METHODS FOR SPIRAL WINDING COMPOSITE FAN BYPASS DUCTS AND OTHER LIKE COMPONENTS

Abstract

Methods for spiral winding a contoured composite component involving providing a triaxial material, cutting the material to a width, loading the width of material onto a creel, transferring the material from the creel to a tensioning device, and using a traversing screw to spirally wind the material from the tensioning device about a contoured curing mandrel such that each subsequent layer of the material overlaps by about half of the width where the contoured composite component has a cylindrical shape and non-crimp or braided material; a conical shape and non-crimp or braided material void of hoop fibers; or a combination thereof.

Description

CROSS REFERENCE TO RELATED APPLICATIONS

This is a Continuation-in-Part of application Ser. Nos. 12/129854 and 12/129862, both filed on May 30, 2008, which are herein incorporated by reference in their entirety.

STATEMENT OF GOVERNMENT RIGHTS

This invention was made, at least in part, with a grant from the Government of the United States (Contract No. F33615-03-D-2352 D07, from the United States Air Force). The Government may have certain rights to the invention.

TECHNICAL FIELD

Embodiments described herein generally relate to methods for spiral winding composite components. More particularly, embodiments herein generally describe automated methods for making spiral wound composite components, such as gas turbine engine fan bypass ducts and containment casings for example.

BACKGROUND OF THE INVENTION

In gas turbine engines, such as aircraft engines, air is drawn into the front of the engine, compressed by a shaft-mounted compressor, and mixed with fuel in a combustor. The mixture is then burned and the hot exhaust gases are passed through a turbine mounted on the same shaft. The flow of combustion gas expands through the turbine, which in turn spins the shaft and provides power to the compressor. The hot exhaust gases are further expanded through nozzles at the back of the engine, generating powerful thrust, which drives the aircraft forward.

In recent years composite materials have become increasingly popular for use in a variety of aerospace applications because of their durability and relative lightweight. Although composite materials can provide superior strength and weight properties, improvements can still be made.

Composite components, such as fan bypass ducts and containments casings for example, are currently fabricated using conventional layup methods such as filament winding, automated tape laying, and hand layup. Filament winding generally involves winding filaments under various amounts of tension over a mandrel in a desired pattern. This method allows for control of the orientation of the filaments so that successive layers can be oriented differently from the previous layer. Automated tape laying generally involves laying up a plurality of plies of tape at various angles to create a laminate. Hand layup generally involves manually positioning a woven fabric mat in a mold, applying resin thereto, and manually removing any air bubbles trapped between the plies of fabric. While all of these methods can be used successfully, such methods can often be time consuming, labor intensive, wasteful of material, and as a result, costly.

Accordingly, there remains a need for methods for making composite components that that are less time, material, and labor consuming and, therefore, more cost effective.

BRIEF DESCRIPTION OF THE INVENTION

Embodiments herein generally relate to methods for spiral winding a contoured composite component comprising providing a triaxial material; cutting the material to a width; loading the width of material onto a creel; transferring the material from the creel to a tensioning device; and using a traversing screw to spirally wind the material from the tensioning device about a contoured curing mandrel such that each subsequent layer of the material overlaps by about half of the width wherein the contoured composite component comprises a cylindrical shape and non-crimp or braided material; a conical shape and non-crimp or braided material void of hoop fibers; or a combination thereof.

Embodiments herein also generally relate to methods for spiral winding a contoured composite component comprising providing a triaxial material; cutting the material to a width; loading the width of material onto a creel; transferring the material from the creel to a tensioning device; and using a traversing screw to spirally wind the material from the tensioning device about a cylindrically shaped curing mandrel such that each subsequent layer of the material overlaps by about half of the width wherein the triaxial material comprises fibers selected from the group consisting of carbon fiber, glass fiber, ceramic fiber, graphite fiber, aramid fiber, and combinations thereof.

Embodiments herein also generally relate to methods for spiral winding a contoured composite component comprising providing a triaxial material void of hoop fibers; cutting the material to a width; loading the width of material onto a creel; transferring the material from the creel to a tensioning device; and using a traversing screw to spirally wind the material from the tensioning device about a conically shaped mandrel such that each subsequent layer of the material overlaps by about half of the width.

These and other features, aspects and advantages will become evident to those skilled in the art from the following disclosure.

