PDF下载分享

[1]刘昊,王君,张留欢.SMC模式下RBCC发动机4Ma工况性能仿真[J].火箭推进,2021,47(02):27-31.
　LIU Hao,WANG Jun,ZHANG Liu Huan.Performance simulation of 4 Ma operating conditionunder SMC mode for RBCC engine[J].Journal of Rocket Propulsion,2021,47(02):27-31.

点击复制

SMC模式下RBCC发动机4Ma工况性能仿真

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 47 期数: 2021年02期页码: 27-31 栏目: 研究与设计出版日期: 2021-04-21

Title:: Performance simulation of 4 Ma operating conditionunder SMC mode for RBCC engine

文章编号:: 1672-9374(2021)02-0000-05

作者:: 刘昊; 王君; 张留欢; 西安航天动力研究所,陕西西安 710100

Author(s):: LIU Hao; WANG Jun; ZHANG Liu Huan; Xi'an Aerospace Propulsion Institute, Xi'an 710100, China

关键词:: RBCC发动机; SMC模式; 火箭混合比; 燃烧室长度

Keywords:: RBCC engine; SMC mode; rocket mixing ratio; combustor length

分类号:: V434-34

文献标志码:: A

摘要:: 为研究SMC模式下火箭混合比对RBCC发动机性能的影响规律,完成了氢/氧火箭推力室中心布局、二元定几何结构模型发动机Ma₀=4/H=17 km弹道点流场仿真,获得了不同火箭混合比(MR=2、3、4、5、6、8)及燃烧室长度的推力、比冲性能。研究表明:1)在火箭燃气富燃条件下(MR<8),产生了正的火箭推力增益,且随着混合比的减小,火箭推力增益增加; 2)二次燃烧过程受火箭射流与冲压主流剪切层掺混主导,在本文给定的基准燃烧室长度下,燃烧效率随着混合比的提高而增加,且火箭射流与冲压主流的超/超射流剪切层燃烧过程一直持续到喷管出口; 3)通过增加燃烧室长度,火箭富燃燃气获得更为充分的燃烧,发动机性能显著提升,但在具体发动机设计中,燃烧室长度的选取需在燃烧效率与结构惩罚之间进行权衡。

Abstract:: In order to obtain the influence of rocket mixing ratio on RBCC engine performance under SMC mode, the flow field simulation of Ma₀=4/H=17 km was conducted for the engine with the center layout of H₂/O₂ rocket trust chamber and two-dimension fixed structure.. The engine thrust and specific impulse of different rocket mixing ratio(MR=2、3、4、5、6、8)and combustor length were analyzed also. The studies indicates that: 1)Positive rocket thrust augmentation is obtained when the rocket operating under rich-fuel state(MR<8), and rocket thrust augmentation reduces with the rocket mixing ratio increasing; 2)The secondary combustion process is dominated by the shear layer mixing effect between the supersonic rocket gas jet and the supersonic air flow captured by ramjet combustor. Under the given reference combustor length in this paper, the combustion efficiency increases with the improvement of mixing ratio, and the supersonic/supersonic jet shear layer combustion process lasts until the nozzle outlet; 3)Engine thrust and specific impulse can be significantly enhanced by increasing the combustor length so that the rocket fuel-rich gas can be fully burned. However, in the specific engine design, the selection of the combustor length should be balanced between the combustion efficiency and the engine structure penalty.

参考文献/References:

