多次启动燃烧室燃油主动冷却模拟试验  

Experiment on the fuel active cooling of multi-working combustion chamber

作　　者：胡锦华 张忠利 邱成旭 周伟星[2] HU Jinhua;ZHANG Zhongli;QIU Chengxu;ZHOU Weixing(National Key Laboratory of Aerospace Liquid Propulsion,Xi'an Aerospace Propulsion Institute,Xi’an 710100,China;Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]西安航天动力研究所航天液体动力全国重点实验室,陕西西安710100 [2]哈尔滨工业大学,黑龙江哈尔滨150001

出　　处：《火箭推进》2024年第1期127-134,共8页Journal of Rocket Propulsion

基　　金：国家重点实验室基金(6142704220204)。

摘　　要：高超声速飞行器在不同马赫数、不同高度间跳跃飞行时,燃烧室在不同工况下间歇工作,热载荷发生交替变化,为保证燃烧室结构正常工作,采用燃油主动冷却对燃烧室进行热防护。为了验证燃烧室在燃油主动冷却时是否结焦积碳进而影响其正常工作,设计了多次启动燃烧室燃油主动冷却模拟试验装置,该装置采用电加热的方法模拟高温来流产生的交变热载荷,对主动冷却燃烧室模拟试验件进行了热壁冷油、热壁热油和燃油不流动状态试验考核。结果表明:主动冷却燃烧室热结构通过3次以上的热壁冷油、热壁热油循环试验后,试件未发生损坏;随循环次数增加,试件流阻增加较小,热壁热油工况的压差增加高于热壁冷油工况;对试验件进行剖切检查,发现冷却槽内积碳不明显,积碳主要出现在燃油出口的燃料集液腔内。When the hypersonic vehicle jumps between different Mach numbers and altitudes,the combustion chamber works intermittently under different working conditions,and the thermal load changes alternately.In order to ensure the normal operation of the combustion chamber structure,fuel active cooling is used to protect the combustion chamber.In order to verify whether the combustion chamber coke and deposition of carbon during the active cooling of the fuel affect its normal work,a multi-worked combustion chamber fuel active cooling simulation test device is designed.The device adopts the method of electric heating to simulate the alternating heat load generated by high-temperature incoming flow,and the active cooling combustion chamber simulation test part is tested and assessed in the hot-wall-cold-oil,hot-wall-hot-oil and fuel-non-flow state.The results show that the thermal structure of the active cooling combustion chamber passes through the hot-wall-cold-oil more than 3 times.After the hot-wall-hot-oil cycle test,the specimen has not been damaged.With the increase of the number of cycles,the flow resistance of the specimen is relatively small,and the pressure difference of the hot-wall-hot-oil condition is higher than that of the hot-wall-cold-oil conditions.The specimen is examined,and it is found that the carbon deposition in the cooling channel is not obvious,and the carbon deposition mainly appears in the collector cavity of the fuel outlet.

关 键 词：超燃冲压发动机 多次启动 燃烧室 主动冷却 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]