|Table of Contents|

Nozzle simulation model of liquid rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2022年02期
Page:
56-65
Research Field:
目次
Publishing date:

Info

Title:
Nozzle simulation model of liquid rocket engine
Author(s):
SUN Dechuan1; YANG Jianwen2
(1.School of Aeronautics and Astronautics, Dalian University of Technology, Dalian 116024, China 2.Xian Aerospace Propulsion Institute, Xian 710100, China)
Keywords:
nozzle performance numerical simulation physical model chamber pressure contour
PACS:
V430
DOI:
-
Abstract:
Based on the models of calorically perfect gas, thermally perfect gas with frozen species,and chemical non-equilibrium gas, a physical model of nozzle performance simulation was established.A WENO scheme with third-order precision was used to calculate the nozzle flow field for these different gas models.According to the calculation of the flowfield, the nozzle performances of the nitrous oxide/methylhydrazine engine and the liquid oxygen/kerosene engine were analyzed. The effects of the chamber pressure and the nozzle expansion contour on the performance of liquid oxygen/kerosene engine were analyzed by the flowfield calculation.The results show that the specific impulse calculated by the caloric perfect gas model is higher than that calculated by the thermal perfect gas model.The calculation deviation given by the two gas models is large and has no regularity,and the calculated results of the two-dimensional chemical kinetics are closer to the real values.Increasing the chamber pressure can not only improve the combustion efficiency, but also reduce the chemical kinetic loss and thus improve the nozzle performance.Modifying the boundary layer of the nozzle contour designed by Raos method can slightly improve the performance, or slightly reduce the nozzle length under the same performance requirements.

References:

[1] 梁俊龙, 张贵田, 秦艳平.基于高阶WENO格式的喷管动态特性仿真分析[J].火箭推进, 2015, 41(4):29-36.
LIANG J L, ZHANG G T, QIN Y P.Simulated analysis on nozzle dynamic characteristics based on high-order WENO scheme[J].Journal of Rocket Propulsion, 2015, 41(4):29-36.
[2] 丁兆波.一种大面积比喷管的分段式设计与数值分析[J].火箭推进, 2013, 39(1):19-23.
DING Z B.Design and numerical analysis of segmental nozzle with high area ratio[J].Journal of Rocket Propulsion, 2013, 39(1):19-23.
[3] 胡海峰, 高新妮, 凌前程, 等.火箭发动机喷管分离流动仿真分析[J].火箭推进, 2014, 40(6):24-30.
HU H F, GAO X N, LING Q C, et al.Simulation analysis on separation flow in rocket engine nozzle[J].Journal of Rocket Propulsion, 2014, 40(6):24-30.
[4] 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.
[5] 王一白, 梁远舰, 赵宇辉, 等.抛物线喷管型面参数对流动分离影响的数值模拟[J].航空动力学报, 2017, 32(4):955-960.
[6] ARAKI L K, MARCHI C H.Verification and validation of numerical solutions of two-dimensional reactive flow in rocket engine nozzles[J].Applied Mathematical Modelling, 2017, 52:544-557.
[7] KARNAL M, BATUL B.Estimation of exhaust gas temperature of the rocket nozzle using hybrid approach[J].Journal of Thermal Science, 2016, 25(6):485-491.
[8] SRINIVAS G, POTTI S R.Numerical simulation of rocket nozzle[J].Advanced Materials Research, 2014, 984/985:1210-1213.
[9] 陈伟, 梁国柱.基于CFD的多级推力固体火箭发动机轴对称喷管型面优化与高精度性能预估[J].固体火箭技术, 2014, 37(1):30-36.
[10] YUMU ?塁 AK M, EYI S.Design optimization of rocket nozzles in chemically reacting flows[J].Computers & Fluids, 2012, 65:25-34.
[11] OGAWA H,BOYCE R R.Nozzle design optimization for axisymmetric scramjets by using surrogate-assisted evolutionary algorithms[J].Journal of Propulsion and Power, 2012, 28(6):1324-1338.
[12] POWELL W B.ICRPG liquid propellant thrust chamber performance evaluation methodology[J].Journal of Spacecraft and Rockets, 1970, 7(1):105-108.
[13] GORDON S, MCBRIDE B J.Computer program for calculation of complex chemical equilibrium compositions, rocket performance, incident and reflected shocks, and Chapman-Jouguet detonations:NASA SP-273[R].Washington, D.C.:NASA Lewis Research Center, 1976.
[14] NICKERSON G, DANG L.A shock wave capability for the improved Two-Dimensional Kinetics(TDK)computer program[R].NASA-CR-171302, 1984.
[15] KAWASAKI A H,COATS D E. TDKP:A 2-phase version of TDK[Z].1991.
[16] NICKERSON G, JOHNSON C.A soot prediction model for the TDK computer program[C]//28th Joint Propulsion Conference and Exhibit.Reston, Virginia:AIAA, 1992.
[17] DUNN S, COATS D.Nozzle performance predictions using the TDK 97 code[C]//33rd Joint Propulsion Conference and Exhibit.Reston, Virginia:AIAA, 1997.
[18] DUNN S, COATS D.Optimum nozzle contours for aerospike nozzles using the TDK 99TM computer code[EB/OL].https://www.researchgate.net/publication/268414880_optimum_nozzle_contours_for_aerospike_nozzles_using_the_tdk_99_tm_computer_code,2014.
[19] MANSKI D, HAGEMANN G.Influence of rocket design parameters on engine nozzle efficiencies[C]//30th Joint Propulsion Conference and Exhibit.Reston, Virigina:AIAA, 1994.
[20] MANSKI D, HAGEMANN G.Influence of rocket design parameters on engine nozzle efficiencies[J].Journal of Propulsion and Power, 1996, 12(1):41-47.
[21] SUTTON G P, BIBLARZ O.Rocket propulsion elements[M].New York:John Wiley & Sons Inc, 2016.
[22] SHU C W.High-order finite difference and finite volume WENO schemes and discontinuous Galerkin methods for CFD[J].International Journal of Computational Fluid Dynamics, 2003, 17(2):107-118.
[23] 刘君, 周松柏, 徐春光.超声速流动中燃烧现象的数值模拟方法及应用[M].长沙:国防科技大学出版社, 2008.
[24] NICKERSON G R, DANG L D.Improved two-dimensional kinetics(TDK)computer program[R].NASA-CR-170922, 1983.

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