Ground vortex distortion flow characteristics of inlet for a transport aircraft

Haigang ZHAO; Yu LIU; Junqi WANG; Liu YANG; Dingding REN

doi:10.13224/j.cnki.jasp.20200429

Chinese

您当前的位置：

首页 >

文章列表页 >

Ground vortex distortion flow characteristics of inlet for a transport aircraft

Aerothermodynamics and Aeroengine Design | 更新时间：2025-04-07

- Ground vortex distortion flow characteristics of inlet for a transport aircraft
- Journal of Aerospace Power Vol. 36, Issue 8, Pages: 1720-1728(2021)
- 作者机构：
  
  中国航空工业集团公司有限公司中国飞行试验研究院，西安 710089
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20200429
  CLC：
- 稿件说明：
移动端阅览
Haigang ZHAO, Yu LIU, Junqi WANG, et al. Ground vortex distortion flow characteristics of inlet for a transport aircraft[J]. Journal of Aerospace Power, 2021, 36(8): 1720-1728.
DOI：

Haigang ZHAO, Yu LIU, Junqi WANG, et al. Ground vortex distortion flow characteristics of inlet for a transport aircraft[J]. Journal of Aerospace Power, 2021, 36(8): 1720-1728. DOI： 10.13224/j.cnki.jasp.20200429.

摘要

以配装大涵道比涡扇发动机的某型运输机在未铺装跑道静止开车、滑行等实战使用环境为背景，建立了全尺寸三维仿真计算模型，通过数值仿真，分析研究了风速、风向以及滑跑速度对该型飞机进气道地面涡的流动特性及发动机进口畸变特性的影响。结果表明：该型运输机270°侧风条件下，随着风速的增加，地面涡强度呈现先增加后减小的规律，风速为2~4 m/s时强度最大，风速在6 m/s以上地面涡特性消失；风速为3 m/s时，在风向为210°左右地面涡强度达到最大，外物吸入能力最高，其导致的进气道出口周向压力畸变最强。该型运输机滑行状态相对于其静止、逆风环境，地面涡的范围、强度均较小，对进气道出口流场品质也影响较弱。

Abstract

Based on idle and engine driving of a military transport aircraft equipped with a large bypass ratio turbofan engine in unpaved runway ground，a full⁃scale three⁃dimensional simulation model was established，By means of numerical simulation，the ground vortex distortion flow characteristics under different wind speed，wind direction and running speed were studied.The result showed that the ground vortex intensity first increased and then decreased under the 270 degree crosswind condition.The ground vortex intensity was maximal under wind speed range from 2 m/s to 4 m/s.The ground vortex disappeared when wind speed was more than 6 m/s.The ground vortex intensity was maximal and it had strongest suction capacity to foreign objects at 210 degree wind direction under the wind speed of 3 m/s.Also it had greatest influence on the inlet's outlet flow field.The ground vortex intensity and scope was weak under the condition of aircraft running compared with stationary，headwind.

关键词

Keywords

references

屈玉池 , 霍建武 . 大型军民用飞机飞行事故分析 [M]. 西安：中国飞行试验研究院， 2009 .

QU Yuchi , HUO Jianwu . Analysis of flight accidents of large military and civilian aircraft [M]. Xi'an : Chinese Flight Test Establishment , 2009 . （in Chinese）

EDDON J , GOLDSMITH E L . Intake aerodynamics [M]. London : Blackwell Science , 1999 : 136 ⁃ 145 .

BARATA J , MANETA A , SILVA A . Numerical study of a gas turbine engine ground vortex [R].AIAA 2009 ⁃4801 , 2009 .

DE SIERVI A . A flow visualization study of the inlet vortex phenomenon [J]. Cambridge,MA , US:Massachusetts Institute of Technology , 1981 .

SHMILOVICH A , YADLIN Y . Engine ground vortex control [R].AIAA 2006 ⁃3006 , 2006 .

LUIS G , ROBERTO D . Crosswind effects on engine inlets:the inlet vortex [J]. Journal of Aircraft , 2010 , 47 （ 2 ）: 46 ⁃ 52 .

RHODES G D . An investigation into artificial vortex generation and effects on inlet flow quality using scaled turbofan engine simulators [D]. Columbus,Ohio , US:The Ohio State University , 2016 .

