Experimental investigation of exit temperatures of a infrared suppressor model

ZHU Ying; HUANG Yong

Chinese

您当前的位置：

首页 >

文章列表页 >

Experimental investigation of exit temperatures of a infrared suppressor model

更新时间：2026-07-07

- Experimental investigation of exit temperatures of a infrared suppressor model
- Vol. 22, Issue 7, (2007)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院,北京,100083
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2007
- 稿件说明：
移动端阅览
ZHU Ying, HUANG Yong. Experimental investigation of exit temperatures of a infrared suppressor model[J]. 2007, 22(7).
DOI：

ZHU Ying, HUANG Yong. Experimental investigation of exit temperatures of a infrared suppressor model[J]. 2007, 22(7). DOI：

摘要

利用地面模拟试验件实验研究了气流参数对直升机发动机喷管出口温度的影响。实验中主喷管气流温度610℃

压力为常压

下洗气流温度为常温

速度范围为4.4～11 m/s。结果表明

模型出口排气温度随着主喷管流量增加而线性增加

引射系数随着下洗气流速度增加而减小

出口排气温度随下洗气流增加时有一个峰值

增加下洗气流速度有助于降低外套壁温。实验发现外套出口和混合管之间夹层存在气流倒流现象

倒流平均速度随着主喷管流量和下洗气流速度增加而增加。

Abstract

An experiment was conducted to study the influences of airflow parameters on exit temperatures of an infrared suppressor model.The temperature of the main flow was about 610 ℃ and the pressure of the main flow was atmospheric pressure.The downwash flow velocity ranged from 4.4 to 11 m/s.The temperature of downwash flow was atmospheric temperature.The results show that

the exhaust flow temperature grows linearly with the increase of the main nozzle flux.The entrainment coefficient decreases with the increase of the downwash flow.With the increase of the downwash flow velocity

the exhaust temperature has a peak value the exhausting duct temperature decreases with the increase of the downwash flow velocity.The averaged gas velocity of flowing backward between the exhausting duct and the mixture tube increases with the rise of the main nozzle flux and the downwash flow velocity.

关键词

Keywords

references

Views

409

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Influences of the Downwash Flow from a Helicopter Rotor on the Performances of an Infrared Suppressor

Numerical simulation on the temperature field of a helicopter accessory cabin

Helicopoter coupled rotor/fuselage air resonance dynamic stability in forward flight

Numerical simulation of airflow field of helicopter inlet cabin

Elimination of Coupling Instability Using Few Parallel Connection Notch Filters for Helicopter Rotor/Power Train

Related Author

WANG Xian-wei

HUANG Yong

LU Yu-xia

XIE Yong-qi

YU Jian-zu

WANG Xian-wei

LI De-qiang

XUE Hai-feng

Related Institution

Beijing University of Aeronautics and Astronautics

School of Aeronautic Science and Technology, Beijing Unirersty of Aeronautics and Astronautics

China Helicopter Research and Development Institute

Military Representative of PLA Navy at Angang

Naval Aeronautical Engineering Academy Qingdao Branch

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