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Method for manufacturing a compressor impeller for a turbomachine

A compressor and impeller technology, applied to turbines, engine components, machines/engines, etc., can solve the problems of unfavorable mechanical characteristics of casting, unfavorable and expensive centrifugal impellers, etc.

Pending Publication Date: 2021-09-28
SAFRAN HELICOPTER ENGINES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] However, this degree of freedom for optimization is considerably constrained by the manufacturing process: milling manufacturing is limited by the pitch of the blades and their curvature, which can be detrimental to achieving inner and outer domes
There are other manufacturing processes, but they all have disadvantages: casting is not conducive to mechanical properties, powder metallurgy is complex, expensive and requires precision molds, laser additive manufacturing on powder beds due to the undercut slope of the face of the blade (lower surface) and due to mechanical properties in terms of fatigue, which are considerably adversely affected
[0010] These manufacturing constraints, which limit the optimization of the blades, prove to be detrimental not only to centrifugal impellers, but also to axial or so-called mixing or diagonal impellers

Method used

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  • Method for manufacturing a compressor impeller for a turbomachine
  • Method for manufacturing a compressor impeller for a turbomachine
  • Method for manufacturing a compressor impeller for a turbomachine

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Embodiment Construction

[0030] The basic idea of ​​the invention is to start from a blank defining at least the hub of the impeller and to finish this blank so as to use a fusion / sintering type additive manufacturing process, by powder injection or another material feed, that is to say, by the The process implements localized material additions to form or complete the blade.

[0031] Unlike additive manufacturing processes on a powder bed, such as the SLM process (which stands for Selective Laser Melting), the melting / sintering by jetting process allows localized material addition using nozzles positioned over the feed area, also known as BPP (Blown Powder process). According to the WFP process, locally added material can also be fed in the form of a wire to be melted.

[0032] In these localized material addition processes, LMD (Laser Metal Deposition), sometimes referred to by the registered trademark CLAD which stands for Laser Structure for Direct Addition, involves the use of an equipment group...

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PUM

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Abstract

The invention relates to a method for manufacturing a compressor impeller or rotor comprising a hub (21) that carries blades (26), involving a step of manufacturing a hub (21) which comprises all or some of the blades (22), and a step of additive manufacture by adding localised material using a method such as the LMD process to form or finish each blade (26).

Description

technical field [0001] The invention concerns the manufacture of an axial or centrifugal compressor wheel intended to equip a turbine engine, such as a turbojet engine. Background technique [0002] As shown in FIG. 1 , a centrifugal compressor wheel 1 is a generally integral part comprising a hub 2 having a shape of revolution about an axis AX carrying blades 3 . These blades are curved walls, oriented obliquely with respect to the axis AX, spaced apart from each other around the axis AX. [0003] In the case of a centrifugal impeller, such as impeller 1, the hub 2 in flight mode has an axisymmetric, bell-shaped outer surface 4 that extends from the intake end 6 to the exhaust end 7, where it typically has a substantially radial shape. [0004] When the impeller is mounted in a turbine engine, it is surrounded by a casing, not shown, called the casing, and bell-like in shape with its inner surface parallel to the tops of the blades 3, ie their outer edges. In operation, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/04F04D29/28B22F3/105B22F5/04B22F7/08B22F5/00B23K11/00B33Y10/00B33Y80/00F01D5/28B22F7/06
CPCF04D29/284F01D5/048B22F7/08B22F2007/068B22F5/04F05D2230/31F01D5/28F05D2230/22F05D2230/14B22F5/009B33Y10/00B33Y80/00B23K2101/001B23K26/342Y02P10/25B22F12/53B22F10/50B22F10/25
Inventor 雷纳·托马斯劳伦特·皮埃尔·塔诺夫斯基马修·劳伦特·赫兰卢多维奇·安德烈·乔尔·诺多特
Owner SAFRAN HELICOPTER ENGINES