采用钝体式孔板淬熄的富油-淬熄-贫油驻涡燃烧室排放性能试验研究

推进技术 ›› 2016, Vol. 37 ›› Issue (4): 675-683.

采用钝体式孔板淬熄的富油-淬熄-贫油驻涡燃烧室排放性能试验研究

蒋波,何小民,金义,吴泽俊,丁国玉,宋耀宇

南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016,南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:蒋波，男，博士生，研究领域为低排放燃烧机理与燃烧技术。
基金资助:
工业与信息化部民用航空发动机燃烧室基础预研项目；江苏省普通高校研究生科研创新计划资助项目

Emission Characteristics of a Rich-Quench-Lean Trapped-Vortex Combustor Utilizing Quenching Device of Orifice Plate Combined with Bluff-Body

Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China,Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China and Nanjing University of Aeronautics and Astronautics，Jiangsu Province Key Laboratory of Aerospace Power Systems，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 设计研制了采用钝体式孔板淬熄装置进行淬熄作用的富油-淬熄-贫油(Rich-quench-lean，RQL)驻涡燃烧室(Trapped-vortex Combustor，TVC)模型和试验系统，实现了富油燃烧-快速淬熄-贫油燃烧的分级燃烧。在常压状态下采用RP3航空煤油作为燃料开展了排放试验研究，分析并总结了当量比(包含总当量比和富油区当量比)、进口速度(马赫数)和进口温度等参数对采用钝体式孔板淬熄的RQL-TVC排放性能的影响。研究结果表明:不同进口温度或进口马赫数条件下，随着当量比的增大，氮氧化物(NO_x)的排放指数(Emission Index，EI)呈现出先急剧升高，然后急剧下降并趋于平缓的趋势，在富油燃烧区当量比为1.1左右达到峰值，一氧化碳(CO)的EI值先保持平稳而后急剧下降，未燃碳氢化合物(UHC)的EI值呈现连续降低的趋势，燃烧效率持续增大，燃烧效率均高于95%，最大值达99%以上；进口温度较高或进口马赫数较小时，UHC和CO的EI值均较小，燃烧效率较高，而NO_x的EI值较大，反之亦然。

关键词: 航空推进；燃烧；富油-淬熄-贫油驻涡燃烧室RQL-TVC；排放指数EI

Abstract: By utilizing quenching device of orifice plate combined with bluff-body，a rich-quench-lean trapped-vortex combustor (RQL-TVC) was designed，and the staged combustion of rich-burn quick-quench lean-burn was realized. The experimental investigation of emission performance was accomplished at atmospheric pressure by using RP3 jet fuel. The effects of equivalence ratio (including the global equivalence ratio and rich-burn equivalence ratio)，inlet Mach number and inlet temperature on the performance of emissions and combustion efficiency were analyzed. The results show that under different inlet conditions of temperature or Mach number，as equivalence ratio increases，Emission Index(EI)values of nitrogen oxides (NO_x) reveal a sharp rise firstly，and then a rapid drop following a slight drop. A peak is of existing around 1.1 of rich-burn equivalence ratio. EI values of carbon moNO_xide(CO)firstly maintain steadily and then decline sharply. EI values of unburned hydrocarbons (UHC) give a continuous decreasing trend. The combustion efficiency increases continuously along with the increasing of equivalence ratio，and all of that is higher than 95%，the maximum value is above 99%. At higher inlet temperature or smaller inlet Mach number conditions，EI values of UHC and/or CO all are smaller，EI value of NO_x is bigger，combustion efficiency is higher，and vice versa.

Key words: Aerospace propulsion；Combustion；Rich-quench-lean trapped-vortex combustor；Emission Index

蒋波,何小民,金义,吴泽俊,丁国玉,宋耀宇. 采用钝体式孔板淬熄的富油-淬熄-贫油驻涡燃烧室排放性能试验研究[J]. 推进技术, 2016, 37(4): 675-683.

JIANG Bo,HE Xiao-min,JIN Yi,WU Ze-jun,DING Guo-yu,SONG Yao-yu. Emission Characteristics of a Rich-Quench-Lean Trapped-Vortex Combustor Utilizing Quenching Device of Orifice Plate Combined with Bluff-Body[J]. Journal of Propulsion Technology, 2016, 37(4): 675-683.

