Composite airfoil construction

• US 4,051,289 A
• Filed: 04/12/1976
• Issued: 09/27/1977
• Est. Priority Date: 04/12/1976
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Adamson, Arthur P.
• Primary Examiner(s): Lesmes, George F.
• Assistant Examiner(s): Thibodeau, P. J.
• Application Number:
  US05/675,902
• Time in Patent Office: 533 Days
• Field of Search: 428/113, 428/174, 428/181, 428/378, 428/408, 428/902, 428/367, 428/265, 428/72, 428/116, 416/224, 416/226, 416/230, 416/229 R, 416/223 R, 416/241 A, 244/123-124, 244/DIG. 1
• US Class Current: 428/113
• CPC Class Codes: B29C 70/08 comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
• CPC Class Codes: B29C 70/205 the structure being shaped to form a three-dimensional configuration
• CPC Class Codes: B29C 70/347 combined with compressing after the winding of lay-ups having a non-circular cross-section, e.g. flat spiral windings
• CPC Class Codes: B29D 99/0021 provided with plain or filled structures, e.g. cores, placed between two or more plates or sheets, e.g. in a matrix
• CPC Class Codes: B29D 99/0025 Producing blades or the like, e.g. blades for turbines, propellers, or wings
• CPC Class Codes: B32B 2307/542 Shear strength
• CPC Class Codes: B32B 2603/00 Vanes, blades, propellers, rotors with blades
• CPC Class Codes: B32B 3/18 characterised by an internal layer formed of separate pieces of material which are juxtaposed side-by-side B32B5/02 takes precedence
• CPC Class Codes: B32B 3/28 characterised by a layer comprising a deformed thin sheet , i.e. the layer having its entire thickness deformed out of the plane, e.g. corrugated, crumpled B32B29/08 takes precedence
• CPC Class Codes: B32B 5/12 characterised by the relative arrangement of fibres or filaments of different layers, e.g. the fibres or filaments being parallel or perpendicular to each other
• CPC Class Codes: E04C 2/3405 spaced apart by profiled spacer sheets
• CPC Class Codes: E04C 2002/345 with triangular corrugations
• CPC Class Codes: Y10S 428/902 High modulus filament or fiber
• CPC Class Codes: Y10T 156/1051 by folding
• CPC Class Codes: Y10T 428/24124 Fibers
• CPC Class Codes: Y10T 428/24149 Honeycomb-like
• CPC Class Codes: Y10T 428/24628 Nonplanar uniform thickness material
• CPC Class Codes: Y10T 428/24686 Pleats or otherwise parallel adjacent folds
• CPC Class Codes: Y10T 428/2918 including free carbon or carbide or therewith [not as steel]
• CPC Class Codes: Y10T 428/2938 Coating on discrete and individual rods, strands or filaments

Abstract

An article such as a blade fabricated from a plurality of high-strength, reinforcing filaments embedded in a matrix material and characterized by a portion of the filaments oriented transverse to the blade longitudinal axis in a direction through the blade to enhance transverse shear strength. In one embodiment, a plurality of columnar filament cores are each wrapped with a filament sheet and bonded together laterally to form the blade primary structure. The orientation of the filaments within the sheet forms an angle with the core longitudinal axes such that at least a portion of the sheet filaments runs transverse to the blade from one aerodynamic surface to the other. In an alternative embodiment, a blade is formed of a plurality of bonded filament laminates accordian folded with the fold lines angled with respect to the longitudinal axes of the filaments, the distance between fold lines being equal to or greater than the blade thickness.

Claims

1. A composite article having an upper surface and a lower surface and comprising a plurality of columnar elements bonded together along adjacent complementary interfaces, each of said element characterized by:

a bundled core of high modulus, substantially parallel core filaments embedded in a core matrix; and

a sheet of high modulus, substantially parallel sheet filaments embedded in a sheet matrix, wherein

the longitudinal axes of the sheet filaments are oriented at an angle to the core filaments and said sheet is wrapped and bonded about said core such that at least a portion of the sheet filaments run transverse to the core filaments through the article in a direction from the upper surface to the lower surface, at the interface.

