基于旋转阀的固体火箭发动机燃烧室压强振荡特性

Oscillation Characteristics of Pressure in Combustor with Rotary Valve for Solid Rocket Engine

针对基于旋转阀的固体推进剂压强耦合响应函数测试系统存在不易进行相位角测量、压强振荡及内流场分析的难点,设计一套旋转阀冷流实验系统,建立对应的压强振荡理论计算模型和三维瞬态内流场仿真模型,研究燃烧室压强振荡及其内流场特性。开展不同排气频率的冷流实验和理论计算,并与仿真模型进行对比。结果表明:仿真计算中单个转子排气通道周期性摆动运动可代替多转子排气通道单向旋转运动,且误差小于1%;仿真计算获取的排气周期与实验对比的误差小于1.2%;对于压强峰-峰值,仿真比实验小且相差数值由20 Hz的0.019 MPa降低至300 Hz的0.001 MPa,验证了仿真模型的有效性;为后续研究旋转阀工作过程中燃烧室压强振荡及流场变化提供了新的思路和途径。

The pressure-coupled response function test system of solid propellant based on rotary valve is difficult to perform the measurement of phase angle,and the analysis of pressure oscillation and internal flow field.A set of cold-flow experimental system with rotary valve was designed,and a corresponding theoretical calculation model of pressure oscillation and a three-dimensional transient flow field simulation model based on dynamic mesh technology were established.Cold flow experiment and theoretical calculation at different exhaust frequencies were made,and the experimental and calculated results were compared with the simulated results.The results show that the periodic swing motion of a single-rotor exhaust duct can replace the unidirectional rotary motion of the multi-rotor exhaust duct in the simulation calculation,and the error is less than 1%.The errors of the exhaust cycle obtained by simulation calculation and experiment are less than 1.2%;the simulated peak-to-peak pressure is smaller than the experimental one,and the difference value is reduced from 0.019 MPa at 20 Hz to 0.001 MPa at 300 Hz,which verifies the effectiveness of the simulation model.