环喉型圆锥塞式喷管的水下流动分离特性

推进技术 ›› 2015, Vol. 36 ›› Issue (1): 37-46.

环喉型圆锥塞式喷管的水下流动分离特性

何淼生,覃粒子,刘宇

北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191,北京航空航天大学宇航学院，北京 100191

发布日期:2021-08-15
作者简介:何淼生 (1987—)，男，博士生，研究领域为非定常流动。

Numerical Investigation of Flow Separation in an Annular Conical Aerospike Nozzle for Underwater Propulsion

School of Astronautics， Beijing University of Aeronautics and Astronautics， Beijing 100191，China,School of Astronautics， Beijing University of Aeronautics and Astronautics， Beijing 100191，China and School of Astronautics， Beijing University of Aeronautics and Astronautics， Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 将塞式喷管概念扩展到水下固体火箭发动机应用领域，为了研究高背压环境下塞式喷管的水下流动分离特性，建立水下塞式喷管流动分析模型，并采用流体体积法(VOF)两相流模型对设计马赫数2.0的环喉型圆锥塞式喷管水下工作时的过膨胀流场进行了气/水耦合数值模拟，计算考虑了气体的压缩性和粘性。计算结果显示:圆锥塞式喷管在水下的过膨胀流动也存在间歇性的颈缩、胀鼓以及回击等不稳定现象；与空气环境下的工作条件不同，气/水界面表现出类似于壁面的约束作用，塞锥外流场形成的波系结构由塞锥壁面和内喷管出口下游气/水界面共同决定；水下超声速气体射流的不稳定振荡引起喷管出口背压和气/水界面的脉动，塞锥表面的分离流场随射流的振荡而变化，根据流场激波结构以及塞锥表面分离特征的不同，可以区分为5种不同的分离流动形态；塞式喷管在水下和空气环境下的分离流动振荡的驱动机理不同，水下分离流场的振荡主要受气/液两相相互作用诱导的射流振荡过程的影响，分离流场附近壁面压强振荡频率覆盖0~1000Hz范围内的较宽频带，且没有显著的特征频率。

关键词: 数值研究；水下推进；多相流；塞式喷管；流动分离

Abstract: A submerged annular conical aerospike nozzle for a design Mach number of 2.0 has been numerically studied under over-expanded condition. Particular attention has been paid to the flow separation characteristics in aerospike nozzle for underwater propulsion application. The detailed Navier-Stokes flow computations were utilized to elucidate the gas-water interactions under the framework of a Volume of fluid model. The calculation results show that，the intermittently necking/bulging or necking/back-attack phenomenon also exists in the submerged over-expanded annular conical aerospike nozzle flowfield. The back pressure for underwater nozzle is not only determined by the pressure of the water environment but also by the pressure in the gas bubble，and the gas/water interface restricts the gaseous jet as a wall， which is extremely different from the air environment condition. The gas/water interface around the plug flowfield is observed to be severely affected by the pulsation of the nozzle expansion back pressure，and shows continual oscillation between necking and bulging. The flow separation characteristics develop and change along with the jet oscillation. Depending on shock structures in the nozzle and flow separation characteristic on the plug surface，the nozzle exhibits different flow separation regimes which can be broadly classified into five types. Further，the mechanism for unsteady separation in submerged over-expanded aerospike nozzle is different from the one under air environment condition. The predicted wall fluctuating pressure shows a broad-frequency phenomenon with the bandwidth of 0~1000Hz by the current Navier-Stokes computation. As a result of the complicated coupling effects among the back pressure pulsation，the flow separation process and the jet oscillation，flow separation behavior in the present annular conical aerospike nozzle for underwater propulsion shows highly irregular oscillation characteristics.

Key words: Numerical investigation；Underwater propulsion；Multiphase flow；Aerospike nozzle；Flow separation

何淼生,覃粒子,刘宇. 环喉型圆锥塞式喷管的水下流动分离特性[J]. 推进技术, 2015, 36(1): 37-46.

