摘要
针对某火箭发动机考虑汽化的注水气液两相流问题,研究了液态水的汽化机理。根据不同环境压力下水的饱和温度建立了汽化模型,编制适合于液态水的专用汽化相变求解程序,并通过添加汽化组分源项及热源项的方法将汽化相变计算嵌入到多相流场控制方程中,实现了考虑液态水汽化相变的三维多相流场求解。结合经典算例进行了对比,特征点的两相流场温度计算值和试验的误差控制在8.5%以内,验证了程序三维计算的可靠性。距火箭喷嘴不同距离横截面的两相质量转化率曲线显示,质量转化率从最低值上升到最高值,然后降低到最低值,揭示了考虑相变的气液两相相间反应转化机理。该方法可为运载火箭发射平台发射起始阶段水室的汽化降温提供参考。
In order to research the gas-liquid two-phase flow problem considering vapori- zation phenomenon for the rocket engine, the vaporization mechanism of liquid water was studied. The vaporization model for water was established according to the saturation temperature of water at different pressures. A program to solve the vaporization phase change process for liquid water was written on the basis of vaporization model, and the vaporization phase change calculation results were added to the multi-phase flow field equations as vapori- zation component source term and heat source term, so the three-dimensional multiphase flow field numerical solution considering the liquid water vaporization phase change was real- ized. Combining with the classical example, the errors of the temperature calculating values and experimental values of the two-phase flow field for the feature points were controlled within 8.5%, verifying the reliability of the three-dimensional calculation of the program. The mass conversion rate curves of two-phase from the different distance of the rocket nozzle showed that the mass conversion rate of two-phase rose from the lowest value to the highest value and then decreased to the lowest value, the transformation mechanism of the liquid and gas phases was revealed. The method can provide direct reference for the vaporization and cooling of the water chamber in the launching stage of launch platform for launch vehicle.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2017年第7期1545-1553,共9页
Journal of Aerospace Power
基金
江苏省自然科学青年基金(BK20160296)
关键词
喷嘴
气液两相流
汽化相变
演化机理
质量转化率
nozzle
gas liquid two-phase flow
vaporization phase change
evolution mechanism
mass conversion rate
