LPP低污染燃烧室两相喷雾燃烧数值研究

推进技术 ›› 2013, Vol. 34 ›› Issue (3): 353-361.

LPP低污染燃烧室两相喷雾燃烧数值研究

邓远灏^1,2,颜应文¹,朱嘉伟¹,李诗¹,徐华胜²,张靖周¹

南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;中国燃气涡轮研究院,四川成都 610500;南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:邓远灏(1979—),男,博士生,高级工程师,研究领域为低污染燃烧技术。 E-mail:dengyuanhao_gte@163.com联系人:颜应文,男,博士,副教授。E-mail:yanyw@nuaa.edu.cn
基金资助:
国家自然科学基金(50906040)；中央高校基本科研业务费专项资金(NZ2012107)。

Numerical Study of Two-Phase Spray Combustion for Lean Premixed Prevaporized Low-Emission Combustor

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;China Gas Turbine Establishment, Chengdu 610500, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Published:2021-08-15

摘要/Abstract

摘要： 提出一种带有多点燃油直接喷射双环预混旋流(TAPS/MLDI)头部的贫油预混预蒸发(LPP)低污染圆筒燃烧室,为了获得该燃烧室两相喷雾燃烧流场与燃烧性能,利用Fluent数值研究三种LPP燃烧室头部方案和四种进口工况。计算结果表明:(1)LPP燃烧室头部冷态流场存在中心回流区、角落回流区和唇口回流区,流场结果与PIV试验结果吻合较好。(2)在头部方案不变的情况下,工况从100%推力下降到7%推力时,出口平均温度逐渐下降,污染物NO_x排放相应减少。(3)在进口工况不变时,头部方案B燃烧性能相对最优。(4)热力型NO_x的生成速率与燃气温度超过1950K区域的大小和最高燃气温度直接相关, 热力型NO_x的生成主要分布在火焰锋面附近。 

关键词: 贫油预混预蒸发;低污染燃烧室;两相喷雾燃烧;粒子图像测速法;燃烧性能 

Abstract: A lean premixed prevaporized (LPP) low-emission combustor based on a twin annular premixed swirler (TAPS) and multipoint lean direct injection (MLDI) was put forward. In order to gain two phase spray combustion flow and combustion performance of the LPP combustor, different inlet condition and combustor structures were studied with sofware Fluent. The results reveal that:(1) There are a Primary Recirculation Zone (PRZ), a Corner Recirculation Zone (CRZ) and a Lip Recirculation Zone (LRZ) in LPP combustor, and numerical results are in good agreement with experimental data of Particle Image Velocimetry (PIV). (2) With the decrease of engine thrust, average temperature and NO_x mass fraction at exit of combustor drop gradually. (3) At the same inlet condition, combustion performance of the combustor B is the best. (4) Thermal NO_x production rate closely relates to zone area where gas temperature overrun 1950K and the highest temperature in combustor. 

Key words: Lean premixed prevaporized(LPP); Low-emission combustor;Two phase spray combustion;Particle image velocimetry (PIV); Combustion performance

邓远灏,颜应文,朱嘉伟,李诗,徐华胜,张靖周. LPP低污染燃烧室两相喷雾燃烧数值研究[J]. 推进技术, 2013, 34(3): 353-361.

DENG Yuan-hao^1,2,YAN Ying-wen¹,ZHU Jia-wei¹,LI Shi¹,XU Hua-sheng²,ZHANG Jing-zhou¹. Numerical Study of Two-Phase Spray Combustion for Lean Premixed Prevaporized Low-Emission Combustor[J]. Journal of Propulsion Technology, 2013, 34(3): 353-361.

参考文献

[1] 赵坚行.民用发动机污染排放及低污染燃烧技术发展趋势[J].航空动力学报,2008,23(6):986-996.
[2] 彭云晖, 许全宏, 张驰, 等.我国大飞机发动机低污染燃烧室发展考虑[C].深圳:中国航空学会 2007年学术年会动力专题54,2007.
[3] 尚守堂, 程明, 张军峰, 等.低排放长寿命燃烧室关键技术分析[C].深圳:中国航空学会2007年学术年会动力专题58,2007.
[4] 史家荣, 徐华胜.民机发动机燃烧室设计特点与研制的关键技术[C].深圳:中国航空学会2007年学术年会动力专题57,2007.
[5] Bahr W W, Gleason C C.Experiment Clean Combustor Program, Phase Ⅰ:Final Report[R].NACA-CR-134737,5.
[6] Imamura A, Yoshida M, Kawano M.Research and Development of a LPP Combustor with Swirling Flow for Low NO_x[R].AIAA 2001-3311.
[7] Huh J, Cernansky N, Choi K.Mixing of Axially Injected Liquid Jets and Pre-Atomized Sprays in a Lean-Direct-Injection(LDI) Mode[R].AIAA 98-3831.
[8] Mongia H C.TAPS-A 4^th Generation Propulsion Combustor Technology for Low Emissions[R].AIAA 2003-2657.
[9] 颜应文,徐榕,邓远灏,等．贫油预混预蒸发低污染燃烧室头部流场研究[J]．航空学报, 2012,3(6):965-976.
[10] Stouffer S D, Ballal D R,Mongia H C.Development and Combustion Performance of a High-Pressure WSR and TAPS Combustor[R].AIAA 2005-1416.
[11] Dodds W.Twin Annular Premixing Swirler(TAPS) Combustor[C].Berkeley: The Roaring 20th Aviation Noise and Air quality Symposium,2005.
[12] Dhanuka S K, Temme J E, Driscoll J F, et al.Vortex-shedding and Mixing Layer Effects on Periodic Flashback in a Lean Premixed Prevaporized Gas Turbine Combustor[J].Proceedings of the Combustion Institute,2009,2(2):2901-2908.
[13] Yongqiang Fu,San-mou Jeng.Experimental Investigation of Swirling Air Flows in a Multipoint LDI Combustor[R].AIAA 2007-5685.
[14] Nayan Patel, Mehmet Kirtas, Vaidya Sankaran, et al, Simulation of Spray Combustion in a Lean-Direct Injection Combustor[J].Proceedings of the Combustion Intitute, 2007,1(2):2327-2334.
[15] 颜应文,李红红,赵坚行,等.双环预混旋流低污染燃烧室数值研究[J].航空动力学报,2009,24(9):1923-1929.