流动参数对超临界喷射特性影响的数值模拟

范珍涔; 范玮

doi:10.7527/S1000-6893.2013.0191

航空学报 >

2013 , Vol. 34 >Issue 5: 1018 - 1027

DOI: https://doi.org/10.7527/S1000-6893.2013.0191

流体力学与飞行力学

流动参数对超临界喷射特性影响的数值模拟

范珍涔 ,
范玮

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西北工业大学动力与能源学院, 陕西西安 710072

范珍涔男, 博士研究生。主要研究方向: 发动机燃烧与流动。 Tel: 029-88460756 E-mail: fanzhencen@126.com;范玮女, 博士, 教授, 博士生导师。主要研究方向: 航空宇航推进理论与工程。 Tel: 029-88492748 E-mail: weifan419@nwpu.edu.cn

收稿日期: 2012-06-18

修回日期: 2012-08-26

网络出版日期: 2012-09-05

基金资助

国家自然科学基金(50976094)

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Numerical Simulation on Effects of Flow Parameters on Supercritical Injection Characteristics

FAN Zhencen ,
FAN Wei

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School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2012-06-18

Revised date: 2012-08-26

Online published: 2012-09-05

Supported by

National Natural Science Foundation of China (50976094)

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摘要

目前航空发动机燃烧室雾化系统设计主要是针对亚临界喷射的,但高性能要求使得未来飞行器发动机的燃料喷射系统会以跨临界/超临界喷射为主。基于此,对液态碳氢燃料的超临界喷射特性进行了研究。首先选取了适合超临界流体物性参数特点的计算和求解方法,建立了超临界喷射特性计算的数学模型;然后采用该模型对JetA燃料喷射到N₂环境中的喷射过程进行了数值计算研究,并通过与已有的实验结果进行对比验证了模型的正确性;最后对流动参数对于超临界喷射特性的影响进行了数值模拟,得到了喷射长度和喷射扩张角与流动参数之间的关系。

关键词： 航空发动机; 超临界喷射; 液态碳氢燃料; 数值模拟; 喷射特性; 流动参数

本文引用格式

范珍涔 , 范玮 . 流动参数对超临界喷射特性影响的数值模拟[J]. 航空学报, 2013 , 34(5) : 1018 -1027 . DOI: 10.7527/S1000-6893.2013.0191

Abstract

Currently, the design of atomization systems for combustors of aircraft engines is generally made for subcritical injection conditions. However, most of the injections will be supercritical or transcritical in future advanced aircraft for higher performance requirements. Therefore, this paper investigates the supercritical injection characteristics of liquid hydrocarbon fuel. Firstly, a numerical model incorporating the physical properties calculation method of supercritical fluid is developed for studying supercritical injection characteristics. The model is then employed for numerical investigations for the injection of JetA into N₂. The calculated results are compared and validated against the available experimental data, showing an excellent agreement. The effects of flow parameters on supercritical injection characteristics are also studied with the numerical model and the variations of the injection length and jet spreading angle with flow parameters are obtained.

Key words： aircraft engine; supercritical injection; liquid hydrocarbon fuel; numerical simulation; injection characteristic; flow parameter

参考文献

[1] Huang H, Spadaccini L J, Dobel D R. Fuel-cooled thermal management for advanced aero engines. ASME Paper, GT-2002-30070, 2002.
[2] Wu P K, Chen T H. Injection of supercritical ethylene in nitrogen. AIAA-1995-382, 1995.
[3] Wu P K, Shahnam M, Kirkendall K. Expansion and mixing processes of underexpanded supercritical fuel jets injection into superheated conditions. AIAA-1997-2852, 1997.
[4] Chehroudi B, Talley D, Coy E. Visual characteristics and initial growth rates of round cryogenic jets at subcritical and supercritical pressures. Physics of Fluids, 2002,14(2): 850-861.
[5] Barata J M M, Gkalp I, Silva A R R. Numerical study of cryogenic jets under supercritical conditions. Journal of Propulsion and Power, 2003, 19(1): 142-147.
[6] Chen L D, Sui P C. Atomization during the injection of supercritical fluid into high-pressure environment. 1994 IUTAM on Droplets and Sprays, 1994.
[7] Chen L. Heat transfer, fouling and combustion of supercritical fuels. Report#940321, 1994.
[8] Doungthip T, Ervin J S, Williams T F, et al. Studies of injection of jet fuel at supercritical conditions. Industrial & Engineering Chemistry Research, 2002, 41(23): 5856-5866.
[9] Minotti A, Bruno C. Comparison between real and ideal sub and supercritical combustion simulations of LO2-CH4 LRE flames at 15 MPa. AIAA-2008-951, 2008.
[10] Peng D Y, Robinson D B. A new two-constant equation of state. Industrial & Engineering Chemistry Fundamentals, 1976, 15(1): 59-64.
[11] Reid R C, Prausnitz J M, Poling B E. The prosperities of gases and liquids. 4th ed. NewYork: McGraw Hill International Editions, 1989: 8-11.
[12] http://webbook.nist.gov/.
[13] Congiunti A, Bruno C, Ciacomazzi E. Supercritical combustion properties. AIAA-2003-478, 2003.
[14] Chung T H, Ajlan M, Lee L L. Generalized multiparameter corresponding state correlation for polyatomic, polar fluid transport prosperities. Industrial & Chemical Engineering Research, 1988, 27(4): 671-679.
[15] Edwards T, Maurice L Q. Surrogate mixtures to represent complex aviation and rocket fuels. Journal of Propulsion and Power, 2001, 17(2): 461-466.
[16] Weiss J M, Smith W A. Preconditioning applied to variable and constant density flows. AIAA Journal, 1995, 33(11): 2050-2057.
[17] Branam R, Mayer W. Characterization of cryogenic injection at supercritical pressure. Journal of Propulsion and Power, 2003, 19(3): 342-355.
[18] Pitts W M. Effects of global density ratio on the centerline mixing behavior of axisymmetric turbulent jets. Experiments in Fluids, 1991, 11(2): 125-134.
[19] Oschwald M, Micci M. Spreading angle and centerline variation of density of supercritical nitrogen jets. Atomization and Sprays, 2002, 12(1-3): 91-106.
[20] Chehroudi B, Chen S H, Bracco F V, et al. On the intact core of full cone sprays. SAE Technical Paper, 1985, 94: 85-126.

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