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Method for checking the position of a preform in a mold

A technology of preforms and molds, which can be applied to household appliances, household components, and other household appliances, etc., and can solve the problems of not being able to apply two-part molds and high costs

Active Publication Date: 2019-12-24
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This technique cannot be applied to two-part molds when the laser beam is positioned above the tool, moreover, the technique is extremely costly

Method used

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  • Method for checking the position of a preform in a mold
  • Method for checking the position of a preform in a mold
  • Method for checking the position of a preform in a mold

Examples

Experimental program
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Effect test

Embodiment Construction

[0046] figure 1 A method according to the prior art for producing a turbine engine blade from composite material is shown. The method comprises a first step during which, as figure 2 As shown, the preform is produced by three-dimensional yarn weaving (not shown). This preform 10 has a corresponding figure 1 The general vertical orientation of the horizontal orientation.

[0047] The preform 10 is produced by weaving a single piece, usually made of carbon fibre, the preform 10 basically comprises a blade root part 12 and a blade vane part 14, the blade root part 12 is used to secure the attachment of the final blade to the turbine engine rotor The disk, blade vane member 14 is intended to cooperate with the flow or gas inside the turbine engine.

[0048] In a second step of the method, the preform 10 is placed on the lower part 16 of the mold 18, e.g. figure 1 as shown in . The lower part 16 comprises a recess 20 which substantially matches the lower part 21 of the prefo...

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PUM

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Abstract

The invention relates to a method for manufacturing a turbine blade from a preform (10) made of composite material polymerized in a mold comprising a lower part (16) and an upper part, the method involving at least A closing step, during said at least one closing step, urging the upper part of the mold closer to the lower part (16) of the mold accommodating the preform (10). The method involves at least one sub-step of inserting a position marker (28) into the preform (10) prior to said closing step; using an insert (34) intended to be accommodated in the upper part of the mold (18) ) at least one substep of compressing the preform; and at least one substep of checking the position of the marker (28) relative to the frame of reference (30) of the insert (34).

Description

technical field [0001] The field of the invention is that of manufacturing gas turbine engines, such as turbine engines, in particular turbine engines for propelling aircraft. [0002] More specifically, the invention relates to a method for manufacturing a turbine engine blade from composite material, a preform for forming a turbine engine blade and a mold for performing such a method. Background technique [0003] Turbine engine blades typically have a root and buckets, the root including sloped sides that connect to the blade and serve to form a support surface in the rotor disk assembly chamber. The blades are usually manufactured from lightweight materials to help reduce the weight of the turbine engine and limit the inertia of the rotor to which the blades belong. [0004] Turbine engine blades also experience particularly high stresses at their roots, especially on the support surfaces. In fact, in the region radially outside the blade, the forces exerted by the bla...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/68B29C70/48B29C70/54B29B11/16B29L31/08
CPCB29B11/16B29C70/48B29C70/54B29C70/681B29L2031/085B29C70/545B29C33/306B29C2793/009B29L2031/08B29C33/12B29C70/541B29K2713/00B29L2031/082D03D1/00F01D5/282F05D2230/20F05D2300/6034
Inventor 马克·以马内利·泰彻尼古拉斯·艾史塔瑞
Owner SAFRAN AIRCRAFT ENGINES SAS