Abstract
The thermal shock load has an important effect on the stability of thin-walled blades under high-speed operation of aircraft engines. According to the actual working conditions, the linear interpolation distribution of blade temperature is obtained by the numerical fitting method. A thermal buckling model is built to obtain the linear and nonlinear modal response of the blade through the finite element method. The results show that the blade stiffness changes under the influence of thermal buckling and the obvious torsional deformations are produced along the radial direction of the blade. Meanwhile, the largest deformation of about 1.3 mm and stress of 81 Mpa occurs on the blade tip for both the linear and nonlinear response. The buckling stress distribution and critical load factor of thermal buckling are also calculated, consistent with the rubbing part of blade. The changing radial length is the main reason for the distance reduction between the blade and casing, causing more probability of friction impact. Therefore, reasonable local thermal buckling technology is helpful to improve the design level of thermal-shock loaded blades.
Highlights
When the aircraft engine operates in a high speed and temperature environment, the blades are prone to structural bending and thermal deformation and can even evolve into a rubbing fault between the blade and casing
It is agreed that the local thermal buckling deformation of high temperature plate and shell components has become one of the main failure modes under a large temperature gradient
In order to carry out thermal buckling analysis, the thermal distribution needs to be loaded first to solve the thermal stress
Summary
The rotating blades are widely used in aerospace fields owing to their lightweight, high specific strength properties, bending and reverse characteristics, and so on. The rotating blade is a plate and shell structure It has many advantages, it is easy to cause vibration, buckling instability and fatigue cracking [2]. For this high-temperature plate and shell structure under a mechanical/thermal load environment, when the structural size and temperature load increases, only static analysis cannot meet the needs of engineering design. It should be comprehensively considered from the dynamic design of plate and shell to determine the complete anti-fatigue fracture position of the blade under complex deformation. By obtaining the critical load and the form of instability of thermal buckling blades, it has great significance to reduce the damage from thermal–structural coupled vibration
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