Composite sandwich with improved ballistic toughness

• US 20060093847A1
• Filed: 11/02/2004
• Published: 05/04/2006
• Est. Priority Date: 11/02/2004
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Hornick, David Charles, Foose, Andrew, Treat, Robert Kenneth
• Application Number:
  US10/979,265
• Publication Number:
  US 20060093847A1
• Time in Patent Office: Days
• US Class Current: 428/523
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• CPC Class Codes: F02K 3/04 the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
• CPC Class Codes: F05D 2220/327 to drive shrouded, high solidity propeller
• CPC Class Codes: F05D 2250/283 honeycomb
• CPC Class Codes: F05D 2300/433 Polyamides, e.g. NYLON
• CPC Class Codes: F05D 2300/44 Resins
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/612 Foam
• CPC Class Codes: F05D 2300/614 Fibres or filaments
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 428/24149 Honeycomb-like
• CPC Class Codes: Y10T 428/31938 Polymer of monoethylenically unsaturated hydrocarbon

Abstract

A composite structure having improved ballistic toughness and suitable for use in a fan containment case is provided. The composite structure includes a plurality of core layers, a plurality of inner plies position between adjacent ones of the core layers, each of the inner plies being formed from an organic matrix composite, an inner skin located adjacent an innermost one of the core layers, and an outer skin located adjacent an outermost one of the core layers. In a preferred embodiment, the core layers are formed from a honeycomb material made from aluminum or an aluminum alloy.

Claims

1. A composite structure comprising:

three core layers;

each of said core layers being formed from an aluminum or aluminum alloy honeycomb material;

a plurality of inner plies positioned between adjacent ones of said core layers, each of said inner plies being formed from an organic matrix composite;

an inner skin located adjacent an innermost one of said core layers; and

an outer skin located adjacent an outermost one of said core layers.

5. A composite structure according to claim 1, wherein each said core layer has a thickness in the range of 0.1 to 1.5 inches and each of said inner plies has a thickness in the range of 0.08 to 0.25 inches.

6. A composite structure according to claim 1, wherein each of said inner and outer skins is formed from an organic matrix material.

7. A composite structure according to claim 1, wherein said organic matrix material comprises a plurality of fibers surrounded by a matrix and said fibers are selected from the group consisting of Fiberglass, aramid, carbon and mixtures thereof.

8. A composite structure according to claim 7, wherein said matrix is selected from the group consisting of epoxy, bismaleimide, polyamide resins, and mixtures thereof.

2-3. -3. (canceled)

4. A composite structure comprising:

three core layers;

a plurality of inner plies positioned between adjacent ones of said core layers, each of said inner plies being formed from an organic matrix composite;

an inner skin located adjacent an innermost one of said core layers;

an outer skin located adjacent an outermost one of said core layers; and

wherein each of said core layers is formed from a foam material.

15. A composite structure according to claim 4, wherein each said core layer has a thickness in the range of from 0.1 to 1.5 inches and each of said inner plies has a thickness in the range of from 0.08 to 0.25 inches.

9. A gas turbine engine comprising:

a fan having a plurality of blades;

a fan containment case surrounding said fan; and

said fan containment case being formed from a composite structure comprising three core layers, each of said core layers being formed from a foam material or an aluminum or aluminum alloy honeycomb material, a plurality of inner plies positioned between adjacent ones of said core layers, each of said inner plies being formed from an organic matrix composite, an inner skin located adjacent an innermost one of said core layers, and an outer skin located adjacent an outermost one of said core layers.

11. A gas turbine engine according to claim 9, wherein each of said inner and outer skins is formed from an organic matrix composite.

12. A gas turbine engine according to claim 11, further comprising means for retaining a broken fan blade fragment surrounding said composite structure.

13. A gas turbine engine according to claim 12, wherein said retaining means comprises a plurality of plies formed from an aromatic polyamide fiber material.

10. (canceled)

14. A composite structure comprising:

a plurality of core layers;

a plurality of inner plies positioned between adjacent ones of said core layers, each of said inner plies being formed from an organic matrix composite, said organic matrix material comprising a plurality of fibers surrounded by a matrix, said fibers being selected from the group consisting of Fiberglass, aramid, carbon, and mixtures thereof, and said matrix being selected from the group consisting of bismaleimide, polyamide resins, and mixtures thereof;

an inner skin located adjacent an innermost one of said core layers; and

an outer skin located adjacent an outermost one of said core layers.

16. A gas turbine engine comprising:

a fan having a plurality of blades;

a fan containment case surrounding said fan;

said fan containment case being formed from a composite structure comprising a plurality of core layers, a plurality of inner plies positioned between adjacent ones of said core layers, each of said inner plies being formed from an organic matrix composite, an inner skin located adjacent an innermost one of said core layers, and an outer skin located adjacent an outermost one of said core layers; and

means for retaining a broken fan blade fragment surrounding the outer skin, said retaining means supplying a compression load which generates shear forces in the core layers of the composite structure.

17. The gas turbine engine of claim 16, wherein said retaining means comprises an aromatic polyamide fiber wrap surrounding the outer skin.

18. The gas turbine engine of claim 17, wherein said aromatic polyamide fiber wrap comprises a plurality of plies of an aromatic polyamide fiber.