附加涵道风扇系统叶尖涡轮流动特征

张衍; 夏晨; 向鑫; 黄国平

doi:10.13224/j.cnki.jasp.2018.04.007

附加涵道风扇系统叶尖涡轮流动特征

doi: 10.13224/j.cnki.jasp.2018.04.007

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，南京 210016

计量
- 文章访问数: 944
- HTML浏览量: 0
- PDF量: 967
- 被引次数: 0
出版历程
- 收稿日期: 2016-10-12
- 刊出日期: 2018-04-28

Flow characteristic of tip turbine of additional ducted-fan system

摘要

摘要: 针对一种可极大提升涵道比的气驱附加涵道风扇推进动力系统开展研究，采用数值模拟手段重点分析了其核心部件叶尖涡轮的流动特征和工作机理，为后续发展这种大涵道比推进动力奠定理论基础。研究表明：叶尖涡轮实质上是具有低稠度低展弦比特征的轴流涡轮，稠度可低至0.6，展弦比可低至0.4。低展弦比造成的叶尖涡轮间隙泄漏损失增大为原来的2倍，泄漏涡径向侵入叶根，主流流动损失加剧，大大降低了低稠度涡轮能量提取效果；稠度降低会使得喉道位置迁移，导致气流偏转和膨胀加速能力大幅下降；基于这一结构，提出有效提能区和能量提取率来阐明其做功机理并表征低稠度叶尖涡轮的出功能力。
- 附加涵道风扇 /
- 叶尖涡轮 /
- 低稠度 /
- 低展弦比 /
- 间隙泄漏 /
- 流动特征
Abstract: Based on a novel high bypass ratio turbofan propulsion system with additional tip-driving fan, the flow characteristics and working mechanism of the core components tip-turbine were investigated using numerical simulation, which laid a theoretical foundation for the further development of high bypass ratio propulsion. Research results indicated that tip-turbine was essentially the axial flow turbine with low solidity and low aspect ratio characteristic, solidity can be as low as 0.6, aspect ratio as low as 0.4. The reduction of solidity caused the migration of throat position, which led to a substantial decrease in the flow deflection and the acceleration of the expansion; the gap leakage loss caused by the low aspect ratio was 2 times larger than the original one, and the influence of leakage vortex was gradually extended to the vicinity of the root of the blade, which reduced the effective extraction of energy area and the energy extraction rate greatly; for the novel power system, effective extraction of energy region and energy extraction rate were proposed to measure the specific work of tip-turbine qualitatively and quantitatively.
- additional ducted-fan /
- tip turbine /
- low solidity /
- low aspect ratio /
- clearance leakage /
- flow characteristics

HTML

参考文献(18)

[1]	刘大响,金捷,彭友梅,等.大型飞机发动机的发展现状和关键技术分析［J］.航空动力学报,2008,23(6):976-980.LIU Daxiang,JIN Jie,PENG Youmei,et al.Summarization of development status and key technologies for large air plane engines［J］.Journal of Aerospace Power,2008,23(6):976-980.(in Chinese)
[2]	陈光.高涵道比涡轮风扇发动机发展综述［J］.航空制造技术,2008,51(13):40-45.CHEN Guang.Development of high-bypass ratio turbofan aeroengine［J］.Aeronautic Manufacturing Technology,2008,51(13):40-45.(in Chinese)
[3]	陈懋章,刘宝杰.大涵道比涡扇发动机风扇/压气机气动设计技术分析［J］.航空学报,2008,29(3):513-526.CHEN Maozhang,LIU Baojie.Fan/compressor aero design technology for high bypass ratio turbofan［J］.Acta Aeronautica et Astronautica Sinca,2008,29(3):513-526.(in Chinese)
[4]	陈懋章,刘宝杰.风扇/压气机气动设计技术发展趋势——用于大型客机的大涵道比涡扇发动机［J］.航空动力学报,2008,23(6):961-975.CHEN Maozhang,LIU Baojie.Fan/compressor aero design trend and challenge on the development of high bypass ratio turbofan［J］.Journal of Aerospace Power,2008,23(6):961-975.(in Chinese)
[5]	梁春华.欧盟大涵道比涡扇发动机技术研究计划［J］.航空发动机,2007,33(2):57-58.LIANG Chunhua.The technology research program of EU high bypass ratio turbofan engine［J］.Aeroengine,2007,33(2):57-58.(in Chinese)
[6]	梁春华.21世纪大飞机发动机的预研计划于关键技术［J］.航空制造技术,2009,52(17):40-44,2009.LIANG Chunhua.Advanced program and key technology for 21st century largecommercial jet engine［J］.Aeronautic Manufacturing Technology,2009,52(17):40-44.(in Chinese)
[7]	陈云,王雷,王刚.大涵道比发动机多级低压涡轮气动设计［J］.航空发动机,2013,39(4):51-55.CHEN Yun,WANG Lei,WANG Gang.Aerodynamic design of multistage low pressure turbine for high bypass ratio aeroengine［J］.Aeroengine,2013,39(4):51-55.(in Chinese)
[8]	梁春华.商用飞机发动机几项关键新技术［J］.国际航空,2002,4(9):52-54.LIANG Chunhua.New technology used for commercial aircraft engine［J］.International Aviation,2002,4(9):53-54.(in Chinese)
[9]	LARSSON L,GRNSTEDT T,KYPRIANIDIS K G.Conceptual design and mission analysis for a geared turbofan and an open rotor configuration［R］.ASME Paper GT2011-46451,2011.
[10]	KURZKE J.Fundamental differences between conventional and geared turbofans［R］.ASME Paper GT2009-59745,2009.
[11]	HUFF D.Technologies for turbofan noise reduction［R］.Manchester,United Kingdom：NASA Glenn Research Center Cleveland,2005.
[12]	黄国平,向鑫,陈杰,等.叶尖喷气驱动风扇的大涵道比涡扇发动机:CN201410823725.0［P］.2014-06-03.
[13]	XIN X,HUANG G,LU W,et al.High bypass ratio turbofan engine with additional tip-driving fan:a design innovation［R］.Orlando,USA：the 51st AIAA/SAE/ASEE Joint Propulsion Conference,2015.
[14]	孙广华.CFMI公司开始研制LEAP-X发动机［J］.航空发动机,2008,34(4):50.SUN Guanghua.CFMI company began to develop LEAP-X engine［J］.Aeroengine,2008,34(4):50.(in Chinese)
[15]	《世界中小型航空发动机手册》编委会.世界中小型航空发动机手册［M］.北京：航空工业出版社,2006.
[16]	邓阳.高亚音微型轴流涡轮叶型设计及叶尖间隙影响研究［D］.南京：南京航空航天大学,2013.DENG Yang.Study on airfoil design and influence of tip clearance of high subsonic micro axial turbine［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2013.(in Chinese)
[17]	KOFSKEY M G,KATSANIS T,SCHUMANN L F.Aerodynamic design of a free power turbine for a 75 kW gas turbine automotive engine［R］.NASA TM X-71714,1975.
[18]	DOUGHTY R,MOSES H,GREGORY B.The effect of blade solidity on the aerodynamic loss of a transonic turbine cascade［R］.AIAA 92-0393,1992.