HE Miao-sheng, QIN Li-zi, LIU Yu. Numerical Investigation of Flow Separation in an Annular Conical Aerospike Nozzle for Underwater Propulsion[J]. Journal of Propulsion Technology, 2015, 36(1): 37-46.

参考文献

[1] Hagemann G, Immich H, Nguyen T V, et al. Advanced Rocket Nozzles[J].Journal of Propulsion and Power, 1998, 14(5): 629-634.
[2] 潘哲, 王宝寿, 宋志平. 火箭发动机水下分离特性试验研究[J]. 船舶力学, 2004, 8(4): 22-26.
[3] Stark R, Boehm C, Haidn O J, et al. Cold Flow Testing of Dual-Bell Nozzles in Altitude Simulation Chamber[C]. Moscow: Preceedings of EUCASS European Conference for Aerospace Sciences, 2006.
[4] Berman K, Crimp F W, Jr. Performance of Plug-Type Rocket Exhaust Nozzles[J]. ARS Journal, 1961, 31(1): 18-23.
[5] Ruf J H, McConnaughey P K. The Plume Physics Behind Aerospike Nozzle Altitude Compensation and Slipstream Effect[R]. AIAA 97-3217.
[6] Fick M, Schmucker R H. Performance Aspects of Plug Cluster Nozzles[J]. Journal of Spacecraft and Rockets, 1996, 33(4): 507-512.
[7] Rommel T, Hagemann G, Schley, C-A, et al. Plug Nozzle Flowfield Analysis[J]. Journal of Propulsion and Power, 1997, 13(5): 629-634.
[8] Wasko R A. Performance of Annular Plug and Expansion-Deflection Nozzles Including External Flow Effects at Transonic Mach Numbers[R]. NASA TN D-4462, 1968.
[9] Rao G V R. Recent Developments in Rocket Nozzle Configurations[J]. ARS Journal, 1961, 31(11): 1488-1494.
[10] Angelino G. Approximate Method for Plug Nozzle Design[J]. AIAA Journal, 1964, 2(10): 1834-1835.
[11] Huzel D K, Huang D H. Design of Liquid Propellant Rocket Engines[R]. NASA SP-125, 1967: 89-95.
[12] Humphreys R P, Thompson H D, Hoffmann J D. Design of Maximum Thrust Plug Nozzles for Fixed Inlet Geometry[J]. AIAA Journal, 1971, 9(8): 1581-1587.
[13] Migdal D. Supersonic Annular Nozzles[J]. Journal of Spacecraft and Rockets, 1972, 9(1): 3-6.
[14] Sule W P, Mueller T J. Annular Truncated Plug Nozzle Flowfield and Base Pressure Characteristics[J]. Journal of Spacecraft and Rockets, 1973, 10(11): 689-695.
[15] Hall C R, Jr, Mueller T J. Exploratory Analysis of Nonuniform Plug Nozzle Flowfields[J]. Journal of Spacecraft and Rockets, 1972, 9(5): 373-342.
[16] Angelino G. Theoretical and Experimental Investigations of the Design and Performance of a Plug Type Nozzle[R]. NASA TN-12, 1963.
[17] Hagemann G, Immich H, Terhardt M. Flow Phenomena in Advanced Rocket Nozzles-The Plug Nozzle[R]. AIAA 98-3522.
[18] Norris G. Solid Performance for Aerospike[N].Flight International, 3 May 2004, (Technology).