[1] 刘洋, 何国强, 刘佩进, 等. RBCC组合循环推进系统研究现状和进展[J]. 固体火箭技术, 2009, 32(3): 288-293. [2] 崔朋, 徐万武, 陈健, 等. 火箭基组合循环燃烧组织研究现状[J]. 火箭推进, 2015, 41(4): 1-7.CUI P, XU W W, CHEN J, et al. Research progress about rocket based combined cycle combustion organization[J]. Journal of Rocket Propulsion, 2015, 41(4): 1-7. [3] 王振国, 梁剑寒, 丁猛, 等. 高超声速飞行器动力系统研究进展[J]. 力学进展, 2009, 39(6): 716-739. [4] LEHMAN M, PAL S, BRODA J, et al. Raman spectroscopy based study of RBCC ejector mode performance[C]//37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: AIAA, 1999. [5] LEHMAN M, PAUL S, SANTORO R J. Experimenatl investigation of the RBCC rocket-ejector mode[R]. AIAA 2000-3725, 2000. [6] 王国辉, 何国强, 刘佩进, 等. RBCC引射模态DAB模式二次燃烧数值研究[J]. 固体火箭技术, 2004, 27(1): 5-8. [7] RUSSELL R, BROCCO D, DAINES R. Modeling and validation of an ejector primary rocket for shielded afterburning fuel injection[C]//35th Joint Propulsion Conference and Exhibit. Reston, Virigina: AIAA, 1999. [8] BOND R, EDWARDS J. CFD analysis of an independently fueled ramjet stream in an RBCC engine[C]//41st Aerospace Sciences Meeting and Exhibit. Reston, Virigina: AIAA, 2003. [9] 崔朋. SMC模式下火箭基组合循环引射/亚燃模态性能研究[D]. 长沙: 国防科学技术大学, 2015. [10] 潘科玮, 何国强, 刘佩进, 等. RBCC混合燃烧模态一次火箭对燃烧稳定影响[J]. 推进技术, 2010, 31(5): 544-548. [11] 吕翔, 刘佩进, 何国强, 等. 火箭引射模态下一次火箭流量优化方法研究[J]. 固体火箭技术, 2010, 33(6): 631-635. [12] 黄生洪, 何国强, 何洪庆. 支板火箭引射冲压发动机引射模态燃烧流动(Ⅰ)瞬时掺混燃烧流场的数值模拟[J]. 推进技术, 2003, 24(2): 160-165. [13] KAMHAWI H, KRIVANEK T, THOMAS S, et al. Direct-connect ejector ramjet combustor experiment[C]//41st Aerospace Sciences Meeting and Exhibit. Reston, Virigina: AIAA, 2003. [14] JOS C C, ANDERSON W E, SANKARAN V, et al. Ducted rocket tests with a fuel rich primary Thruster[R]. AIAA 2005-4282, 2005. [15] LI Y F, HE G Q, LIU P J. Experimental investigation of rocket ejector in SMC combustion mode[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. Reston, Virigina: AIAA, 2006. [16] 李宇飞, 何国强, 刘佩进. SMC燃烧模式下引射火箭性能影响因素的实验研究[J]. 推进技术, 2006, 27(2): 97-100. [17] 魏祥庚, 秦飞, 石磊, 等. RBCC用变工况气氧/煤油引射火箭发动机设计和试验研究[J]. 西北工业大学学报, 2018, 36(3): 558-564. [18] 朱韶华, 田亮, 刘亚冰, 等. RBCC引射火箭燃烧室设计及试验研究[J]. 推进技术, 2014, 35(10): 1378-1386. [19] 刘佩进, 何国强, 李宇飞. RBCC引射火箭模态二次燃烧实验[J]. 推进技术, 2004, 25(1): 75-77. [20] 刘昊, 王君. RBCC发动机火箭推力增益之探讨[J]. 火箭推进, 2017, 43(1): 18-23.LIU H, WANG J. Discussion of rocket thrust augmentation for RBCC engine[J]. Journal of Rocket Propulsion, 2017, 43(1): 18-23.

相似文献/References:

[1]刘晓伟,刘昊,张蒙正.RBCC火箭对直扩通道抗反压能力的影响研究[J].火箭推进,2015,41(06):7.
　LIU Xiaowei,LIU Hao,ZHANG Mengzheng.Influence of RBCC rocket on resisting backpressure ability of straight-expanded flowpath[J].Journal of Rocket Propulsion,2015,41(02):7.
[2]刘晓伟,李永洲.侧置火箭对发动机尾喷管的影响研究[J].火箭推进,2015,41(04):43.
　LIU Xiaowei,LI Yongzhou.Impact of sidewall rocket on engine nozzle[J].Journal of Rocket Propulsion,2015,41(02):43.
[3]张留欢,周建平,杜泉,等.RBCC发动机热力/推进效率计算及影响因素研究[J].火箭推进,2016,42(06):31.
　ZHANG Liuhuan,ZHOU Jianping,DU Quan,et al.Calculation and analysis on thermodynamic and propulsive efficiencies of RBCC engine[J].Journal of Rocket Propulsion,2016,42(02):31.
[4]严俊峰,张蒙正,路媛媛.基于分层燃烧的RBCC发动机热力循环浅析[J].火箭推进,2017,43(04):29.
　YAN Junfeng,ZHANG Mengzheng,LU Yuanyuan.Brief analysis on thermodynamic cycle of RBCC engine based on stratified combustion[J].Journal of Rocket Propulsion,2017,43(02):29.
[5]南向军,李斌,何国强.RBCC发动机火箭及火箭冲压模态热力循环分析[J].火箭推进,2023,49(05):39.
　NAN Xiangjun,LI Bin,HE Guoqiang.Thermodynamic cycle analysis of RBCC engine rocket and rocket-scramjet mode[J].Journal of Rocket Propulsion,2023,49(02):39.
[6]王壮,李钰航,张蒙正,等.RBCC发动机不同构型隔离段流场仿真[J].火箭推进,2023,49(06):82.
　WANG Zhuang,LI Yuhang,ZHANG Mengzheng,et al.Simulation on flow field in isolator of RBCC engine with different configurations[J].Journal of Rocket Propulsion,2023,49(02):82.

备注/Memo

收稿日期:2020-07-08
作者简介:刘昊(1984—),男,博士,高级工程师,研究领域为组合推进技术。

更新日期/Last Update: 1900-01-01