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] 林宇震, 许全宏, 刘高恩, 等. 燃气轮机燃烧室 [M].北京:国防工业出版社, 2008.
[3] 徐华胜, 邓远灏, 马存祥. 民用航空发动机低排放燃烧室技术[J]. 航空科学技术, 2014, (2).
[4] Gupta A K. Gas Turbine Combustion: Prospects and Challenges [J]. Energy Conversion and Management, 1997, 38: 1311-1318.
[5] Mongia H C. Aero-Thermal Design and Analysis of Gas Turbine Combustion Systems: Current Status and Future Direction [R]. AIAA 98-3982.
[6] Plencner R M. Engine Technology Challenges for the High-Speed Civil Transport Plane[R]. AIAA 98-25025.
[7] Van C A, Richman M H. Technical Challenges Associated with the Development of Advanced Combustion Systems [C]. USA: RTO AVT Symposium on "Gas Turbine Engine Combustion, Emissions and Alternative Fuels", 1998.
[8] Smith R. Advanced Low Emissions Subsonic Combustor Study [R]. NASA 19990024925, 1998.
[9] Sturgess G J, Shouse D T, Zelin J, et al. Emissions Reduction Technologies for Military Gas Turbine Engines [R]. AIAA 2003-2622.
[10] Lefebvre A H. Gas Turbine Combustion [M]. New York: Taylor & Francis, 1999.
[11] Roquemore W M, Shouse D, Burrus D, et al. Trapped Vortex Combustor Concept for Gas Turbine Engines [R]. AIAA 2001-0483.
[12] Hsu K Y, Goss L P, Roquemore W M. Characteristics of a Trapped-Vortex Combustor [J]. Journal of Propulsion and Power, 1998, 14(1): 57-65.
[13] Hsu K-Y, Goss L P, Trump D D. Performance of a Trapped-Vortex Combustor [R]. AIAA 95–0810.
[14] Straub D L, Casleton K H, Lewis R E, et al. Assessment of Rich-Burn, Quick-Mix, Lean-Burn Trapped Vortex Combustor for Stationary Gas Turbines[J]. Journal of Engineering for Gas Turbines and Power, 2005,127:36-41.
[15] Agarwal K K, Krishna S, Ravikrishna R V. Mixing Enhancement in a Compact Trapped Vortex Combustor [J]. Combustion Science and Technology, 2013, 185(3): 363-378.
[16] 岑可法, 姚强, 骆仲泱, 等. 高等燃烧学 [M]. 杭州:浙江大学出版社, 2003.
[17] 樊未军, 严明, 易琪, 等. 富油/快速淬熄/贫油驻涡燃烧室低NO_x排放[J]. 推进技术, 2006, 27(1): 88-91. (FAN Wei-jun, YAN Ming, YI Qi, et al. Low NO_x Emission of Rich-Burn, Quick-Mix, Lean-Burn Trapped Vortex Combustor[J]. Journal of Propulsion Technology, 2006, 27(1): 88-91.)
[18] 何小民, 许金生, 苏俊卿. 驻涡燃烧室燃烧性能试验[J]. 航空动力学报, 2009, 24(2): 318-323.
[19] 金义, 何小民, 蒋波. 富油燃烧/快速淬熄/贫油燃烧(RQL) 工作模式下驻涡燃烧室排放性能的试验研究 [J]. 航空动力学报, 2011, 26(5): 1031-1036.
[20] Jin Yi, He Xiaomin, Zhang Jinyu, et al. Experimental Study on Emission Performance of an LPP/TVC[J]. Chinese Journal of Aeronautics, 2012, 25(3): 335–341.
[21] Jin Yi, He Xiaomin, Jiang Bo, et al. Design and Performance of an Improved Trapped Vortex Combustor[J]. Chinese Journal of Aeronautics, 2012, 25(6): 864–870.
[22] Jin Yi, Yefang Li, He Xiaomin, et al. Experimental Investigations on Flow Field and Combustion Characteristics of a Model Trapped Vortex Combustor[J]. Applied Energy, 2014, 134: 257-269.
[23] 蒋波, 何小民, 金义, 等. 低排放驻涡燃烧室冷态流场特性试验研究[J]. 航空动力学报, 2013, 28(8): 1719-1726.
[24] Webb R L, Kim N H. Principles of Enhanced Heat Transfer [M]. New York: Taylor&Francis, 2005.*　收稿日期:2014-12-17；修订日期:2015-01-09。基金项目:工业与信息化部民用航空发动机燃烧室基础预研项目；江苏省普通高校研究生科研创新计划资助项目 (CXLX12_0172)。作者简介:蒋波,男,博士生,研究领域为低排放燃烧机理与燃烧技术。E-mail: bojiang815@outlook.com(编辑:张荣莉)