A Nozzle Contour Optimization Method Considering the Change in Fuel Gas Properties

doi:10.3969/j.issn.1000-1093.2018.11.008

Abstract

Abstract: Space rocket engine nozzle usually has large area ratio, and the improvement in its performance is one of the goals of engine design. A design method for divergent section considering the changes in properties of the real fuel gas in nozzle is proposed based on the Rao's method. For an apogee rocket engine, the Rao's method is used to design an original nozzle contour, and then the function of specific heat of the real fuel gas is calculated and a new nozzle contour of divergent section of nozzle is designed. The vacuum specific impulses of the new nozzle contour and the original one are compared through numerical simulations. Simulated results show that the calculation method of fuel gas specific heat can be used for the nozzle flow simulation; the specific heat of fuel gas has great effect on the nozzle contour design; for the nozzles with the same length, the nozzle contour designed by considering the change in specific heat capacity has smaller exit area ratio, but has higher vacuum specific impulse; and for the space engine which has not too large thrust, the increase in vacuum specific impulse is less then 1s, and the gain of performance by the boundary layer displacement is very small. Key

Key words: rocketengine, nozzle, fuelgasproperty, simulationoptimization, chemicalkinetics, specificheat

CLC Number:

V434⁺.24

SUN De-chuan， YU Ze-you. A Nozzle Contour Optimization Method Considering the Change in Fuel Gas Properties[J]. Acta Armamentarii, 2018, 39(11): 2145-2152.

References

［1］ ArianeGroup GmbH. 400 N bipropellant apogee motors［EB/OL］. ［2018-03-21］.http:∥www.space-propulsion.com/spacecraft-propulsion/apogee-motors/index.html.
［2］ Stechman C, Woll P, Fuller R, et al. A high performance liquid rocket engine for satellite main propulsion［C］∥Proceedings of the 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. Huntsville, AL, US: AIAA, 2000.
［3］ Liu C G, Chen J, Han H Y, et al. A long duration and high reliability liquid apogee engine for satellites［J］. Acta Astronautica, 2004, 55(6/7/8/9): 401-408.
［4］周红玲, 徐方涛, 张绪虎, 等. 490 N远地点发动机抗氧化涂层厚度对性能的影响［J］. 宇航材料工艺, 2011, 41(5): 66-68,73.
ZHOU Hong-ling, XU Fang-tao, ZHANG Xu-hu, et al. Effect of thickness on oxidation resistance of coating on 490 N apogee engines［J］. Aerospace Materials & Technology, 2011, 41(5): 66-68, 73.(in Chinese)
［5］ Fiedler T, Bker M, Rsler J. Large heat flux exposure of metallic coatings for rocket engine applications［J］. Surface and Coatings Technology, 2017, 332: 30-39.
［6］ Zhang X Y. Coupled simulation of heat transfer and temperature of the composite rocket nozzle wall［J］. Aerospace Science and Technology, 2011, 15(5):402-408.
［7］ Sciti D, Zoli L, Silvestroni L, et al. Design fabrication and high velocity oxy-fuel torch tests of a C-f-ZrB2-fiber nozzle to evaluate its potential in rocket motors［J］. Materials & Design, 2016, 109: 709-717.
［8］ Rao G V R. Exhaust nozzle contour for optimum thrust［J］. Jet Propulsion, 1958, 28(6):377-382.
［9］卢鑫, 岳连捷, 肖雅彬, 等. 超燃冲压发动机尾喷管流线追踪设计［J］. 推进技术, 2011, 32(1): 91-96.
LU Xin, YUE Lian-jie, XIAO Ya-bin, et al. Design of scramjet nozzle based on streamline tracing technique［J］. Propulsion Technology, 2011, 32(1): 91-96.(in Chinese)

［10］郭善广, 王振国, 赵玉新, 等. 超声速/高超声速双拐点喷管设计［J］. 航空动力学报, 2012, 27(12): 2742-2748.
GUO Shan-guang, WANG Zhen-guo, ZHAO Yu-xin, et al. Contour design of super/hypersonic dual-inflection nozzle［J］. Journal of Aerospace Power, 2012, 27(12): 2742-2748. (in Chinese)
［11］ Lyu Z, Xu J L, Mo J W. Design of a three-dimensional scramjet nozzle considering lateral expansion and geometric constraints［J］. Acta Astronautica, 2017, 141:172-182.
［12］王玉峰, 吴宝元, 王东东. 变比热对超燃冲压发动机尾喷管设计的影响分析［J］. 火箭推进, 2010, 36(2): 43-47.
WANG Yu-feng, WU Bao-yuan, WANG Dong-dong. Scramjet engine nozzle design with variable specific heat［J］. Journal of Rocket Propulsion, 2010, 36(2): 43-47.(in Chinese)
［13］易仕和, 赵玉新, 何霖, 等. 超声速和高超声速喷管设计［M］.北京:国防工业出版社,2013.
YI Shi-he, ZHAO Yu-xin, HE Lin, et al. Supersonic and hypersonic nozzle design［M］. Beijing:National Defense Industry Press, 2013. (in Chinese)

