PDF下载 分享
[1]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):29-33.
　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(04):29-33.
点击复制

基于分层燃烧的RBCC发动机热力循环浅析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 43 期数: 2017年04期 页码: 29-33 栏目: 研究与设计 出版日期: 2017-10-01
Title:
Brief analysis on thermodynamic cycle of RBCC engine based on stratified combustion
作者:
严俊峰; 张蒙正; 路媛媛
西安航天动力研究所, 陕西 西安 710100
Author(s):
YAN Junfeng;  ZHANG Mengzheng; LU Yuanyuan
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
关键词:
分层燃烧; RBCC发动机; 热力循环; 热力学分析
Keywords:
stratified combustion;  RBCC engine;  thermodynamic cycle;  thermodynamic analysis
分类号:
V434-34
文献标志码:
A
摘要:
针对分层燃烧循环RBCC发动机，建立了热力学理论模型，引入压缩效率、加热比和增压比，对RBCC发动机的热力循环过程进行分析，推导了发动机热效率计算公式，探讨了热效率随不同参数的变化及其与各参数之间的关系。分析表明，压缩效率、加热比及喷管压比越高，热效率越大；存在最优增压比，可使热效率达到最高值。
Abstract:
A theoretical thermodynamic cycle model was set up for RBCC engine with stratified combustion(SC) cycle. The thermodynamic cycle process of RBCC engine is analyzed by importing the parameters of compression efficiency, pressure ratio and heating ratio. A computational formula of the engine's thermal efficiency was derived. The variation of thermal efficiency with different parameters and relationship between the parameters are deduced. The analysis results show that the higher the compression efficiency, heating ratio and nozzle pressure ratio are, the higher the thermal efficiency becomes; the pressure ratio can make the thermal efficiency reach the maximum value.

参考文献/References:

[1]张蒙正, 李平, 陈祖奎. 组合循环动力系统面临的挑战及前景[J]. 火箭推进, 2009, 35(1): 1-8.
ZHANG Mengzheng, LI Ping, CHEN Zukui. Challenge and perspective of combined cycle propulsion[J]. Journal of rocket propulsion, 2009, 35(1):1~8.
[2]黄伟, 罗世斌, 王振国. 火箭基组合循环(RBCC)发动机性能分析[J]. 火箭推进, 2007, 33(5): 6-10.
HUANG Wei, LUO Shibin, WANG Zhenguo. Performance analysis of RBCC engine[J]. Journal of rocket propulsion, 2007, 33(5): 6-10.
[3]张蒙正, 李斌, 王君, 等. 关于RBCC动力系统的思考[J].火箭推进, 2013, 39(1): 1-7.
ZHANG Mengzheng, LI Bin, WANG Jun, et al. Thinking about RBCC power system[J]. Journal of rocket propulsion, 2013, 39(1): 1-7.
[4]TOMIOKA S, KATO K, TAN K. Performance of a rocket-ramjet combined-cycle engine model under ramjet-mode operations, AIAA 2012-3921[R]. Reston: AIAA, 2012.
[5]刘国球, 任汉芬, 朱宁昌, 等. 液体火箭发动机原理[M]. 北京: 中国宇航出版社, 1993.
[6]朱明善, 刘颖, 林兆庄, 等. 工程热力学[M]. 北京: 清华大学出版社, 2011.
[7]胡建新, 张为华. 冲压推进技术[M]. 长沙: 国防科技大学出版社, 2013.
[8]石秀勇, 王禹, 倪计民, 等. 基于多孔介质燃烧的发动机理论热力循环分析[J]. 同济大学学报, 2013, 41(4):559-564.

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(04):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(04):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(04):31.
[4]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.
　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(04):27.
[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(04):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(04):82.

备注/Memo

收稿日期：2014-12-01；修回日期：2015-09-13 作者简介：严俊峰（1980—），男，硕士，高级工程师，研究领域为组合推进设计

更新日期/Last Update: 1900-01-01