导流片结构参数对先进旋涡燃烧室性能影响研究 *

推进技术 ›› 2015, Vol. 36 ›› Issue (3): 405-412.

导流片结构参数对先进旋涡燃烧室性能影响研究 *

王志凯¹,曾卓雄²,徐义华¹,田佳莹¹

南昌航空大学飞行器工程学院，江西南昌 330063,上海电力学院能源与机械工程学院，上海 200090,南昌航空大学飞行器工程学院，江西南昌 330063,南昌航空大学飞行器工程学院，江西南昌 330063

发布日期:2021-08-15
作者简介:王志凯(1989—)，男，硕士生，研究领域为航空宇航推进理论与工程。E-mail: nhwzk12@126.com 通讯作者:曾卓雄(1972—)，男，博士，教授，研究领域为航空宇航推进理论与工程。
基金资助:
国家自然科学基金(51066006，51266013)；航空科学基金(2013ZB56002，2013ZB56004)；江西省研究生创新基金 (YC2014-S397)。

Effects of Flow Guide Vanes Structure Parameters on Characteristics of Advanced Vortex Combustor

School of Aircraft Engineering，Nanchang Hangkong University，Nanchang 330063，China,College of Power and Mechanical Engineering，Shanghai University of Electric Power，Shanghai 200090，China,School of Aircraft Engineering，Nanchang Hangkong University，Nanchang 330063，China and School of Aircraft Engineering，Nanchang Hangkong University，Nanchang 330063，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究带导流片的先进旋涡燃烧室燃烧及流动性能，对导流片不同结构参数下燃烧室的流场分布、温度分布、总压损失、燃烧效率及污染物排放进行了数值模拟。结果表明，带导流片的先进旋涡燃烧室性能表现出明显的优越性，能够在不依赖凹腔射流的情况下形成理想的双旋涡结构，有利于增强凹腔稳焰及燃气掺混，大幅度提高燃烧效率，改善出口温度分布，降低NO排放。导流片结构参数对燃烧室性能影响呈现出一定的规律。当导流片伸入凹腔的长度与前钝体高度之比(a/B)为0.2，导流片到前钝体上端面的距离与燃烧室进气通道高度之比(b/H)为0.4，导流片到前钝体后端面的距离与凹腔长度之比(c/L)为0.1～0.2时，燃烧室在贫燃条件下可以实现低压降、低污染的稳定燃烧，而且出口温度分布均匀。

关键词: 先进旋涡燃烧室；导流片；双旋涡；数值模拟

Abstract: In order to investigate the combustion and flow characteristics of Advanced Vortex Combustor (AVC) with flow guide vanes，the effects of different structural parameters on flow fields，temperature distribution，the total pressure loss，combustion efficiency and pollutant emission were numerically studied. The results show that AVC with flow guide vanes has better performance than formal AVC. It can form a desirable dual-vortex structure even without any cavity air injection and it can enhance the stability of flame and the mixing of gas，combustion efficiency and exit temperature distribution. Meanwhile it can reduce pollutant emission. Structural parameters of flow guide vanes have certain significant effects on the combustor characteristics. Stable combustion with lower total pressure loss and lower pollution can be achieved when a/B=0.2，b/H=0.4，c/L=0.1～0.2 (where a is defined as the length of vane inside the cavity，b is defined as the distance from vane to the upper surface of the front-body，c is the distance from vane to the rear surface of the front-body，B is the front-body height，H is height of the inlet，L is the cavity length)under lean conditions，and the combustor exit temperature distribution becomes more uniform.

Key words: Advanced vortex combustor；Flow guide vanes；Dual-vortex；Numerical simulation

王志凯,曾卓雄,徐义华,田佳莹. 导流片结构参数对先进旋涡燃烧室性能影响研究 *[J]. 推进技术, 2015, 36(3): 405-412.

WANG Zhi-kai¹,ZENG Zhuo-xiong²,XU Yi-hua¹,TIAN Jia-ying¹. Effects of Flow Guide Vanes Structure Parameters on Characteristics of Advanced Vortex Combustor[J]. Journal of Propulsion Technology, 2015, 36(3): 405-412.

