基于支板燃烧室的喷管化学非平衡效应

程诚; 覃粒子; 刘宇

基于支板燃烧室的喷管化学非平衡效应

北京航空航天大学宇航学院, 北京 100191

详细信息

中图分类号: V 231.2
计量
- 文章访问数: 1760
- HTML全文浏览量: 314
- PDF下载量: 528
- 被引次数: 0
出版历程
- 收稿日期: 2011-09-19
- 网络出版日期: 2013-01-31

Nozzle chemical non-equilibrium effects based on strut combustor

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

摘要

摘要: 采用有限体积法全隐式格式和代用燃料C₁₂H₂₃的10组元13步化学反应Arrhenius有限速率模型研究煤油燃料超燃冲压发动机单边膨胀喷管(SERN, Single Expansion Ramp Nozzle)内的化学非平衡流动,通过建立支板燃烧室——喷管模型有效解决了单边膨胀喷管模型的"入口薄层"问题.计算结果表明,整个单边膨胀喷管内,流动呈现化学非平衡效应,喷管入口附近区域尤其显著;非平衡流动喷管性能明显高于冻结流动,随发动机当量混合比 ε增加,非平衡流动的喷管推力系数和升力系数相对冻结流动的百分比增量 δ不断升高,当 ε=0.8时,推力系数百分比增量 δ_{C_F}达到9.41%,升力系数百分比增量 δ_{C_Y}达到16.39%,化学非平衡效应对煤油燃料超燃冲压发动机尾喷管性能的影响不可忽略.
- 超燃冲压发动机 /
- 单边膨胀喷管 /
- 煤油 /
- 支板 /
- 化学非平衡 /
- 性能
Abstract: The finite volume method in implicit scheme and surrogate fuel C₁₂H₂₃'s 10 species and 13 step reactions Arrhenius finite-rate model were adopted to investigate the non-equilibrium chemical reaction flow in kerosene-fueled scramjet single expansion ramp nozzle (SERN), and the ‘inlet thin layer' problem in SERN model was effectually solved by establishing the strut combustor-SERN model. Numerical simulation results show that the chemical non-equilibrium effect exits in the whole SERN, especially near the nozzle inlet zone; The SERN performance with non-equilibrium chemical reaction flow is obviously higher than that with frozen flow. With the increase of engine equivalent mixture ratio (ε) the δ grows up, which is the percentage of increment about nozzle thrust coefficient and lift coefficient with non-equilibrium chemical reaction flow relative to frozen flow.When the ε=0.8, thrust coefficient increment δ_{C_F}=9.41%, lift coefficient increment δ_{C_Y}=16.39%, thus the chemical non-equilibrium effect of kerosene-fueled scramjet nozzle cannot be ignored.
- scramjet engine /
- single expansion ramp nozzle /
- kerosene /
- strut /
- chemical non-equilibrium /
- performance

HTML全文

参考文献(16)

[1]	司徒明.碳氢燃料超燃研究与应用[J].流体力学实验与测量,2000,14(1):43-50 Situ Ming.Study and application of hydrocarbon-fueled supersonic combustion[J].Experiments and Measurements in Fluid Mechanics,2000,14(1):43-50(in Chinese)
[2]	余勇,丁猛,刘卫东,等.煤油超音速燃烧的试验研究[J].国防科技大学学报,2004,26(1) :1-4 Yu Yong,Ding Meng,Liu Weidong,et al.Experimental study of supersonic combustion of kerosene[J].Journal of National University of Defense Technology,2004,26(1) :1-4 (in Chinese)
[3]	Kumaran K,Babu V.Mixing and combustion characteristics of kerosene in a model supersonic combustor[J].Journal of Propulsion and Power,2009,25(3):583-592
[4]	王新月,杨振鹏,王彦青.化学非平衡流动对超燃冲压发动机尾喷管性能的影响[J].航空动力学报,2009,24(5):1022-1027 Wang Xinyue,Yang Zhenpeng,Wang Yanqing.Effects of non-equilibrium chemical reaction flow on the performance of scramjet nozzle[J].Journal of Aerospace Power,2009,24(5):1022-1027(in Chinese)
[5]	Link T,Koschel W W.Computation of a nonequilibrium expansion flow in a single expansion ramp nozzle[J].Journal of Propulsion and Power,2001,17(6):1353-1360
[6]	Kaneko M,Menshov I,Nakamuka Y.Numerical simulation of non-equilibrium flow in high-enthalpy shock tunnel with EIH scheme.AIAA 2001-2860,2001
[7]	刘欧子,蔡元虎,胡欲立,等.液体煤油超声速燃烧数值分析的湍流模型[J].空气动力学学报,2007,25(3):362-367 Liu Ouzi,Cai Yuanhu,Hu Yuli,et al.The turbulence models for numerical analysis of liquid kerosene supersonic combustion[J].Acta Aerodynamica Sinica,2007,25(3):362-367(in Chinese)
[8]	黄生洪,徐胜利,刘小勇.煤油超燃冲压发动机两相流场数值研究(Ⅲ)[J].推进技术,2005,26(2) :101-105 Huang Shenghong,Xu Shengli,Liu Xiaoyong.Combustion flow of kerosene-fueled scramjet with 3D cavity(Ⅲ)[J].Journal of Propulsion Technology,2005,26(2) :101-105 (in Chinese)
[9]	Kundu K P,Penko P F,Yang S l.Simplified jet-A/air combustion mechanisms for calculation of NOX emissions.AIAA 98-3986,1998
[10]	Ten-See W.Thermophysics characterization of kerosene combustion[J].Journal of Thermophysics and Heat Transfer,2001,15(2):140-147
[11]	李建平.超燃冲压发动机尾喷管设计及性能研究.西安:西北工业大学动力与能源学院,2006 Li Jianping.Scramjet nozzle design and performance study.Xi'an:School of Power and Energy,Northwestern Polytechnical University,2006 (in Chinese)
[12]	吴先宇.超燃冲压发动机一体化流道设计优化研究.长沙:国防科学技术大学航天与材料工程学院,2007 Wu Xianyu.Research on design and optimization of integrated scramjet flowpath.Changsha:School of Aerospace and Materials Engineering,National University of Defense Technology,2007 (in Chinese)
[13]	刘欧子,蔡元虎,胡欲立,等.超声速气流中煤油燃烧的实验研究[J].推进技术,2005,26(3) :276-279 Liu Ouzi,Cai Yuanhu,Hu Yuli,et al.Experimental investigation of kerosene fuel combustion in the supersonic flow[J].Journal of Propulsion Technology,2005,26(3) :276-279 (in Chinese)
[14]	Ramya P H,Marathe A G.A computational study on supersonic combustion with struts as flame holder.AIAA 2008-4712,2008
[15]	杨顺华,乐嘉陵,赵慧勇,等.煤油超燃冲压发动机三维大规模并行数值模拟[J].计算物理,2009,26(4) :534-540 Yang Shunhua,Le Jialing,Zhao Huiyong,et al.Three-dimensional massively parallel numerical simulation of kerosene-fueled scramjet[J].Chinese Journal of Computational Physics,2009,26(4):534-540 (in Chinese)
[16]	Pierce M,Ely W.A computational exploration of the importance of three-dimensionality,boundary layer development,and flow chemistry to the prediction of scramjet nozzle forces and moments.AIAA 1991-5059,1991