High-low-cycle complex fatigue test clamp of turbine joggle joint structure

Abstract

The invention relates to a high-low-cycle complex fatigue test clamp of an aero-engine turbine joggle joint structure. A fatigue machine clamps the lower end of a mortise clamp and fixes a mortise test piece through bolts; the mortise test piece is connected with a tenon test piece through tenon teeth and limited to slide in the mortise direction of the mortise through a limiting baffle; a tenon clamp clamps a tenon test piece clamping part through a double-wedged surface; the upper portion of the tenon clamp is connected with a force transmission pull rod through threads; three threaded holesare formed in the force transmission pull rod, high-cycle vibration excitation rods are screwed in the threaded holes, and the upper portion of the force transmission pull rod is in clearance fit with a roller transmission shaft through a shaft hole structure; the two ends of the roller transmission shaft are symmetrically provided with a pair of ball bearings to form a roller structure, the rollers move along two guide grooves in an installation box, and the constraint of the high-cycle load application direction is released; the top end of the installation box is clamped by the fatigue machine; a low-cycle load is applied by the fatigue machine, the excitation rods are externally connected with a vibration exciter to apply a high-cycle load, and the joggle joint position is externally connected with an electric induction heating copper coil to apply a heat load.

Description

technical field [0001] The invention belongs to the technical field of aerospace engines, and in particular relates to a high-low cycle composite fatigue test fixture with a turbine tenon joint structure. Background technique [0002] Aeroengine is an extreme product. Engine turbine blades and turbine disks work under complex load environments such as high temperature, high pressure, and high speed. The high-low cycle composite fatigue failure of the turbine tenon joint structure is the main failure mode of the tenon joint structure. In order to conduct in-depth research on the high-low cycle composite fatigue life of the tenon joint structure, a large number of composite fatigue tests on the tenon joint structure of the turbine are required, and the experimental research on the tenon joint structure of the turbine blades of the turboshaft engine is also a crucial task. Due to the small size of turboshaft engine turbine blades, usually less than 70 mm, and complex profiles, ...

AI Technical Summary

Problems solved by technology

[0006] The technical problem to be solved by the present invention is to provide a high-low-cycle composite fatigue test fixture for a turbine tenon joint structure, which overcomes the difficulty that the turbine tenon joint structure is simultaneously loaded with a lateral high-cycle load under the condition of a low-cycle heavy load, and the blade directly The clamping is prone to slippage and uneven stress distribution, which can meet the effective and stable application of various loads, and can carry out the high-low cycle composite fatigue test of the turbine tenon joint

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