Fatigue performance assessment clamp structure for thickness-adjustable blade of aero-engine

Abstract

The invention relates to an aero-engine blade clamp, in particular to a fatigue performance assessment clamp structure for a thickness-adjustable blade of an aero-engine. No right-angle step is arranged between the large shaft diameter of the thickness-adjustable blade and a margin plate, and the diameter of the large shaft diameter is increased to be the same as that of the margin plate. The clamp divides a whole pressing block into an upper pressing block and a lower pressing block, two sets of positioning pins are additionally arranged between the upper pressing block and the lower pressingblock for limiting and positioning, semicircular grooves are formed in the upper pressing block and the lower pressing block correspondingly, and large shaft diameters of truncated blades are engagedafter the upper pressing block and the lower pressing block are buckled up and down. According to the fatigue performance assessment clamp structure for the thickness-adjustable blade of the aero-engine, through the improvement of the blade shaft diameter of the thickness-adjustable blade and the clamp, the blade fatigue assessment test research work is smoothly completed, a large amount of precious time is saved for the blade development, and an important basis is provided for the long-term test of the blade installation.

Description

technical field [0001] The invention relates to an aeroengine blade fixture, in particular to a fixture structure for evaluating the fatigue performance of an aeroengine blade with adjustable thickness. Background technique [0002] In the development process of an engine blade, in order to assess the fatigue performance of the blade and estimate the fatigue reserve of the blade, the fatigue performance assessment test research work was carried out. However, during the test, continuous fractures occurred at the connection between the shaft diameter and the edge plate, which made the test impossible. Solving the fracture problem at the shaft diameter is the technical key to whether the fatigue test can be passed, and it is also an important factor to ensure the smooth installation and long-term test of the blade. The shaft diameter at both ends of the thickness-adjustable blade is thinner, the weight of the blade body is heavier, and the shaft diameter is the installation pl...

AI Technical Summary

Problems solved by technology

However, during the vibration fatigue test, the blade bears a large alternating load, there are stress concentration and shear stress at the joint between the shaft diameter and the flange plate, and fretting wear occurs between the shaft diameter and the pressure block. Micro-cracks in the joints of the plates eventually lead to fractures such as Figure 5 shown

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