混合排气二元收敛喷管气动与红外隐身综合设计方法

李娜; 吉洪湖; 黄伟; 陈俊; 斯仁; 刘常春

混合排气二元收敛喷管气动与红外隐身综合设计方法

计量
- 文章访问数: 1654
- HTML浏览量: 5
- PDF量: 40
- 被引次数: 0
出版历程
- 收稿日期: 2010-11-24
- 修回日期: 2011-02-18
- 刊出日期: 2011-11-28

Comprehensive design of aerodynamic and infrared stealth of 2-D convergent nozzle with mixed flow

摘要

摘要: 为使混合排气二元收敛喷管的设计在满足发动机推力性能要求的同时,也具有良好的红外特征信号抑制效果,从固定式混合排气二元收敛喷管的设计要求出发,提出了一套混合排气二元收敛喷管气动与红外隐身综合设计的方法和流程.并通过算例计算验证了该设计方法的可行性.另外,计算结果表明:二元喷管的进口截面位置、喷管总长、出口面积以及出口宽高比等几何参数对实现喷管推力性能均起到关键作用;而合理确定出口宽高比,对实现喷管红外隐身性能具有重要作用.
- 二元收敛喷管 /
- 气动特性 /
- 红外隐身 /
- 流量匹配 /
- 设计方法
Abstract: A design method of two-dimensional convergent nozzle of mixed flow turbofan engine was developed to meet aerodynamic and infrared stealth requirements.The feasibility of the design procedures was verified by numerical simulation.And the results indicate that nozzle inlet section position,nozzle length,throat area and aspect ratio properly play a key role for the required nozzle gross thrust.Choosing a reasonable aspect ratio is important for meeting the infrared stealth requirement.
- two-dimensional convergent nozzle /
- aerodynamic performance /

HTML

参考文献(13)

[1]	Capone F J.The nonaxisymmetric nozzle:it is for real .AIAA-1979-1810,1979.
[2]	Hiley P E,Wallance W.Nonaxisymmetric nozzles installed in advanced fighter aircraft[J].J. Aircraft,1976,13(12):1000-1006.
[3]	Stevens H L.F-15/Nonaxisymmetric nozzle system integration study support program .NASA-CR-135252,1978.
[4]	Banken G J,Cornette W M,Gleason K M.Investigation of infrared characteristics of three generic nozzle concepts .AIAA-1980-1160,1980.
[5]	Chu C W,Der J J,Wun W.A simple 2D-nozzle plume model for IR analysis .AIAA-1980-1808,1980.
[6]	Chu C W,Der J J.ADEN plume flow properties for infrared analysis .AIAA-1982-44750,1982.
[7]	翟普,隋俊友,崔杰,等.弹用航空发动机尾喷流红外抑制技术研究[J].推进技术,1996,17(4):17-20. ZHAI Pu,SUI Junyou,CUI Jie,et al.A research on radiation restriction technique of a nozzle flow of aero-engine for missile[J].Journal of Propulsion Technology,1996,17(4):17-20.(in Chinese)
[8]	李荣松,王强,额日其太.尾缘修形的二元喷管内外流场数值研究[J].航空动力学报,2005,20(3):389-393. LI Rongsong,WANG Qiang,Eriqitai.Numerical investigation of two-dimensional nozzle with trailing edge modification[J].Journal of Aerospace Power,2005,20(3):389-393. (in Chinese)
[9]	张勃.大宽高比矩形喷管的射流掺混与红外抑制特性研究 .南京:南京航空航天大学,2005. ZHANG Bo.Investigation of jet mixing characteristics and radiation restriction technology of rectangular nozzle with high aspect ratio .Nanjing:Nanjing University of Aeronautics and Astronautics,2005.(in Chinese)
[10]	罗明东.无人机排气系统红外隐身技术研究 .南京:南京航空航天大学,2006. LUO Mingdong.Investigation of infrared stealth technology of the exhaust system for unmanned aerial vehicle .Nanjing:Nanjing University of Aeronautics and Astronautics,2006.(in Chinese)
[11]	黄伟,吉洪湖,罗明东,等.低速排气非对称二元喷管红外辐射特性实验研究[J]. 南京航空航天大学学报,2008,40(1):16-20. HUANG Wei,JI Honghu,LUO Mingdong,et al.Experimental investigation on IR characteristics of unsymmetrically two-dimensional nozzle at low exhaust velocity[J].Journal of Nanjing University of Aeronautics and Astronautics,2008,40(1):16-20.(in Chinese)
[12]	李娜.混合排气二元收敛喷管气动与红外隐身综合设计方法研究 .南京:南京航空航天大学,2010. LI Na.Aerodynamic and infrared stealth comprehensive design of 2D convergent nozzle of mixed flow .Nanjing:Nanjing University of Aeronautics and Astronautics,2010.(in Chinese)
[13]	罗明东,吉洪湖,黄伟.非加力涡轮发动机排气系统红外辐射强度的数值计算[J].航空动力学报,2007, 22(10):1609- 1616. LUO Mingdong,JI Honghu,HUANG Wei.Numerical evaluation on infrared radiant intensity of exhaust system of turbine engine without afterburning[J].Journal of Aerospace Power,2007,22(10):1609-1616.(in Chinese)