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Method of repairing composite component using support member

A technology of composite parts and supporting components, which is applied in the direction of household components, supporting components of blades, applications, etc., and can solve the problems of not replacing parts and expensive gas turbine parts

Pending Publication Date: 2022-06-07
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] However, gas turbine components formed from CMC materials can be very expensive
In this regard, when CMC gas turbine components become worn or damaged, repair rather than component replacement may be required

Method used

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  • Method of repairing composite component using support member
  • Method of repairing composite component using support member
  • Method of repairing composite component using support member

Examples

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Embodiment Construction

[0029] Reference will now be made in detail to the exemplary embodiments of the disclosed subject matter, one or more examples of which are illustrated in the accompanying drawings. The various examples are provided by way of illustration and should not be construed as limiting the present disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the disclosure. For example, features shown or described as part of one embodiment can be used with another embodiment to yield yet another embodiment. Accordingly, this disclosure is intended to cover such modifications and changes as come within the scope of the appended claims and their equivalents.

[0030] As used herein, the terms "first," "second," and "third" are used interchangeably to distinguish one element from another, and are not intended to denote the location or importance of an indi...

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PUM

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Abstract

A method for repairing a composite component includes positioning one or more repair fiber layers relative to a repair interface of the composite component such that a butt joint is formed at the repair interface between the one or more repair fiber layers and the composite component. Further, the method includes forming a cavity within the composite component such that the cavity extends through the repair interface. In addition, the method includes mounting a support member within the cavity. In this regard, the support member extends across the butt joint such that a first portion of the support member is positioned within the composite component and a second portion of the support member is positioned within the one or more layers of repair fibers.

Description

technical field [0001] The present disclosure relates generally to methods for repairing components, and more particularly, to methods for securing new composite materials to worn or damaged existing composite components. Background technique [0002] The use of unconventional high temperature materials such as ceramic matrix composite (CMC) materials in gas turbine engines has grown dramatically in recent years. Specifically, there has been considerable interest in replacing metal alloy components in the combustion and turbine sections of gas turbine engines with CMC components. CMC materials can withstand higher operating temperatures than metal alloys. In turn, higher operating temperatures increase the efficiency of gas turbine engines. Additionally, CMC parts require less cooling than metal parts. Additionally, CMC materials are lighter than metal components and can reduce structural requirements on the engine. [0003] However, gas turbine components formed from CM...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/00F01D25/00
CPCF01D5/005F01D25/005F01D25/00B29C73/04B29C73/10B29L2031/3076B29L2031/7504
Inventor 赫伯特·奇德西·罗伯茨西奥多·罗伯特·格罗斯曼
Owner GENERAL ELECTRIC CO
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