参考文献

[1] Ezhil Kumar P K, Mishra D P. Numerical Simulation of Cavity Flow Structure in an Axisymmetric Trapped Vortex Combustor[J]. Aerospace Science and Technology, 2012, 21(1): 16-23.
[2] Ghenai C, Zbeeb K, Janajreh I. Combustion of Alternative Fuels in Vortex Trapped Combustor[J]. Energy Conversion and Management, 2013, 65: 819-828.
[3] Zhang R C, Fan W J. Flow Field Measurements in the Cavity of a Trapped Vortex Combustor Using PIV[J]. Journal of Thermal Science, 2012, 21(4): 359-367.
[4] 孙海俊, 曾卓雄, 徐义华, 等. AVC 预混燃烧流动特性的数值模拟[J]. 科学技术与工程, 2013, 13(17): 4843-4848.
[5] Meyer T R, Brown M S, Fonov S, et al. Optical Diagnostics and Numerical Characterization of a Trapped-vortex Combustor[R]. AIAA 2002-3863.
[6] Stone C, Menon S. Simulation of Fuel-Air Mixing and Combustion in a Trapped-Vortex Combustor[R]. AIAA 2000-0478.
[7] 邢菲, 孟祥泰, 李继保, 等. 凹腔双驻涡稳焰冷态流场初步研究[J]. 推进技术, 2008, 29(2): 135-138.(XING Fei, MENG Xiang-tai, LI Ji-bao, et al. Elementary Study on Cool Flow Field of Double Vortex in Cavity for Flame Stabilization[J]. Journal of Propulsion Technology, 2008, 29(2): 135-138.)
[8] 张韬, 宋双文, 樊未军, 等. 双涡/贫油驻涡燃烧室的贫油熄火特性试验[J]. 航空动力学报, 2011, 26(6): 1328-1333.
[9] 樊未军, 易琪, 严明, 等. 驻涡燃烧室凹腔双涡结构研究 [J]. 中国电机工程学报, 2006, 26(9): 66-70.
[10] Agarwal K K, Ravikrishna R V. Experimental and Numerical Studies in a Compact Trapped Vortex Combustor: Stability Assessment and Augmentation[J]. Combustion Science and Technology, 2011, 183(12): 1308-1327.
[11] 王志凯, 曾卓雄, 徐义华. 先进旋涡燃烧室后钝体开口结构的数值研究[J]. 推进技术, 2014, 35(6): 809-814. (WANG Zhi-kai, ZENG Zhuo-xiong, XU Yi-hua. Numerical Simulation of Open Structure of the Rear Blunt Body in Advanced Vortex Combustor [J]. Journal of Propulsion Technology, 2014, 35(6): 809-814.)
[12] 彭泽琰, 刘刚, 桂幸民, 等. 航空燃气轮机原理[M]. 北京:国防工业出版社, 2008.
[13] 黄勇. 燃烧与燃烧室[M]. 北京:北京航空航天大学出版社, 2009.
[14] Edmonds R G, Steele R C, Williams J T, et al. Ultra-low NO_x Advanced Vortex Combustor[R]. ASME GT 2006-90319.
[15] 张智博, 李智明, 杨洪磊, 等. 旋转流线涡技术对驻涡燃烧室性能的影响[J]. 热科学与技术, 2013, (2): 141-147.(编辑:史亚红)　　　　　　　　　　　　　　收稿日期:2014-02-20；修订日期:2014-03-20。基金项目:国家自然科学基金(51066006,51266013)；航空科学基金(2013ZB56002,2013ZB56004)；江西省研究生创新基金 (YC2014-S397)。作者简介:王志凯(1989—),男,硕士生,研究领域为航空宇航推进理论与工程。E-mail: nhwzk12@126.com通讯作者:曾卓雄(1972—),男,博士,教授,研究领域为航空宇航推进理论与工程。E-mail: zengzhuoxiong@tsinghua.org.cn