Fan blade with composite cover and sacrificial filler

Patent metadata

Field	Value
Publication number	US-10344772-B2
Application number	US-201415039268-A
Country	US
Kind code	B2
Filing date	Sep 29, 2014
Priority date	Nov 26, 2013
Publication date	Jul 9, 2019
Grant date	Jul 9, 2019

Abstract

A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening and at least one cavity for purposes of reducing the weight of the fan blade. The cover overlays the opening and includes a peripheral edge that is received in a slot defined by the body. The cavities are filled with a sacrificial material.

First claim

What is claimed:

1. A fan blade comprising:
a body having a pressure side, a suction side adjoining the pressure side along a leading edge and a trailing edge, the pressure side, the body having a base and a distal tip;
the suction side defining an opening communicating with one or more cavities, the opening having a perimeter;
the body further defining a slot extending from all or part of the perimeter away from the opening and into the body;
the body further including a lip extending inwardly toward the opening and terminating at the perimeter of the opening;
a semi-flexible cover comprising fiber or resin and having a peripheral edge that may be received into the slot to help secure the cover to the body, thereby covering part or all of the one or more cavities, the cover having an inner surface configured to face the opening; and
a filler material disposed within at least one of the one or more cavities, wherein the body further includes a lip extending inwardly toward the opening and terminating at the perimeter of the opening, wherein the body includes an inner wall that, with the lip defines the slot, the inner wall having an upper surface upon which the cover is located when the cover is located in the opening and a peripheral edge of the cover is received in the slot.

2. The fan blade of claim 1 wherein the filler material is a sacrificial material that can decompose, ablate or otherwise diminish in size or weight.

3. The fan blade of claim 1 wherein the filler material has a density less than that of the fan blade body.

4. The fan blade of claim 2 wherein:
the cover is made of a resin having a curing temperature; and
the sacrificial material has a melting point lower than the curing temperature.

5. The fan blade of claim 2 further comprising a flow path configured to allow the sacrificial material to escape from within the body.

6. The fan blade of claim 2 wherein;
the body defines at least one root opening at the fan blade base and at least one tip opening at the fan blade distal tip to allow the sacrificial material to escape from within the body.

7. The fan blade of claim 6 wherein:
the number of cavities is at least two;
the cavities are separated by walls; and
the walls define wall openings configured to allow for a flow of the sacrificial material through the wall openings.

8. A method for fabricating a fan blade of a turbofan gas turbine engine, the method comprising:
manufacturing a body including a pressure side and a suction side, the pressure side and the suction side being disposed between and connected to a leading edge and a trailing edge, the pressure side and the suction side also being disposed between and connected to a base and a distal tip, the suction side including a plurality of cavities that extend through the suction side and towards the pressure side, the cavities being surrounded by a slot that extends outwardly away from the cavities and into the body, the body further including a lip that extends inwardly towards the cavities and that at least partially defines the slot, wherein the body includes an inner wall that, with the lip defines the slot, the inner wall having an upper surface upon which a cover is located when the cover is located within an opening communicating with the plurality of cavities and a peripheral edge of the cover is received in the slot;
at least partially filling the cavities with a sacrificial material; and
covering the cavities with the cover by inserting the peripheral edge of the cover into the slot of the body so that the lip at least partially covers the cover.

9. The method of claim 8 comprising the additional step of removing at least some of the sacrificial material from the fan blade body.

10. The method of claim 8 wherein at least some of the sacrificial material is removed from the fan blade body.

11. The method of claim 10 wherein at least some of the sacrificial material is removed from the fan blade body after the cavities have been covered with the cover.

12. The method of claim 8 wherein at least some of the sacrificial material is removed from the body due to gravity or by being sucked out under negative pressure.

13. The method of claim 8 wherein the sacrificial material has a density less than that of the fan blade body.

14. The method of claim 8 comprising the additional step of:
making the cover using rapid resin transfer under a vacuum assisted cure.

15. The method of claim 14 wherein:
the cover is made of a resin having a curing temperature; and
the sacrificial material has a melting point lower than the curing temperature.

16. The method of claim 8 wherein:
the manufacturing step includes making the body with a flow path configured to allow the sacrificial material to escape from within the body.

17. The method of claim 8 wherein:
the manufacturing step includes making the body so that the body defines at least one root opening at the fan blade base and at least one tip opening at the fan blade distal tip to allow the sacrificial material to escape from within the body.

18. The method of claim 8 wherein:
the manufacturing step includes making the body with multiple cavities separated by walls, the walls defining wall openings configured to allow for a flow of the sacrificial material through the wall openings.

19. The method of claim 8 wherein the cover is fabricated from graphite epoxy material.

20. The method of claim 8 wherein the body is manufactured from a material selected from the group consisting of aluminum, an aluminum alloy, titanium, a titanium alloy and combinations thereof.

Assignees

• United Technologies Corp

Inventors

• Roche Charles H

Classifications

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F04D29/324

  Blades · CPC title

• F01D5/282 Primary

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F01D5/147

  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 title

• B29L2031/08

  Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers · CPC title