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Study on Global Aerodynamic Shape Optimization of Transonic Compressor Blade

  • Yanhui Duan EMAIL logo , Zhaolin Fan , Wenhua Wu and Ti Chen
Published/Copyright: December 22, 2018
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Abstract

In this paper, global optimization design of a transonic compressor 3D blade (Rotor 37) has been carried out by a self-developed aerodynamic shape optimization (ASO) platform based on improved parallel synchronous particle swarm optimization (PSPSO). To improve the performance of PSPSO, coefficient of variation (COV) based attenuation method with new parameters is proposed and then validated by optimization tests. Flow field of blade is calculated by an in-house computational fluid dynamic (CFD) code called PMB3D-Turbo, which is validated by Rotor 37. Choosing Rotor 37 as the case, optimization object is to maximize the peak adiabatic efficiency, meanwhile constraining mass flow and total pressure ratio. The solutions show that, the ASO platform is effective to transonic compressor blade and variations of thickness distribution near the trailing edge can help improve the adiabatic efficiency of a transonic compressor blade.

PACS: 47.85.Gj

Nomenclature

L

variables should appear in first column with the description in second column, m

I

all variables should appear in italics

sr

two-letter abbreviations should appear in italics

rad

three-letter abbreviations should not appear in italics

Re

Reynolds number and similar abbreviations do not use italics

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Received: 2018-05-01
Accepted: 2018-06-03
Published Online: 2018-12-22
Published in Print: 2022-08-26

© 2018 Walter de Gruyter GmbH, Berlin/Boston

Articles in the same Issue

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  2. Editorial
  3. Study on Global Aerodynamic Shape Optimization of Transonic Compressor Blade
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