涡轮级间燃烧室燃烧性能试验

丁国玉; 何小民; 金义; 秦伟林; 吴泽俊; 蒋波

涡轮级间燃烧室燃烧性能试验

南京航空航天大学能源与动力学院, 南京 210016

计量
- 文章访问数: 1594
- HTML浏览量: 3
- PDF量: 517
- 被引次数: 0
出版历程
- 收稿日期: 2011-11-14
- 刊出日期: 2012-11-28

Experiment of performance of interstage turbine combustor

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 开展了进口空气马赫数、驻涡区余气系数影响涡轮级间燃烧室燃烧性能的试验研究,获得了燃烧室性能参数的变化规律:随着进口马赫数的增大,总压损失从1.5%增加到7%,流阻系数变化不大,出口温度分布系数OTDF(overall temperature distribution factor)也相应变大;对于不同的进口马赫数,燃烧效率、OTDF随驻涡区余气系数的增大分别为降低和基本不变;燃烧效率大多在70%~85%之间;试验中得到的在燃烧室进口温度为473K时的最大贫油熄火余气系数为9.7.
- 涡轮级间燃烧室 /
- 驻涡 /
- 燃烧性能 /
- 马赫数 /
- 余气系数
Abstract: Experiments were conducted to study the interstage turbine combustor performance with different inlet air Mach number and the excess air coefficient of cavity.Experimental result shows that total pressure loss increases from 1.5% to 7% varying with the increase of the inlet air Mach number,the flow drag coefficient is 16 which changes little with the inlet air flow Mach number,and overall temperature distribution factor (OTDF) increases with the increase of the inlet air Mach number;OTDF holds the line as the excess air coefficient of cavity increases while the combustion efficiency decreases;the combustion efficiency is almost between 70% through 85%;the maximal lean blow out(LBO) excess air coefficient is 9.7 at the inlet air temperature of 473K.
- interstage turbine combustor /
- trapped-vortex /
- combustion performance /
- Mach number /
- excess air coefficient

HTML

参考文献(17)

[1]	Sirignano W A,Liu F.Performance increases for gas-turbine engines through combustion inside the turbine[J].Journal of Propulsion and Power,1999,15(1):111-118.
[2]	尚守堂,程明,刘殿春,等.涡轮级间燃烧室技术的研究现状与发展趋势[J].航空科学技术,2011(4):79-82. SHANG Shoutang,CHENG Ming,LIU Dianchun,et al.The status and direction of inter-stage turbine burner technology[J].Aeronautical Science & Technology,2011(4):79-82.(in Chinese)
[3]	Balu S.Effect of trapped vortex combustion with radial vane cavity arrangements on predicted inter-turbine burner performance [R].AIAA-2009-4603,2009.
[4]	Hsu K Y,Gross L P.Characteristics of a trapped vortex combustor[J].Journal of Propulsion Power,1998,14(1):57-65.
[5]	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. HE Xiaomin,XU Jinsheng,SU Junqing.Experimental research of the performance of the trapped-vortex combustor[J].Journal of Aerospace Power,2009,24(2):318-323.(in Chinese)
[6]	刘世青,钟兢军.驻涡燃烧室最佳中心驻体宽度选择的数值研究[J].航空动力学报,2010,25(5):1005-1010. LIU Shiqing,ZHONG Jingjun.Numerical simulation of center-body width in a trapped vortex combustor[J].Journal of Aerospace Power,2010,25(5):1005-1010.(in Chinese)
[7]	Zelina J,Ehret J,Hankcock R D,et al.Ultra-compact combustion technology using high swirl for enhanced burning rate.AIAA-2002-3725,2002.
[8]	Zelina J,Sturgess G J, Shouse D T.The behavior of an ultra-compact combustor (UCC) based on centrifugally-enhanced turbulent burning rates [R].AIAA-2004-3541,2004.
[9]	何小民,王家骅.驻涡火焰稳定器冷态流场特性的初步研究[J].航空动力学报,2002,17(5):567-571. HE Xiaomin WANG Jiahua.An investigation on the fluid characteristics of trapped-vortex combustor[J].Journal of Aerospace Power,2002,17(5):567-571.(in Chinese)
[10]	何小民,许金生,苏俊卿.驻涡区进口结构参数影响TVC燃烧性能的研究[J].航空动力学报,2007,22(11):1798-1802. HE Xiaomin,XU Jinsheng,SU Junqing.Effect of air and fuel injection patterns in pilot zone on the trapped-vortex combustor performance[J].Journal of Aerospace Power,2007,22(11):1798-1802.(in Chinese)
[11]	何小民,姚锋.流动和油气参数对驻涡燃烧室燃烧性能的影响[J].航空动力学报,2006,21(5):810-813. HE Xiaomin,YAO Feng.Effect of flow parameters and equivalence ratio on the trapped-vortex combustor performance[J].Journal of Aerospace Power,2006,21(5):810-813.(in Chinese)
[12]	苏俊卿.驻涡燃烧室设计与试验验证研究 [D].南京:南京航空航天大学,2007. SU Junqing.Reserch on design and test verification of the trapped-vortex combustor [D].Nanjing:Nanjing University of Aeronautics and Astronautics,2007.(in Chinese)
[13]	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):66-71. FAN Weijun,YI Qi,YAN Ming,et al.A study of double vortex structure in the trapped vortex combustor[J].Proceedings of the CSEE,2006,26(9):66-71.(in Chinese)
[14]	张荣春,樊未军,邢菲.涡轮级间单涡燃烧室壁温研究[J].航空动力学报,2010,25(7):1512-1517. ZHANG Rongchun,FAN Weijun,XING Fei.Study of wall temperature on the interstage turbine single vortex combustor[J].Journal of Aerospace Power,2010,25(7):1512-1517.(in Chinese)
[15]	张荣春,樊未军,邢菲.环形级间驻涡燃烧室壁温分布试验[J].航空动力学报,2010,25(6):1238-1244. ZHANG Rongchun,FAN Weijun,XING Fei.Experimental study of wall temperature distribution on annular interstage trapped vortex combustor[J].Journal of Aerospace Power,2010,25(6):1238-1244.(in Chinese)
[16]	孔祥雷,樊未军,邢菲,等.单涡/贫油驻涡燃烧室的出口温度分布试验[J].航空动力学报,2010,25(4):794-799. KONG Xianglei,FAN Weijun,XING Fei,et al.Experimental study on outlet temperature distribution in single vortex/lean oil trapped vortex combustor[J].Journal of Aerospace Power,2010,25(4):794-799.(in Chinese)
[17]	成本林,周文祥,张堃元.带级间燃烧的涡轴发动机性能仿真[J].航空动力学报,2011,26(11):2543-2548. CHENG Benlin,ZHOU Wenxiang,ZHANG Kunyuan.Performance simulation of turboshaft engines with interstage turbine burner[J].Journal of Aerospace Power,2011,26(11):2543-2548.(in Chinese)