航天推进技术研究院主办
[1]党枭睿,许开富,金路,等.带凹槽结构的涡轮泵平衡活塞工作特性分析[J].火箭推进,2022,48(01):45-52.
DANG Xiaorui,XU Kaifu,JIN Lu,et al.Analysis on working characteristics of balanced piston with groove structure for turbopump[J].Journal of Rocket Propulsion,2022,48(01):45-52.
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DANG Xiaorui,XU Kaifu,JIN Lu,et al.Analysis on working characteristics of balanced piston with groove structure for turbopump[J].Journal of Rocket Propulsion,2022,48(01):45-52.
带凹槽结构的涡轮泵平衡活塞工作特性分析
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
48
期数:
2022年01期
页码:
45-52
栏目:
研究与设计
出版日期:
2022-02-28
- Title:
- Analysis on working characteristics of balanced piston with groove structure for turbopump
- 文章编号:
- 1672-9374(2022)01-0045-08
- Keywords:
- balanced piston; groove structure; numerical simulation; pressure distribution; flow characteristic; sensitivity analysis
- 分类号:
- V434.2
- 文献标志码:
- A
- 摘要:
- 在涡轮泵中设计平衡活塞结构是用来平衡轴向力的重要方法之一,平衡活塞通过调节涡轮泵叶轮和壳体间隙的压力分布降低轴向力大小,而在平衡活塞内增设凹槽结构则可以更好地平衡轴向力、扩大平衡轴向力的工作范围。针对凹槽结构的工作特性研究问题,建立了带不同凹槽结构的平衡活塞后泄漏流道数值仿真模型,并根据仿真结果对平衡活塞后泄漏流道内的压力分布、流动特性和敏感性进行分析。数值仿真结果表明:凹槽结构带来的进出口轴向速度,即转静空腔径向速度增加导致平衡活塞后泄漏流道总流阻降低,泄漏流量增加,迷宫密封处压降升高。流经凹槽结构的流体角动量和切向速度降低是径向压差降低的主要原因。凹槽结构上半部分对于平衡轴向力起主要作用,下半部分则无明显平衡轴向力效果。此外,轴向力对凹槽宽度变化十分敏感,凹槽深度变化则对其影响较小。
- Abstract:
- The design of balanced piston structure in turbopump is one of the most important methods to balance the axial force. The balanced piston reduces the axial force by adjusting the pressure distribution between the impeller and shell,while adding a groove structure in the balanced piston can better balance the axial force and expand its working range. In view of the working characteristics of the groove structure,a numerical simulation model of the balanced piston with different grooves was established,and the pressure distribution,flow characteristics and sensitivity analysis of the balanced piston were analyzed based on the numerical simulation results. The numerical simulation results show that the increase of inlet and outlet axial velocity caused by the groove structure,which is the radial velocity of the rotating static cavity,leads to a decrease of the total flow resistance,an increase of the leakage flow,and an increase of the pressure drop at the labyrinth seal. In addition,the decrease of the angular momentum and tangential velocity of the fluid flowing through the groove structure is the main reason for the decrease of the radial pressure difference. The upper part of the groove structure plays a major role in balancing the axial force,while the lower part has no obvious effect on balancing axial force. Moreover,the axial force is sensitive to the change of the groove width,but the change of the groove depth has little effect on it.
参考文献/References:
[1] 谭永华,杜飞平,陈建华,等.液氧煤油高压补燃循环发动机深度变推力系统方案研究[J].推进技术,2018,39(6):1201-1209.
[2] 董玮. 离心泵叶轮后盖板侧腔体流动机理及轴向力特性的研究[D].西安:西北工业大学,2018.
[3] DONG W,CHU W L,LI X J,et al. Numerical analysis of the influences of balance hole diameter on the flow characteristics of the back chamber of centrifugal pump[C]//ASME Turbo Expo 2016:Turbomachinery Technical Conference and Exposition. New York:ASME,2016.
[4] YOKOTA H,YOKOTA S. Device for balancing axial thrust on the impeller shaft of pumps[Z].1973.
[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] 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.
[7] SHIMURA T,HASEGAWA S. Axial thrust balancing of the LE-7 LOX turbopump[J].Journal of the Japan Society for Aeronautical and Space Sciences,1993,41(477):590-596.
[8] SHIMURA T,KAWASAKI S,UCHIUMI M,et al. Internal flow and axial thrust balancing of a rocket pump[C]//ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. New York:ASME,2011.
[9] KIMURA T,KAWASAKI S,SHIMAGAKI M,et al. Effects of swirl brakes on the leakage flow between the casing and the shroud of a centrifugal impeller[C]//ASME-JSME-KSME 2011 Joint Fluids Engineering Conference. New York:ASME,2011.
[10] MATSUI J,MUGIYAMA T. Effect of J-groove on the axial thrust in centrifugal pump[J].AIP Conference Proceedings,2010,1225(1):129-136.
[11] CHOI Y D,KUROKAWA J. A method of axial thrust control in centrifugal pump[J].The KSFM Journal of Fluid Machinery,2007,10(4):15-20.
[12] KUROKAWA J,KAMIJO K,SHIMURA T. Axial thrust analysis in LOX-pump[C]//AIAA/SAE/ASME/ASEE 27th Joint Propulsion Conference.Reston,Virginia:AIAA,1991.
[13] NOH J G,CHOI C H,KIM J. Numerical study on the effect of cavity vanes to control the axial thrust of a turbopump[J].Journal of Fluid Machinery,2006,9(2):39-43.
[14] MAIER S,WAGNER B,VEGGI L,et al. Analytical and numerical assessment of axial thrust balancing systems in liquid rocket engine LOx turbopumps[EB/OL].https://www.semanticscholar.org/paper/Analytical-and-numerical-assessment-of-axial-thrust-Maier-Wagner/ae2b5ae60b898146de8e097aceee38866dc47ea7,2017.
[15] PONCET S,CHAUVE M P,SCHIESTEL R. Batchelor versus Stewartson flow structures in a rotor-stator cavity with throughflow[J].Physics of Fluids,2005,17(7):075110.
[16] 华绍曾. 实用流体阻力手册[M].北京:国防工业出版社,1985.
[17] DAILY J W,NECE R E. Chamber dimension effects on induced flow and frictional resistance of enclosed rotating disks[J].Journal of Basic Engineering,1960,82(1):217-230.
[18] KUROKAWA J,TOYOKURA T.Axial thrust,disc friction torque and leakage loss of radial flow turbomachinery[C]//International Conference on Pump and Turbine Design and Development. Glasgow:[s.n.],1976.
[19] KUROKAWA J,SAKURA M. Flow in a narrow gap along an enclosed rotating disk with through-flow[J].JSME International Journal,1988,31(2):243-251.
[20] CHEAH S C,IACOVIDES H,JACKSON D C,et al. Experimental investigation of enclosed rotor-stator disk flows[J].Experimental Thermal and Fluid Science,1994,9(4):445-455.
[21] WATANABE K,OGATA S. Drag reduction of an enclosed rotating disk with fine spiral grooves[J].Journal of Environment and Engineering,2007,2(1):97-107.a
备注/Memo
收稿日期:2021-04-12; 修回日期:2021-06-17
基金项目:国家重大基础研究项目(631321)
作者简介:党枭睿(1999—),男,硕士,研究领域为液体火箭发动机涡轮泵。
更新日期/Last Update:
1900-01-01