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Method for manufacturing a blade comprising a squealer tip integrating a small wall

A technology for blades and turbine engines, which is applied in the directions of blade support elements, processing and manufacturing, and additive manufacturing, and can solve the problems of complicated manufacturing, insufficient solidity of the core, and increased rejection rate.

Active Publication Date: 2018-03-27
SAFRAN AIRCRAFT ENGINES SAS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This significantly complicates manufacture and thus tends to increase the scrap rate and further tends to result in cores not being sufficiently robust

Method used

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  • Method for manufacturing a blade comprising a squealer tip integrating a small wall
  • Method for manufacturing a blade comprising a squealer tip integrating a small wall
  • Method for manufacturing a blade comprising a squealer tip integrating a small wall

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0028] as in figure 1 As can be seen in , a blade 16, such as that made by casting, comprises an arch inner surface wall 17 and an arch outer surface wall 18 extending substantially along the spanwise direction EV of the blade and which is referenced 19 The top edges of the blades 16 and 21 define the tip of the blade 16 .

[0029] These arch inner surface walls 17 and arch outer surface walls 18 are separated from each other, while on the one hand at the leading edge of the blade marked 22 and on the other hand at the trailing edge of the blade, not shown in the figures, the inner arch The surface wall and the arch outer surface wall are interconnected, the two edges, the leading edge and the trailing edge, extending almost parallel to the spanwise direction EV.

[0030] These walls are interconnected again at the tip of the blade by a wall called a closure wall, designated 23, which extends perpendicularly to the spanwise direction and at the same time is spaced apart at a ...

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PUM

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Abstract

The invention relates to a method for manufacturing a turbine engine blade (16) including an active-surface wall (17) and a passive-surface wall (18) separated from one another, this blade (16) including a tip that has a closing wall grouping together the active-surface (17) and passive-surface (18) walls in the region of this tip to define the bottom (23) of a squealer tip shape located at the tip of the blade, the method comprising a molding step implementing a core defining the squealer tip shape. According to the invention, there is a step of adding metal to the bottom (23) of the squealertip by means of a Direct Laser Additive Manufacturing (CLAD) method, to deposit material onto the bottom of the squealer tip to form therein an inner partition (28) supported by the bottom thereof (23).

Description

technical field [0001] The invention relates to the manufacture of aircraft engines of the turbine engine type, such as for example a turbojet or turboprop. Background technique [0002] exist figure 1 In such an engine, referenced 1 in , air enters an inlet casing 2 to pass through a fan comprising a series of rotating blades 3 before being divided into a central main flow and a secondary flow surrounding the main flow. [0003] The main flow is compressed by turbines 4 and 6 before reaching the combustion chamber 7, after which it expands and passes through the turbine 8 before being released to generate thrust. The secondary flow is pushed directly by the fan to generate additional thrust. [0004] Each turbine 8 comprises a series of blades radially oriented and evenly spaced about an axis of rotation AX supported by an outer casing 9 enclosing the assembly. [0005] Cooling of the blades is ensured by circulating in each blade the air collected upstream of the combus...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C64/153B22F3/105B22F5/04B23P15/04F01D5/00F01D5/14F01D5/20B22F3/24B22F5/00B33Y10/00
CPCF01D5/20B22F2003/247B22F2005/005B23H9/10F05D2230/31B33Y80/00B33Y10/00B29C64/153B22F2998/10B22F2999/00B22F5/04B23P15/02B29C64/188Y02P10/25Y02T50/60B22F10/66B22F10/25B22F7/062B22F7/08B22F7/064F05D2240/307
Inventor 马修·让·卢克·沃勒布雷特科拉列·盖拉尔帕特里克·埃米利安·保罗·埃米尔·胡彻
Owner SAFRAN AIRCRAFT ENGINES SAS