不同造型方法下鼓包参数对跨声速压气机叶栅性能的影响

胡义; 韩吉昂; 钱薪伟; 丁小娟; 钟兢军

doi:10.16411/j.cnki.issn1006-7736.2021.02.010

大连海事大学学报 >

2021 , Vol. 47 >Issue 2: 83 - 96

DOI: https://doi.org/10.16411/j.cnki.issn1006-7736.2021.02.010

船舶与海洋工程

不同造型方法下鼓包参数对跨声速压气机叶栅性能的影响

胡义 ,
韩吉昂 ,
钱薪伟 ,
丁小娟 ,
钟兢军

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（1. 大连海事大学船舶与海洋工程学院辽宁大连 116026；2. 上海海事大学商船学院,上海 201306）

胡义（1994 — ），男，硕士生，E-mail：hy12280410@163.com.

收稿日期: 2021-01-02

修回日期: 2021-02-03

网络出版日期: 2021-02-03

基金资助

国家自然科学基金资助项目（51406022;51436002）；辽宁省高等学校创新团队资助项目（LT2015004）.

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Influence of bump parameters on the performance of a transonic compressor cascade under different bump configuration method

HU Yi ,
HAN Ji-ang ,
QIAN Xin-wei ,
DING Xiao-juan ,
ZHONG Jing-jun

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(1. Naval Architecture and Ocean Engineering College,Dalian Maritime University, Dalian 116026, China;2. Merchant Marine College, Shanghai Maritime University, Shanghai 201306, China)

Received date: 2021-01-02

Revised date: 2021-02-03

Online published: 2021-02-03

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摘要

为探究鼓包造型方法及鼓包参数对跨声速平面叶栅气动性能的影响，利用HicksHenne函数、CST参数化方法、Parsec描形方法以及多项插值函数分别构造鼓包，并采用数值模拟方法对具有不同造型方法及参数构造鼓包的跨声速压气机平面叶栅进行仿真研究.结果表明：随着鼓包起始安装λ置的后移，由不同造型方法构造鼓包的叶栅前缘激波形状均逐渐由“λ”激波转变为“X”形激波；但造型方法和鼓包高度不同时，叶栅前缘激波形状会在“λ”激波和“X”形激波之间转换.采用CST参数化方法构造鼓包时，鼓包最佳起始安装λ置应选择为0.475倍弦长；而采用其他三种造型方法构造鼓包时，鼓包的起始安装λ置建议选择为0.525倍弦长.采用多项式差值函数构造鼓包时，鼓包高度宜选为0.01倍弦长；而采用其他三种造型方法构造鼓包时，其鼓包高度建议选为0.0125倍弦长.采用CST参数化方法构造鼓包时，鼓包长度建议选为0.3倍弦长；而采用其他三种造型方法构造鼓包时，其鼓包长度建议选为0.4倍弦长.

关键词： 跨声速压气机; 平面叶栅; 造型方法; 鼓包参数; 气动性能; 数值模拟

本文引用格式

胡义 , 韩吉昂 , 钱薪伟 , 丁小娟 , 钟兢军 . 不同造型方法下鼓包参数对跨声速压气机叶栅性能的影响[J]. 大连海事大学学报, 2021 , 47(2) : 83 -96 . DOI: 10.16411/j.cnki.issn1006-7736.2021.02.010

Abstract

In order to investigate the effect of bump configuration methods and parameters of the bump on the aerodynamic performance of transonic compressor linear cascade, the HicksHenne function, the CST parametric method, the Parsec tracing method and the polynomial interpolation function were adopted to construct the bump respectively, and numerical simulation of the linear cascade of transonic compressor with different configuration methods and parameters of the bump were carried out. The calculation results show that the blade leading edge shock shape with different configuration methods gradually changes from “λ” shock to “X” shock as the initial installation position of the bump moves backward, but the blade leading edge shock shape will change between the “λ” shock and the “X” shock when the configuration method and the height of the bump are different. When the CST parametric method is employed to construct the bump, the best initial installation position of the bump should be 0.475 times the chord length. While the other three configuration methods are used, the initial installation position of the bump is suggest to be 0.525 times the chord length. When using polynomial interpolation function to construct the bump, the height of the bump should be 0.01 times the chord length, when the other three configuration methods are adopted, the height of the bump should be 0.0125 times the chord length. When using CST parametric method to construct the bump, the length of the bump should be 0.3 times the chord length, when the other three configuration methods are adopted, the length of the bump should be 0.4 times the chord length.

Key words： transonic compressor; planar cascade; configuration method; bump parameters; aerodynamic performance; numerical simulation

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