Applications of numerical optimization techniques to design of axial compressor blades

Choon-Man Jang; Kwang-Yong Kim

Chinese

您当前的位置：

首页 >

文章列表页 >

Applications of numerical optimization techniques to design of axial compressor blades

研究论文 | 更新时间：2026-07-07

- Applications of numerical optimization techniques to design of axial compressor blades
- Applications of numerical optimization techniques to design of axial compressor blades
- 航空动力学报 2007年22卷第4期
- 作者机构：
  
  1. Fire and Engineering Services Research Department, KICT,.of,Rep,Korea
  2. Department of Mechanical Engineering, Inha University,.of,Rep,Korea
- 作者简介：
- 基金信息：
- DOI：
  中图分类号：
- 纸质出版：2007
- 稿件说明：
移动端阅览
Choon-Man Jang, Kwang-Yong Kim. Applications of numerical optimization techniques to design of axial compressor blades[J]. 航空动力学报, 2007,22(4).

Choon-Man Jang, Kwang-Yong Kim. Applications of numerical optimization techniques to design of axial compressor blades[J]. 2007, 22(4).
Choon-Man Jang, Kwang-Yong Kim. Applications of numerical optimization techniques to design of axial compressor blades[J]. 航空动力学报, 2007,22(4). DOI：

Choon-Man Jang, Kwang-Yong Kim. Applications of numerical optimization techniques to design of axial compressor blades[J]. 2007, 22(4). DOI：

摘要

This paper describes the shape optimization of NASA rotor 37 and rotor and stator blades in a single-stage transonic axial compressor.Shape optimization of the blades operating at the design flow condition has been performed using the response surface method and three-dimensional Navier-Stokes analysis.Thin-layer approximation is introduced to the Navier-Stokes equations

and an explicit Runge-Kutta scheme is used to solve the governing equations.The three design variables

blade sweep

lean and skew

are introduced to optimize the three-dimensional stacking line of the blades.The objective function of the shape optimization is an adiabatic efficiency.Throughout the optimization of rotor and stator blades

optimal blade shape can be obtained.It is noted the increase of adiabatic efficiency by optimization of the blade shape with the stacking line in the single-stage transonic axial compressor is more effective in a rotor blade rather than a stator blade because of the large deformation of blade shape in the stator blade.

Abstract

and an explicit Runge-Kutta scheme is used to solve the governing equations.The three design variables

blade sweep

lean and skew

关键词

Keywords

references

浏览量

482

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

Influences of meridional flowpath on the performance of swept blade in an axial compressor stage

发动机零部件稳态应力计算的状态函数法

Hybrid system-a promising way solving future energy problems

LES of film cooling for different jet fluids

与发动机匹配的旁路式双喉道气动矢量喷管数值模拟研究