二元非对称喷管可调方案试验研究

张留欢; 徐惊雷; 莫建伟

doi:10.7527/S1000-6893.2013.0136

航空学报 >

2013 , Vol. 34 >Issue 4: 772 - 778

DOI: https://doi.org/10.7527/S1000-6893.2013.0136

流体力学与飞行力学

二元非对称喷管可调方案试验研究

张留欢 ,
徐惊雷 ,
莫建伟

展开

南京航空航天大学能源与动力学院, 江苏南京 210016

张留欢男, 硕士研究生。主要研究方向: 高超声速内流气体动力学。 E-mail: zhangliuhuan2008@126.com;徐惊雷男, 教授, 博士生导师。主要研究方向: 高超声速进排气气动力学。 Tel: 025-84892204 E-mail: xujl@nuaa.edu.cn

收稿日期: 2012-05-09

修回日期: 2012-07-06

网络出版日期: 2013-04-23

基金资助

国家自然科学基金(90916023)

收起

Experimental Study of 2D Adjustable Asymmetric Nozzles

ZHANG Liuhuan ,
XU Jinglei ,
MO Jianwei

Expand

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2012-05-09

Revised date: 2012-07-06

Online published: 2013-04-23

Supported by

National Natural Science Foundation of China (90916023)

Fold

摘要

针对某二元非对称喷管提出了两种可调方式(方案A和方案B),开展了不同落压比(NPR)的喷管风洞试验,获得了喷管壁面压力分布和流场纹影。根据风洞试验条件,进行了详细的三维数值模拟研究,并与试验结果进行对比,两者吻合良好,验证了本文所采用的数值模拟方法的可靠性。根据数值模拟与试验结果,得出了两种方案推力性能的差异。其中,方案B(喉道和出口面积均可调节)较方案A(仅喉道面积可调节)面积膨胀比更接近喷管理想膨胀比,因此方案B推力性能较好。在落压比为3.8时,方案B较方案A推力系数提高了8%。

关键词： 二元非对称喷管; 可调; 数值模拟; 风洞试验; 推力性能

本文引用格式

张留欢, 徐惊雷, 莫建伟. 二元非对称喷管可调方案试验研究[J]. 航空学报, 2013, 34(4): 772-778. DOI: 10.7527/S1000-6893.2013.0136

Abstract

Two adjustable programs (Plan A and Plan B) of a 2D adjustable asymmetric nozzle are presented in this paper. A tunnel test is carried out at different nozzle pressure ratios (NPR), and the schlieren of the flowfield and the distribution of pressure along the nozzle wall are obtained. Based on the boundary conditions of the tunnel test, a detailed 3D numerical simulation is performed, and the results of the simulation are in good agreement with those of the tunnel test, which testifies the validity of the method of numerical simulation. A comparison of the results of 3D numerical simulation and tunnel test reveals the difference of thrust performance between Plan A and Plan B. Plan B (in which the area of throat and outlet is adjustable) is found to be better than Plan A (in which only the area of throat is adjustable) on thrust performance. When the nozzle pressure ratio is 3.8, the thrust coefficient of Plan B increases by 8% over that of Plan A.

Key words： 2D asymmetric nozzle; adjustable; numerical simulation; tunnel test; thrust performance

参考文献

[1] Xu J L, Zhang Y H, Zhang K Y. Numerical simulation of single expansion ramp nozzle for scramjet on the designing point. Journal of Propulsion Technology, 2007, 28(3): 282-286. (in Chinese) 徐惊雷, 张艳慧, 张堃元. 超燃冲压发动机非对称喷管非设计状态性能计算. 推进技术, 2007, 28(3): 282-286.
[2] Zhang K Y, Zhang R X, Xu H. Investigation of single expansion ramp nozzle. Journal of Propulsion Technology, 2001, 22(5): 380-382.(in Chinese) 张堃元, 张荣学, 徐辉. 非对称大膨胀比喷管研究. 推进技术, 2001, 22(5): 380-382.
[3] Ge J H, Xu J L, Wang M T, et al. The prediction of flow separation in SERN. Acta Aeronautica et Astronautica Sinica, 2012, 33(8): 1394-1399. (in Chinese) 葛建辉, 徐惊雷, 王明涛, 等.非对称喷管流动分离的预测.航空学报, 2012, 33(8): 1394-1399.
[4] Xu J L, Sha J, Zhang K Y, et al. Numerical study of improving the performance of the overexpanded SERN by using SJA. AIAA-2010-679, 2010.
[5] Deere K A, Asbury S C. Experimental and computational investigation of a translating-throat, single-expansion-ramp-nozzle. NASA/TP-1999-209138, 1999.
[6] Hao D X,Wang Z X. The design and flow field simulation of single expansion ramp nozzle with variable flaps. Machinery Design ＆ Manufacture, 2009(12): 9-10. (in Chinese) 郝东兴, 王占学. 下斜板可调的单膨胀斜面喷管型面设计和流场模拟.机械设计与制造, 2009(12): 9-10.
[7] Kojima T, Kobayashi H. Design and fabrication of variable nozzle for precooled turbojet engine. AIAA-2009-7312, 2009.
[8] Taguchi H. Design study on hypersonic engine components for TBCC space planes. AIAA-2003-7006, 2003.
[9] Bartolotta P A, Mcnelis N B. High speed turbines: development of a turbine accelerator (RTA) for space access. AIAA-2003-6943, 2003.
[10] Gamble E, Haid D. Improving off-design nozzle performance using fluidic injection. AIAA-2004-1206, 2004.
[11] Miyagi H, Miyagawa H. Combined cycle engine research in Japanese HYPR project. AIAA-1995-2751, 1995.
[12] Miyagi H, Kimura H, Kishi K,et al. Combined cycle engine research in Japanese HYPR program. AIAA-1998-3278, 1998.
[13] Chang I, Hunter L G. Over-under nozzle CFD and comparision with data. AIAA-1994-2939, 1994.
[14] Mo J W, Xu J L, Zhang L H, et al. The experimental and numerical study of the over-under TBCC exhaust system. AIAA-2011-2234, 2011.
[15] Li N, Zhang K Y, Xu J L. Simulation and experiment validation of a two dimensional asymmetric ramp nozzle. Journal of Aerospace Power, 2004, 19(6): 802-805. (in Chinese) 李念, 张堃元, 徐惊雷. 二维非对称喷管数值模拟与验证. 航空动力学报, 2004, 19(6): 802-805.

Options

文章导航

摘要
本文引用格式
Abstract
参考文献

模态框（Modal）标题

摘要

本文引用格式

Abstract

参考文献