BRIEF DESCRIPTION OF THE DRAWINGS

While the specification concludes with claims particularly pointing out and distinctly claiming the invention, it is believed that the embodiments set forth herein will be better understood from the following description in conjunction with the accompanying figures, in which like reference numerals identify like elements.

FIG. 1 is a schematic cross sectional view of one embodiment of a low bypass gas turbine engine in accordance with the description herein;

FIG. 2 is a schematic perspective view of one embodiment of a composite component in accordance with the description herein;

FIG. 3 is a schematic perspective view of one embodiment of a spiral winding system in accordance with the description herein; and

FIG. 4 is a schematic cross sectional view of one embodiment of a composite component made using the spiral winding system in accordance with the description herein.

DETAILED DESCRIPTION OF THE INVENTION

Embodiments described herein generally relate to methods for spiral winding composite components, and in particular, composite fan bypass ducts and containment casings, such as fan casings. More particularly, embodiments herein generally relate to automated methods for making composite components using a spiral winding system including a creel, a tensioning device, a traversing screw and a curing mandrel as described herein below. Those skilled in the art will understand that although the embodiments herein focus on low bypass gas turbine engines, the description should not be limited to such.

Turning to the figures, FIG. 1 is a schematic representation of one embodiment of a low bypass gas turbine engine 10 that generally includes a fan surrounded by a fan casing 12, a low pressure compressor 14, a fan bypass duct 16, burners 18, turbines 20, a fan exhaust 22, and a nozzle 24. In addition, engine 10 has an intake 26.

Referring to FIG. 2, one embodiment of an acceptable composite component 30 is shown. As used herein, “contoured composite component” refers to any structure having a contoured shape fabricated from a composite material or combination of composite materials. As used herein throughout, “contour(ed)” means at least a portion of the shape or surface is non-planar. In one embodiment, contour refers to any of a cylindrical shape, a conical shape, or some combination thereof. In one embodiment, composite component 30 may comprise a spirally wound fan bypass duct 31, though those skilled in the art will understand that the methods and systems described herein should not be limited to such. In another embodiment, composite component 30 may comprise a spirally wound containment casing such as a fan casing 12, as shown generally in FIG. 1.

Bypass duct 31 may be fabricated as described herein below from a material 32 having fibers selected from the group consisting of carbon fiber, glass fiber, ceramic fiber, graphite fiber, aramid fiber, and combinations thereof. In one embodiment, composite component may comprise a cylindrical shape 29 and material 32 may comprise any triaxial non-crimp or braided material. In another embodiment, composite component can comprise a conical shape 33 and material 32 may comprise any triaxial non-crimp, or braided, material that is void of hoop (90°) fibers. The absence of hoop fibers can help the material conform to a conically shaped curing mandrel as described herein below. The following methods are equally applicable whether or not the material comprises hoop fibers.

Initially, material 32 may be cut to a width W and spooled onto a creel 34 of a spiral winding system 36 as shown generally in FIG. 3. Material 32 can have a width W that can vary depending on need, however, in one embodiment, width W can be from about 4 inches (about 10.2 cm) to about 8 inches (about 20.3 cm). In one embodiment, creel 34 may have a width corresponding to the width W of material 32.

Once loaded onto creel 34, material 32 can be transferred through a tensioning device 38 with the aid of guide rollers 40 and wrapped about a curing mandrel 42 with the aid of a traversing screw 44. More specifically, material 32 can be transferred through tensioning device 38, which can apply needed tension to material 32 to help ensure uniformity. Tensioning device 38 may comprise anything capable of providing tension to the material. In one embodiment, tensioning device 38 may comprise a magnetic break on the creel. In another embodiment, tensioning device 38 may comprise a friction break attached to the creel.

From tensioning device 38, material 32 can be wrapped about curing mandrel 46. In particular, material 32 may be spirally wound about curing mandrel 42. As used herein, “spirally wound” indicates that each subsequent layer of the material overlaps the previous layer by about half of width W of material 32. In this way, two layers of material 32 can be layed up about the curing mandrel concurrently. As an example, and as shown in FIG. 4, if material 32 has a width W of about 4 inches (about 10.2 cm), then each subsequent layer can overlap by about 2 inches (about 5.1 cm).

This desired overlap can be achieved using traversing screw 44, which as shown in FIG. 3, can be positioned to lie along a length L of curing mandrel 42. As each subsequent width W of material 32 is applied to mandrel 42, tensioning device 38 can move laterally along traversing screw 44 to achieve the desired spirally wound bypass duct preform 46.

