航天推进技术研究院主办
[1]管杰,何宏疆,董万峰,等.流量调节器快速起调过程[J].火箭推进,2022,48(05):61-68.
GUAN Jie,HE Hongjiang,DONG Wanfeng,et al.Rapid start-up process of liquid-flow regulator[J].Journal of Rocket Propulsion,2022,48(05):61-68.
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GUAN Jie,HE Hongjiang,DONG Wanfeng,et al.Rapid start-up process of liquid-flow regulator[J].Journal of Rocket Propulsion,2022,48(05):61-68.
流量调节器快速起调过程
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年05期
页码:
61-68
栏目:
目次
出版日期:
2022-10-25
- Title:
- Rapid start-up process of liquid-flow regulator
- 文章编号:
- 1672-9374(2022)05-0061-08
- 分类号:
- V434.2
- 文献标志码:
- A
- 摘要:
- 针对补燃循环发动机启动过程中流量调节器的工作特性,首先建立了描述流量调节器起调过程的动力学模型。然后设计并开展了液流试验,分析了流量调节器在快速起调过程中的特性,获得了不同阻尼孔孔径下的试验特性。试验结果表明,流量调节器在快速起调过程中,流量存在大幅超调的现象,通过增大阻尼孔孔径,可以有效地减小流量超调量。最后通过试验结果验证了仿真模型的合理性,并基于计算结果,分析了流量调节器在起调过程中滑阀位移和流量的变化过程,进一步分析了阻尼孔孔径和升压速率对起调过程的影响。仿真结果表明,为了减小起调过程中的流量波动,流量调节器进出口压差的升压速率应先慢后快。
- Abstract:
- In view of the working characteristics of the liquid-flow regulator during the starting process of the staged combustion cycle engine, a dynamic model describing the start-up process of the flow regulator was established.Then, a liquid flow test was designed and carried out, and the test characteristics under different damping orifice diameters were obtained by analyzing the characteristics of the liquid-flow regulator during the rapid start-up process.The test results show that there is a large overshoot phenomenon for the flow rate during the rapid start-up process of the liquid-flow regulator.By increasing the orifice diameter, the flow rate overshoot can be effectively reduced.Finally, the rationality of the simulation model was verified by the test results.Based on the calculation results, the change process of the spool displacement and flow rate during the start-up process was analyzed.The effects of orifice diameter and pressure rise rate on the regulating process were further analyzed.The simulation results show that in order to reduce the flow fluctuation during the start-up process, the pressure rise rate of the differential pressure should be slow first and then fast.
参考文献/References:
[1] 谭永华,杜飞平,陈建华,等.液氧煤油高压补燃循环发动机深度变推力系统方案研究[J].推进技术,2018,39(6):1201-1209.
[2] 张贵田.高压补燃液氧煤油发动机[M].北京:国防工业出版社,2005.
[3] 李斌,张小平,马冬英.我国新一代载人火箭液氧煤油发动机[J].载人航天,2014,20(5):427-431.
[4] 张晓光,董国创,陈晖.基于机电伺服控制的液氧煤油发动机推力调节技术[J].载人航天,2020,26(2):230-236.
[5] 徐浩海,李春红,陈建华,等.深度变推力液氧煤油发动机初步方案研究[J].载人航天,2016,22(2):150-155.
[6] 王海燕,邢理想,高玉闪,等.富氧补燃循环液氧煤油发动机深度推力调节方案对比分析[J].载人航天,2019,25(3):389-396.
[7] 岳春国,李进贤,侯晓,等.变推力液体火箭发动机综述[J].中国科学:E辑,2009,39(3):464-468.
[8] 许志宇,李小明.过载对流量调节器静态特性的影响研究[J].火箭推进,2016,42(3):63-67.
XU Z Y,LI X M.Effects of overload on static characteristics of liquid-flow regulator[J].Journal of Rocket Propulsion,2016,42(3):63-67.
[9] 刘红军.稳流型流量调节器动态响应特性研究[J].推进技术,1999,20(1):60-64.
[10] 刘红军.补燃循环发动机静态特性与动态响应特性研究[D].西安:中国航天工业总公司第十一研究所,1998.
[11] 王昕.流量调节器动态特性研究[J].火箭推进,2004,30(3):19-24.
WANG X.Study on dynamic characteristics of flow regulator[J].Journal of Rocket Propulsion,2004,30(3):19-24.
[12] 刘上,刘红军,徐浩海,等.流量调节器-管路系统频率特性及稳定性[J].推进技术,2012,33(4):631-638.
[13] LIU S,LIU H J,SUN H M,et al.Research of the flow regulator nonlinear frequency characteristics by incremental harmonic balance method[J].Tuijin Jishu/Journal of Propulsion Technology,2012,33(5):814-819.
[14] 张淼,李斌,邢理想.流量调节器动力学模型优化及自激振荡动特性研究[C]//中国航天第三专业信息网第四十届技术交流会暨第四届空天动力联合会议论文集.昆明:中国航天第三专业信息网,2019.
[15] JUNG T.Static characteristics of a flow regulator for a liquid rocket engine[J].Journal of Spacecraft and Rockets,2011,48(3):541-544.
[16] JUNG T,LEE S,KWON S.Dynamic characteristics of a bellows-type mixture-ratio stabilizer for a liquid rocket engine[J].Journal of Spacecraft and Rockets,2010,47(5):849-856.
[17] 管杰,刘上,刘志让.补燃发动机完全自身起动过程富氧燃气温度控制[J].火箭推进,2020,46(3):33-40.
GUAN J,LIU S,LIU Z R.Temperature control of oxygen-riched gas during complete self start-up process for staged combustion cycle engine[J].Journal of Rocket Propulsion,2020,46(3):33-40.
[18] 黄敏超,刘昆,邢宝玉.液体火箭发动机动态性能分析[M].长沙:国防科技大学出版社,2015.
[19] 刘上,刘红军,孙宏明,等.基于增量谐波平衡法的流量调节器非线性频率特性[J].推进技术,2012,33(5):814-819.
[20] 王飞.大推力液氧煤油发动机起动过程研究[D].西安:中国航天科技集团有限公司第十一研究所,2015.
备注/Memo
收稿日期:2021-06-24 修回日期:2021-08-12
基金项目:国家液体火箭发动机技术重点实验室基金(6142704180308)
作者简介:管杰(1995—),男,硕士,研究领域为液体火箭发动机系统动力学。
更新日期/Last Update:
1900-01-01