Fiber preform for a hollow turbine engine vane

Patent metadata

Field	Value
Publication number	US-10240466-B2
Application number	US-201415031563-A
Country	US
Kind code	B2
Filing date	Oct 3, 2014
Priority date	Oct 23, 2013
Publication date	Mar 26, 2019
Grant date	Mar 26, 2019

Abstract

A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.

First claim

The invention claimed is:

1. A fiber preform for a hollow turbine engine vane, the preform comprising:
a main fiber structure obtained by three-dimensional weaving and including a main part extending in a radial direction; and
a second fiber structure obtained by weaving and configured to be fitted to an edge of the main fiber structure,
wherein the main part presents a loop and includes, in order around the loop:
a first link strip,
a first main longitudinal portion suitable for forming essentially a pressure side wall of an airfoil,
a U-turn bend portion suitable for forming essentially a leading edge or a trailing edge of the airfoil,
a second main longitudinal portion facing the first main longitudinal portion and suitable for forming essentially a suction side wall of the airfoil, and
a second link strip,

wherein the first and second link strips are secured to each other and form a link portion of the main fiber structure,
wherein the main longitudinal portions are spaced apart so as to form a gap between said main longitudinal portions suitable for forming a hollow in the airfoil, and
wherein at least one of the fiber structures comprises a radial portion extending from a bottom edge or a top edge of the first main longitudinal portion or the second main longitudinal portion of the main part, the radial portion being suitable for forming a platform or a fastener flange.

2. The fiber preform according to claim 1 , wherein the first and second link strips are woven together in interlinked manner.

3. The fiber preform according to claim 1 , wherein at least one of the fiber structures includes an overlap portion that, when the fiber preform is flat, is situated upstream from at least part of the link portion of the main part, a gap being left between said overlap portion and the link portion.

4. The fiber preform according to claim 1 , wherein at least one of a radially bottom end or a radially top end of the link portion of the main part presents a smaller width in a direction perpendicular to the radial direction than a middle of the link portion of the main part in the radial direction.

5. A hollow vane comprising a single piece of composite material from a fiber preform according to claim 1 , said preform being shaped in a mold and embedded in a matrix.

6. The hollow vane according to claim 5 , wherein the fiber preform is made with fibers of ceramic oxide, carbon, or carbide type.

7. The hollow vane according to claim 6 , wherein the fiber preform is made with fibers of alumina, mullite, silica, zirconia, silicon carbide, or a mixture thereof.

8. The hollow vane according to claim 5 , wherein the matrix is of ceramic oxide, carbide, or nitride type, or is organic of epoxy type.

9. The hollow vane according to claim 8 , wherein the matrix is made of alumina, mullite, silica, zirconia, silicon nitride or carbide, or a mixture thereof.

10. A turbine engine, comprising a hollow vane according to claim 5 .

11. A method of fabricating a hollow vane, the method including weaving a fiber preform according to claim 1 .

12. The method according to claim 11 , wherein the weaving is performed using a three-dimensional loom having a bundle of warp yarns and at least one shuttle suitable for inserting a weft yarn between the warp yarns;
wherein the shuttle performs a succession of go-and-return movements in a first direction or a second direction, the first direction starting from a link zone, traveling within a first main longitudinal zone, performing a U-turn in a bend zone, traveling within a second main longitudinal zone facing the first main longitudinal zone, and returning to the link zone, the second direction being opposite the first direction; and
wherein the weft yarn cooperates with the warp yarns to form a three-dimensional weave within the link zone, the first and second main longitudinal zones, and the bend zone.

13. The method according to claim 11 , further comprising:
cutting out the fiber preform;
folding and shaping the fiber preform in a mold possessing the shape of a desired blank;
placing an insert in the gap between the two main longitudinal portions;
injecting and solidifying the matrix around the fiber preform in order to obtain the blank;
removing the insert; and
machining the link part of the blank corresponding to the link portion of the fiber preform in order to obtain the leading or trailing edge of the final part.

14. The method according to claim 13 , wherein the machining the link part of the blank, corresponding to the link portion of the fiber preform, comprises tapering down said link part to obtain the trailing edge.

Assignees

• Safran Aircraft Engines
• Safran

Inventors

• Podgorski Michael
• Dambrine Bruno Jacques Gerard
• Le Hong Son
• Coupe Dominique Marie Christian
• Molliex Ludovic Edmond Camille
• Goering Jonathan

Classifications

• C04B2235/5216

  Inorganic · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• C04B2235/3463

  Alumino-silicates other than clay, e.g. mullite · CPC title

• F05D2230/21

  by casting · CPC title

• B29C70/546

  Measures for feeding or distributing the matrix material in the reinforcing structure · CPC title