2. The composite article as recited in claim 1 wherein said sheet comprises a lamination of several layers of substantially parallel sheet filaments embedded in a sheet matrix and wherein at least one layer is characterized by the filaments thereof being oriented at an angle to the core filaments.

3. The composite article as recited in claim 1 wherein two adjacent cores and elements are substantially triangular in cross section, the adjacent elements being bonded in alternating inverted relationship to each other with the triangle bases generally parallel to the upper and lower surfaces.

4. The composite article as recited in claim 1 further comprising two filament composite facing sheets bonded to said elements and sandwiching said elements therebetween.

5. The composite article as recited in claim 4 wherein the filaments within the facing sheets are oriented at an angle to the core filament longitudinal axes.

6. The composite article as recited in claim 1 further characterized by a sheet formed into a substantially U-shaped channel having a base and two sides, the channel receiving a core which is bonded within the closed end thereof, filaments within the base of the channel running transverse to the core filaments in a direction from the upper surface to the lower surface.

7. The composite article as recited in claim 6 wherein each core is substantially triangular in cross section and each U-shaped channel is contoured such that one side forms an acute angle with the base and the other side forms an obtuse angle with the base.

8. The composite article as recited in claim 1 further characterized by a plurality of said sheets formed into substantially U-shaped channels, each having a base and two sides and each channel receiving a core bonded within the closed end thereof, and wherein laterally adjacent pairs of cores and channels are bonded together with the sides of at least one channel receiving therebetween the next laterally adjacent core and channel.

9. The composite article as recited in claim 8 wherein said cores are substantially triangular in cross section, each core being bonded within its associated channel in alternating inverted relationship to each other.

10. The composite article recited in claim 8 further characterized by the upper and lower surfaces being contoured to a blade aerodynamic profile.

11. The composite article as recited in claim 1 wherein the core filaments and the sheet filaments are comprised of a first material, and the core matrix and the sheet matrix are comprised of a second material.

12. The composite article as recited in claim 1 further characterized by the upper and lower surfaces being contoured to a blade aerodynamic profile.

13. A composite article comprising a sheet of high modulus collimated filaments embedded in a matrix material wherein the sheet is accordian folded with the fold lines angled with respect to the longitudinal axes of the filaments, the distance between fold lines being substantially equal to the thickness of the article, and wherein at least a portion of the filaments are oriented through the thickness of the article.

14. The composite article as recited in claim 13 contoured to a blade aerodynamic profile.

15. The composite article are recited in claim 13 wherein the sheet comprises a lamination of several layers of high modulus, collimated filaments embedded in a matrix and wherein at least one layer is characterized by the filaments thereof being oriented at an angle to the fold lines.

16. The composite article as recited in claim 13 further comprising two filament composite facing sheets bonded to and sandwiching the folded sheet therebetween.

17. The composite article as recited in claim 16 wherein the filaments within the facing sheets are oriented at an angle to the fold lines.

18. The composite article as recited in claim 13 wherein the fold line locations of the sheet, prior to folding, fan out to provide taper to the folded article.

19. A composite blade having an upper surface and a lower surface and comprising a plurality of columnar elements bonded together along adjacent complementary interfaces, each of said elements characterized by:

a bundled core of high modulus, substantially parallel, core filaments embedded in a core matrix; and

a sheet of high modulus, substantially parallel, sheet filaments embedded in a sheet matrix; and

wherein

the longitudinal axes of the sheet filaments are oriented at an angle to the core filaments; and

said sheet is wrapped and bonded about said core such that at least a portion of the sheet filaments runs transverse to the core filaments through the blade in a direction from the upper surface to the lower surface, at the interfaces.

20. The composite blade as recited in claim 19 wherein the bundled core of filaments is twisted along its longitudinal axis.

21. The composite blade as recited in claim 20 wherein the direction of twist is such as to counter the inherent blade untwist under centrifugal loads.

22. In a method of manufacturing a composite article, the step of accordian folding a sheet of high modulus collimated filaments embedded in a matrix, with the fold lines angled with respect to the longitudinal axes of the filaments and the distance between fold lines substantially equal to the thickness of the article.