RP-3航空煤油不同替代模型的空化流动特性

推进技术 ›› 2016, Vol. 37 ›› Issue (3): 563-571.

RP-3航空煤油不同替代模型的空化流动特性

陈泰然¹,顾玲燕²,王国玉¹,黄彪¹

北京理工大学机械与车辆学院，北京 100081,南京机电液压工程研究中心航空机电系统综合航空科技重点实验室，江苏南京 211106,北京理工大学机械与车辆学院，北京 100081,北京理工大学机械与车辆学院，北京 100081

发布日期:2021-08-15
作者简介:陈泰然，男，博士生，研究领域为空化热流体动力特性与机理。
基金资助:
国家自然科学基金资助项目(51479002)；航空科学基金项目(2013ZC09001)。

Cavitating Flow Characteristics of RP-3 Aviation Kerosene Surrogate Mixture Models

School of Mechanical Engineering，Beijing Institute of Technology，Beijing 100081，China,Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration，Nanjing Engineering Institute of Aircraft Systems，Nanjing 211106，China,School of Mechanical Engineering，Beijing Institute of Technology，Beijing 100081，China and School of Mechanical Engineering，Beijing Institute of Technology，Beijing 100081，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究RP-3航空煤油空化流动特性，采用GERG-2004方程构建了4种RP-3航空煤油的物理替代模型并给出其主要物性参数，对收缩扩张流道内航空煤油替代模型、正十二烷(C12H26)和水体的空化流动进行了数值计算研究，计算时考虑了饱和蒸汽压修正及航空煤油物性参数随流场温度变化。结果表明:由45％正十二烷、25%正十烷、5%辛烷、5%甲基环己烷和20%甲苯(摩尔比)组成的替代模型能够较好拟合RP-3的物质属性，可用来替代RP-3进行空化流动计算。常温下航空煤油的初生空化数小于水体，相同空化数下(σ=1.5)，水体的空穴长度约为航空煤油的1.4倍，航空煤油的空化强度更弱，液汽交界面较模糊。随着温度的升高，航空煤油空化热力学效应增强，但其在煤油泵工作温度区域内空化热力学效应不显著，在煤油泵空化性能预测时可以忽略煤油空化热力学效应的影响。

关键词: RP-3航空煤油；替代模型；空化流动；计算流体力学

Abstract: To study the cavitating flow characteristics of RP-3 aviation kerosene，four kinds of RP-3 aviation kerosene surrogate mixture models were established by GERG-2004 equations，and the main physical properties of these surrogate mixture models were illustrated. The modified saturated vapor pressure and material properties at different temperature were applied in the CFD codes. The dodecane and water cavitating flows in a converging-diverging flow channel were calculated. The surrogate C，which is made up of 45%dodecane，25%decane，5%octane，5%methyl cyclohexane，and 20%toluene(mole fraction)，shows better agreement with RP-3 aviation kerosene in certain properties，and then it was considered as RP-3 in cavitating flow computation. The inception cavitation number of aviation kerosene is smaller than that of water at room temperature. The cavity length of water is approximately 1.4 times that of aviation kerosene when cavitation number is 1.5，and the intensity of cavitation is weaker than water under the same conditions and the cavity of aviation kerosene is mushy. As temperature increases，the intensity of thermodynamic effects on aviation kerosene cavitating flow increases，however，it is not notable during the working temperature of aviation kerosene pumps. Thus thermodynamic effects of cavitation could be ignored in the prediction of cavitating flow characteristics of aviation kerosene pumps.

Key words: RP-3 aviation kerosene；Surrogate mixture model；Cavitating flows；Computational fluid dynamics

陈泰然,顾玲燕,王国玉,黄彪. RP-3航空煤油不同替代模型的空化流动特性[J]. 推进技术, 2016, 37(3): 563-571.

CHEN Tai-ran¹,GU Ling-yan²,WANG Guo-yu¹,HUANG Biao¹. Cavitating Flow Characteristics of RP-3 Aviation Kerosene Surrogate Mixture Models[J]. Journal of Propulsion Technology, 2016, 37(3): 563-571.

