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Method for controlling the conformity of the profile of a curved surface of a turbomachine element

A control method and consistent technology, applied in the direction of using mechanical devices, mechanical measuring devices, optical devices, etc., can solve the problems of inability to detect and reveal

Active Publication Date: 2019-04-26
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

But this method cannot detect and reveal all possible flaws in the cross-section of turbine elements, especially blades

Method used

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  • Method for controlling the conformity of the profile of a curved surface of a turbomachine element
  • Method for controlling the conformity of the profile of a curved surface of a turbomachine element
  • Method for controlling the conformity of the profile of a curved surface of a turbomachine element

Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0075] image 3 A method of controlling the conformity of the cross-sectional profile of the leading and / or trailing edge of a turbine blade 2 is shown.

[0076] The control method includes the following steps:

[0077] - Step 100 : Acquiring the coordinates of a plurality of measurement points of a section of the leading and / or trailing edge of the blade 2 in a frame of reference defined for said section;

[0078] - Step 200: From the coordinates of these measurement points P, calculate the radius of curvature of the blade 2 at each of these points to obtain a measurement of the radius of curvature from the position of the measurement points P along the section along the leading and / or trailing edge The evolution curve Cm of

[0079] - step 300 : comparing the measured evolution curve Cm of the radius of curvature obtained in the calculation step 200 with a predetermined theoretical evolution curve Ct of the radius of curvature of the section of the blade 2 ;

[0080] - St...

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PUM

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Abstract

The invention relates to a method for controlling the conformity of a profile of a section of a curved surface of a turbomachine element, comprising the following step: (100) acquiring coordinates ofa plurality of measurement points of the section in a frame of reference defined for said section; characterised in that the method comprises the following steps: (200) calculating, based on the coordinates of these measurement points, the radius of curvature of the section at each of these points, in order to obtain a measured evolution curve of the radius of curvature according to the position of the measurement points along said section; (300) comparing the measured evolution curve of the radius of curvature, obtained in the preceding step, with a theoretical evolution curve of the radius of curvature of the predetermined section; (400) evaluating the conformity of the section based on the comparison carried out in the preceding step.

Description

technical field [0001] The present invention relates to a method of controlling the conformity of the profile of a curved section of a turbomachine element, such as that of a turbine blade for an aircraft, to verify that the section of the curved surface of said element complies with the manufacturing specifications set during the design of said element. standard. [0002] Therefore, the present invention may particularly relate to a method of controlling the conformity of the radial profile of the leading and / or trailing edge of a blade to verify that the shape of the leading and / or trailing edge of the blade complies perfectly with the shape set during the design of the blade. manufacturing standards. Background technique [0003] During the manufacture of curved surfaces for turbine elements, it is known to control the conformity of the cross-sectional profile of the curved surfaces in order to verify that the element complies with the manufacturing criteria set during t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01B11/00G01B11/24
CPCG01B11/002G01B11/24G01B5/205G01B21/20G01B5/213G01B5/008
Inventor 多米尼克·莫里斯·杰拉德·贝尼翁安托万·贝尔森
Owner SAFRAN AIRCRAFT ENGINES SAS