非预混喷注对旋转爆震发动机影响的数值研究

doi:10.7527/S1000-6893.2015.0195

流体力学与飞行力学

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非预混喷注对旋转爆震发动机影响的数值研究

徐雪阳¹, 卓长飞¹, 武晓松¹, 李杰², 马虎¹

1. 南京理工大学机械工程学院, 南京 210094;
2. 豫西工业集团有限公司, 南阳 473000

收稿日期:2015-04-27 修回日期:2015-06-30 出版日期:2016-04-15 发布日期:2015-07-10
通讯作者: 武晓松,Tel.:025-84315456 E-mail:nust203@mail.njust.edu.cn E-mail:nust203@mail.njust.edu.cn
作者简介:徐雪阳,男,硕士研究生。主要研究方向:旋转爆震发动机。E-mail:xuxueyang1012@163.com;卓长飞,男,博士研究生。主要研究方向:新型动力装置。E-mail:njust203zcf@126.com;武晓松,男,博士,教授,博士生导师。主要研究方向:爆震发动机。Tel:025-84315456,E-mail:nust203@mail.njust.edu.cn
基金资助:
国家自然科学基金(51376091);国家自然科学青年基金(11402119)

Numerical simulation of injection schemes with separate supply of fuel and oxidizer effects on rotating detonation engine

XU Xueyang¹, ZHUO Changfei¹, WU Xiaosong¹, LI Jie², MA Hu¹

1. School of Mechanical Engineering, Nanjing University of Science and Technology, Nanjing 210094, China;
2. Yuxi Industrial Group Co. Ltd., Nanyang 473000, China

Received:2015-04-27 Revised:2015-06-30 Online:2016-04-15 Published:2015-07-10
Supported by:
National Natural Science Foundation of China (51376091);National Natural Science Youth Foundation of China (11402119)

摘要/Abstract

摘要：

为了研究真实情况下非预混喷注对旋转爆震发动机工作过程的影响,采用氢氧7组分8步化学反应的基元反应模型,忽略黏性、热传导和扩散等输运效应。对真实情况下燃料(H₂)和氧化剂(Air)分开喷注的旋转爆轰发动机进行三维数值模拟,深入分析了非预混条件下的旋转爆震波流场结构,探讨了燃料喷注方式对发动机性能的影响。计算结果表明:本文方法可有效模拟燃料与氧化剂非预混喷注的旋转爆震波流场。在给定的计算条件下,不同喷注方式发动机的爆震波平均传播速度大约为1640~1840 m/s;平均推力为90~100 N;基于混合物的比冲为820~900 m/s。随着燃料喷注位置的前移,发动机性能明显提高;燃料喷注角度对发动机性能影响较小,随着喷注角度的减小,发动机性能逐渐提高,提高幅度较小;燃料双侧喷注的性能明显优于单侧喷注。旋转爆震发动机的性能与燃料/氧化剂的冷流掺混效果成正比。

关键词: 旋转爆震, 流场结构, 喷注方式, 数值仿真, 发动机性能

Abstract:

In order to study the operation process of rotating detonation engine (RDE) with separate supply of fuel (H₂) and oxidizer (Air) in the real situation, a reduced kinetic mechanism based on 7-step reaction and 8 specie is used to simulate three-dimensional RDE, and the transport processes such as thermal conduction,diffusion and viscosity are ignored. The flow field structure of RDE and the influence of fuel injection strategies on RDE characteristics are discussed in detail. Results show that:the numerical method used in this article can simulate the flow field structure of the RDE effectively; In a given calculation condition, different injection schemes are comparatively studied. The average propagation velocity of rotating detonation wave changes from 1 640 m/s to 1 840 m/s and the average thrust of the rotating detonation engine changes from 90 N to 100 N. The specific impulse based on mixtures changes from 820 m/s to 900 m/s. As the injection position moved forward, the RDE characteristics are obviously improved. But the change of the injection angle has a little influence. As the injection angle decreases, the RDE performance is gradually improved. The RDE performance with the double side injection method was much better than that with the unilateral injection. The RDE performance is proportional to the mixing effect. The study provides some references for the further research of RDE.

Key words: rotating detonation, flow field structure, injection schemes, numerical simulation, engine performance

中图分类号:

V235

徐雪阳, 卓长飞, 武晓松, 李杰, 马虎. 非预混喷注对旋转爆震发动机影响的数值研究[J]. 航空学报, 2016, 37(4): 1184-1195.

XU Xueyang, ZHUO Changfei, WU Xiaosong, LI Jie, MA Hu. Numerical simulation of injection schemes with separate supply of fuel and oxidizer effects on rotating detonation engine[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(4): 1184-1195.

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非预混喷注对旋转爆震发动机影响的数值研究

Numerical simulation of injection schemes with separate supply of fuel and oxidizer effects on rotating detonation engine

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