Aerodynamic Optimization Design Investigation for Rotor Blade in a 1.5-stage Compressor

Huan Long Chen; Hua Ping Liu; Lin Xi Li

Aerodynamic Optimization Design Investigation for Rotor Blade in a 1.5-stage Compressor

Huan Long Chen
, Hua Ping Liu^*
, Lin Xi Li

^*Corresponding author for this work

School of Energy Science and Engineering, Harbin Institute of Technology

Research output: Contribution to journal › Article › peer-review

1 Scopus citations

Abstract

On the flow instability caused by the boundary-layer flow separation due to the shock wave and the low-energy fluid accumulation in the corner area for the transonic compressor passage, based on the optimization design concepts of matching flow between blade rows and control the camber line curvature, a rotor blade is optimized for a 1.5-stage compressor in the E³. The results indicates that the aerodynamic optimization design technique based on the curvature control method for camber line can skillfully reduce the number of optimization variables and effectively improve the aerodynamic performance of the compressor blade passage at design and off-design points.

Original language	English
Pages (from-to)	740-747
Number of pages	8
Journal	Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics
Volume	38
Issue number	4
State	Published - 1 Apr 2017
Externally published	Yes

Keywords

Boundary-layer
Compressor
Optimized design
Shock wave
Stall margin

Cite this

@article{1281d23e65f340838b6033c59ce570d3,

title = "Aerodynamic Optimization Design Investigation for Rotor Blade in a 1.5-stage Compressor",

abstract = "On the flow instability caused by the boundary-layer flow separation due to the shock wave and the low-energy fluid accumulation in the corner area for the transonic compressor passage, based on the optimization design concepts of matching flow between blade rows and control the camber line curvature, a rotor blade is optimized for a 1.5-stage compressor in the E3. The results indicates that the aerodynamic optimization design technique based on the curvature control method for camber line can skillfully reduce the number of optimization variables and effectively improve the aerodynamic performance of the compressor blade passage at design and off-design points.",

keywords = "Boundary-layer, Compressor, Optimized design, Shock wave, Stall margin",

author = "Chen, \{Huan Long\} and Liu, \{Hua Ping\} and Li, \{Lin Xi\}",

year = "2017",

month = apr,

day = "1",

language = "英语",

volume = "38",

pages = "740--747",

journal = "Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics",

issn = "0253-231X",

publisher = "Science Press ",

number = "4",

}

TY - JOUR

T1 - Aerodynamic Optimization Design Investigation for Rotor Blade in a 1.5-stage Compressor

AU - Chen, Huan Long

AU - Liu, Hua Ping

AU - Li, Lin Xi

PY - 2017/4/1

Y1 - 2017/4/1

N2 - On the flow instability caused by the boundary-layer flow separation due to the shock wave and the low-energy fluid accumulation in the corner area for the transonic compressor passage, based on the optimization design concepts of matching flow between blade rows and control the camber line curvature, a rotor blade is optimized for a 1.5-stage compressor in the E3. The results indicates that the aerodynamic optimization design technique based on the curvature control method for camber line can skillfully reduce the number of optimization variables and effectively improve the aerodynamic performance of the compressor blade passage at design and off-design points.

AB - On the flow instability caused by the boundary-layer flow separation due to the shock wave and the low-energy fluid accumulation in the corner area for the transonic compressor passage, based on the optimization design concepts of matching flow between blade rows and control the camber line curvature, a rotor blade is optimized for a 1.5-stage compressor in the E3. The results indicates that the aerodynamic optimization design technique based on the curvature control method for camber line can skillfully reduce the number of optimization variables and effectively improve the aerodynamic performance of the compressor blade passage at design and off-design points.

KW - Boundary-layer

KW - Compressor

KW - Optimized design

KW - Shock wave

KW - Stall margin

UR - https://www.scopus.com/pages/publications/85021250973

M3 - 文章

AN - SCOPUS:85021250973

SN - 0253-231X

VL - 38

SP - 740

EP - 747

JO - Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics

JF - Kung Cheng Je Wu Li Hsueh Pao/Journal of Engineering Thermophysics

IS - 4

ER -

Aerodynamic Optimization Design Investigation for Rotor Blade in a 1.5-stage Compressor

Abstract

Keywords

Other files and links

Fingerprint

Cite this