| 超声波/离心组合喷嘴性能研究 |
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| 引用本文： | 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[J].航空动力学报,2012,27(2):335-342. |
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| 作者姓名： | 金义 何小民 吴泽俊 丁国玉 秦伟林 |
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| 作者单位： | 南京航空航天大学能源与动力学院,南京,210016 |
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| 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) |
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| 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%.
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| 关 键 词： | 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 |
| 收稿时间： | 2011/3/28 0:00:00 |
| 修稿时间： | 2011/7/29 0:00:00 |
Investigation on the performance of an ultrasonic/pressure-swirl hybrid injector |
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| JIN Yi,HE Xiao-min,WU Ze-jun,DING Guo-yu and QIN Wei-lin.Investigation on the performance of an ultrasonic/pressure-swirl hybrid injector[J].Journal of Aerospace Power,2012,27(2):335-342. |
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| Authors: | JIN Yi HE Xiao-min WU Ze-jun DING Guo-yu and QIN Wei-lin |
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| Institution: | 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;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| 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 117 mm×60 mm 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 8~12 μm without air supply,the SMD falls between 8~12 μm 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%. |
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| Keywords: | aero-engine hybrid injector mass flow characteristics atomization characteristics feasibility |
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