机构地区: 西北工业大学航天学院固体火箭发动机燃烧、热结构与内流场国防科技重点实验室
出 处: 《固体火箭技术》 2010年第1期21-24,共4页
摘 要: 针对固体火箭发动机测压导管内二相流动开展了数值分析,揭示了测压导管末端压强滞后现象的内在机理。在此基础上,提出了抑制方案,并开展了实验研究。结果表明,凝聚相颗粒在导管内壁面发生沉积形成的沉积物,可能会导致导管内燃气流通发生壅塞现象。这是引发导管末端压强滞后的主要原因,沉积物的形成主要发生在发动机点火上升阶段。基于流-固分离原理提出的抑制方案,通过有效减小进入导管内颗粒的质量,可解决测压导管末端压强的滞后问题。 Numerical simulation of two-phase flow in piezometric tube was carried out, and the main factor contributing to the piezometric tube end pressure delay was discovered. Also the suppressing method was presented and validated by experiments. Re- suits show that the deposition formed by impingement of condensed particles on the inner surface of piezometric tube may chock the gas flow in the piezometric tube, resulting in the delay of pressure at tube end. The suppressing method presented can solve the pressure delay phenomena by reducing the mass of particle deposition in piezometrie tube.
领 域: [航空宇航科学与技术] [航空宇航科学技术]