Analysis of dynamic characteristics of sand particles in air intake and compressor cascade of aero⁃engine

Qiannan XU; Feng HU; Youhong XIAO; Hai ZHANG

doi:10.13224/j.cnki.jasp.20210803

Chinese

您当前的位置：

首页 >

文章列表页 >

Analysis of dynamic characteristics of sand particles in air intake and compressor cascade of aero⁃engine

Turbomachinery | 更新时间：2025-04-07

- Analysis of dynamic characteristics of sand particles in air intake and compressor cascade of aero⁃engine
- Journal of Aerospace Power Vol. 36, Issue 8, Pages: 1776-1782(2021)
- 作者机构：
  
  1.哈尔滨工程大学动力与能源工程学院，哈尔滨 150001
  2.中国航空发动机集团有限公司四川燃气涡轮研究院;高空模拟技术重点实验室，四川绵阳 621700
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210803
  CLC：
- 稿件说明：
移动端阅览
Qiannan XU, Feng HU, Youhong XIAO, et al. Analysis of dynamic characteristics of sand particles in air intake and compressor cascade of aero⁃engine[J]. Journal of Aerospace Power, 2021, 36(8): 1776-1782.
DOI：

Qiannan XU, Feng HU, Youhong XIAO, et al. Analysis of dynamic characteristics of sand particles in air intake and compressor cascade of aero⁃engine[J]. Journal of Aerospace Power, 2021, 36(8): 1776-1782. DOI： 10.13224/j.cnki.jasp.20210803.

摘要

为提高发动机的吞砂、防砂能力，需要了解砂粒在发动机中运动规律及对发动机性能的影响。采用欧拉⁃拉格朗日法对E

发动机整流罩、风扇和增压级进行了砂粒与气流的耦合作用分析计算，加入颗粒碰撞模型和侵蚀模型。仿真分析结果表明：砂粒运动轨迹和侵蚀区域符合发动机使用规律。砂粒进入发动机与风扇叶片压力面发生碰撞，砂粒发生碰撞后大部分进入了外涵流道。砂粒碰撞位置主要集中在风扇叶片压力面处，风扇对颗粒运动轨迹的影响最显著，碰撞后的颗粒有明显的径向运动趋势，叶顶区域的颗粒富集程度较高。整流罩、风扇叶片压力面及外机匣壁面都发生较为严重的砂粒侵蚀现象，而增压级叶片砂粒侵蚀现象不明显。

Abstract

In order to improve the sand swallowing and sand control capabilities of the aero⁃engine，it is necessary to understand the law of sand movement in the engine and its impact on engine performance.The Euler⁃Lagrangian method was used to analyze and calculate the coupling effect of sand particles and airflow on the E3 engine fairing，fan and supercharger stage，and the particle collision model and erosion model were added.The simulation analysis results showed that the sand movement trajectory and erosion area conformed to the engine usage law.The sand particles entered the engine and collided with the pressure surface of the fan blades，and most of the sand particles entered the outer culvert flow channel after the collision.The collision position of sand particles was mainly concentrated at the pressure surface of the fan blades.The fan had the most significant influence on the particle movement trajectory.The particles after collision had an obvious radial movement trend，and the particle concentration in the tip area was relatively high.The fairing，the pressure surface of the fan blades and the wall of the outer casing all had serious sand erosion，while the sand erosion of the booster stage blades was not obvious.

关键词

Keywords

references

SAXENA S , JOTHIPRASAD G , BOURASSA C , et al . Numerical simulation of particulates in multi⁃stage axial compressors [R]. ASME Paper GT⁃2016⁃67917 , 2016 .

HAMED A , TABAKOFF W , WENGLARA R . Erosion and deposition in turbomachinery [J]. Journal of Propulsion and Power , 2012 , 22 ( 2 ): 350 ⁃ 360 .

GHENAIET A , TAN S C , ELDER R L . Numerical simulation of the axial fan performance degradation due to sand ingestion [R]. ASME Paper GT⁃2002⁃30644 , 2002 .

PEPI M , SQUILLACIOTI R , PFLEDDERER L , et al . Solid particle erosion testing of helicopter rotor blade materials [J]. Journal of Failure Analysis and Prevention , 2012 , 12 ( 1 ): 96 ⁃ 108 .

BALAN C , TABAKOFF W . Axial flow compressor performance deterioration [R]. AIAA 84⁃1208 , 1984 .

GHENAIET A , TAN S C , ELDER R L . Particle trajectories through an axial fan and performance degradation due to sand ingestion [R]. ASME Paper GT⁃2001⁃0497 , 2001 .

