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Method of element-level strength test for cantilever beams of fan blades

A fan blade and strength test technology, which is applied in the direction of strength characteristics, testing of mechanical components, testing of machine/structural components, etc., can solve the problem that the performance of composite fan blades is greatly affected by the process, so as to reduce the test cost and reduce the The effect of R&D cost and short test cycle

Active Publication Date: 2021-05-11
AECC SHANGHAI COMML AIRCRAFT ENGINE MFG CO LTD +1
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  • Abstract
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  • Claims
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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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  • Method of element-level strength test for cantilever beams of fan blades
  • Method of element-level strength test for cantilever beams of fan blades
  • Method of element-level strength test for cantilever beams of fan blades

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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, which is based on a pyramid test verification strategy, obtains the local strength performance of the fan blade and identifies the design weak points of the fan blade, and supports the part-level test of the fan blade, including the following steps: S 1 , determining a sampling position on the fan blade to obtain a component-level test piece, the sampling position is located at the leading edge and the trailing edge of the fan blade; S 2 , Determine the size of the test piece; S 3 , carry out the sampling of described test piece to described fan blade; S 4 1. The fixed end of the test piece is clamped by the fixture, and the other end is cyclically loaded and unloaded by the loading head until the test piece is destroyed. The invention has strong pertinence and can adapt to the local characteristics of the fan blades made of composite materials. The purpose of the test verification is clear, and the stiffness and strength performance of the leading and trailing edges of the blade can be obtained, as well as the corresponding typical failure modes, which is conducive to identifying design weak points.

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 Patents(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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