低速风洞进气道试验柱形分布式引射器优化设计

巫朝君; 徐彬彬; 张为卓

doi:10.13224/j.cnki.jasp.2020.12.002

低速风洞进气道试验柱形分布式引射器优化设计

doi: 10.13224/j.cnki.jasp.2020.12.002

计量
- 文章访问数: 118
- HTML浏览量: 2
- PDF量: 188
- 被引次数: 0
出版历程
- 收稿日期: 2020-05-28
- 刊出日期: 2020-12-28

Design and optimization of columniform distributed ejector for low speed wind tunnel inlet test

Low Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China

摘要

摘要: 为适应低速风洞发动机进气道试验的大流量模拟的迫切需要，介绍了适用于4 m量级低速风洞的柱形分布式引射器的设计方案。通过ANSYS-CFX软件采用有限体积法对引射器内流场进行了数值模拟,重点优化了引射器的引射面积比、离散的喷嘴分布方式和喷嘴出口设计点总压、马赫数等参数。综合考虑引射器在风洞中的使用条件限制和吸入流量技术指标要求,完成了引射器设计。优化后的引射器方案解决了小体积、大吸入流量需求之间的矛盾。在FL-14风洞的验证试验表明,优化后引射器的最大吸入流量达到9.07 kg/s,满足4 m量级低速风洞进气道试验大流量模拟需求。
- 进气道 /
- 流量模拟 /
- 风洞试验 /
- 引射器 /
- 优化设计
Abstract: In order to meet the urgent requirement of large flow simulation in low speed wind tunnel for engine inlet test, a design scheme of columniform distributed ejector for 4 m-scale low speed wind tunnel was proposed. The internal flow filed of ejector was simulated by ANSYS-CFX software using the finite volume method. The design parameters were optimized, including the ejecting area rate, discrete distribution of nozzles and the design point total pressure and Mach numbers of nozzle outlet. The improved design of ejector met the limited condition in wind tunnel and the acquirement of large mass flow, and solved the contradiction of small size and large mass flow. The experiment in FL-14 wind tunnel indicated that the max absorbing mass flow rate of improved ejector can reach 9.07 kg/s, fulfilling the large mass flow needs of inlet test in 4 m-scale low speed wind tunnel.
- inlet /
- flow simulating /
- wind tunnel test /
- ejector /
- improved design

HTML

参考文献(19)

[1]	李周复.风洞验手册［M］.北京:航空工业出版社,2015:467-477.
[2]	鲍国华.风洞特种实验［M］.西安:西北工业大学出版社,1990:1-8.
[3]	German-Dutch Wind Tunnel.Annual report 2004［EB/OL］.［2019-11-20］.http:∥www.dnw.aero/.
[4]	樊玉辰,范洁川.世界风洞［M］.北京:航空工业出版社,1996:81-82,175-176.
[5]	高静,郝卫东,闫永昌,等.进气道低速特性试验技术研究［J］.流体力学实验与测量,2004,18(1):38-39. GAO Jing,HAO Weidong,YAN Yongchang,et al.Experimental investigation on low speed characteristics of inlet［J］.Experiments and Measurements in Fluid Mechanics,2004,18(1):38-39.(in Chinese)
[6]	张召明,李志强.飞机机身腹部与两侧进气道性能比较试验研究［J］.航空动力学报,2004,19(1):74-75. ZHANG Zhaoming,LI Zhiqiang.Comparision of inlet performance with the underfuselage inlet and fuselage side inlets［J］.Journal of Aerospace Power,2004,19(1):74-75.(in Chinese)
[7]	陈洪,刘李涛,巫朝君.８ m×６ m风洞大尺度模型进气道和喷流试验技术［J］.空气动力学学报,2017,35(6):875-878. CHEN Hong,LIU Litao,WU Chaojun.Inlet and jet test technigues for large scale model in 8 m×6 m low speed wind tunnel［J］.Acta Aerodynamica Sinica,2017,35(6):875-878.(in Chinese)
[8]	王勋年.低速风洞试验［M］.北京:国防工业出版社,2002:182-183.
[9]	巫朝君,杨万富,李征初,等.入口形式对进气道低速特性的影响试验研究［J］.流体力学实验与测量,2003,17(2):32-36. WU Chaojun,YANG Wanfu,LI Zhengchu,et al.Experiments and measurements in fluid mechanics［J］.Experiments and Measurements in Fluid Mechanics,2003,17(2):32-36.(in Chinese)
[10]	林左鸣.世界航空发动机手册［M］.北京:航空工业出版社,2006.
[11]	巫朝君,胡卜元,王勋年,等.飞行器进气道低速风洞试验方法:GJB 8216-2014［S］.北京:中国人民解放军总装备部,2015:3-4.
[12]	李德海,肖新鹰.环状引射器的工作性能优势分析［J］.航空发动机,2006,32(3):25-26. LI Dehai,XIAO Xinying.Performance advantages of annular ejector［J］.Aeroengine,2006,32(3):25-26.(in Chinese)
[13]	王勋年,巫朝君,陈洪,等.战斗机推进系统模拟低速风洞试验技术研究［J］.实验流体力学,2011,25(3):46-49. WANG Xunnian,WU Chaojun,CHEN Hong,et al.Investigation on test technique of fighters with propulsion simulation in low wind tunnel［J］.Journal of Experiments in Fluid Mechanic,2011,25(3):46-49.(in Chinese)
[14]	李真旭,王勋年,杨万富.引射式发动机模拟器的设计与校准试验研究［J］.流体力学实验与测量,2004,18(2):28-31. LI Zhenxu,WANG Xunnian,YANG Wanfu.The design and calibration of ejected engine simulator［J］.Experiments and Measurements in Fluid Mechanics,2004,18(2):28-31.(in Chinese)
[15]	章荣平,王勋年,晋荣超.低速风洞引射短舱动力模拟技术新进展［J］.空气动力学学报,2016,34(6):756-761. ZHANG Rongping,WANG Xunnian,JIN Rongchao.Development in ejector nacelle simulation testing in low speed wind tunnel［J］.Acta Aerodynamica Sinica,2016,34(6):756-761.(in Chinese)
[16]	廖大雄,陈吉明,余永生.引射器增强混合喷嘴性能实验研究［J］.实验流体力学,2007,21(3):24-29. LIAO Daxiong,CHEN Jiming,YU Yongsheng.Experimental study on the performance of mixing-enchanging nozzles in ejctors［J］.Journal of Experiments in Fluid Mechanics,2007,21(3):24-29.(in Chinese)
[17]	NICOLOFF G B,WEBER H A.Characteristics of an ejector-type engine simulator for STOL model testing［R］.AIAA 72-1028,1972.
[18]	邱义芬,王俊清,袁修干,等.多喷嘴引射器性能计算模型［J］.北京航空航天大学学报,1997,23(5):621-626. QIU Yifen,WANG Junqing,YUAN Xiugan,et al.Multiple nozzle ejector performance calculating model［J］.Journal of Beijing Uiversity of Aeronautics and Astronautics,1997,23(5):621-626.(in Chinese)
[19]	姜正行.飞机内流空气动力学［M］.北京:航空工业出版社,1989:1-9.