PDF下载 分享
[1]张晨曦,马晓丹.火箭发动机涡轮泵集成设计系统[J].火箭推进,2015,41(04):79-83.
　ZHANG Chenxi,MA Xiaodan.Integration design system for turbo pump in rocket engine[J].Journal of Rocket Propulsion,2015,41(04):79-83.
点击复制

火箭发动机涡轮泵集成设计系统

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年04期 页码: 79-83 栏目: 研究与设计 出版日期: 2015-09-30
Title:
Integration design system for turbo pump in rocket engine
作者:
张晨曦1; 马晓丹2
1. 西安航天动力研究所，陕西 西安 710100； 2. 第二炮兵工程大学，陕西 西安 710125
Author(s):
ZHANG Chenxi1;  MA Xiaodan2
1. Xi’an Aerospace Propulsion Institute, Xi’an 710100, China; 2. Second Artillery Engineering University, Xi’an 710125, China
关键词:
火箭发动机设计; 涡轮泵; 集成设计; 数字化设计
Keywords:
rocket engine design;  turbo pump;  integration design;  digitalization design
分类号:
V432-34
文献标志码:
A
摘要:
针对火箭高密度发射常态化现状，结合发动机设计自身特点，从提高效率、标准化和可靠性等出发，建立了发动机数字化集成设计系统。该系统通过对涡轮泵设计分析模型和应用进行封装，对设计方法、程序、参数及软件进行封装，实现了设计全流程数字化、模块化及流程化。通过详述涡轮泵设计流程的设计过程，实现了高集成化、模块化、多学科、高效及可靠的集成设计平台系统。
Abstract:
In order to meet the needs of the frequently rocket launch, according to the characteristics of rocket engine, a integration design system for rocket engine was constructed to improve the standardization, dependability and efficiency. Digitalization design and modularity design in the whole design flow were actualized by integration of design methods, program, parameters and software, and thorough analysis of liquid rocket engine design information. The design flow and result of turbo pump integration design are described. The advantages (high integration, modularity, multidisciplinary comprehension, high efficiency and high reliability) of integration design system for liquid rocket engine are elaborated in detail.

参考文献/References:

[1]朱宁昌. 液体火箭发动机设计[M]. 北京: 宇航出版社, 1994.
[2]白晓瑞. 液体火箭推进系统动态特性仿真研究[D]. 长沙: 国防科技大学, 2008.
[3]解红雨. 固体火箭分布式集成设计平台及其关键技术[D]. 长沙: 国防科技大学, 2006.

相似文献/References:

[1]李 彤,刘站国,窦 昱,等.涡轮泵水力试验系统扭矩现场校准技术研究[J].火箭推进,2015,41(03):73.
　LI Tong,LIU Zhan-guo,DOU Yu,et al.Field calibration technology for torque of turbo pump hydraulic test system[J].Journal of Rocket Propulsion,2015,41(04):73.
[2]窦 唯,刘占生.液体火箭发动机涡轮泵转子弯扭耦合振动研究[J].火箭推进,2012,38(04):17.
　DOU Wei,LIU Zhan-sheng.Research on bend-twist coupling vibration of liquid rocket engine turbopump rotors[J].Journal of Rocket Propulsion,2012,38(04):17.
[3]唐 飞,李家文.诱导轮平面叶栅汽蚀不稳定现象的数值分析[J].火箭推进,2011,37(01):34.
　TANG Fei,LI Jia-wen.Numerical analysis of instable cavitation phenomenon in 2D blade cascade of inducer[J].Journal of Rocket Propulsion,2011,37(04):34.
[4]白东安,段增斌,张翠儒.涡轮泵端面密封性能与漏气量影响研究[J].火箭推进,2010,36(01):38.
　Bai Dong'an,Duan Zenbin,Zhang Cuiru.Effects of leaking rate on turbopump end-face sealing performance[J].Journal of Rocket Propulsion,2010,36(04):38.
[5]邓长华,周云端.涡轮泵环形颗粒阻尼器设计[J].火箭推进,2009,35(05):29.
　Deng Changhua,Zhou Yunduan.Design of circular particle damper for turbopump[J].Journal of Rocket Propulsion,2009,35(04):29.
[6]白东安.涡轮泵超低工况性能研究[J].火箭推进,2008,34(03):13.
　Bai Dong'an.Research on the turbo-pump performance under ultra--low operation condition[J].Journal of Rocket Propulsion,2008,34(04):13.
[7]凌桂龙,张黎辉,唐家鹏,等.泵压式氢/氧液体火箭发动机质量分析[J].火箭推进,2007,33(01):1.
　Ling Guilong Zhang Lihui Tang Jiapeng.Mass analysis of pump-pressurized hydrogen/oxygen liquid propellant rocket engine[J].Journal of Rocket Propulsion,2007,33(04):1.
[8]黄智勇,李昌奂,黄红,等.高工况涡轮泵轴系状态对工作可靠性的影响[J].火箭推进,2007,33(01):32.
　Huang Zhiyong,Li Changhuan,Huang Hong.The effect of high operating condition turbopump shafting status on reliability[J].Journal of Rocket Propulsion,2007,33(04):32.
[9]徐悦,田爱梅.基于CFD的涡轮泵转子密封流体激振研究进展[J].火箭推进,2005,31(01):8.
　Xu Yue,Tian Aimei.Progress of investigation on turbopump annular seal fluid-induced vibration based on CFD[J].Journal of Rocket Propulsion,2005,31(04):8.
[10]张忠利.高空滑行期间氧化剂泵壳体冷却方案研究[J].火箭推进,2005,31(01):24.
　Zhang Zhongli.Investigation on cooling of oxidizer pump case during coast period[J].Journal of Rocket Propulsion,2005,31(04):24.

备注/Memo

收稿日期：2015-03-13；修回日期：2015-05-05 作者简介：张晨曦（1985—），男，工程师，研究领域为液体火箭发动机数字化集成设计

更新日期/Last Update: 1900-01-01