高压低混合比氢氧预燃室出口温度均匀性分析  

Analysis on outlet temperature uniformity of hydrogen/oxygen preburner with high-pressure and low-mixture-ratio

作　　者：潘刚[1] 牛旭东 潘亮[1] 郑孟伟[1] 孙纪国 丁兆波 PAN Gang;NIU Xudong;PAN Liang;ZHENG Mengwei;SUN Jiguo;DING Zhaobo(Beijing Aerospace Propulsion Institute,Beijing 100076,China;Academy of Aerospace Propulsion Technology,Xi'an 710100,China)

机构地区：[1]北京航天动力研究所,北京100076 [2]航天推进技术研究院,陕西西安710100

出　　处：《火箭推进》2023年第1期29-35,共7页Journal of Rocket Propulsion

摘　　要：为了深入了解高压低混合比氢氧预燃室的出口燃气温度均匀性,设计了一个缩尺预燃室,开展了不同缩进深度比、扰流结构、工况下缩尺预燃室出口燃气温度均匀性的研究,并通过全尺寸预燃室试验验证了设计方案的合理性。试验结果表明:随着缩进深度比的增加,燃气温度均匀性逐渐提高;随着室压、混合比的升高,扰流环结构的均温效果提高;扰流环与拐弯结构的组合方式可使燃烧室内的温度均匀性提高54.8%~89%;在喷嘴设计参数下,相对于同轴离心喷嘴,采用同轴直流喷嘴的缩尺预燃室在50%~100%工况下的出口燃气温度均匀性较优;当采用扰流环及90°拐弯结构时,全尺寸预燃室的出口燃气温度均匀性在±50 K范围内,同时相对于氢涡轮侧出口,氧涡轮侧出口的燃气温度均匀性更优。In order to deeply understand the outlet temperature uniformity of high-pressure and low-mixture-ratio hydrogen/oxygen preburner,a subscale preburner was designed.The uniformity of outlet combustion gas temperature was carried out under different recess ratios,turbulence structures and operating conditions.In addition,the rationality of the design scheme was verified experimentally by the full-scale preburner.The experimental results show that the gas temperature uniformity increases gradually with the increase of recess ratio.With the increase of the combustor pressure and mixture ratio,the temperature homogenization effect of the turbulator is improved.The temperature uniformity in combustor can be improved 54.8%-89%by the combination of turbulator and elbow structure.Under the design parameters of the injector in this paper,compared with the swirl coaxial injector,the temperature uniformity of subscale preburner is better with shear coaxial injector under 50%-100%operating conditions.The temperature uniformity of full-scale preburner is less than±50 K when the turbulator and the 90°elbow are used.At the same time,the gas temperature uniformity of the outlet near the oxygen turbine is better than that of the outlet near the hydrogen turbine.

关 键 词：氢氧 预燃室 缩进深度比 扰流结构 变工况 出口温度均匀性 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]