间的变化规律.结果表明内部节点的压力、质量流量以相近的趋势随进口压力变化,但有相应的延迟,延迟时间约为0.01s,温度随边界温度变化而变化.将准静态结果与软件Flowmaster的模拟结果对比,吻合很好,压力最大相对误差为0.051%.Abstract: The characteristics method was used to solve continuity equation and momentum equation of transient second air system in engine,and the energy equation was solved iteratively.The time-dependent change rules of pressure,mass flow rate and temperature of the flow in second air system were calculated.The result shows that the changes in pressure and mass flow rate of inner nodes vary similarly with the changes of inlet pressure with a corresponding delay time of 0.01s,and the temperatures of elements vary with the boundary temperature.The quasi-static results show good agreement with that of software of Flowmaster,and the maximum relative error of pressure is 0.051%.
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Key words:
- transient /
- second air system /
- characteristics method /
- algorithm /
- simulation
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