基于旋转阀的固体火箭发动机燃烧室压强振荡特性

doi:10.3969/j.issn.1000-1093.2021.01.004

摘要/Abstract

摘要： 针对基于旋转阀的固体推进剂压强耦合响应函数测试系统存在不易进行相位角测量、压强振荡及内流场分析的难点，设计一套旋转阀冷流实验系统，建立对应的压强振荡理论计算模型和三维瞬态内流场仿真模型，研究燃烧室压强振荡及其内流场特性。开展不同排气频率的冷流实验和理论计算，并与仿真模型进行对比。结果表明：仿真计算中单个转子排气通道周期性摆动运动可代替多转子排气通道单向旋转运动，且误差小于1%；仿真计算获取的排气周期与实验对比的误差小于1.2%；对于压强峰-峰值，仿真比实验小且相差数值由20 Hz的0.019 MPa降低至300 Hz的0.001 MPa，验证了仿真模型的有效性；为后续研究旋转阀工作过程中燃烧室压强振荡及流场变化提供了新的思路和途径。

关键词: 固体火箭发动机, 旋转阀, 压强振荡, 排气面积, 瞬态流场, 动网格

Abstract: The pressure-coupled response function test system of solid propellant based on rotary valve is difficult to perform the measurement of phase angle, and the analysis of pressure oscillation and internal flow field. A set of cold-flow experimental system with rotary valve was designed, and a corresponding theoretical calculation model of pressure oscillation and a three-dimensional transient flow field simulation model based on dynamic mesh technology were established. Cold flow experiment and theoretical calculation at different exhaust frequencies were made, and the experimental and calculated results were compared with the simulated results. The results show that the periodic swing motion of a single-rotor exhaust duct can replace the unidirectional rotary motion of the multi-rotor exhaust duct in the simulation calculation, and the error is less than 1%. The errors of the exhaust cycle obtained by simulation calculation and experiment are less than 1.2%; the simulated peak-to-peak pressure is smaller than the experimental one, and the difference value is reduced from 0.019 MPa at 20 Hz to 0.001 MPa at 300 Hz, which verifies the effectiveness of the simulation model.

Key words: solidrocketengine, rotaryvalve, pressureoscillation, exhaustarea, transientflowfield, dynamicmesh

中图分类号:

V435⁺.12

席运志，王宁飞，李军伟，张智慧. 基于旋转阀的固体火箭发动机燃烧室压强振荡特性[J]. 兵工学报, 2021, 42(1): 33-44.

XI Yunzhi, WANG Ningfei, LI Junwei, ZHANG Zhihui. Oscillation Characteristics of Pressure in Combustor with Rotary Valve for Solid Rocket Engine[J]. Acta Armamentarii, 2021, 42(1): 33-44.

参考文献

［1］ BECKSTEAD M W. Low frequency instability: a comparison of theory and experiment ［J］. Combustion and Flame, 1968, 12(5): 417-426.
［2］ PRICE E W. Experimental solid rocket combustion instability ［J］. Symposium (International) on Combustion, 1965, 10(1): 1067-1082.
［3］ PRICE E W. Experimental observations of combustion instability ［J］. Progress in Astronautics and Aeronautics, 1984, 90(13): 733-790.
［4］程诚，张小兵. 内弹道两相流三维并行数值模拟［J］.兵工学报,2019, 40(4): 769-776.
CHENG C, ZHANG X B. Parallel numerical simulation on three-dimensional two-phase flow of interior ballistic trajectory ［J］. Acta Armamentarii, 2019, 40(4): 769-776. (in Chinese)
［5］鲍福廷，侯晓. 固体火箭发动机设计［M］. 北京：中国宇航出版社, 2016.
BAO F T, HOU X. Design of solid rocket motor design ［M］. Beijng: China Astronautic Publishing House, 2016. (in Chinese)
［6］刘佩进，何国强. 固体火箭发动机燃烧不稳定及控制技术［M］. 西安:西北工业大学出版社,2015.
LIU P J, HE G Q. Combustion instability and control technology of solid rocket motor ［M］. Xi'an: Northwestern Polytechnical University Press, 2015. (in Chinese)
［7］ CULICK F E C, PAUL K. Unsteady motions in combustion chambers for propulsion systems: AG-AVT-039 ［R］. Amsterdam, the Netherlands: Advisory Group for Aeronautical Research and Deve-lopment, 2006.
［8］ STRAND L D, BROWN R S. Laboratory test methods for combustion stability properties of solid propellants ［J］. AIAA Journal, 1992, 17: 689-718.
［9］ ANDREPONT W, SCHONER R. The T-burner test method for determining the combustion response of solid propellants ［C］ ∥Proceeding of the 8th Joint Propulsion Specialist Conference. New Orleans, LA, US: AIAA, 1972.
［10］ SU W X, WANG N F, LI J W. Improved method of measuring pressure coupled response for composite solid propellants ［J］. Journal of Sound and Vibration, 2014, 333(8): 2226-2240.
［11］ CULICK F E C. Interactions between the flow field combustion and wave motions in rocket motors: NWC TP 5349 ［R］. China Lake, CA, US: Naval Weapons Center, 1972.
［12］ MICHELI P L. Evaluation of pulsed T-burner for metallized propellants:191 ［R］. Sacramento, CA, US: Aerojet Solid Propulsion Co., 1973.
［13］ BROWN R S, ERICKSON J E, BABCOCK W R. Combustion response function measurements by the rotating valve method ［J］. AIAA Journal, 1974, 12(11): 1502-1510.
［14］ BROWN R S,WILLOUGHBY P G, KELLY V L. Rotating valve for velocity coupled combustion response studies ［C］∥Proceeding of the 13rd Propulsion Conference. Orlando, FL,US:AIAA, 1977.
［15］ BROWN R S, WAUGH R C, KELLY V L. Rotating valve for velocity-coupled combustion response measurements ［J］. Journal of Spacecraft and Rockets, 1982, 19(5): 437-444.
［16］苏万兴. 大长径比固体火箭发动机不稳定燃烧预示及抑制方法研究［D］. 北京:北京理工大学, 2015.
SU W X. Prediction and suppression methods of combustion instability in large aspect ratio solid rocket motors ［D］. Beijing: Beijing Institute of Technology, 2015. (in Chinese)
［17］ ANSYS Inc. Fluent user's guide manual. Version 18.0, vols. 1 and 2［M］. Canonsburg, PA, US: ANSYS Inc., 2017.
［18］ ANSYS Inc. Fluent UDF manual. Version 18.0, vols. 1-3［M］. Canonsburg, PA, US: ANSYS Inc., 2018.
［19］ ANSYS Inc. Fluent theory guide. Version 18.0, vols. 1 and 3. Canonsburg, PA, US: ANSYS Inc., 2017
［20］ HOU C W, QIAN J Y, CHEN F Q. Parametric analysis on throttling components of multi-stage high pressure reducing valve ［J］. Applied Thermal Engineering, 2018, 128: 1238-1248.
［21］ WHITE F M. Viscous fluid flow ［M］. New York, NY, US: Mc Graw-Hill, 1974: 248-249.
［22］ BREWSTER M Q, SAARLOOS B. Unsteady stolid propellant pressure combustion responses using a piston burner ［J］. Journal of Propulsion and Power, 2004, 20(1): 127-134.
［23］ HAN M, LIU S Y, WU D F. Numerical analysis and optimisa-tion of the flow forces in a water hydraulic proportional cartridge valve for injection system ［J］. IEEE Access, 2018, 6: 10392-10401.
［24］ AMIRANTE R, VESCOVO G D, LIPPOLIS A. Evaluation of the flow forces on an open centre directional control valve by means of a computational fluid dynamic analysis ［J］. Energy Conversion and Management, 2006, 47(13/14): 1748-1760.
［25］ AMIRANTE R, MOSCATELLI P G, CATALANO L A. Evaluation of the flow forces on a direct (single stage) proportional valve by means of a computational fluid dynamic analysis ［J］. Energy Conversion and Management, 2007, 48(3): 942-953.
［26］ PAN X D,WANG G L, LU Z S. Flow field simulation and a flow model of servo-valve spool valve orifice ［J］. Energy Conversion and Management, 2011, 52(10): 3249-3256.