参考文献

[1] 李向宾, 王国玉, 张敏弟, 等.绕水翼超空化流动形态与速度分布[J]. 力学学报, 2008, 40(3): 315-322.
[2] Rood E P. Review-Mechanisms of Cavitation Inception[J]. Journal of Fluid Engineering, 1991, 113(2): 163-175.
[3] 季斌, 罗先武, 彭晓星, 等. 绕扭曲翼型三维非定常空泡脱落结构的数值分析[J]. 水动力学研究与进展, 2010, 25(2): 217-223.
[4] Kawanami Y, Kato H. Mechanism and Control of Cloud Cavitation[J]. Journal of Fluids Engineering, 1997, 119(8): 788-794.
[5] Hosangadi A, Ahuja V. Numerical Study of Cavitation in Cryogenic Fluids[J]. Journal of Fluids Engineering, 2005, 127(2): 267-281.
[6] 季斌, 罗先武, 吴玉林, 等. 考虑热力学效应的高温水空化模拟[J]. 清华大学学报(自然科学版), 2010, 50(2): 262-265.
[7] 斯捷潘诺夫 A J. 泵与鼓风机、多相流[M]. 吴达人, 译. 北京:机械工业出版社, 1986.
[8] Edwards T, Maurice L Q. Surrogate Mixtures to Represent Complex Aviation and Rocket Fuels[J]. Journal of Propulsion and Power, 2001, 17(2): 461-466.
[9] Dagaut P. On the Kinetics of Hydrocarbons Oxidation from Natural Gas to Kerosene and Diesel Fuel[J]. Physical Chemistry Chemical Physics, 2002, 4(4): 2079-2094.
[10] Montgomery C J, Cannon S M, Mawid M A, et al. Reduced Chemical Kinetic Mechanisms for JP-8 Combustion[C]. Reno, Nevada: 40th AIAA Aerospace Science Meeting and Exhibit, 2002: 1-10.
[11] 范学军, 俞刚. 大庆RP-3航空煤油热物性分析[J]. 推进技术, 2006, 27(2): 187-192. (FAN Xue-jun, YU Gang, Analysis of Thermophysical Properties of Daqing RP-3 Aviation Kerosene[J]. Journal of Propulsion Technology, 2006, 27(2): 187-192.)
[12] Violi A, Yan S, Eddings E G, et al. Experimental Formulation and Kinetic Model for JP-8 Surrogate Mixtures[J]. Combustion Science and Technology, 2002, 174(11&12): 399-417.
[13] 曾文, 李海霞, 马洪安, 等. RP-3航空煤油模拟替代燃料的化学反应简化机理[J]. 推进技术, 2014, 35(8): 1139-1145. (ZENG Wen, LI Hai-xia, MA Hong-an, et al. Reduced Chemical Reaction Mechanism of Surrogate Fuel for RP-3 Kerodene[J]. Journal of Propulsion Technology, 2014, 35(8): 1139-1145.)
[14] Kunz O, Klimeck R, Wagner W, et al. The GERG-2004 Wide-Range Equation of State for Natural Gases and Other Mixtures[R]. VDI 6, 557, 2007.
[15] Kubota A, Kato H, Yamauchi H, et al. Unsteady Structure Measurement of Cloud Cavitation on a Foil Section using Conditional Sampling Technique[J]. Journal of Fluids Engineering, 1989, 111(2): 204-210.
[16] Singhal A K, Athavale M M, Li H, et al. Mathematical Basis and Validation of the Full Cavitation Model[J]. Journal of Fluids Engineering, 2002, 124(3): 617-624.
[17] Dunn P F, Thomas F O, Davis M P, et al. Experimental Characterization of Aviation-Fuel Cavitation[J]. Physics of Fluids, 2010, 22(11): 117102.
[18] Franc J P, Rebattet C, Coulon A. An Experimental Investigation of Thermal Effects in a Cavitating Inducer[C]. Osaka: Fifth International Symposium on Cavitation, 2003.
[19] Utturkar Y, Wu J, Wang G, et al. Recent Progress in Modeling of Cryogenic Cavitation for Liquid Rocket Propulsion[J]. Progress in Aerospace Sciences, 2005, 41(7): 558-608.
[20] Goel T, Zhao J, Thakur S, et al. Surrogate Model Based Strategy for Cryogenic Cavitation Model Validation and Sensitivity Evaluation[J]. International Journal for Numerical Methods in Fluids, 2008, 58(9): 969-1007.
[21] 尹敦兵, 陈铁重, 丛培胜, 等. 基于JP-10与RP-3燃烧的数值模拟[J]. 海军航空工程学院学报, 2008, 23(3): 276-280.
[22] Ely J F, Huber M L. NIST Standard Reference Datebase 4-NIST Thermophysical Properties of Hydrocarbon Mixtures[M]. Gaithersburg: National Inst.of Standards, MD, 1990.(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2014-10-10；修订日期:2015-01-02。基金项目:国家自然科学基金资助项目(51479002)；航空科学基金项目(2013ZC09001)。作者简介:陈泰然,男,博士生,研究领域为空化热流体动力特性与机理。E-mail: chentairan617@163.com