反压诱导方式对超燃冲压发动机隔离段流动特性影响

发布时间：2018-03-07 11:41

本文选题：超燃冲压发动机　切入点：隔离段　出处：《航空动力学报》2016年11期 　论文类型：期刊论文

【摘要】：为了探究传统机械限流方式同燃烧释热对隔离段流动特性影响的异同,采用实验结合数值计算的方法研究了限流方式与实际燃烧诱导压升的差异.使用氢燃料进行不同当量比的燃烧实验,并使用燃烧室出口安装楔块的方式进行限流实验,对比了来流条件相同,且隔离段出口压比相同时两种实验下的压力分布.使用经过验证的数值方法模拟了不同隔离段出口压力下燃烧状态及对应的限流状态,对比了两种状态下隔离段流场细节.实验结果表明:激波链即将进入隔离段时,两者的压力分布大致相同;激波链进入隔离段后,隔离段出口压比2.3,两者的壁面压力分布有明显差别.此状态下的计算结果表明:燃烧状态下隔离段内分离区首先出现于下壁面,激波链向上偏折;而限流状态分离区出现于上壁面,两者的流场会有一定差异.反压继续增大的计算结果表明:隔离段出口压比达3.0时,两者的隔离段内流场差别逐渐减小并最终趋于一致.燃烧反压场与限流实验的模拟反压场一致时,才能直接采用限流实验的结果评估反压对进气道的扰动风险.
[Abstract]:In order to explore the influence of traditional mechanical flow limiting mode and combustion heat release on the flow characteristics of isolation section, The difference between the current limiting mode and the actual combustion induced pressure rise is studied by means of experiments and numerical calculations. The hydrogen fuel is used to carry out combustion experiments with different equivalent ratios, and the flow limiting experiments are carried out by installing wedge blocks at the outlet of the combustion chamber. The pressure distributions under the same conditions and the same outlet pressure ratio are compared. The combustion state and the corresponding current limiting state at the outlet pressure of different isolation sections are simulated by using the verified numerical method. The experimental results show that the pressure distribution of the shock chain is approximately the same when the shock chain is about to enter the isolation section, and the shock chain enters the isolation section after the shock chain enters the isolation section. When the outlet pressure ratio of the isolation section is 2.3, the wall pressure distribution is obviously different between the two. The calculated results show that the separation zone in the isolation section first appears on the lower wall under the combustion condition, and the shock chain deflects upward. However, the separation zone of limiting state appears on the upper wall, and the flow field will be different between them. The calculation results of increasing backpressure show that: when the outlet pressure of isolation section is Prida 3.0, The difference of flow field in the isolated section decreases gradually and tends to be consistent eventually. Only when the simulated backpressure field of combustion backpressure field and the simulated backpressure field of the limiting experiment are consistent can the results of the flow limiting experiment be used directly to evaluate the disturbance risk of the inlet.
【作者单位】：西北工业大学动力与能源学院;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;
【基金】：高超声速冲压发动机技术重点实验室开放课题(STSKFKT2012002)
【分类号】：V231

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