[1]	顾兴鹏，李军伟，乔文生，武胜，韩磊，汪琪，王宁飞. 固相颗粒在C1xb固体火箭发动机中的运动规律[J]. 兵工学报, 2022, 43(3): 489-502.
[2]	官典, 李世鹏, 刘筑, 王宁飞. 横向过载对固体火箭发动机推进剂点火建压过程的影响[J]. 兵工学报, 2021, 42(9): 1877-1887.
[3]	周柏航，陶如意，王浩，阮文俊. 带侵蚀燃烧效应的阶梯多根装药火箭发动机三维内流场特性[J]. 兵工学报, 2021, 42(8): 1604-1612.
[4]	高峰，张泽. 含装药缺陷的固体火箭发动机性能评估综述[J]. 兵工学报, 2021, 42(8): 1789-1802.
[5]	马宝印，李军伟，张海龙，赵桂琦，张智慧，席运志，王宁飞. 阻尼环对固体火箭发动机热声振荡的影响[J]. 兵工学报, 2021, 42(5): 930-943.
[6]	席运志, 李军伟, 陈雪莉, 韩磊, 王宁飞. 基于旋转阀的固体推进剂压强耦合响应测试方法[J]. 兵工学报, 2021, 42(3): 511-520.
[7]	张兵，侯明，王殿宇，董友亮. 迎角对导弹初始弹射弹道的影响[J]. 兵工学报, 2021, 42(2): 438-448.
[8]	张晓光，李斌，党会学，温金鹏，孙潘. 水下航行体充气上浮仿真方法研究[J]. 兵工学报, 2020, 41(7): 1249-1261.
[9]	伍鹏，李高春，韩永恒，赵汝岩，谭洁，刘著卿. 固体火箭发动机矩形粘接试件多角度拉伸过程变形测量与破坏模式[J]. 兵工学报, 2020, 41(11): 2234-2242.
[10]	叶青，余永刚. 星型装药固体火箭发动机烤燃特性[J]. 兵工学报, 2020, 41(10): 1970-1978.
[11]	李阳天，李海滨，韦广梅，翁洁鑫. 基于改进型多项式混沌展开的固体火箭发动机药柱低温点火不确定性量化分析[J]. 兵工学报, 2020, 41(1): 40-48.
[12]	王利利，刘影，李达钦，吴钦，王国玉. 固体火箭发动机水下超音速射流数值研究[J]. 兵工学报, 2019, 40(6): 1161-1170.
[13]	陈方正，于剑桥, 沈元川，马安鹏. 筒射串翼无人机展开动力学分析[J]. 兵工学报, 2019, 40(1): 89-98.
[14]	施红辉，周东辉，孙亚亚，贾会霞，侯健. 水下连发射弹的超空泡流动特性研究[J]. 兵工学报, 2018, 39(11): 2228-2235.
[15]	张胜，王强，何晓晖，高亚明，王新文. 基于流体-固体耦合的液压滑阀开启过程仿真分析与优化[J]. 兵工学报, 2017, 38(3): 608-615.