[19] Verma S B. Performance Characteristics of an Annular Conical Aerospike Nozzle with Freestream Effect[J]. Journal of Propulsion and Power, 2009, 25(3): 783-791.
[20] Loth E, Faeth G M. Structure of Underexpanded Round Air Jets Submerged in Water[J]. International Journal of Multiphase Flow, 1989, 15(4): 589-603.
[21] Surin V A, Evchenko V N, Rubin V M. Propagation of a Gas Jet in a Liquid[J]. Journal of Engineering Physics, 1983, 45(4): 1091-1101.
[22] 戚隆溪, 曹勇, 王柏懿. 水下欠膨胀高速气体射流的实验研究[J]. 力学学报, 2000, 32(6): 667-675.
[23] 王柏懿, 戴振卿, 戚隆溪, 等. 水下超音速气体射流回击现象的实验研究[J]. 力学学报, 2007, 39(2): 267-272.
[24] Dai Zhenqing, Wang Baiyi, Qi Longxi, et al.Experimental Study on Hydrodynamic Behaviors of High-speed Gas Jets in Still Water[J].Acta Mechanica Sinica, 2006, 22(5): 443-448.
[25] 戴振卿. 水下超音速气体射流的实验研究[D]. 北京: 中国科学院力学研究所, 2006.
[26] 施红辉, 王柏懿, 戚隆溪, 等. 水下超音速气体射流[C]. 北京:第七届全国水动力学学术会议暨第十九届全国水动力学研讨会文集(上册), 2005: 75-81.
[27] 王晓刚, 王超, 郭强, 等. 二维水下高速气体射流的振荡流流型研究[J]. 浙江理工大学学报, 2009, 26(4): 613-618.
[28] 施红辉, 郭强, 王超, 等. 水下超音速气体射流胀鼓和回击的关联性研究[J]. 力学学报, 2010, 42(6): 1206-1210.
[29] 鲁传敬, 陈方, 樊泓, 等. 导弹水下点火的流体动力研究[J]. 航空学报, 1992, 13(4): B124-B130.
[30] 黄建春, 叶取源, 朱世权. 不同发射深度下导弹水下点火气水流体动力计算[J]. 应用力学学报, 1994, 11(3): 19-24.
[31] Rogers K W. A Theoretical and Experimental Investigation of the Transient Phase of Underwater Rocket Motor Firing[R]. University of Southern California Engineering Center Report, 1962.
[32] 张有为, 王晓宏. 导弹水下点火推力峰值问题的数值研究[J]. 应用力学学报, 2007, 24(1): 298-301.
[33] Tang J N, Li S P, Wang NF, et al. Flow Structures of Gaseous Jet Injected into Liquid for Underwater Propulsion[R]. AIAA 2010-6911.
[34] 朱卫兵, 陈宏, 黄舜. 水下高速射流气泡变化过程数值研究[J]. 推进技术, 2010, 31(4): 496-502.(ZHU Wei-bing, CHEN Hong, HUANG Shun.Numerical Study of the Process of the Evolution of Bubble of High-Speed Jet Underwater[J]. Journal of Propulsion Technology, 2010, 31(4): 496-502.)
[35] 曹嘉怡, 鲁传敬, 李杰, 等. 水下超音速燃气射流动力学特性研究[J]. 水动力学研究与进展, A辑, 2009, 24(5): 575-582.
[36] 贺小艳, 马汉东, 纪楚群, 等. 水下气体射流初期数值研究[J]. 水动力学研究进展, A辑, 2004, 19(2): 207-212.
[37] Tang Jianing, Wang Ningfang, Wei Shyy. Flow Structures of Gaseous Jets Injected into Water for Underwater Propulsion[J]. Acta Mechanica Sinica, 2011, 27(4): 461-472.
[38] 唐嘉宁, 刘向阳, 李世鹏, 等. 水下固体火箭发动机推力特性研究[J]. 导弹与航天运载技术, 2012(5): 15-21.
[39] Shi Honghui, Wang Baiyi, Dai Zhenqing. Research on the Mechanics of Underwater Supersonic Gas Jets[J]. Science China Ser G Sci-Phys Mech Astron, 2010, 53(3): 527-535.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2013-11-20；修订日期:2014-03-11。作者简介:何淼生 (1987—),男,博士生,研究领域为非定常流动。E-mail:hms@sa.buaa.edu.cn