高负荷跨声速压气机流场结构分析

潘若痴1; 孙鹏*2; 高海洋1; 傅文广2

doi:10.16411/j.cnki.issn1006-7736.2015.02.014

大连海事大学学报 >

2015 , Vol. 41 >Issue 2: 77 - 83

DOI: https://doi.org/10.16411/j.cnki.issn1006-7736.2015.02.014

热能与动力

高负荷跨声速压气机流场结构分析

潘若痴¹ ,
孙鹏^*2 ,
高海洋¹ ,
傅文广²

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(1.中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015;2.大连海事大学轮机工程学院, 辽宁大连 116026)

潘若痴(1978-), 男, 硕士, 高级工程师.

收稿日期: 2014-10-09

修回日期: 2014-12-11

网络出版日期: 2015-06-07

基金资助

国家自然科学基金资助项目(51006014);中央高校基本科研业务费专项资金资助(3132014048).

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Flow-field analysis of a highly loaded transonic compressor

PAN Ruo-chi¹ ,
SUN Peng^*2 ,
GAO Hai-yang¹ ,
FU Wen-guang²

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(1. Shenyang Aircraft Engine Design Institute, China Aviation Industry Corporation, Shenyang 110015, China; 2. Marine Engineering College, Dalian Maritime University, Dalian 116026, China)

Received date: 2014-10-09

Revised date: 2014-12-11

Online published: 2015-06-07

Supported by

;the Fundamental Research Funds for the Central Universities

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摘要

为研究某压气机内部流场结构,采用全流道非定常数值模拟方法,对跨声速压气机最高效率点和近失速点流场进行求解,重点分析近失速工况下压气机内部流场结构.研究表明：在近失速工况下,动叶槽道激波前推与前缘脱体激波融合为一道激波,强度增强；动叶20%叶高处激波前推最为严重,引起动叶吸力面附面层严重分离；静叶根部受上游动叶尾迹影响形成大范围的分离区,并有空间环涡结构形成.

关键词： 压气机; 流场结构; 非定常; 激波; 分离

本文引用格式

潘若痴¹ , 孙鹏^*2 , 高海洋¹ , 傅文广² . 高负荷跨声速压气机流场结构分析[J]. 大连海事大学学报, 2015 , 41(2) : 77 -83 . DOI: 10.16411/j.cnki.issn1006-7736.2015.02.014

Abstract

Full-annulus unsteady simulations were carried out to obtain the internal flow field structure in an axial flow compressor at design point and near stall point, especially the internal flow of compressor at stall point was studied. Results show that, at near stall point, shock waves in rotor passages move forward, and form stronger shock waves by combining with the detached shock waves. The shock waves at 20% span of rotor move forward most seriously, leading to a heavy boundary separation on the rotor suction side. Influenced by rotor wake flow, large scale separation zones generated at stator corner and space ring vortex formed.

Key words： compressor; flow-field; unsteady; shock wave; separation

参考文献

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