航天推进技术研究院主办
[1]陈 帆,武 越,张恒昕,等.环管燃烧室火焰筒空气流量试验[J].火箭推进,2019,45(04):85-90.
CHEN Fan,WU Yue,ZHANG Hengxin,et al.Experimental on air flow in flame tube of cannular combustor[J].Journal of Rocket Propulsion,2019,45(04):85-90.
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CHEN Fan,WU Yue,ZHANG Hengxin,et al.Experimental on air flow in flame tube of cannular combustor[J].Journal of Rocket Propulsion,2019,45(04):85-90.
环管燃烧室火焰筒空气流量试验
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
45
期数:
2019年04期
页码:
85-90
栏目:
测控与试验
出版日期:
2019-08-30
- Title:
- Experimental on air flow in flame tube of cannular combustor
- 文章编号:
- 1672-9374(2019)04-0085-06
- 分类号:
- V434.3
- 文献标志码:
- A
- 摘要:
- 为确保环管型燃烧室火焰筒流量分布的均匀性,要求单台火焰筒流量相对偏差δ位于±1.5%之内。采用模拟压比法与相似理论,建立了火焰筒空气流量特性对比试验的数学模型,并对数据处理模型的误差传递进行分析,得出现有模型存在一个不能对火焰筒真实特性进行判定的区间,火焰筒入口空气压力偏差Δp1是引起δ误差的关键因素。为此,设计了一种基于两级扩散、整流集气装置的空气流量试验系统,并对一组16台火焰筒试验件进行了入口压力p1为20 kPa,40 kPa,60 kPa及80 kPa下的空气流量试验研究。数据显示火焰筒入口压力偏差小于±0.05 kPa,入口压力脉动相对值小于0.25%,产品特性参数C值的相对误差不大于±0.01%,可以实现对火焰筒流量特性一致性的判定。
- Abstract:
- In order to ensure the uniformity of flow distribution in the cannular combustor,the relative deviation δ of the single flame tube flow is required to be within±1.5%.For this reason,a mathematical model for the comparison test of the air flow characteristics in flame tube was established by using simulated pressure ratio method and similarity theory.The error transfer analysis of the data processing model shows that there is an interval in the existing model that cannot determine the true characteristics of the flame tube,and the inlet air pressure deviation Δp1 of the flame tube is a key factor causing the δ error.Furthermore,an air flow test system based on two-stage diffusion and rectifier gas collection device was designed,and the air flow experiments were carried out for a group of 16 flame tubes under the inlet pressure p1 of 20 kPa,40 kPa,60 kPa and 80 kPa,respectively.The results show that the inlet pressure deviation of flame tube is less than±0.05 kPa,the relative value of inlet pressure pulsation is less that 0.25%,and the relative error of product characteristic parameter C is not more than±0.01%,which could determine the consistency of flow characteristics for the flame tube.
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备注/Memo
收稿日期:2018-06-16; 修回日期:2018-09-11作者简介:陈帆(1989—),男,硕士,研究领域为液体火箭发动机介质试验技术
更新日期/Last Update:
2019-08-31