Fan blade cantilever beam element-level strength test method

A technology of fan blade and strength test, applied in the direction of strength characteristics, testing of mechanical parts, testing of machine/structural parts, etc., can solve the problem that the performance of composite fan blades is greatly affected by the process

Active Publication Date: 2021-03-19
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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  • Abstract
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  • Claims
  • Application Information

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Problems solved by technology

[0008] The technical problem to be solved by the present invention is to provide a cantilever beam element-level strength test method for fan blades in order to overcome the defects in the prior art that the fan blades of composite materials are anisotropic, and the performance of fan blades of composite materials is greatly affected by the process.

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  • Fan blade cantilever beam element-level strength test method
  • Fan blade cantilever beam element-level strength test method
  • Fan blade cantilever beam element-level strength test method

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Embodiment Construction

[0059] 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.

[0060] 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.

[0061] 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 fan blade cantilever beam element-level strength test method. Based on a pyramid test verification strategy, local strength performance of a fan blade is obtained, design weakpoints of the fan blade are recognized and a part level test of the fan blade is supported; the method comprises the following steps: S1, determining sampling positions on the fan blade, to obtain aelement-level test piece, wherein the sampling positions are located at the front edge and the tail edge of the fan blade; S2, determining the size of the test piece; S3, performing sampling of the test piece on the fan blade; and S4, clamping the fixed end of the test piece through a clamp, and circularly loading and unloading the other end of the test piece through a loading head until the testpiece is damaged. The method is high in pertinence and can adapt to local characteristics of the fan blade made of a composite material. Test verification aims are clear, rigidity, strength performance and corresponding typical damage forms of the front edge and the tail edge of the blade can be obtained, and weak points can be recognized and designed favourably.

Description

technical field [0001] The invention relates to the field of strength testing of aeroengine blades, in particular to a method for testing the strength of a fan blade cantilever beam element level. Background technique [0002] In the prior art, the aero-engine has two types of working blades, the rotor and the stator, and the blades perform work during the working process. Among them, the fan blade is located at the front end of the air inlet, which plays the role of air induction and thrust generation through high-speed rotation, and is mainly composed of a tenon and a blade body. Under normal working conditions, the fan blades are mainly subjected to aerodynamic loads and centrifugal loads, and the tenons transmit the loads on the blades to the fan disk. [0003] With the development of aero-engine technology towards lighter weight, higher reliability, and better economy, turbofan aero-engines with large bypass ratios have been widely used, and large-size fan blades have ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/32G01N3/36G01N3/04G01M13/00G01M15/00
CPCG01M13/00G01M15/00G01N3/04G01N3/32G01N3/36G01N2203/0044G01N2203/0067G01N2203/0658
Inventor 覃文源李继保王祯鑫贾林时起珍
Owner AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD
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