超声波/离心组合喷嘴性能研究

金义; 何小民; 吴泽俊; 丁国玉; 秦伟林

超声波/离心组合喷嘴性能研究

南京航空航天大学能源与动力学院, 南京 210016

基金项目: 航空科学基金(2008ZB52013); 江苏省普通高校研究生科研创新计划(CXLX11_0211)

计量
- 文章访问数: 1594
- HTML浏览量: 0
- PDF量: 452
- 被引次数: 0
出版历程
- 收稿日期: 2011-03-28
- 修回日期: 2011-07-29
- 刊出日期: 2012-02-28

Investigation on the performance of an ultrasonic/pressure-swirl hybrid injector

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

摘要

摘要: 采用试验研究方法初步探索了一种超声波/离心组合喷嘴应用于航空发动机燃烧室的可行性.对该组合喷嘴开展冷态试验,得到了其流量特性和雾化特性(包括油雾索太尔平均直径(SMD)和雾化锥角),设计加工了横截面尺寸为117mm×60mm的单头部矩形燃烧室模型,并在不同进口条件下开展了相关的燃烧性能试验.结果表明:在冷态情况下,喷嘴流量特性符合传统离心喷嘴的流量特性,流量与供油压差呈二次函数关系;喷嘴雾化细度较好,无气状态下,油雾SMD在38~45μm之间变化,在满足产生超声波要求的气压条件范围内油雾SMD在8~12μm之间变化;喷雾锥角主要受供气条件影响,供油压力对喷雾锥角基本无影响;装有该喷嘴的模型燃烧室在所有试验工况下均可以稳定燃烧,燃烧效率最高达到99%.
- 航空发动机 /
- 组合式喷嘴 /
- 流量特性 /
- 雾化特性 /
- 燃烧性能 /
- 可行性
Abstract: The feasibility for an ultrasonic/pressure-swirl hybrid injector to be applied in aero-engine combustors was investigated experimentally.Mass flow characteristics,atomization performance including Sauter mean diameter (SMD) and spray angle were obtained by cool spraying experiments.A single-dome rectangular combustor rig has been constructed with the cross section dimensions 117mm×60mm and series of experiments have been conducted.Results indicate that the mass flow characteristics are in accord with that of a conventional pressure-swirl injector,the SMD falls between 8~12μm without air supply,the SMD falls between 8~12μm under the existence of ultrasonic wave (kerosene is employed as the fuel),and the spray angle is strongly dependent on the air supply.Good flame stability has been obtained for all the combustion experiments conducted.Under certain situations,combustion efficiency of the combustor rig can achieve 99%.
- aero-engine /
- hybrid injector /
- mass flow characteristics /
- atomization characteristics /
- feasibility /

HTML

参考文献(14)

[1]	Lefebvre A H.Atomization and spray[M].Washington,DC:Hemisphere Publishing Corporation,1989.
[2]	孙晓霞.超声波雾化喷嘴的研究进展[J].工业炉,2004,26(1):19-32. SUN Xiaoxia.Recent research advances of ultrasonic atomizer[J].Industrial Furnace,2004,26(1):19-32.(in Chinese)
[3]	马其良,张松寿.超声波雾化油喷嘴的试验研究[J].工业炉,2000,22(2):6-7,25. MA Qiliang,ZHANG Songshou.Experimental test on spray characteristics of ultrasonic oil sprayer[J].Industrial Furnace,2000,22(2):6-7,25.(in Chinese)
[4]	梁荣,党新安,赵小娟.超声波雾化喷嘴的设计[J].上海有色金属,2006,27(4):14-17. LIANG Rong,DANG Xinan,ZHAO Xiaojun.Research on design of ultrasonic atomizer[J].Shanghai Nonferrous Metals,2006,27(4):14-17.(in Chinese)
[5]	陈义良,张孝春,孙慈,等.燃烧原理[M].北京:航空工业出版社,1992.
[6]	侯晓春.高性能航空燃气轮机燃烧技术[M].北京:国防工业出版社,2002.
[7]	张绍坤.流体动力式超声波喷嘴的实验研究.北京:北京工业大学,2007. ZHANG Shaokun.Experimental study on characteristics of fluid dynamic ultrasonic atomizer.Beijing:Beijing University of Technology,2007.(in Chinese)
[8]	张绍坤,王景甫,马重芳,等.流体动力式超声波喷嘴雾化特性的研究[J].冶金设备,2007,29(特刊):13-16. ZHANG Shaokun,WANG Jingfu,MA Chongfang,et al.Research on atomization characteristics of fluid dynamic and ultrasonic atomizer[J].Metallurgical Equipment,2007,29(extra edition):13-16.(in Chinese)
[9]	朱永刚,王兴甫.超声波喷嘴试验研究[J].推进技术,1997,18(3):68-72. ZHU Yonggang, WANG Xingfu. An experimental study on ultrasonic injection nozzle[J].Journal of Propulsion Technology, 1997,18(3):68-72.(in Chinese)
[10]	甘晓华.航空燃气轮机燃油喷嘴技术[M].北京:国防工业出版社,2006.
[11]	黄勇,林宇震,樊未军,等.燃烧与燃烧室[M].北京:北京航空航天大学出版社,2009.
[12]	张弛,张荣伟,徐国强,等.直射式双旋流空气雾化喷嘴的雾化效果[J].航空动力学报,2006,21(5):805-809. ZHANG Chi,ZHANG Rongwei,XU Guoqiang,et al.Experimental investigation on atomization of an air-blast atomizer with plain-orifice nozzle and dual-swirl cup[J].Journal of Aerospace Power,2006,21(5):805-809.(in Chinese)
[13]	李名远,黄悉然,徐银龙.超声雾化波喷嘴的性能试验[J].动力工程,1982,2(1):14-21. LI Mingyuan,HUANG Xiran,XU Yinlong.Performance test of an ultrasonic liquid atomizing nozzle[J].Power Engineering,1982,2(1):14-21.(in Chinese)
[14]	郭新华,林宇震,张驰,等.离心式同向双旋流器空气雾化喷嘴雾化特性研究[J].航空动力学报,2009,24(10):2249-2254. GUO Xinhua,LIN Yuzhen,ZHANG Chi,et al.Experimental investigation on atomization characteristic of an air-blast atomizer with centrifugal nozzle and co-dual-swirl cup[J].Journal of Aerospace Power,2009,24(10):2249-2254.(in Chinese)