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[1]李爱民,金 路,苗旭升,等.基于串联刚度模型的涡轮泵轴向力计算方法[J].火箭推进,2020,46(06):30-34.
　LI Aimin,JIN Lu,MIAO Xusheng,et al.Calculation method of axial force in turbopump based on serial stiffness model[J].Journal of Rocket Propulsion,2020,46(06):30-34.
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基于串联刚度模型的涡轮泵轴向力计算方法

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 46 期数: 2020年06期 页码: 30-34 栏目: 研究与设计 出版日期: 2020-12-31
Title:
Calculation method of axial force in turbopump based on serial stiffness model
文章编号:
1672-9374(2020)06-0030-05
作者:
李爱民1; 金 路1; 苗旭升2; 李惠敏1; 李春乐1
(1.西安航天动力研究所,陕西 西安 710100; 2.西北工业大学,陕西 西安 710072)
Author(s):
LI Aimin1; JIN Lu1; MIAO Xusheng2; LI Huimin1; LI Chunle1
(1.Xi'an Aerospace Propulsion Institute, Xi'an 710100, China; 2.Northwest Polytechnical University, Xi'an 710072, China)
关键词:
涡轮泵;  轴向力;  串联刚度模型;  轴承
Keywords:
turbopump;  axial force;  serial stiffness model;  bearing
分类号:
V434.21
文献标志码:
A
摘要:
转子轴向力为液体火箭发动机涡轮泵工作过程中的一项重要参数,把转子轴向力有效控制在主轴承的承载范围内是涡轮泵可靠工作的基础。为准确获取涡轮泵轴向力,采用基于串联刚度模型的方法,利用转子轴端位移和轴承的静刚度试验数据,结合有限元分析,得到某发动机涡轮泵转子轴系的轴向载荷,与轴向力传感器实测误差为4.1%。利用该方法,可实现涡轮泵试验过程中转子位移与轴向载荷之间的相互验证,提高测试数据可靠性,保证试验成功率,减少试验次数,降低试验成本。
Abstract:
The axial force of rotor is an important parameter in the working process of liquid rocket engine turbopump.Controlling the axial force of rotor within the load carrying capacity that the main bearing, which is the foundation that turbopump can work in stability and reliability.Based on the serial stiffness model and the finite element analysis, combined with the test data of shaft displacement and the static stiffness of the bearing, the axial load of rotor shaft system in an engine turbopump was obtained.The relative error between the calculated value and the experimental value was 4.1%.By using this method, the rotor displacement and the axial load can be verified during the turbopump test, and the reliability of the test data can be improved.Therefore, it guarantees the success rate of test, and reduces the test time and expense.

参考文献/References:

