HOLLOW FAN BLADE FOR A GAS TURBINE ENGINE

• US 20160177732A1
• Filed: 07/20/2015
• Published: 06/23/2016
• Est. Priority Date: 07/22/2014
• Status: Abandoned Application

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: McComb, Patrick J., Whitehurst, Sean A.
• Application Number:
  US14/803,237
• Publication Number:
  US 20160177732A1
• Time in Patent Office: Days
• US Class Current: 1/1
• 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 5/18 Hollow blades, i.e. blades with cooling or heating channels or cavities structure of hollow blades in general F01D5/147; Heating, heat-insulating or cooling means on blades
• CPC Class Codes: F01D 5/28 Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: F05D 2300/612 Foam
• CPC Class Codes: F05D 2300/615 Filler
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A blade includes a hollow metal airfoil having an opening to an internal cavity in a first major surface. A metal cover is adhesively bonded to the airfoil around the opening. The cover encloses the cavity and provides a continuous first major surface. The cavity is divided into at least first and second subcavities. A different filler material is disposed within the first and second subcavities.

Claims

1. A blade comprising:

a root; and

an airfoil connected to the root and formed from a first metallic material, the airfoil comprising;

first and second major surfaces;

an internal cavity comprising at least one rib dividing the internal cavity into at least first and second subcavities;

a first filler material disposed within the first subcavity; and

a second filler material disposed within the second subcavity, wherein the first filler material is different than the second filler material.

2. The blade of claim 1, further comprising:

an opening in the first major surface; and

a cover covering the opening.

3. The blade of claim 2, further comprising a socket around the opening, wherein the cover is received in the socket.

4. The blade of claim 3, further comprising an adhesive bond between the cover and the socket

5. The blade of claim 1, wherein the first filler material and the second filler material each comprise a material selected from the group consisting of:

a plastic, a composite, a non-metallic foam, a solid metal, a metallic foam, and a gas.

6. The blade of claim 1, wherein the second filler material comprises a material selected from the group consisting of:

a plastic, a composite, a non-metallic foam, a solid metal, a metallic foam, and a gas.

7. The blade of claim 5, wherein the metallic foam is selected from the group consisting of:

6XXX-series aluminum alloy, and 7XXX-series aluminum alloy.

8. The blade of claim 2, further comprising an adhesive bond between the cover and the at least one rib.

9. The blade of claim 2, wherein the at least one rib extends between the cover and the second major surface.

10. The blade of claim 2, further comprising an adhesive bond between the cover and at least one of the first and second filler material disposed within the cavity.

11. The blade of claim 1, further comprising a sheath formed from a second metallic material and covering a portion of the airfoil.

12. The blade of claim 1, wherein the first metallic material is a 7XXX-series aluminum alloy.

13. The blade of claim 11, wherein the second metallic material is a material selected from the group consisting of:

titanium, and nickel alloy.

14. The blade of claim 1, wherein the blade comprises a fan blade of a gas turbine engine.

15. The blade of claim 1, wherein the first filler material comprises a first density, the second filler material comprises a second density, and the first density is different than the second density.

16. A gas turbine engine comprising:

a fan section, a compressor section, a combustor section and a turbine section in serial flow communication;

at least one of the fan section, the compressor section and the turbine section including a blade comprising;

a root; and

an airfoil connected to the root and formed from a first metallic material, the airfoil comprising;

first and second major surfaces;

an internal cavity comprising at least one rib dividing the internal cavity into at least first and second subcavities;

a first filler material disposed within the first subcavity;

a second filler material disposed within the second subcavity, wherein the first filler material is different than the second filler material.

17. The gas turbine engine of claim 16, further comprising:

an opening in the first major surface; and

a cover covering the opening.

18. The gas turbine engine of claim 16, wherein the first filler material and the second filler material each comprise a material selected from the group consisting of:

a plastic, a composite, a non-metallic foam, a solid metal, a metallic foam, and a gas.

19. The gas turbine engine of claim 17, wherein the metallic foam is selected from the group consisting of:

6XXX-series aluminum alloy, and 7XXX-series aluminum alloy.

20. The gas turbine engine of claim 16, wherein the first filler material comprises a first density, the second filler material comprises a second density, and the first density is different than the second density.