一级旋流强度对双旋流杯下游油气分布的影响

推进技术 ›› 2014, Vol. 35 ›› Issue (11): 1482-1487.

一级旋流强度对双旋流杯下游油气分布的影响

于博文,张　弛,杨　谦,许全宏,林宇震

北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京100191

发布日期:2021-08-15
作者简介:于博文(1990—)，男，硕士生，研究领域为航空发动机燃烧机传热传质。

Effects of Primary Swirl Intensity on Flow and Fuel Distribution Downstream a Dual-Swirl Cup

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China;National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China;National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China;National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China;National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为了改善双旋流杯点火性能，需要优化其下游的流场和油雾场。利用激光粒子动态分析技术(PDA)测量基准双旋流杯下游的流场和油雾场，据此提出一级旋流器旋流数仅增大6.7%，但切向动量矩减小44%的改进方案，并进行了流场和油雾场对比试验。试验结果表明:减小双旋流杯一级旋流切向动量矩会使旋流杯下游流场结构发生较大变化，使其从收扩型转变为扩张型，同时减小油雾的索太尔平均直径(SMD)；当与旋流杯出口距离超过2.5倍文氏管喉道直径时，流场输运和油滴蒸发作用增强，使得油雾分布更加均匀，燃油SMD更小。在航空发动机燃烧室双旋流杯设计中，不仅要考虑传统的旋流数概念，还应考虑各级切向动量矩的综合影响作用。

关键词: 航空发动机；燃烧室；旋流杯；旋流数；切向动量矩

Abstract: In order to improve the ignition performance of dual-swirl cup，the downstream flowfield and fuel distribution should be optimized. The flowfield and fuel distribution downstream a baseline dual-swirl cup were measured by Particle Dynamics Analyzer (PDA). Based on the results，an improved dual-swirl cup scheme was proposed with only 6.7% increase of swirl number and 44% decrease of tangential momentum moment for the primary swirl，and the flowfield and fuel distribution were measured and compared with the baseline one. The experimental results indicate that the reduced tangential momentum moment of the primary swirl will affect the flowfield downstream the dual-swirl cup，and then change the flowfield structure from converge-diverge type to diverge one and decrease the Sauter Mean Diameter (SMD) of the fuel spray. When the distance downstream the swirl cup reaches 2.5 times the venturi throat diameter，the effect of flowfield transportation and droplet evaporation could be enhanced to make fuel distribution more uniform and SMD smaller. Both the swirl number and tangential momentum moment of swirlers should be considered in dual-swirl cup design for aeroengine combustor.

Key words: Aero-engine；Combustor；Swirl cup；Swirl number；Tangential momentum moment

于博文,张　弛,杨　谦,许全宏,林宇震. 一级旋流强度对双旋流杯下游油气分布的影响[J]. 推进技术, 2014, 35(11): 1482-1487.

YU Bo-wen,ZHANG Chi,YANG Qian,XU Quan-hong,LIN Yu-zhen. Effects of Primary Swirl Intensity on Flow and Fuel Distribution Downstream a Dual-Swirl Cup[J]. Journal of Propulsion Technology, 2014, 35(11): 1482-1487.

参考文献

[1] 陈大光, 张津, 朱之丽. 推重比15一级发动机有关总体性能的关键技术和难点分析[J]. 航空动力学报, 2001, 16(1): 7-12.
[2] 王占学, 刘增文, 蔡元虎, 等. 推重比15一级发动机关键技术及分析[J]. 航空发动机, 2010, 36(1): 57-62.
[3] 林宇震, 林阳, 张弛, 等. 先进燃烧室中心分级燃烧空气流量分配的探讨[J]. 航空动力学报, 2010, 25(9): 1923-1930.
[4] 李继保, 胡正义. 高温升高热容燃烧室设计技术分析[J]. 燃气涡轮试验与研究, 2000, 13(4): 5-8.
[5] Mongia H C, AI-Roub M, Danis A, et al. Swirl Cup Modeling Part I[R].AIAA 2001-3576.
[6] 彭云晖, 林宇震, 许全宏, 等. 双旋流空气雾化喷嘴喷雾、流动和燃烧性能[J].航空学报, 2008, 29(1):1-14.
[7] Wang H R, McDonell V G, Samuelsen G S. Influence of Hardware Design on the Flow Field Structures and the Patterns of Droplet Dispersion Part I:Mean Quantities[J].Journal of Engineering for Gas Turbine and Power, 1995, 117(2): 288-289.
[8] Lang H J, Huang R, Guo Z H. The Flow Fields in a Model Combustor with Primary Holes After Different Swirl Cups[R].ASME GT-2006-90489.
[9] Ateshkadi A, McDonell V G, Samuelsen G S. Effect of Mixer Geometry on Fuel Spray Distribution, Emissions and Stability[R].AIAA 98-0247.
[10] 袁怡祥, 林宇震, 刘高恩, 等. 燃油周向分级对贫油熄火油气比的影响[J] 航空动力学报, 2003, 18(5):639-644.
[11] Lefebvre A H. Gas Turbine Combustion[M]. Philadelphia: Talor＆Francis, 1999.
[12] Mehta J , Shin H , Wisler D. Mean Velocity and Turbulent Flow-Field Characteristics Inside an Advanced Combustor Swirl Cup[R]. AIAA 89-0215.
[13] 党新宪, 赵坚行, 徐榕.试验研究旋流数对燃烧室气动性能的影响[J].航空动力学报, 2011, 26(1):21-27.
[14] 韩启祥, 许铁军, 黄键.双旋流器单头部模型燃烧室冷态流场试验[J].航空动力学报, 2008, 23(8):1370-1374.
[15] 于锦峰, 郭志辉, 张君锋.等.套筒长度对火焰筒流场和雾化特性的影响[J].航空动力学报, 2009, 24(11):2506-2513.
[16] 刘殿春, 董玉玺, 尚守明, 等.单环腔中心分级燃烧室流场数值模拟[J]. 航空动力学报, 2010, 6(25):1251-1257.
[17] Wang H Y, McDonell V G, Sowa W A. Characterization of a Two-Phaseflow Field Downstream of a 3x-Scale Gas Turbine Co-Axial Counter-Swirling Combustor Dome Swirl Cup[R]. AIAA 92-0229.
[18] 林宇震, 许全宏, 刘高恩. 燃气轮机燃烧室[M]. 北京: 国防工业大学出版社, 2008.(编辑:梅瑛)　　　　　　　　　　　　　　收稿日期:2013-10-15；修订日期:2013-12-12。作者简介:于博文(1990—),男,硕士生,研究领域为航空发动机燃烧机传热传质。E-mail:dtyubw90@163.com