Topological optimization method for constraining and damping blades of aeroengine

An aero-engine, restrained damping technology, applied in instruments, calculations, electrical and digital data processing, etc., can solve the problems of increasing additional mass, unfavorable lightweight of aero-engines, etc., to achieve the best damping and vibration reduction effect, and improve the resistance to fatigue damage. Ability, the effect of small vibration stress

Inactive Publication Date: 2015-04-29
AECC SHENYANG ENGINE RES INST +1
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Problems solved by technology

[0003] Traditional constrained damping generally covers the surface of the structure to be treated. Although it can effectively

Method used

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  • Topological optimization method for constraining and damping blades of aeroengine
  • Topological optimization method for constraining and damping blades of aeroengine
  • Topological optimization method for constraining and damping blades of aeroengine

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Embodiment 1

[0028] This embodiment provides a topology optimization method for constrained damping aeroengine blades, which is characterized in that: the topology optimization method for constrained damping aeroengine blades uses lightweight aluminum foil as the constraining material, which is sequentially pasted on the surface of the aeroengine blades Viscoelastic material and constrained material, conduct constrained damping treatment on blades, and establish finite element model of constrained damped blades;

[0029] Determine the target order of optimization and the amount of constrained damping material used, and establish a topology optimization model for constrained damping blades:

[0030] find : x i , i = 1,2 . . . n ...

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Abstract

The invention relates to a topological optimization method for constraining and damping blades of an aeroengine. The method comprises the following steps: taking lightweight aluminum foil as a constraining material, sequentially sticking a viscoelastic material and the constraining material onto the surface of each blade of the aeroengine, carrying out constraining and damping processing on the blades, and establishing finite element models of the constrained and damped blades; carrying out modal analysis on the constrained and damped blades according to the finite element models of the constrained and damped blades, and filtering sensitivity of constrained and damped cell units by adopting an independent grid filtering technology; solving an optimization model by adopting an asymptotic optimization algorithm, programming an optimization program, searching for the optimal layout of a constraining and damping material on each blade, and cutting and regularizing optimized layout, so as to adapt to engineering application. The method has the advantages that the aim of achieving the maximal aeroengine blade damping vibration reduction effect with the minimal damping material additionally-added amount is realized, so that the vibration stress of the blades of the aeroengine is remarkably lowered, and the fatigue damage resistance of the blades is improved.

Description

technical field [0001] The invention relates to a constrained damping structure optimization design method, in particular to a topology optimization method for constrained damping aeroengine blades. Background technique [0002] The structural integrity of the aero-engine blade is the key to the safety of the aero-engine operation. With the increase of the thrust-to-weight ratio of the aero-engine, the vibration stress of the blade increases, and the problem of fatigue damage becomes more and more prominent. At present, damping shrouds or dry friction damping are mostly used to increase blade damping and reduce blade vibration stress. Constrained damping structure, as a structural form that effectively increases damping, has the characteristics of simple and efficient processing. [0003] Traditional constrained damping generally covers the surface of the structure to be treated. Although it can effectively increase the structural damping, it greatly increases the additiona...

Claims

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Application Information

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IPC IPC(8): G06F17/50
Inventor 李成刚郑玲房占鹏王延军宁智毅
Owner AECC SHENYANG ENGINE RES INST
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