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

CHEN Zhu; SHAN Yong; SHEN Xi-gang; ZHANG Jing-zhou; SHAO Wan-ren

doi:10.13224/j.cnki.jasp.2016.03.026

Chinese

您当前的位置：

首页 >

文章列表页 >

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

更新时间：2026-07-07

- Numerical simulation on re-ingestion characteristicsunder landing state for thrust reverser
- Vol. 31, Issue 3, Pages: 733-739(2016)
- 作者机构：
  
  1. 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
  2. 中国航空工业集团公司中国燃气涡轮研究院,成都,610500
  3. 中国航空工业集团公司沈阳发动机设计研究所,沈阳,110015
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2016.03.026
  CLC：
- Published：2016
- 稿件说明：
移动端阅览
陈著, 单勇, 沈锡钢, 张靖周, 邵万仁. 着陆滑跑状态下的反推力装置重吸入特性数值模拟[J]. 航空动力学报, 2016, 31(3): 733-739.

doi: 10.13224/j.cnki.jasp.2016.03.026
陈著, 单勇, 沈锡钢, 张靖周, 邵万仁. 着陆滑跑状态下的反推力装置重吸入特性数值模拟[J]. 航空动力学报, 2016, 31(3): 733-739. DOI： 10.13224/j.cnki.jasp.2016.03.026.

doi: 10.13224/j.cnki.jasp.2016.03.026 DOI：

摘要

对大涵道比涡扇发动机叶栅式反推力装置

利用CFD技术

展示了叶栅式反推力装置开启后的流场流动特征

计算分析了飞机着陆滑跑马赫数和侧风速度对发动机进气道重吸入特性的影响.结果表明:在无侧风影响时

进气道对反推力气流的重吸入现象随着滑跑马赫数的增加而逐渐减弱并消失

重吸入特征参数值随着滑跑马赫数的增加而减小并达到允许值

该临界滑跑马赫数为0.08;在侧风环境中

侧风使得反推力气流在发动机一侧进入发动机进气道

导致风扇进口截面的总温畸变增大

重吸入特征参数值随着侧风速度的增加而增大

侧风的存在使得反推力装置关闭的临界滑跑马赫数从不存在侧风时的0.08提高到0.12.

Abstract

A numerical study was carried out for a cascade thrust reverser of a turbofan engine with high bypass ratio to investigate the influences of the landing Mach number and crosswind speed on the re-ingestion characteristics of the engine and the flow characteristics with the thrust reverser opened. The results showed that:with the increase of the landing Mach number

the level of re-ingestion of the engine inlet decreased

and then disappeared. The value of the characteristic parameter used to evaluate re-ingestion characteristics reached to an allowable value when the critical landing Mach number was 0.08 without the crosswind. When the thrust reverser encountered the crosswind

crosswind changed the flow direction for the thrust reverser flow. It caused the reverser flow to re-ingest into the engine on the crosswind side with the increase of the total temperature distortion on the air inlet. The value of the re-ingestion parameter increased along with the increases of crosswind speed. Therefore

the critical landing Mach number for the safety increased from 0.08 to 0.12 for the cause of crosswind.

关键词

Keywords

references

Views

394

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Ground vortex distortion flow characteristics of inlet for a transport aircraft

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

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

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

Experiment of jet noise reduction technology using lobed mixer

Related Author

Yu LIU

Junqi WANG

Liu YANG

Dingding REN

Haigang ZHAO

TU Baofeng

HU Jun

GUO Jin

Related Institution

Chinese Flight Test Establishment， Aviation Industry Corporation of China Limited

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

中国航空发动机集团有限公司四川燃气涡轮研究院

中国航空发动机集团有限公司沈阳发动机研究所

Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics

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