机动飞行条件下固冲发动机补燃室绝热层烧蚀实验研究  

Experimental study on ablation of thermal insulation layer in afterburning chamber of solid rocket ramjet during maneuvering flight conditions

作　　者：闫航 程吉明 刘杰 李海波 冯喜平[1] 侯晓[1] YAN Hang;CHENG Jiming;LIU Jie;LI Haibo;FENG Xiping;HOU Xiao(National Key Laboratory of Solid Rocket Propulsion,Northwestern Polytechnical University,Xi’an 710072,China;Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]西北工业大学固体推进全国重点实验室,陕西西安710072 [2]北京动力机械研究所,北京100074

出　　处：《推进技术》2025年第1期94-102,共9页Journal of Propulsion Technology

摘　　要：总体机动飞行引发的过载效应会导致固体火箭冲压发动机补燃室燃气积聚,并在绝热层局部形成烧蚀严重区域。针对这一问题,设计并搭建了一套模拟机动飞行条件下补燃室烧蚀热环境的实验装置,通过数值模拟获得了装置内两相流场参数的变化规律,实现了补燃室内压力、绝热层表面温度、燃气速度、燃气与绝热层间夹角等烧蚀影响参数的可控。利用该装置对某典型固冲发动机机动飞行工况开展了实验,结果表明,实验结果满足补燃室烧蚀严重区域目标参数模拟要求,目标压强为0.45 MPa,实验测量压强为0.467 MPa,与目标压强相对误差为3.78%;实验过程中温度测试结果为1245 K,1341 K,与数值仿真结果相比相对误差分别为5.62%和5.14%,数值仿真得到的试件中心温度为2367 K,与目标温度相比相对误差为2.9%;实验用绝热层在燃气直接作用区域形成了冲刷凹坑,最大烧蚀位置的线烧蚀率约为0.03 mm/s,非直接作用区域试件膨胀,凹坑形状受试件附近流场分布规律影响。The overload effect caused by maneuvering flight can result in the accumulation of combustion gases within afterburning chamber of solid rocket ramjet,leading to a serious erosion area in the thermal insulation layer.To address this issue,a test device is designed and established to simulate the thermal environment of the afterburning chamber during maneuvering flight.Numerical simulation is employed to obtain variations in two-phase flow field parameters.Controllability is achieved for ablation parameters such as combustor pressure,surface temperature of the thermal insulation layer,gas velocity,and angle between the gas and thermal insulation layer.An experimental investigation is conducted on the maneuvering flight conditions of a certain type of solid rocket ramjet using the device,the results demonstrate that the experimental findings satisfy the simulation requirements for serious ablation area in the afterburning chamber.The target pressure is 0.45 MPa,and the measured pressure is 0.467 MPa,resulting in a relative error of 3.78%.Additionally,temperature tests during the experiment yielded values of 1245 K and 1341 K,exhibiting relative errors of 5.62%and 5.14%compared to numerical simulation results,respectively.Furthermore,the center temperature of the test specimen is 2367 K,which corresponds to a relative error of 2.9%when compared to the target temperature.The experimental thermal insulation layer exhibits erosion craters in the direct action area of the gas,with a maximum linear erosion rate of approximately 0.03 mm/s.In the indirect action area,specimen expands,and the crater shapes were influenced by the distribution pattern of the flow field near the specimen.

关 键 词：固冲发动机 模拟机动条件 富氧两相环境 烧蚀实验系统 硅橡胶绝热层 

分 类 号：V285[航空宇航科学技术]