Spirally wound bypass duct preform 46 may then be treated with any acceptable resin and cured using conventional infusion and curing techniques known to those skilled in the art to produce a spiral wound bypass duct 31.

Constructing a composite component having a spirally wound design as described previously herein can offer several benefits over current fabrications techniques. Spiral winding is an automated method that can provide the ability to quickly produce complex geometries using fabric that can be tailored to specific design needs. Moreover, spiral winding can replace labor intensive hand lay-up process, as well as material wastes from filament winding and single source braiding. Additionally, spiral winding can provide precise lay-ups, the ability to construct complex geometries, and the ability to make a component having any desired fiber orientation.

This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to make and use the invention. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.

Claims

1. A method for spiral winding a contoured composite component comprising: wherein the contoured composite component comprises a cylindrical shape and non-crimp or braided material; a conical shape and non-crimp or braided material void of hoop fibers; or a combination thereof.

providing a triaxial material;

cutting the material to a width;

loading the width of material onto a creel;

transferring the material from the creel to a tensioning device; and

using a traversing screw to spirally wind the material from the tensioning device about a contoured curing mandrel such that each subsequent layer of the material overlaps by about half of the width

2. The method of claim 1 wherein the triaxial material comprises fibers selected from the group consisting of carbon fiber, glass fiber, ceramic fiber, graphite fiber, aramid fiber, and combinations thereof.

3. The method of claim 2 wherein the width of the material is from about 4 inches (about 10.2 cm) to about 8 inches (about 20.3 cm).

4. The method of claim 3 wherein the width of the material corresponds to a width of the creel.

5. The method of claim 4 wherein the tensioning device is a magnetic break or a friction break.

6. The method of claim 5 wherein the curing mandrel comprises a length and the traversing screw is positioned to lie along the length of the contoured curing mandrel.

7. The method of claim 4 comprising laterally moving the tensioning device along the traversing screw to produce a spirally wound composite component preform about the contoured curing mandrel.

8. The method of claim 7 wherein each layer of the material overlaps by about 2 inches (about 5.1 cm).

9. The method of claim 8 comprising treating the composite component preform with a resin followed by curing the preform to produce the contoured composite component.

10. The method of claim 9 wherein the contoured composite component comprises a fan bypass duct or a containment casing.

11. A method for spiral winding a contoured composite component comprising: wherein the triaxial material comprises fibers selected from the group consisting of carbon fiber, glass fiber, ceramic fiber, graphite fiber, aramid fiber, and combinations thereof.

providing a triaxial material;

cutting the material to a width;

loading the width of material onto a creel;

transferring the material from the creel to a tensioning device; and

using a traversing screw to spirally wind the material from the tensioning device about a cylindrically shaped curing mandrel such that each subsequent layer of the material overlaps by about half of the width

12. The method of claim 11 wherein the width of the material is from about 4 inches (about 10.2 cm) to about 8 inches (about 20.3 cm).

13. The method of claim 12 wherein the curing mandrel comprises a length and the traversing screw is positioned to lie along the length of the curing mandrel.

14. The method of claim 13 comprising laterally moving the tensioning device along the traversing screw to produce a spirally wound contoured composite component preform about the curing mandrel.

15. The method of claim 14 wherein each layer of the material overlaps by about 2 inches (about 5.1 cm).

16. A method for spiral winding a contoured composite component comprising:

providing a triaxial material void of hoop fibers;

cutting the material to a width;

loading the width of material onto a creel;

transferring the material from the creel to a tensioning device; and

using a traversing screw to spirally wind the material from the tensioning device about a conically shaped mandrel such that each subsequent layer of the material overlaps by about half of the width.

17. The method of claim 16 wherein the triaxial material comprises fibers selected from the group consisting of carbon fiber, glass fiber, ceramic fiber, graphite fiber, aramid fiber, and combinations thereof.

18. The method of claim 17 wherein the width of the material is from about 4 inches (about 10.2 cm) to about 8 inches (about 20.3 cm) and wherein each layer of the material overlaps by about 2 inches (about 5.1 cm).

19. The method of claim 18 wherein the curing mandrel comprises a length and the traversing screw is positioned to lie along the length of the curing mandrel.

20. The method of claim 19 comprising laterally moving the tensioning device along the traversing screw to produce a spirally wound contoured composite component preform about the curing mandrel.