SHMILOVICH A , YADLIN Y , SMITH D M . Active system for wide,area suppression of engine vortex : US6763651 [P]. 2004⁃07⁃20 .

SHMILOVICH A , CHANG K C . An algorithm for predicting the flow past fuselage⁃mounted engine arrangements [R]. AIAA 92⁃0151 , 1992 .

BUNING P G , JESPESEN D C , PULLIAM T H , et al . Overflow user's manual [R]. Moffett Field，US : NASA Ames Research Center , 1998 .

BENEK J A , BUNING P G , STEGER J L . A 3⁃D chimera grid embedding technique [R]. AIAA 85⁃1523 , 1985 .

BUNING P G , CHUI I T , OBAYASHI S . Numerical simulation of the integrated space shuttle vehicle in ascent [R].AIAA 1988 ⁃4359 , 1988 .

YADLIN Y , SHMILOVICH A . Simulation of vortex flows for airplanes in ground operations [R]. Reno,US : the 44th AIAA Aerospace Sciences Meeting and Exhibit , 2006 .

MOTYCKA D L , WALTER W A . An experimental investigation of ground vortex formation during reverse engine operation [R]. AIAA 75⁃1322 , 1975 .

MOTYCKA D L . Ground vortex⁃limit to engine reverser operation [J]. Journal of Engineering for Gas Turbines and Power , 1976 , 98 （ 2 ）： 258 ⁃ 264 .

MOTYCKA D L , WALTER W A , MULLER G . An analytical and experimental study of inlet ground vortices [R]. AIAA 73⁃1313 , 1973 .

彭成一 . 新机试飞中的进气道旋流测量 [J]. 推进技术 , 1994 , 15 （ 4 ）: 8 ⁃ 13 .

PENG Chengyi . Measurement of inlet swirl in new aircraft flight test [J]. Journal of Propulsion Technology , 1994 , 15 （ 4 ）: 8 ⁃ 13 . （in Chinese）

杨国才 . 内流涡控技——反进气道旋流措施的预研 [J]. 燃气涡轮试验与研究 , 2002 ， 15 （ 1 ）: 58 ⁃ 62 .

YANG Guocai . Internal flow vortex control technology：pre⁃study of reverse inlet swirl measure [J]. Gas Turbine Experiment and Research , 2002 , 15 （ 1 ）: 58 ⁃ 62 . （in Chinese）

李超东 , 宁方飞 , 贾新亮 . 地面涡对进发匹配的影响 [J]. 燃气涡轮试验与研究 , 2015 , 28 （ 4 ）: 7 ⁃ 10 .

LI Chaodong , NING Fangfei , JIA Xinliang . Influence of ground vortexes on inlet/engine matching [J]. Gas Turbine Experiment and Research , 2015 , 28 （ 4 ）: 7 ⁃ 10 . （in Chinese）

刘浩 . 地面涡对短舱进气道性能的影响研究 [D]. 南京：南京航空航天大学 , 2016 .

LIU Hao . Research on the influence of ground vortex on nacelle inlet [D]. Nanjing : Nanjing University of Aeronautics and Astronautics , 2016 . （in Chinese）

王成 . 带有风扇叶片的短舱进气道地面涡影响研究 [D]. 南京：南京航空航天大学， 2017 .

WANG Cheng . Research on the influence of ground vortex on nacelle inlet with blades [D]. Nanjing : Nanjing University of Aeronautics and Astronautics , 2017 . （in Chinese）

JENNY H , KEVIN G , RENAN F S . Vortex induced aerodynamic forces on a flat plant in ground proximity [J]. AIAA Journal , 2016 , 28 （ 3 ）: 327 ⁃ 341 .

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Numerical simulation of high bypass ratio turbofan engine with total pressure inlet distortion

A design method for propeller with arbitrary circulation distribution

Threedimensional unsteady numerical simulation and analysis of deployment for cascade thrust reverser

Numerical simulation on re-ingestion characteristicsunder landing state for thrust reverser

Numerical investigation on influence of reverser flow to engine inlet flow field

Related Author

TU Baofeng

HU Jun

GUO Jin

祝小平

周洲

范中允

沈锡钢

陈著

Related Institution

西北工业大学无人机特种技术重点实验室

西北工业大学航空学院

中国航空发动机集团有限公司沈阳发动机研究所

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

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