High-low cycle complex fatigue test clamp for mortise-joint structure of small blade of turbine

Abstract

The invention relates to a high-low cycle complex fatigue test clamp for a mortise-joint structure of a small blade of a turbine on an aeroengine. By adoption of the high-low cycle complex fatigue test clamp, synchronous loading of longitudinal low-cycle large load, horizontal high-cycle vibration load and heat load in test of the mortise-joint structure of the small blade of the turbine is realized. The high-low cycle complex fatigue test clamp is characterized in that a top holding structure is clamped on a fatigue machine, and a turbine disc is fixed by a clamping bolt; the turbine disc isconnected with the turbine blade in a mortise-joint manner; a small blade clamp clamps a blade body of the turbine blade by means of frictional force; the bottom part of the small blade clamp is tightly screwed with a high-cycle excitation rod by a bolt, and the top part of the small blade clamp is in clearance fit with a force-transmission top plate by a shaft-hole structure; the force-transmission top plate is in clearance fit with force-transmission pulling plates by shaft-hole structures, the stability of the structure is maintained by fixed long bolts; the force-transmission pulling plates are tightly screwed with a low-cycle force applying structure by nuts; the lower part of the low-cycle force applying structure is clamped by the fatigue machine; the fatigue machine applies the low-cycle load, the excitation rod is externally connected with an exciter to apply the high-cycle load, and the mortise-joint position is externally connected with an induction heating copper coil to apply the heat load. The high-low cycle complex fatigue test clamp has the beneficial effects that stable clamping of the mortise-joint structure of the small blade of the turbine can be met, and the high-low cycle compounding fatigue under the high-temperature condition can be realized.

Description

technical field [0001] The present invention is a loading technology for the high-low cycle composite fatigue test of the mortise joint structure of the turbine blades of the aero-engine. The thermal load loading technology belongs to the technical field of aerospace engines. 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 turbosha...

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 the mortise joint structure of the small turbine blades, which overcomes the difficulty that the tenon joint structure of the turbine blades is simultaneously loaded with a lateral high cycle load under the condition of bearing a low cycle large load, As well as the problems of slippage and uneven stress distribution of small blade blades, it can meet the effective and stable application of various loads, and can carry out high and low cycle composite fatigue tests of small turbine blade tenon joints

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