[1] BATCHELOR G K.Note on a class of solutions of the navier-stokes equations representing steady rotationally-symmetric flow[J].The Quarterly Journal of Mechanics and Applied Mathematics,1951,4(1): 29-41.
[2] DAILY J W,NECE R.Chamber dimension effects on induced flow and frictional resistance of enclosed rotating disks[J].Journal of Basic Engineering,1960,82(1): 217-230.
[3] KUROKAWA J,TOYOKURA T.Axial thrust,disk friction torque and leakage loss of radial flow turbomachinery[J].Proceedings of Pumps and Turbines Conference in Glasgow,1976(1):1-5.
[4] KUROKAWA J,KAMIJO K,SHIMURA T.Axial thrust behavior in LOX-pump of rocket engine[J].Journal of Propulsion and Power,1994,10(2): 244-250.
[5] 黄智勇,逯婉若,李惠敏.补燃发动机涡轮泵轴向力平衡系统研究[J].火箭推进,2004,30(2): 1-5. HUANG Z Y,LU W R,LI H M.Axial force equilibrium study of staged combustion rocket engine turbopump [J].Journal of Rocket Propulsion,2004,30(2): 1-5.
[6] PONCET S,CHAUVE M,SCHIESTEL R.Batchelor versus Stewartson flow structures in a rotor-stator cavity with throughflow[J].Physics of Fluids,2005,17(7): 253-668.
[7] BARABAS B,CLAUSSl S,SCHUSTER S,et al.Experimental and numerical determination of pressure and velocity distribution inside a rotor-stator cavity at very high circumferential Reynolds numbers[C] //11th European Conference on Turbomachinery Fluid dynamics and Thermodynamics.Madrid,Spain:[s.n.],2015.
[8] TAKAMI Y,MAKINOUCHI K,OTSUKA G,et al.Quantitative approach to control spinning stability of the impeller in the pivot bearing-supported centrifugal pump[J].Artificial Organs,1997,21(12): 1292-1296.
[9] ICHIKAWA S,NISHIMURA I,MIKAMI M,et al.The balance of the impeller-driver magnet affects the antithrombogenicity in the gyro permanently implantable pump[J].Artificial Organs,2002,26(11): 927-930.
[10] 杜大华,黄金平,邢理想,等.液体火箭发动机泵动态特性水力试验研究[J].火箭推进,2013,39(3): 50-57. DU D H,HUANG J P,XING L X,et al.Hydraulic test research on dynamic characteristics of oxygen pump of liquid rocket engine[J].Journal of Rocket Propulsion,2013,39(3): 50-57.
[11] 黄智勇,李惠敏.试验转速对大流量高转速轴流泵性能的影响[J].火箭推进,2006,32(4): 1-5. HUANG Z Y,LI H M.Effect of test rotation speed on the performance of axial flow pump with high flow rate and speed[J].Journal of Rocket Propulsion,2006,32(4): 1-5.
[12] 陈锦.泵水力试验测控系统故障模式分析[J].火箭推进,2006,32(2): 46-51. CHEN J.Analysis of malfunction mode of measure and control system for pump hydraulic test[J].Journal of Rocket Propulsion,2006,32(2): 46-51.
[13] 张萍.预压涡轮泵水力性能试验系统[J].火箭推进,2003,29(6): 23-25. ZHANG P.Test system of hydraulic performance of a prepressurized turbopump[J].Journal of Rocket Propulsion,2003,29(6): 23-25.
[14] 白东安.三组元液体火箭发动机涡轮泵变工况研究[J].火箭推进,2004,30(4): 22-26. BAI D A.Study on tripropellant turbopump for the liquid rocket engine with variable operation conditions[J].Journal of Rocket Propulsion,2004,30(4): 22-26.
[15] 冀秀彦,孟晨,李铭,等.一种泵轴向力测试系统和方法介绍[J].水泵技术,2014(4): 36-39.
[16] 曹磊,高德平,江和甫.弹性环刚度特性研究[J].燃气涡轮试验与研究,2007,20(1): 36-38.
[17] 方昆凡.工程材料手册—有色金属材料卷[M].北京: 北京出版社,2002.
[18] 《航空发动机设计手册》总编委会.航空发动机设计手册第19册:转子动力学及整机振动[M].北京: 航空工业出版社,2000.
[19] 邓四二,贾群义,薛进学.滚动轴承设计原理[M].2版.北京: 中国标准出版社,2014.
[20] 王东峰,方斌,李庆荣,等.角接触球轴承刚度计算与分析[J].轴承,2016(4): 1-5.

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[10]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(06):8.
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　HUANG Jinping,WANG Jun,HUANG Daoqiong,et al.Experimental study on high-speed running of rolling bearing-rotor system of turbo-pump[J].Journal of Rocket Propulsion,2020,46(06):50.

备注/Memo

收稿日期:2019-06-19; 修回日期:2020-09-10 基金项目:国家重大基础研究项目(613321) 作者简介:李爱民(1986—),男,博士,高级工程师,研究领域为液体火箭发动机涡轮泵

更新日期/Last Update: 1900-01-01