摘要
针对故障模式下矢量喷管应急回中问题,提出一种关于矢量喷管作动简回中孔结构的设计方案。基于流体动力学平衡方程,建立应急回中装置的非线性数学模型。就设计过程中设计参数多于方程个数的求解,采用进油孔直径、活塞速度分段求解非线性方程组和作动筒左、右两腔仿真调试的组合方法,获得限定速度段内满足作动筒回中性能要求的回中孔结构参数。AMESim仿真结果表明,矢量喷管作动简回中结构参数,能满足喷管作动筒在任何工作状态下一旦出现故障迅速应急回中的要求,进入回中状态后能以足够的回中位置精度保持其安全的非矢量控制状态。
Aimed at the problem of vector nozzle returning back in emergency, an oil return hole structuredesign scheme of vector nozzle actuator was proposed, and based on the fluid dynamics equilibrium equa?tion, nonlinear mathematical model of return mechanism was established. To solve the problem that thenumber of design parameters is more than that of the equation, the method of solving nonlinear equations bysegmentation of velocity of vector nozzle actuator and diameter of fuel feed hole and the method of simula?tion and debugging of the actuator simulation model together were combined, and then the actuator structureparameters meeting the performance requirements in the limit velocity section were obtained. The AMESimsimulation results show that the design scheme and parameter of the return structure can meet the demandof returning back fast in any working condition, once the aero-engine vector nozzle control system failed. Af?ter entering the return state, high return position accuracy can assure the safe control state of non-vector infault model.
作者
芦海洋
王曦
王华威
王栋
王大迪
LU Hai-yang;WANG Xi;WANG Hua-wei;WANG Dong;WANG Da-di(School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing100191,China;Collaborative Innovation Center for Advanced Aero-Engine,Beijing 100191,China;Xi’an Aero-engine PLC,Xi’an 710077,China)
出处
《燃气涡轮试验与研究》
北大核心
2016年第3期43-48,共6页
Gas Turbine Experiment and Research
关键词
航空发动机
作动筒
矢量喷管
流体动力学
回中速度
回中位置精度
aero-engine
actuator cylinder
vector nozzle
fluid dynamics
return speed
return displacement precision
