Test piece configuration method for overrun fracture test of aero-engine rotor

Abstract

The invention provides a test piece configuration method for an overrun fracture test of an aero-engine rotor. The test piece configuration method comprises the following steps of: S1, carrying out overrun analysis on a rotor assembly of an aero-engine, S2, determining a minimum fracture margin wheel disc in the rotor assembly, S3, constructing a preliminary design scheme of the test piece configuration, S4, performing overrun fracture analysis on the configuration of the test piece, S5, judging whether the test piece configuration design meets criterion requirements or not, S6, determining the configuration of the test piece, S7, finishing processing and assembling of the test piece, and S8, determining the fracture rotating speed of the rotor part. The method is based on an extreme strain method, does not contain any coefficient and factor, is simple and direct in test verification, and can save a large amount of test expenditure and time. Therefore, the fracture starting position ofthe rotor can be predicted accurately, the worst combination within the position tolerance range can be directly selected as the worst size of the fracture, the operability is high, a theoretical basis is provided, and the method is suitable for being applied to the engineering development process.

Description

technical field [0001] The invention relates to the field of aero-engines, in particular to a test piece configuration method for an over-rotation rupture test of an aero-engine rotor. Background technique [0002] The aeroengine rotor is one of the main load-bearing parts of civil aeroengines. It has been working under severe working conditions such as high temperature (up to 650°C) and high speed (3000-17000r / min) for a long time. For the design of the aero-engine rotor, in addition to meeting the requirements of static strength, low-cycle fatigue life, and high-cycle fatigue life, it must also meet the over-rotation requirements of the airworthiness clause CCAR33. The block will penetrate the casing, and may hit the engine pipeline, fuel tank, etc., or even hit the cabin, which will seriously endanger flight safety. [0003] The overrotation airworthiness AC document CFR 33.27AC No.33.27-1 requires: "It must be determined through analysis or test methods (1) to determine...

AI Technical Summary

Problems solved by technology

[0014] The technical problem to be solved by the present invention is to provide a test piece structure for the over-rotation rupture test of the aero-engine rotor in order to overcome the time-consuming and labor-intensive rotor over-rotation rupture test in the prior art and the inability to accurately evaluate the quality of the test piece design. type method

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