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Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades

A turbojet and blade technology, applied in engine manufacturing, engine components, engine functions, etc., can solve the problems of complex implementation and the need for assembly tools

Inactive Publication Date: 2013-05-01
SAFRAN LANDING SYSTEMS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The solution is complex to implement and requires assembly tools

Method used

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  • Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades
  • Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades
  • Turbojet engine blade, in particular a guide blade, and turbojet engine receiving such blades

Examples

Experimental program
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Effect test

Embodiment Construction

[0020] refer to figure 1 with 2 , wherein the illustrated blade 1 is a guide vane for extending behind the fan of a turbojet. In this embodiment, the blade 1 has a leading edge 2 in the form of a one-piece elongated structure. The blade 1 also has a trailing edge 3 which is likewise in the form of a one-piece elongated structure.

[0021] The leading edge 2 and the trailing edge 3 are cut out of a segment member obtained by pultrusion, preferably with fibers placed obliquely (the so-called “pullbraiding” method). The segment member has fibers (eg, carbon fibers) arranged substantially along a longitudinal axis so as to form an elongated body. Ideally, substantially 80% of the fibers are arranged along the longitudinal axis X of the leading edge and along the longitudinal axis Y of the trailing edge, while 20% of the fibers are arranged at an inclination of about 60 degrees relative to the longitudinal axis. Such proportions and this arrangement of fibers are given by way o...

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PUM

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Abstract

The invention relates to a turbojet engine blade and to a turbojet engine receiving such blades, particularly a guide blade, said blade comprising the following elements: an elongate one-piece front portion (2) cut into a pultruded profile, comprising resin-bonded fibres and forming a leading edge; an elongate one-piece rear portion (3) cut into a pultruded profile, comprising resin-bonded fibres and forming a trailing edge; and a skin (5) based on resin-impregnated fibres, extending between the leading edge and the trailing edge in order to form the lateral faces of the blade and covering at least particular zones (6, 7) of the leading edge (2) and the trailing edge (3), all of said elements being assembled by means of hot pressing.

Description

technical field [0001] The invention relates to turbojet blades, in particular guide vanes for compressors, and turbojets incorporating such blades. Background technique [0002] Blades made of composite material are known to have ends carrying fastener means for fastening them to the annular casing of the turbojet. [0003] Various fastener arrangements have been proposed. For example, document US 2009 / 0317246 proposes to constitute an end of a cylindrical platform forming part of the outer casing and carrying two fastener flanks, thus resulting in a shape that is complex to manufacture. Document US 2009 / 0317246 recommends connecting the blades together by means of circular rings before installing the assembly manufactured in this way into the housing. This solution is complex to implement and requires assembly tools. Contents of the invention [0004] Therefore, the object of the present invention is to propose a turbojet blade that is simple to manufacture and easy t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D5/14F01D5/28F01D9/04F01D25/24
CPCF05D2240/12F05B2230/60F05D2230/60F04D29/542F05B2260/30F01D25/246F05D2260/30F01D5/32F01D5/282F01D5/147F01D9/042F01D5/12Y02T50/60
Inventor R·梅森P·邓里维B·德茹瓦约
Owner SAFRAN LANDING SYSTEMS