双旋流燃烧室两相喷雾试验和数值研究

刘日超; 乐嘉陵; 陈柳君; 杨顺华; 宋文艳

doi:10.11729/syltlx20170093

Experimental and numerical study on spray atomization in a double-swirler combustor

1.
School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China
2.
Science and Technology on Scramjet Laboratory of Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

Funds:

NSFC 91641205

More Information

Author Bio:
Liu Richao(1986-), male, born in Qingtian Zhejiang province, doctoral candidate.Engaged in combustion and flow in aero-engine research.Address:Xinduhui Ⅱ-806, Beijiao town, Shunde district, Foshan City, Guangdong Province (528311).E-mail:lrc19860517@sina.cn

Corresponding author:
Liu Richao, E-mail: lrc19860517@sina.cn

双旋流燃烧室两相喷雾试验和数值研究

1.
西北工业大学动力与能源学院, 西安 710072
2.
中国空气动力研究与发展中心超高速空气动力研究所高超声速冲压发动机技术国防科技重点实验室, 四川绵阳 621000

详细信息

中图分类号: V231.3
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出版历程
- 收稿日期: 2017-07-04
- 修回日期: 2017-09-25
- 刊出日期: 2017-10-24

摘要

Abstract: Using the particle field pulsed laser holography imaging technique, the spatial distribution of droplet diameter in an aeroengine combustor is measured, the atomization process is studied, and the spatial distribution of droplets diameter in the combustor is obtained too. The numerical sprays models of the primary and secondary atomization are established, and a numerical software for the three-dimensional two-phase combustion in the aeroengine combustor is developed. Based on the LISA atomization model and KH-RT breakup model, the primary atomization process and secondary atomization process in the combustor are simulated numerically, obtaining the distribution of fuel spray droplets in the combustor. The simulation results are compared with experiments. The result indicate that the atomization models developed in this work can properly simulate the whole process of spray atomization under the conditions of high temperature, high pressure and strong swirling in aeroengine combustors.
- aeroengine combustor /
- particle field pulsed laser holography /
- primary atomization /
- secondary atomization
摘要: 采用粒子场脉冲激光全息技术对航空发动机燃烧室中的雾化场进行了测量，得到了燃烧室中燃油液滴直径的空间分布，从而对燃烧室中的雾化过程进行了研究。自主开发完成了适用于航空发动机燃烧室的三维两相数值计算平台，建立了首次雾化模型和二次雾化模型。基于LISA模型和KH-RT模型，对燃烧室中的首次雾化过程和二次雾化过程进行了数值模拟，得到了燃烧室中液雾的空间分布。通过将计算结果与试验结果进行对比，显示开发完成的雾化模型能很好的模拟高温高压，强旋流条件下航空发动机燃烧室的整个喷雾雾化过程。
- 航空发动机燃烧室 /
- 粒子场脉冲激光全息技术 /
- 首次雾化 /
- 二次雾化

HTML全文

图 1 激光全息光路示意图

Fig. 1 Laser hologram optical beam diagram

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图 2 粒子场记录(a)和粒子场的复现(b)

Fig. 2 Particle field information record (a) and reproductive principle diagram (b)

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图 3 液膜的变形过程

Fig. 3 Liquid film formation process diagram

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图 4 计算网格

Fig. 4 Calculation grid

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图 5 边界条件

Fig. 5 Boundary condition

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图 6 Y=0平面上液滴索太尔平均直径沿X轴分布

Fig. 6 The Sauter mean diameter distribution of droplets along X axis (Y=0mm)

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图 7 Z=0平面上液滴索太尔平均直径沿X轴分布

Fig. 7 The Sauter mean diameter distribution of droplets along X axis (Z=0mm)

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图 8 X=31.5mm平面上液滴索太尔平均直径沿Y轴分布

Fig. 8 The Sauter mean diameter distribution of droplets along Y axis (X=31.5mm)

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图 9 X=31.5mm平面上液滴索太尔平均直径沿Z轴分布

Fig. 9 The Sauter mean diameter distribution of droplets along Z axis (X=31.5mm)

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图 10 喷雾结构

Fig. 10 Spray structure

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图 11 冷流状态下燃油液滴分类显示

Fig. 11 Classification of kerosene droplets in cold flow

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图 12 Y=0平面内燃油液滴的索太尔平均直径分布

Fig. 12 The Sauter mean diameter distribution of droplets in Y=0 Plane

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图 13 Z=0平面内燃油液滴的索太尔平均直径分布

Fig. 13 The Sauter mean diameter distribution of droplets in Z=0 Plane

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