Optimal Design System and Method for High Pressure Turbine Disk of Aeroengine Based on Particle Swarm

Abstract

The invention provides an aero-engine high pressure turbine disc optimization design system based on particle swarm and method, and relates to a design technology field of the aero-engine. The system comprises a definition module of the optimization task of the aero-engine high pressure turbine disc, a primary particle swarm / file and a grid generation module, a global optimum selection module based on a gridding neighborhood, a particle update module, a file update module and a file size control module based on the gridding neighborhood, first the gridding jam index precision is improved by using active volume of file in gridding, then the particle jam distance is calculated in the finite region by using the gridding neighborhood message, the confidence level operand is provided for selecting the global optimum and deleting the file particle, the obtained ultimately file is the result of a plurality of the target optimization. During designing a plurality of the target optimization for the aero-engine high pressure turbine disc, starting from increasing precision of the global optimum in particle swarm optimization and of the non-particle deleting, the system and method provides the high-quality result of a plurality of the target optimization.

Description

technical field [0001] The invention relates to the technical field of aero-engine design, in particular to a particle swarm-based high-pressure turbine disc optimization design system and method for an aero-engine. Background technique [0002] The high-pressure turbine is the most important and expensive component of a modern aero-engine system. The high-pressure turbine disk is several times the mass of the low-pressure turbine disk, which affects the efficiency, stability, service life and performance of the engine. The weight reduction of the high-pressure turbine disk has always been the primary concern of designers. Thermal expansion and contraction as well as high-speed rotation lead to radial deformation of the high-pressure turbine disk, resulting in tip clearance management problems: too loose tip clearance increases gas leakage at the tip, and too tight tip clearance causes blade and machine friction between the casings, so many commercial aircraft engines use a...

AI Technical Summary

Problems solved by technology

Thermal expansion and contraction as well as high-speed rotation lead to radial deformation of the high-pressure turbine disk, resulting in tip clearance management problems: too loose tip clearance increases gas leakage at the tip, and too tight tip clearance causes blade and machine friction between the casings, so many commercial aircraft engines use active thermal control technology to manage this gap

However, this simplification has the following defects: 1) The calculation granularity of the grid congestion degree is too large, which cannot reflect the distribution characteristics of the archives in each grid, and there is a large gap between the grid positioning results and the actual distribution of each particle in the archives

2) Randomly deleting non-inferior solutions in the second step may lead to uneven distribution of the frontier and easy loss of non-inferior solutions at the border

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