Test piece configuration method for overrotation rupture test of aeroengine rotors

An aero-engine and rupture test technology, applied in the field of aero-engine, can solve the problems of time-consuming and labor-intensive, inability to accurately evaluate the quality of the test piece design, etc., and achieve the effect of simple test verification, large-scale engineering application significance, and strong operability.

Active Publication Date: 2021-08-03
AECC COMML AIRCRAFT ENGINE CO LTD
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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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  • Test piece configuration method for overrotation rupture test of aeroengine rotors
  • Test piece configuration method for overrotation rupture test of aeroengine rotors
  • Test piece configuration method for overrotation rupture test of aeroengine rotors

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[0054] In order to make the above objects, features and advantages of the present invention more comprehensible, specific implementations of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0055] Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same numbers will be used throughout the drawings to refer to the same or like parts.

[0056] In addition, although the terms used in the present invention are selected from well-known and commonly used terms, some terms mentioned in the description of the present invention may be selected by the applicant according to his or her judgment, and the detailed meanings thereof are set forth herein described in the relevant section of the description. ...

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Abstract

The invention provides a test piece configuration method of an over-rotating rupture test of an aero-engine rotor, which comprises the following steps: S 1 , Carry out overrotation analysis on the rotor assembly of the aero-engine; S 2 , determining the minimum fracture margin disc in the rotor assembly; S 3 , Construct the preliminary design scheme of the configuration of the test piece; S 4 , carrying out super-rotational rupture analysis to described test piece configuration; S 5 , judging whether the configuration design of the test piece meets the criterion requirements; S 6 , Determine the configuration of the test piece; S 7 , Complete the processing and assembly of the test piece; S 8 , Determining the rupture speed of the rotor components. The present invention is based on the ultimate strain method, does not contain any coefficients and factors, the test verification is simple and direct, and can save a lot of test funds and time. The starting position of the rotor crack can be accurately predicted, so the most unfavorable combination within the tolerance range of the position can be directly selected as the most unfavorable size of the crack. It has strong operability, has a theoretical basis, and is suitable for application in 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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M13/02G01M13/025
CPCG01M13/02G01M13/025
Inventor 齐晓东陈国光
Owner AECC COMML AIRCRAFT ENGINE CO LTD
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