甩油盘系统内部流场数值模拟

推进技术 ›› 2019, Vol. 40 ›› Issue (3): 593-601.

甩油盘系统内部流场数值模拟

覃文隆¹,樊未军¹,张荣春¹,冯阳²,王倚阳²

北京航空航天大学能源与动力工程学院，北京 100191,北京航空航天大学能源与动力工程学院，北京 100191,北京航空航天大学能源与动力工程学院，北京 100191,中国航发湖南动力机械研究所，湖南株洲 412002,中国航发湖南动力机械研究所，湖南株洲 412002

发布日期:2021-08-15
作者简介:覃文隆，博士生，研究领域为机械旋转雾化。 E-mail: dragon_tandy@126.com 通讯作者:张荣春，博士，讲师，研究领域为航空发动机燃烧室燃烧。
基金资助:
国家自然科学基金(51506003)。

Numerical Simulation of Fluid Field Inside Slinger System

School of Energy and Power Engineering，Beihang University，Beijing 100191，China,School of Energy and Power Engineering，Beihang University，Beijing 100191，China,School of Energy and Power Engineering，Beihang University，Beijing 100191，China,AECC Hunan Aviation Powerplant Research Institute ，Zhuzhou 412002，China and AECC Hunan Aviation Powerplant Research Institute ，Zhuzhou 412002，China

Published:2021-08-15

摘要/Abstract

摘要： 为获取内部流场对雾化性能的影响规律，对实际应用的甩油盘系统，包括分油环、甩油盘进行了数值模拟研究。结果表明，分油环中，流量越大，分流均匀性越差；合适的出口直径可以提升分油环分流均匀性；出口数量越多，分流均匀性越差，数量增加到一定程度时，分流均匀性又会转好；不同位置的出口流量不同，最大流量偏差约2%；出口直径不一致时，分流均匀性最差。在甩油盘研究中，引入了出口液体等效直径的概念来量化研究内部流场对雾化的影响。研究得到，转速增加，甩油盘内部液膜变薄，液雾SMD减小，均匀性变好，穿透深度变小；流量增加，液雾SMD变大，穿透深度增加；出入口之间轴向距离引起出口液体速度及液体等效直径的变化小于5%，可以忽略其影响；在出孔直径小于1.7mm时，增大出孔直径，可以改善雾化；出孔倾斜角主要影响液雾的轴向分布；增加出孔数量，可以减小液雾SMD。

关键词: 甩油盘；分油环；数值模拟；内部流场；雾化

Abstract: To obtain how the internal flow affects the atomization performance， the slinger system which includes oil ring and slinger was studied by numerical simulation. In the oil ring， greater flow rate causes poorer flow distribution uniformity. The appropriate outlet diameter can improve the flow distribution uniformity. Larger number of outlets breaks the distribution uniformity of the flow， but when the number increases to a certain value， the flow distribution will be more even. The outlet flow rates are different when at different locations， the maximum flow deviation is about 2%. The flow distribution uniformity is poorest when the outlet diameters are inconsistent. In the research of slinger， a concept of liquid equivalent diameter was introduced to quantitatively measure the effects of the internal flow on slinger’s atomization. The results show that when the rotating speed increases， the liquid film inside the slinger becomes thinner， the spay SMD becomes smaller and more uniform， and the penetration depth becomes smaller. When the flow rate increases， the spray SMD becomes larger and the penetration depth increases. The axial distance between the inlet and the outlet causes the change of the liquid velocity and the liquid equivalent diameter at outlet to be less than 5%， and the effect can be ignored. Increasing the outlet diameter can improve the spray quality when the outlet diameter is smaller than 1.7mm. The outlet channel angle mainly affects the axial distribution of the spray. Increasing the outlet number can reduce the spray SMD.

Key words: Slinger；Oil ring；Numerical simulation；Inside fluid field；Atomization

覃文隆,樊未军,张荣春,冯阳,王倚阳. 甩油盘系统内部流场数值模拟[J]. 推进技术, 2019, 40(3): 593-601.

TAN Wen-long¹,FAN Wei-jun¹,ZHANG Rong-chun¹,FENG Yang²,WANG Yi-yang². Numerical Simulation of Fluid Field Inside Slinger System[J]. Journal of Propulsion Technology, 2019, 40(3): 593-601.

