粒子流量可调的喷管烧蚀试验方法  

A test method for erosion of the nozzle with adjustable particle mass flow

作　　者：李江[1] 董昊[1] 王文彬[1] 魏祥庚[1] 王勇[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2008年第1期96-98,共3页Journal of Solid Rocket Technology

摘　　要：发展了一种保持燃气参数不变的情况下能实现粒子流量可调的喷管烧蚀试验方法,并研制了试验装置。该试验方法是将两相流燃气中的一部分粒子收集起来,以减少流经喷管的粒子流量,通过改变收集孔和收敛角的大小来调节粒子流量。采用该方法开展了变粒子流量的喷管烧蚀试验,试验结果验证了该方法是有效的,试验条件下喷管喉部平均线烧蚀率随粒子流量减小而降低。A test method for erosion of the nozzle was investigated, which can realize adjustable particle mass flow under constant gas parameters, and the test device was developed. Partial particles of two-phase flow gas were collected so as to reduce particle mass flow in the nozzle, moreover particle mass flow was adjusted by changing the size of collecting hole or the convergent angle. The method was used for erosion test of the nozzle with adjustable particle mass flow. The results show that the method is effective, and the average linear erosion rate of the nozzle throat is reduced remarkably with the decrease of particle mass flow.

关 键 词：固体推进剂火箭发动机 喷管 烧蚀 粒子 试验方法 

分 类 号：V435.6[航空宇航科学与技术—航空宇航推进理论与工程]