［14］赵一龙, 赵玉新, 王振国, 等. 超声速型面可控喷管设计方法［J］. 国防科技大学学报, 2012, 34(5): 1-4.
ZHAO Yi-long, ZHAO Yu-xin, WANG Zhen-guo, et al. Designing method of supersonic nozzle with controllable contour［J］. Journal of National University of Defense Technology, 2012, 34(5): 1-4. (in Chinese)
［15］胡振震, 李震乾, 石义雷, 等. 基于轴线马赫数分布的喷管扩张段无粘型面设计［J］. 实验流体力学, 2016, 30(4): 97-104.
HU Zhen-zhen, LI Zhen-qian, SHI Yi-lei, et al. Design of nozzle inviscid contour based on axial Mach number distribution［J］. Journal of Experiments in Fluid Mechanics, 2016, 30(4): 97-104.(in Chinese)
［16］吴盛豪, 房詠柳, 陈吉明, 等. 超声速喷管性能优化研究与应用［J］. 航空动力学报, 2017, 32(9): 2139-2144.
WU Sheng-hao, FANG Yong-liu, CHEN Ji-ming, et al. Application research on supersonic nozzle performance optimization［J］. Journal of Aerospace Power, 2017, 32(9): 2139-2144.(in Chinese)
［17］方丁酉. 喷管扩张段优化型面近似计算［J］. 固体火箭技术, 1991, 14(1): 50-56.
FANG Ding-you. Approximate calculation of optimal contour of nozzle divergent section ［J］. Solid Rocket Technology, 1991, 14(1): 50-56.(in Chinese)

［18］方国尧, 王庆, 高山辉. 火箭发动机喷管内型面优化设计［J］. 推进技术, 1993 (3): 16-21.
FANG Guo-yao, WANG Qing, GAO Shan-hui. The optimum design of solid rocket motor nozzles［J］. Journal of Propulsion Technology, 1993 (3): 16-21.(in Chinese)

［19］方杰, 童晓艳, 毛晓芳, 等. 某型发动机喷管的多学科设计优化［J］. 推进技术, 2004, 25(6): 557-560.
FANG Jie, TONG Xiao-yan, MAO Xiao-fang, et al. An MDO approach for engine nozzle design［J］. Journal of Propulsion Technology, 2004, 25(6): 557-560.(in Chinese)

［20］虞跨海, 莫展, 张亮, 等. 固体火箭发动机特型喷管造型设计与优化［J］. 弹箭与制导学报, 2012, 32(4): 137-138, 142.
YU Kua-hai, MO Zhan, ZHANG Liang, et al. Profile design and optimization of SRM nozzle［J］. Journal of Projectiles, Rockets, Missiles and Guidance, 2012, 32(4): 137-138, 142.(in Chinese)
［21］ Yumu?瘙塂ak M, Eyi S. Design optimization of rocket nozzles in chemically reacting flows［J］. Computers & Fluids, 2012, 65: 25-34.
［22］ Zucrow M J, Hoffman J D. Gas dynamics［M］. New York, NY, US: John Wiley & Sons, 1976.
［23］赵学端，廖其奠. 粘性流体力学［M］. 北京: 机械工业出版社, 1983.
ZHAO Xue-duan, LIAO Qi-dian. Viscous fluid mechanics［M］. Beijing:China Machine Press, 1983.(in Chinese)

［24］孙得川, 陈杰, 林庆国, 等. 喷管性能的化学动力学分析［J］. 推进技术, 2003, 24(3): 222-224.
SUN De-chuan, CHEN Jie, LIN Qing-guo, et al. Chemical kinetics analysis for nozzle performance［J］. Journal of Propulsion Technology, 2003, 24(3): 222-224.(in Chinese)

第39卷
第11期2018 年11月兵工学报ACTA
ARMAMENTARIIVol.39No.11Nov.2018

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