HYBRID STRUCTURE FAN BLADE

• US 20100266415A1
• Filed: 04/16/2009
• Published: 10/21/2010
• Est. Priority Date: 04/16/2009
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Smith, Peter G., Strife, James R., Nardone, Vincent C., Lamm, Foster P., Viens, Daniel V.
• Granted Patent: US 8,083,489 B2
• Time in Patent Office: Days
• US Class Current: 416/226
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F04D 29/023 especially adapted for elastic fluid pumps
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/388 characterised by construction
• CPC Class Codes: F05D 2300/43 Synthetic polymers, e.g. plastics; Rubber
• CPC Class Codes: F05D 2300/437 Silicon polymers
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/615 Filler

Abstract

A hybrid fan blade for a gas turbine engine is provided that includes an airfoil and a composite panel. The airfoil has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The airfoil includes a plurality of cavities disposed in the first side of the airfoil, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The composite panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

Claims

1. A hybrid fan blade for a gas turbine engine, comprising:

an airfoil having a first side and a second side orientated opposite the first side, which first and second sides extend between a tip, a base, a leading edge and a trailing edge, the airfoil including a plurality of cavities disposed in the first side of the airfoil and extending inwardly toward the second side, which cavities collectively form an opening, and at least one rib disposed between the cavities and having a mounting surface disposed at a distal end, and a shelf disposed around the opening, the shelf having a first mounting surface; and

a first composite panel attached to the first mounting surface and the rib mounting surface, and which is sized to enclose the opening, wherein the first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

2. The fan blade of claim 1, further comprising at least one cavity disposed in the second side of the airfoil, which cavity forms an opening in the second side, and a second shelf disposed around the opening in the second side, the second shelf having a first mounting surface;

and

a second composite panel attached to the first mounting surface in the second shelf, and which second composite panel is sized to enclose the opening in the second side, wherein the second composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

3. The fan blade of claim 2, wherein a plurality of cavities is disposed in the second side, separated from one another by a rib.

4. The fan blade of claim 2, wherein at least one of the cavities extends through the airfoil between the first and second sides.

5. The fan blade of claim 1, wherein the composite panel has an inner surface and an outer surface, and comprises features extending out from the inner surface.

6. The fan blade of claim 1, wherein the composite panel is formed from a polymer matrix composite having at least one of woven, braided and laminated fibers.

7. The fan blade of claim 6, wherein the polymer matrix is composed of at least one of epoxy, polyester, bismaleimide, silicon, and/or polybenzimidazole, and wherein the fibers are at least one of graphite fibers, glass fibers, and organic fibers.

8. The fan blade of claim 1, wherein a filler material is disposed within at least one of the cavities.

9. The fan blade of claim 1, wherein the shelf further comprises a second mounting surface disposed around the opening, the shelf having a first mounting surface that extends between the first mounting surface and an outer surface of the first side.

10. The fan blade of claim 9, wherein the shelf has a height substantially equal to a thickness of the composite panel.

11. The fan blade of claim 1, wherein the shelf and the composite panel form a mating configuration.

12. A hybrid fan blade for a gas turbine engine, comprising:

an airfoil having a first side and a second side orientated opposite the first side, which first and second sides extend between a tip, a base, a leading edge and a trailing edge, the airfoil including a spar extending in a direction between the base and the tip, and extending in a direction between the leading edge and the trailing edge, the spar having a first side and a second side, wherein the spar defines an first opening in the first side having a first shelf disposed around the first opening, and a second opening in the second side having a second shelf disposed around the second opening; and

a first composite panel attached to the first shelf, which first composite panel is sized to enclose the first opening, wherein the first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil; and

a second composite panel attached to the second shelf, which second composite panel is sized to enclose the second opening, wherein the second composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

13. The fan blade of claim 12, wherein the spar includes a plurality of first ribs extending outwardly from the first side of the spar, each rib having a distal end attached to an inner surface of the first composite panel, and wherein the spar includes a plurality of second ribs extending outwardly from the second side of the spar, each second rib having a distal end attached to an inner surface of the second composite panel.

14. The fan blade of claim 13, wherein at least one of the first and second composite panels has a uniform thickness.

15. The fan blade of claim 13, wherein one or both of the first and second composite blades includes one or more features extending outwardly from the inner surface of the respective composite panel and attached to the spar.

16. The fan blade of claim 13, wherein one or both of the first and second composite blades includes one or more features extending outwardly from the inner surface of the respective composite panel, through the spar and are attached to other of the composite panels.

17. The fan blade of claim 12, wherein the first and second composite panels are formed from a polymer matrix composite having at least one of woven, braided and laminated fibers.

18. The fan blade of claim 17, wherein the polymer matrix is composed of at least one of epoxy, polyester, bismaleimide, silicon, and/or polybenzimidazole, and wherein the fibers are at least one of graphite fibers, glass fibers, and organic fibers.

19. The fan blade of claim 12, wherein a filler material is disposed between the spar and the first composite panel, and disposed between the spar and the second composite material.

20. A hybrid fan blade for a gas turbine engine, comprising:

an airfoil having a first side and a second side orientated opposite the first side, which first and second sides extend between a tip, a base, a leading edge and a trailing edge, the airfoil including a plurality of first cavities disposed in the first side of the airfoil and extending inwardly toward the second side, which first cavities collectively form an first side opening, and at least one rib disposed between the first cavities and having a mounting surface disposed at a distal end, and a first side shelf disposed around the first side opening, the first side shelf having a first mounting surface; and

a first panel attached to the first mounting surface and the rib mounting surface, and which is sized to enclose the opening, wherein the first composite panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

21. The hybrid fan blade of claim 20, wherein the first panel comprises a metallic material.

22. The hybrid panel of claim 21, wherein the airfoil includes a plurality of second cavities disposed in the second side of the airfoil and extending inwardly toward the first side, which second cavities collectively form an second side opening, and at least one rib disposed between the second side cavities and having a mounting surface disposed at a distal end, and a second side shelf disposed around the opening, the second side shelf having a first mounting surface;

and

a second panel attached to the second side shelf, which second side panel is sized to enclose the second opening, wherein the second side panel is a load bearing structure operable to transfer loads to the airfoil and receive loads from the airfoil.

23. The hybrid fan blade of claim 22, wherein the second panel comprises a metallic material.