轴流压气机平面叶栅气动特性的数值研究

李大春; 杨凌; 高宇; 钟兢军

doi:10.16411/j.cnki.issn1006-7736.2017.03.012

大连海事大学学报 >

2017 , Vol. 43 >Issue 3: 71 - 77

DOI: https://doi.org/10.16411/j.cnki.issn1006-7736.2017.03.012

热能与动力

轴流压气机平面叶栅气动特性的数值研究

李大春 ,
杨凌 ,
高宇 ,
钟兢军

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（大连海事大学轮机工程学院，辽宁大连 116026）

李大春（1991-），男，硕士生，E-mail：lidachun336@163.com.

收稿日期: 2017-03-27

修回日期: 2017-04-19

网络出版日期: 2017-04-19

基金资助

国家自然科学基金资助项目(51506020); 辽宁省高校创新团队支持计划(LT2015004) ；高等学校博士学科点专项科研基金资助项目(20132125120006);中央高校基本科研业务费专项资金资助项目（3132016205）；辽宁省自然科学基金资助项目（2015020636）.

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Numerical study on aerodynamic characteristics of axial compressor cascade

LI Da-chun ,
YANG Ling ,
GAO Yu ,
ZHONG Jing-jun

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(Marine Engineering College,Dalian Maritime University, Dalian 116026，China)

Received date: 2017-03-27

Revised date: 2017-04-19

Online published: 2017-04-19

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摘要

以轴流压气机DMU37动叶根部5%叶高典型截面叶型为研究对象，采用Fluent软件，计算分析不同冲角和进口等熵马赫数下叶栅流场损失及气动特性.结果表明：同一冲角下，进口等熵马赫数的提高增加了叶片负荷和扩压能力，同时也使出口总压损失增加，失速冲角范围变小；相同进口马赫数时，随着冲角增加,出口总压损失先减小后增大，-4°冲角时总压损失最小.同时，验证了轴流压气机平面叶栅马赫数、冲角损失特性规律具有相似性，并且，叶栅端壁区域受进口马赫数和冲角变化影响较大.

关键词： 轴流压气机; 平面叶栅; 网格分布; 数值模拟

本文引用格式

李大春 , 杨凌 , 高宇 , 钟兢军 . 轴流压气机平面叶栅气动特性的数值研究[J]. 大连海事大学学报, 2017 , 43(3) : 71 -77 . DOI: 10.16411/j.cnki.issn1006-7736.2017.03.012

Abstract

The axial compressor DMU37 rotor blade 5% typical section blade was taken as the study object, the outlet flow field loss and aerodynamic characteristics of the cascade under different incidence angle and inlet isentropic Mach numbers were calculated and analyzed by using Fluent software. Results show that under the same impact angle, the increase of the inlet isentropic Mach number increases the blade load and the capacity of expanding pressure, but also increase the outlet total pressure loss, and the stall angle becomes smaller. For the same inlet Mach number, the total pressure loss at the outlet decreases first and then increases with the increase of the incidence angle, and the total pressure loss at the angle of -4° is the smallest. At the same time, it is verified that the loss characteristics of inlet isentropic Mach number and incidence angle of the axial compressor cascade are similar. Besides, the influence of change of the inlet Mach number and the angle of incidence on the wall area is lager.

Key words： axial compressor; plane cascade; grid distribution; numerical simulation

参考文献

［1］BIOLLO R,BENINI E.Recent advances in transonic axial compressor aerodynamics［J］.Progress in Aerospace Sciences,2013,56:1-18.
［2］于兰兰,胡骏,屠宝锋,等.轴流压缩系统中主动抑制旋转失速的数值模拟［J］.航空动力学报,2010,25(1):92-101.
YU L L,HU J,TU B F, et al. Numerical simulation of active suppression of rotating stall in axial compression systems［J］.Journal of Aerospace Power,2010,25(1):92-101.(in Chinese)
［3］鞠鹏飞,宁方飞.跨声压气机近失速流动特征的数值模拟研究［J］.推进技术,2016,37(6)：1055-1064.
JU P F,NING F F.Numerical study of near-stall flow feature on transonic compressor［J］.Journal of Propulsion Technology,2016,37(6)：1055-1064.(in Chinese)
［4］CARTENS V, SCHMITT S. Comparison of theoretical and experimental data for an oscillating transonic compressor cascade［C］//ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition.［S.l.］:ASME,1999.
［5］郑丽,罗泽明.某型航空发动机压气机平面叶栅流场数值研究［J］.机械设计与制造工程,2015,44(9)：4-6.
ZHENG L,LUO Z M.Numerical simulation of flow field in the compressor cascade for aero-engine［J］.Machine Design and Manufacturing Engineering,2015,44(9):4-6.(in Chinese)
［6］张志斌,李新亮,沈孟育.平面压气机叶栅非定常流动的数值研究［J］.清华大学学报(自然科学版),2003,43(2):222-226.
ZHANG Z B,LI X L,SHEN M Y.Numerical study of the unsteady flow in a plane compressor cascade［J］. Journal of Tsinghua University(Science and Technology),2003,43(2):222-226.(in Chinese)
［7］刘宝杰,袁春香,于贤君.前缘形状对可控扩散叶型性能影响［J］.推进技术,2013,34(7):890-897.
LIU B J,YUAN C X,YU X J.Effects on leading-edge geometry on aerodynamic performance in controlled diffusion airfoil［J］.Journal of Propulsion Technology,2013,34(7):890-897.(in Chinese)
［8］赵志奇,刘宝,蔡乐.叶片前缘椭圆形状对压气机气动性能的影响［J］.汽轮机技术,2016,58(5):351-354.
ZHAO Z Q, LIU B,CAI L. Effect of leading-edge elliptical shape on aerodynamic performance of compressor［J］.Turbine Technology,2016,58(5)：351-354.(in Chinese)
［9］宋寅,顾春伟.叶片前缘形状对压气机气动性能的影响［J］.工程热物理学报,2013,34(6):1051-1054.
SONG Y,GU C W.Effect of leading edge shape on the aerodynamic performance of compressor［J］.Journal of Engineering Thermophysics,2013,34(6):1051-1054.(in Chinese)
［10］康顺.计算域对CFD模拟结果的影响［J］.工程热物理学报,2005,26(增1):57-60.
KANG S. Influence of computational domain on the CFD results［J］.Journal of Engineering Thermophysics, 2005,26(S1):57-60.(in Chinese)
［11］郭星辉,白俊强,黄琳.前缘网格分布对超临界机翼低速气动特性影响研究［J］.科学技术与工程,2012,12(5): 1069-1072.
GUO X H, BAI J Q,HUANG L. Research about the influence of leading edge grid distribution on low speed characteristics of supercritical wing［J］.Science Technology and Engineering,2012,12(5):1069-1072.(in Chinese)
［12］郭然,贾力平,樊小莉,等.NUMECA系列教程［M］.北京:机械工业出版社,2013:105-106.

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