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

a technology for turbojet engines and blades, which is applied in the direction of machines/engines, stators, liquid fuel engines, etc., can solve the problems of assembly tooling, complex fabrication, complex solutions, etc., and achieve the effect of simple production and convenient mounting

Inactive Publication Date: 2013-07-04
SAFRAN LANDING SYSTEMS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent describes a new design for a vane that is easy to fit into an annular casing. It achieves this by making the leading and trailing edges of the vane extend beyond the casing. This makes it simple to attach the vane to the casing with just a few fasteners. The leading and / or trailing edge of the vane is made from a strong material called pultrusion, which is reinforced with fibers. This design helps the vane to withstand high levels of stress.

Problems solved by technology

For example, document US 2009 / 0317246 recommends ends making up a cylindrical platform forming a portion of the outer casing and carrying two fastener flanks, thereby leading to shapes that are complex to fabricate.
That solution is complex to implement and requires assembly tooling.

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

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Embodiment Construction

[0019]With reference to FIGS. 1 and 2, the vane 1 shown therein is a guide vane for extending behind the fan of a turbojet. In this embodiment, the vane 1 has a leading edge 2 that is in the form of a one-piece elongate structure. The vane 1 also has a trailing edge 3 that is likewise in the form of a one-piece elongate structure.

[0020]The leading edge 2 and the trailing edge 3 are cut from section members obtained by pultrusion, preferably with fibers being placed obliquely (the so-called “pullbraiding” method). The section members have fibers, e.g. carbon fibers, that are arranged essentially along a longitudinal axis in order to form an elongate 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, and 20% of the fibers are arranged at an angle of inclination of about 60 degrees relative to the longitudinal axis. These proportions and this arrangement for the fibers are...

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PUM

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Abstract

A turbojet vane, in particular a compressor guide vane, characterized in that the vane comprises the following elements:an elongate one-piece front portion (2) cut out from a pultruded section member comprising fibers bonded together by resin and forming a leading edge;an elongate one-piece rear portion (3) cut out from a pultruded section member comprising fibers bonded together by resin and forming a trailing edge; anda skin (5) based on resin-impregnated fibers extending between the leading edge and the trailing edge in order to form side faces of the vane and covering at least zones (6, 7) of the leading edge (2) and of the trailing edge (3);these elements being assembled together by hot compaction.

Description

BACKGROUND OF THE INVENTION[0001]Vanes made of composite material are known that have ends carrying fastener means for fastening them to annular casings of a turbojet.[0002]Various fastener means have been proposed. For example, document US 2009 / 0317246 recommends ends making up a cylindrical platform forming a portion of the outer casing and carrying two fastener flanks, thereby leading to shapes that are complex to fabricate. Document[0003]US 2009 / 0317246 recommends joining the vanes together by means of a circular ring prior to mounting the assembly made in this way in the casing. That solution is complex to implement and requires assembly tooling.OBJECT OF THE INVENTION[0004]The object of the invention is thus to propose a turbojet vane that is simple to produce and easy to mount.BRIEF SUMMARY OF THE INVENTION[0005]To this end, the invention provides a turbojet vane, in particular a compressor guide vane comprising the following elements:[0006]an elongate one-piece front portion...

Claims

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Application Information

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IPC IPC(8): F01D5/12
CPCF01D5/147F01D5/282F01D5/32F01D9/042F01D25/246Y02T50/672F05D2230/60F05D2240/12F05D2260/30F01D5/12F04D29/542Y02T50/60
Inventor MASSON, RICHARDDUNLEAVY, PATRICKDESJOYEAUX, BERTRAND
Owner SAFRAN LANDING SYSTEMS