残余限燃环对大型分段式固体火箭发动机凝相沉积的影响  

Influence of residual annular insulator on slag accumulation in segmented SRM

作　　者：晁侃 王健儒 陆贺建 CHAO Kan;WANG Jianru;LU Hejian(National Key Laboratory of Combustion,Flow and Thermo-Structure,The 41st Institute of the Fourth Academy of CASA,Xi’an 710025,China)

机构地区：[1]中国航天科技集团有限公司四院四十一所燃烧、热结构和内流场重点实验室,西安710025

出　　处：《固体火箭技术》2021年第1期9-15,共7页Journal of Solid Rocket Technology

基　　金：总装研究项目。

摘　　要：采用Euler-Lagrangian方法描述固体火箭发动机两相流动过程,数值分析了某大型分段式固体火箭发动机地面试车后在后段燃烧室筒段出现大量的Al 2O 3凝相颗粒沉积现象,计算过程中考虑了气相湍流脉动对凝相颗粒的影响,并通过缩比分段式固体火箭发动机地面粒子沉积试验对计算结果进行验证,数值计算与试验结果基本吻合。二者结果表明,由于前后段燃烧室推进剂燃速差异性,导致在大型两分段式固体火箭发动机工作末期,前段燃烧室高温燃气中的大量微小颗粒受到湍流脉动的影响而被后段燃烧室筒段壁面捕获形成凝相沉积。同时研究表明,燃烧室分段部位的残余限燃环高度对后段凝相沉积量影响非常明显,通过降低分段部位限燃环残余高度,能够明显降低发动机工作过程中后段燃烧室的凝相沉积量。Use the Euler-Lagrangian method to describe the two-phase internal flow of a solid rocket motor(SRM).A numerical analysis was carried out to investigate the phenomena of massive Al 2O 3 condensate particles deposited on the tube section of the rear combustion chamber after a large segmented SRM ground test.The influence of the gas turbulence pulsation on the condensed particles was considered in the calculation.The calculation result was verified by the ground particle deposition test of a scaled segmented SRM,and basically consistent with the test results.The results show that at the end of a large segmented SRM,due to the difference of propellant burning rate in the front and rear combustion chamber,a large number of small particles in the high temperature gas of the front combustion chamber are adsorbed on the wall of the tube of the rear combustion chamber by the influence of the turbulent fluctuation.At the same time,it is shown that the residual annular insulator height of the segmented chamber has a very obvious effect on the particles deposition of rear combustion chamber,as the residual annular insulator height decrease,the amount of slag accumulation in rear combustion chamber also decrease significantly in the large segmented SRM test.

关 键 词：分段固体火箭发动机 分段限燃环 缩比试验 凝相沉积 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]