脉冲爆震燃烧室与冲击式涡轮匹配机理及效率的数值研究

邓芃; 郑龙席; 王凌羿

doi:10.13224/j.cnki.jasp.2018.08.009

脉冲爆震燃烧室与冲击式涡轮匹配机理及效率的数值研究

doi: 10.13224/j.cnki.jasp.2018.08.009

西北工业大学动力与能源学院,西安 710072

计量
- 文章访问数: 537
- HTML浏览量: 3
- PDF量: 512
- 被引次数: 0
出版历程
- 收稿日期: 2017-03-01
- 刊出日期: 2018-08-28

Numerical study on matching mechanism and efficiency ofpulse detonation combustor and impulse turbine

摘要

摘要: 针对脉冲爆震燃烧室（PDC）与涡轮共同工作时,涡轮入口为强非稳态气流的特点,结合涡轮损失机理,确定适合脉冲爆震来流的涡轮类型并开展气动设计工作,运用数值方法计算所设计涡轮的效率和探究PDC与涡轮相互作用的机理。研究结果表明：部分进气、小反力度的冲击式涡轮更适合脉冲爆震来流；在喷嘴收缩段、动叶叶片前缘以及动叶压力面生成向上游传播的反射激波,造成能量损失；在设计点,涡轮效率约为75%。上述研究结果可以为脉冲爆震涡轮发动机的涡轮设计提供一定的参考。
- 脉冲爆震燃烧室（PDC） /
- 冲击式涡轮 /
- 涡轮效率 /
- 气动设计 /
- 匹配机理
Abstract: As the turbine inlet was dominated by strong unsteady airflow when working with the pulse detonation combustor (PDC), the type of turbine was determined based on the loss mechanism and the aerodynamic design work of turbine components was carried out.The numerical method was used to calculate the efficiency of the designed turbine and explore the mechanism of the interaction between the PDC and the turbine.The results showed that partial intake, impulse turbine with less reaction degree was more suitable for PDC; a strong reflection shock wave was formed on the contraction section of nozzle,the leading edge and the pressure surface of the rotor blade, which cause energy loss; the efficiency of turbine was about 75% at the design point. The results can provide some reference for turbine design of pulse detonation turbine engine.
- pulse detonation combustor(PDC) /
- impulse turbine /
- turbine efficiency /
- aerodynamic design /
- matching mechanism

HTML

参考文献(20)

[1]	严传俊,范玮.脉冲爆震发动机原理及关键技术［M］.西安：西北工业大学出版社,2005.
[2]	郑龙席,卢杰,严传俊,等.脉冲爆震涡轮发动机研究进展［J］.航空动力学报,2014,29(5):993-1000.ZHENG Longxi,LU Jie,YAN Chuanjun,et al.Research progress on pulse detonation turbine engine［J］.Journal of Aerospace Power,2014,29(5):993-1000.(in Chinese)
[3]	李晓丰,郑龙席,邱华,等.两相脉冲爆震涡轮发动机原理性试验［J］.航空动力学报,2013,28(12):2731-2736.LI Xiaofeng,ZHENG Longxi,QIU Hua,et al.Two phase pulse detonation turbine engine original rational test［J］.Journal of Aerospace Power,2013,28(12):2731-2736.(in Chinese)
[4]	邓君香,郑龙席,严传俊,等.脉冲爆震燃烧室与涡轮相互作用的试验［J］.航空动力学报,2009,24(2):307-312.DENG Junxiang,ZHENG Longxi,YAN Chuanjun,et al.Experimental investigations of interaction of a pulse detonation combustor with a turbine［J］.Journal of Aerospace Power,2009,24(2):307-312.(in Chinese)
[5]	ZANTE D V,ENVIA E,TURNER M G.The attenuation of a detonation wave by an aircraft engine axial turbine stage［R］.NASA/TM-2007-214972,2007.
[6]	NANGO A,INABA K,KOJIMA T,et al.Aerodynamic effect of turbine blade geometry in pulse detonation combustor［R］.AIAA-2007-1176,2007.
[7]	FERNELIUS M,GORRELL S,HOKE J,et al.Design and fabrication of an experimental test facility to compare the performance of pulsed and steady flow through a turbine［R］.AIAA-2013-0886,2013.
[8]	黄玥.脉冲爆震发动机喷管性能的数值模拟研究［D］.南京:南京航空航天大学,2008.HUANG Yue.Numerical simulation of nozzle performance in pulse detonation engine［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2005.(in Chinese)
[9]	严传俊,何立明,范玮,等.脉冲爆震发动机的研究与发展［J］.航空动力学报,2001,16(3):212-217.YAN Chuanjun,HE Liming,FAN Wei,et al.Research and development of pulse detonation engine［J］.Journal of Aerospace Power,2001,16(3):212-217.(in Chinese)
[10]	李晓丰,郑龙席,邱华.脉冲爆震燃烧室与径向涡轮相互作用数值模拟研究［C］∥第三届爆轰与爆震发动机研讨会.西安:中国航空学会,2013:76-80.
[11]	楚武利,刘前智,胡春波,航空叶片机原理［M］.西安：西北工业大学出版社,2009：150.
[12]	邹正平.航空燃气轮机涡轮气体动力学［M］.上海：上海交通大学出版社,2014.
[13]	华琛,嘉诺塔.内燃机涡轮增压器原理［M］.北京：中国铁道出版社,1990.
[14]	张睿刚.超高膨胀比涡轮机气动性能研究［D］.哈尔滨:哈尔滨工业大学,2014.ZHANG Ruigang.Research on aerodynamic performance of ultra-high expansion turbine［D］.Harbin:Harbin Institute of Technology,2014.(in Chinese)
[15]	罗俊,何立明,陈灯.二维爆震波数值模拟［J］.推进技术,2008,29(1):29-32.LUO Jun,HE Liming,CHENG Deng.Numerical simulation of two-dimensional detonation wave［J］.Journal of Propulsion Technology,2008,29(1):29-32.
[16]	蒋彬,罗凯,高爱军,等.一种微型部分进气冲动式涡轮机设计方法［J］.鱼雷技术,2015,23（5）:353-358.JIANG Bin,LUO Kai,GAO Aijun,et al.Design method of a miniature partial intake impulse turbine［J］.Torpedo Technology,2015,23（5）:353-358.(in Chinese)
[17]	赵寅生.鱼雷涡轮机原理［M］.西安: 西北工业大学出版社,2002.
[18]	刘广涛.大膨胀比涡轮级内流场数值研究［D］.哈尔滨:哈尔滨工业大学,2012.LIU Guangtao.Numerical simulation of turbulent flow in large expansion ratio［D］.Harbin:Harbin Institute of Technology,2014.
[19]	舒士甄.叶轮机械原理［M］.北京:清华大学出版社,1991.
[20]	蒋联友,严传俊,邓君香,等.爆震波与涡轮叶片相互作用的数值模拟［J］.航空动力学报,2009,24(1):60-64.JIANG Lianyou,YAN Chuanjun,DENG Junxiang,et al.Numerical simulation of the interaction between detonation wave and turbine blade［J］.Journal of Aerospace Power,2009,24(1):60-64.(in Chinese)