脉冲燃烧风洞与连续燃烧风洞数据相关性研究  

Analysis of data correlation between impulse and continuous combustion heated facilities

作　　者：吴颖川[1] 贺元元[1] 张小庆[1] 林其[1] 乐嘉陵[1] Wu Yingchuan;He Yuanyuan;Zhang Xiaoqing;Lin Qi;Le Jialing(Science and Technology on Scramjet Laboratory,Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]中国空气动力研究与发展中心超高速空气动力研究所,高超声速冲压发动机技术重点实验室,四川绵阳621000

出　　处：《实验流体力学》2018年第3期58-63,共6页Journal of Experiments in Fluid Mechanics

摘　　要：燃烧加热风洞是目前开展超燃冲压发动机地面模拟试验的主要设备。燃烧加热风洞的试验时间(脉冲式和连续式)及燃烧方式(氢-氧燃烧、碳氢-氧燃烧)均会对发动机试验结果产生一定影响。研究了氢-氧燃烧脉冲风洞与氢-氧燃烧连续风洞、酒精-氧气燃烧连续风洞的数据相关性。研究表明:对于同为氢-氧燃烧的脉冲风洞和连续风洞,在相同试验状态下,发动机推进流道压力系数分布规律一致,连续风洞试验的燃烧室压力高于脉冲风洞试验值,连续风洞的发动机推力收益比脉冲风洞高10%左右;对于氢-氧燃烧脉冲风洞和酒精-氧气燃烧连续风洞,发动机推进流道压力系数分布规律一致,连续风洞试验的燃烧室压力高于脉冲风洞试验值,连续风洞的发动机推力收益比脉冲风洞高5%左右。The comparison tests of impulse and continuous combustion heated facilities were conducted.For Hydrogen-Oxygen combustion heated impulse and continuous facilities,the pressure coefficient distributions of the engine flow path were coincident but the engine thrust gain in continuous facility was 10%larger than that in the impulse facility.For Hydrogen-Oxygen combustion heated impulse facility and Alcohol-Oxygen combustion heated continuous facility,the pressure coefficient distributions of the engine flow path were coincident but the engine thrust gain in continuous facility was 5%larger than that in the impulse facility.

关 键 词：超燃冲压发动机 燃烧加热脉冲风洞 燃烧加热连续风洞 数据相关性 氢-氧燃烧 酒精-氧气燃烧 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]