航天推进技术研究院主办
[1]白东安.涡轮泵超低工况性能研究[J].火箭推进,2008,34(03):13-16.
Bai Dong'an.Research on the turbo-pump performance under ultra--low operation condition[J].Journal of Rocket Propulsion,2008,34(03):13-16.
点击复制
Bai Dong'an.Research on the turbo-pump performance under ultra--low operation condition[J].Journal of Rocket Propulsion,2008,34(03):13-16.
涡轮泵超低工况性能研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
34
期数:
2008年03期
页码:
13-16
栏目:
研究与设计
出版日期:
2008-06-30
- Title:
- Research on the turbo-pump performance under ultra--low operation condition
- Keywords:
- turbo-pump; variable conditions; performance research
- 分类号:
- V434.21
- 文献标志码:
- A
- 摘要:
- 对于泵压式变推力发动机和先进的冲压发动机，需要涡轮泵变工况工作，涡轮 泵变工况性能是该类发动机研究的一个重点。结合上面级验证性发动机试车，对游机涡轮泵 变工况的性能和稳定性进行分析研究。通过泵全流量特性试验和汽蚀试验，得出泵能够在额 定流量点25％处稳定工作的结论。对涡轮工况变化后的燃气参数、入口压力、出口压力及效 率进行分析．认为涡轮也能够稳定工作。给出了游机涡轮泵可以参加验证性试车的结论，并 得到了发动机试车的验证。
- Abstract:
- The capability of turbo-pump working in variable conditions is required and important for pump—pressurized variable thrust rocket engine and ramjet propulsion．Combining with a test of the upper stage rocket engine，the performance and stability of the turbo-pump at low condition are studied in this paper．Through the full flow characteristic and cavitation tests of pump，it is con— eluded that the pump can work stably in 25％rated flow condition．The analyses of gas parameter, inlet pressure，outlet pressure and efficiency of turbo under varied conditions indicated that the turbo can also work stably．The conclusions made above age verified by engine test．
参考文献/References:
[1]阿列玛索夫B E．火箭发动机原理[M]．北京：机械工业
出版社．1989．
[2]黄智勇，李晶奂，黄红．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(1)：32—35．
[3]沃尔科夫E B．火箭发动机静、动力学[M]．北京：机械工
业出版社．1978．
[4]奥夫夏尼科夫B B．高转速叶片泵咖．北京：机械工业出
版社。1975．
[5]莫什金E K．液体火箭发动机动力学过程[M]．北京：机
械工业出版社．1964．
[6]严俊峰，陈炜．基于遗传算法的低比转速高速泵优化设
计[J]．火箭推进，2006，32(3)：1-7．
相似文献/References:
[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.
ZHANG Chenxi,MA Xiaodan.Integration design system for turbo pump
in rocket engine[J].Journal of Rocket Propulsion,2015,41(03):79.
[2]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(03):73.
[3]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(03):17.
[4]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(03):34.
[5]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(03):38.
[6]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(03):29.
[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(03):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(03):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(03):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(03):24.
备注/Memo
收稿日期：2008一OI一14；修回日期：2008—03—20。 作者简介：白东安(1966一)，男。研究员，研究领域为液体火箭发动机涡轮泵设计。
更新日期/Last Update:
1900-01-01