Monobloc preform and blade for turbo machine

Patent metadata

Field	Value
Publication number	US-2016245103-A1
Application number	US-201314442484-A
Country	US
Kind code	A1
Filing date	Nov 12, 2013
Priority date	Nov 13, 2012
Publication date	Aug 25, 2016
Grant date	—

Abstract

A fiber preform for a turbine engine blade or vane obtained by single-piece three-dimensional weaving. The preform includes a first longitudinal segment suitable for forming a root; a second longitudinal segment extending the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform.

First claim

1 - 12 . (canceled)

13 . A fiber preform for a turbine engine blade or vane that is obtained by single-piece three-dimensional weaving, comprising:
a first longitudinal segment suitable for forming a root; a second longitudinal segment extending the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment extending transversely from the junction between the first and second longitudinal segments and suitable for forming a first platform.

14 . A preform according to claim 13 , further comprising a second transverse segment extending transversely from the junction between the first and second longitudinal segments extending the first transverse segment and going away therefrom, suitable for forming a second platform.

15 . A preform according to claim 13 , wherein the first transverse segment is formed by at least a portion of a free tail, said free tail and said second longitudinal segment being woven jointly in non-interlinked manner, said non-interlinking beginning at the junction between the first and second longitudinal segments.

16 . A preform according to claim 15 , wherein the second transverse segment and said first longitudinal segment are woven jointly in non-interlinked manner, said non-interlinking terminating at the junction between the first and second longitudinal segments.

17 . A preform according to claim 13 , wherein the first transverse segment is formed by at least portions of first and second free tails folded one onto the other, said first free tail being woven jointly and in non-interlinked manner with said second longitudinal segment, and also said second free tail being woven jointly and in non-interlinked manner with said second longitudinal segment, a layer crossing being provided at the junction between the first and second longitudinal segments so that the yarns of the first free tail are extended into the second longitudinal segment, and so that the yarns of the second free tail come from the first longitudinal segment.

18 . A preform according to claim 13 , wherein the number of layers of yarns, and thus the thickness, of the second longitudinal segment varies.

19 . A preform according to claim 13 , comprising a third transverse segment and a fourth transverse segment extending transversely on either side of the upstream end of the first longitudinal segment, and suitable for forming fastener flanges of the vane or blade; and
wherein said third and fourth transverse segments are woven jointly in non-interlinked manner, said non-interlinking terminating at the upstream end of the first longitudinal segment.

20 . A preform according to claim 13 , further comprising:
a third longitudinal segment extending the second longitudinal segment and suitable for forming a head; and a fifth transverse segment extending transversely from the junction between the second and third longitudinal segments and suitable for forming a third platform.

21 . A blade or vane for a turbine engine, the blade or vane comprising:
a root; an airfoil portion; and a platform extending transversely from the airfoil at the junction between the root and the airfoil portion; said blade or vane being made as a single piece of composite material by means of a fiber preform according to claim 13 , said preform being shaped in a mold and embedded in a matrix.

22 . An intermediate casing for a turbine engine, the casing comprising a plurality of vanes according to claim 21 arranged angularly between an inner hub and an outer shroud.

23 . A turbine engine fan, comprising a plurality of blades according to claim 21 .

24 . A turbine engine, comprising at least one blade or vane according to claim 21 .

25 . A turbine engine, comprising at least one intermediate casing according to claim 22 .

26 . A turbine engine, comprising at least one fan according to claim 23 .

27 . A blade or vane according to claim 21 , wherein said matrix comprises an organic material.

Assignees

• Snecma
• Safran

Inventors

• Gimat Matthieu
• Coupe Dominique Marie Christian

Classifications

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F05D2300/40

  Organic materials · CPC title

• B29B11/16 Primary

  comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)} · CPC title

• F05D2300/44

  Resins · CPC title

• D03D25/005

  Three-dimensional woven fabrics · CPC title