Compressor disc structural optimization for gas turbine engine

Abstract

Gas turbine engine compressor increases the pressure and temperature of the air stream through it before entering the combustion chamber. Due to the extreme in rotational speed and high temperature, the gas turbine engine compressor is subjected to a complex force system that causes different failures mode in the compressor disc. Therefore, the design and calculation of compressor discs always consist of very high requirements with the problem of reducing the volume and increasing the durability of the disc structure. This paper presents a computational method that optimizes the design of a compressor disc geometry that meets performance and durability parameters but has the lowest mass based on finite element method. The calculation program is implemented by software Abaqus 6.13, algorithms and analysis results are processed through the Python 3 programming language. A post-publication change was made to this article on 11 Jun 2020 to correct the pdf so that it matched the webpage.