BAMMERT K , SANDSTEDE H . Measurement of the boundary layer development along a turbine blade with rough surface [J]. Journal of Engineer for Gas Turbines and Power , 1983 , 102 ( 4 ): 978 ⁃ 983 .

DUNN M G , PADOVA C , MOLLER G E . Performance deterioration of a turbofan and a turbojet engine upon exposure to a dust environment [J]. Gas Turbines Power , 1987 , 109 ( 3 ): 336 ⁃ 343 .

GHENAIET A . Simulation of particle trajectories and erosion in a centrifugal compressor [J]. Journal of Turbomachinery , 2012 , 134 ( 5 ): 051022.1 ⁃ 051022.19 .

GHENAIET A . Study of sand particle trajectories and erosion into the first compression stage of a turbofan [J]. Journal of Turbomachinery , 2012 , 134 ( 5 ): 051025.1 ⁃ 051025.17 .

孙海鸥 , 王萌 , 王忠义 , 等 . 轴流压气机气固两相流及磨损特性数值模拟 [J]. 哈尔滨工程大学学报 , 2018 , 39 ( 2 ): 310 ⁃ 316 .

SUN Haiou , WANG Meng , WANG Zhongyi , et al . Numerical research on two⁃phase flow and erosion characteristic of axial compressor [J]. Journal of Harbin Engineering University , 2018 , 39 ( 2 ): 310 ⁃ 316 . (in Chinese) .

侯圣文 , 吴锋 , 张海 . 轴流压气机吞沙工况的性能变化研究 [C]∥ 中国航天第三专业信息网第四十届技术交流会暨第四届空天动力联合会议论文集：S04航空燃气涡轮推进技术 . 昆明 : 中国航天第三专业信息网 , 2019 ： 95 ⁃ 102 .

BOULANGER A , PATEL H . Preliminary experimental investigation of initial onset of sand deposition in the turbine section of gas turbines [R]. ASME Paper 2016⁃GT⁃56059 , 2016 .

BOJDO N , FILIPPONEA A , PARKES B , et al . Aircraft engine dust ingestion following sand storms [J]. Aerospace Science and Technology , 2020 , 106 : 106072.1 ⁃ 106072.10 .

常鸿雯 , 李艳军 . 航空发动机吞砂试验技术浅析 [J]. 机械工程师 , 2019 ( 8 ): 126 ⁃ 127 .

CHANG Hongwen , LI Yanjun . Technical analysis of sand ingestion test on areo⁃engine [J]. Mechanical Engineer , 2019 ( 8 ): 126 ⁃ 127 . (in Chinese)

曾林 , 程礼 , 李宁 , 等 . 航空发动机吞砂试验标准砂与典型沙粒形貌对比分析 [J]. 航空发动机 , 2019 , 45 ( 1 ): 101 ⁃ 106 .

ZENG Lin , CHENG Li , LI Ning , et al . Comparison and analysis of morphology of standard sand and typical sand particle in aeroengine sand swallowing test [J]. Aeroengine , 2019 , 45 ( 1 ): 101 ⁃ 106 . (in Chinese)

GRANT G , TABAKOFF W . Erosion prediction in turbomachineryresulting from environmental particles [J]. Journal of Aircraft , 1975 , 12 ( 5 ): 471 ⁃ 478 .

BALAN C , TABAKOFF W . Axial compressor performance deterioration [J]. AIAA 84 ⁃ 1208 , 1984 .

孙见忠 , 姜衡 , 陈颖达 . 航空发动机砂尘吸入物静电监测仿真实验 [J]. 航空动力学报 , 2018 , 33 ( 12 ): 2913 ⁃ 2923 .

SUN Jianzhong , JIANG Heng , CHEN Yingda . Aero engine sand dust ingestion electrostatic monitoring simulation experiment [J]. Journal of Aerospace Power , 2018 , 33 ( 12 ): 2913 ⁃ 2923 . (in Chinese)

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Application of neural network model in compressor through⁃flow analysis

Experiment of Reynolds number effects on subsonic compressor plane cascade

Position rule of turboshaft engine surge based on bench test

Theoretical study on amplitude and frequency of compressor instability

Flow control mechanism of diffuser cascade corner-suction surface profiling design

Related Author

Teng FEI

Lucheng JI

Ling ZHOU

Wei WEI

Siyuan REN

Husheng MA

Xuechen LI

Youhai ZONG

Related Institution

School of Aerospace Engineering，Beijing Institute of Technology

Institute for Aero Engine，Tsinghua University

Aerospace Technology Institute，China Aerodynamics Research and Development Center

Aeronautical Foundation Institute，Naval Aviation University

Unit ，People's Liberation Army

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