参考文献

[1] Lefebvre A. Fifty Years of Gas Turbine Fuel Injection[J]. Atomization and Sprays, 2000, 10(3-5): 251-276.
[2] Maskey H C, Marsh F X. The Annular Combustion Chamber with Centrifugal Fuel Injection[R]. SAE Technical Paper, 620007, 1962.
[3] 熊纯, 宋双文, 陈剑, 等. 一种离心甩油盘雾化性能的试验[J]. 航空动力学报, 2012, 27(7): 1517-1522.
[4] 宋双文, 蒋荣伟, 陈剑, 等. 离心甩油折流环形燃烧室的性能试验[J]. 航空动力学报, 2007, 22(9): 1401-1404.
[5] 曾川, 王洪铭, 单鹏. 微涡喷发动机离心甩油盘环形折流燃烧室的设计与实验研究[J]. 航空动力学报, 2003, 18(1): 92-96.
[6] 陈晓丽, 蒋雪辉, 何悟, 等. 微小型甩油盘式燃烧室若干关键技术研究[J]. 推进技术, 2016, 37(2): 296-303. (CHEN Xiao-li, JIANG Xue-hui, HE Wu, et al. A Study on Key Technologies of Micro Combustor with a Slinger Injector[J]. Journal of Propulsion Technology, 2016, 37(2): 296-303.)
[7] 黄维娜, 李中祥. 国外航空发动机简明手册 [M]. 西安:西北工业大学出版社, 2014.
[8] Morishita T. A Development of the Fuel Atomizing Device Utilizing High Rotational Speed[R]. ASME 81-GT-180.
[9] Werner D. Fundamental Analysis of Liquid Atomization by Fuel Slingers in Small Gas Turbines[R]. AIAA 2002-3183.
[10] Dahm W J A, Patel P R, Lerg B H. Analysys of Liquid Breakup Regimes in Fuel Slingler Atomization[J]. Atomization and Sprays, 2006, 16(8): 945-962.
[11] Dahm W J A, Patel P R, Lerg B H. Experimental Visualizations of Liquid Breakup Regimes in Fuel Slinger Atomization[J]. Atomization and Sprays, 2006, 16(8): 933-944.
[12] Sescu C, Kucinschi B R, Afjeh A A, et al. Experimental Test Rig with Results on Liquid Atomization by Slinger Injectors[J]. Journal of Engineering for Gas Turbines and Power, 2011, 133(11).
[13] Carmen S, Bogdan K, Abdollah A. Computational Analysis of a Slinger Atomizer[R]. AIAA 2010-6581.
[14] Sescu C, Kucinschi B, Masiulaniec K, et al. Experimental Test Rig with Results on Atomization by Slinger Injectors[R]. AIAA 2008-4771.
[15] Sescu C, Kucinschi B, Afjeh A, et al. Parametric Study of Liquid Atomization by Slinger Injectors[R]. AIAA 2009-4829.
[16] Choi S M, Jang S H. Spray Behavior of the Rotary Atomizer with in-Line Injection Orifices[J]. Atomization and Sprays, 2010, 20(10): 863-875.
[17] Choi S M, Jang S H, Lee D H, et al. Spray Characteristics of the Rotating Fuel Injection System of a Micro-Jet Engine[J]. Journal of Mechanical Science and Technology, 2010, 24(2): 551-558.
[18] Choi S M, Yun S, Jeong H J, et al. Spatial Drop Behavior of a Rotary Atomizer in a Cross Flow[J]. Atomization and Sprays, 2012, 22(12): 1077-1095.
[19] Choi S M, Yun S, Jeong H J, et al. Spray in Cross Flow of a Rotary Atomizer[J]. Atomization and Sprays, 2012, 22(2): 143-161.
[20] Wu P, Kirkendall K, Fuller R, et al. Breakup Processes of Liquid Jets in Subsonic Crossflows[R]. AIAA 96-3024.
[21] Wu P, Kirkendall K A, Fuller R P, et al. Spray Structures of Liquid Jets Atomized in Subsonic Crossflows[J].Journal of Propulsion and Power, 1998, 14(2): 173-182.
[22] 李国能, 林江, 李凯, 等. 横向射流中心轨迹和扩展宽度[J]. 化工学报, 2011, 62(1): 66-70.　　　　　　　　　　　　　　收稿日期:2018-03-06；修订日期:2018-05-09。基金项目:国家自然科学基金(51506003)。作者简介:覃文隆,博士生,研究领域为机械旋转雾化。 E-mail: dragon_tandy@126.com通讯作者:张荣春,博士,讲师,研究领域为航空发动机燃烧室燃烧。E-mail: zhangrongchun@buaa.edu.cn(编辑:梅瑛)