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Method of repairing a mobile vane of a turbomachine, turbomachine vane and turbomachine comprising this vane

A technology of turbine blade and repair method, applied in the direction of blade support element, machine/engine, mechanical equipment, etc., can solve problems such as difficulty in implementing coating

Inactive Publication Date: 2008-11-05
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Contact between titanium surfaces makes most coatings difficult to apply

Method used

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  • Method of repairing a mobile vane of a turbomachine, turbomachine vane and turbomachine comprising this vane
  • Method of repairing a mobile vane of a turbomachine, turbomachine vane and turbomachine comprising this vane
  • Method of repairing a mobile vane of a turbomachine, turbomachine vane and turbomachine comprising this vane

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Embodiment Construction

[0024] figure 1 The arrangement described in the EP 165860 patent is shown. The figure shows a rotor disk 1 of a turbine engine rotor with a flange on which a conical front cowl 3 is fastened. A plurality of approximately axial cavities 4 are machined on the rim of the rotor disk 1 using a broaching process. These cavities have a wedge-shaped cross-section matching the shape of the lower part 13' of the root 13 of the blade 10. The blade root 13 is that part of the blade 10 which is located below the platform 9 which forms the demarcation line of the gas flow. The locking key 11 slides over the lower portion 13' of the blade root 13, thereby locking the blade in the cavity. On the downstream face, the rim of the rotor disk has a radial flange 5 for securing a locking ring 7 and a sealing ring 8 by means of bolts 6 .

[0025] The locking ring 7 is provided with the same number of radially inward grooves 18 as the chambers, all facing the chambers. Furthermore, th...

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Abstract

The process for repairing a portion of an axial support surface (14) of a movable turbomachine blade (10) by surfacing, comprises depositing metal particles on the surface by buffer electrolysis and electrolysis in bath or micro-bath, and applying titanium or its alloy to the blade of blowing apparatus. The metal layer has a thickness of 10 mu m to 1 mm. Base (13) of the blade has a swallow-tail section. An independent claim is included for a movable turbomachine blade.

Description

technical field [0001] The present invention relates to the field of turbomachines and in particular to the repair of worn areas of blade surface parts, and more particularly of the worn parts of the blade root area. Background technique [0002] A turbine engine with a bypass gas turbine consists of a fan rotor consisting of blades mounted on the rim of a rotor disk driven by the gas generator low pressure rotor shaft. Fan blades made of titanium or titanium alloy material are installed in the cavities of the respective blades generally arranged in the axial direction of the turbine. The root of the blade is shaped as a wedge-shaped section to match its mounting cavity. According to one type of turbine, the blades are extended downstream by axial projections which securely hold the blades within the chamber. An example is presented by the applicant in patent document EP 165 860 . The blades are held axially fixed by a downstream locking ring against which the blades rest...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C25D3/12F01D5/00
CPCC25D5/06F01D5/005B23P6/007F05D2300/133C25D3/12F05D2230/80F05D2230/30C25D7/00F05C2201/0412C25D5/02Y10T29/49318B23P6/002
Inventor 克里斯戴勒·福彻尔克劳得·马克·芒斯
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A