Frangible gas turbine engine airfoil

• US 10,450,870 B2
• Filed: 02/09/2016
• Issued: 10/22/2019
• Est. Priority Date: 02/09/2016
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Nandula, Phani, Subramanian, Suresh, Kray, Nicholas Joseph, Gemeinhardt, Gregory Carl
• Primary Examiner(s): Nguyen, Andrew H
• Application Number:
  US15/018,902
• Publication Number:
  US 20170226867A1
• Time in Patent Office: 1,351 Days
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• 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: F02C 3/06 the compressor comprising only axial stages F02C3/10 takes precedence
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.

Claims

1. An airfoil for an aircraft engine, the airfoil comprising:

a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base, wherein the airfoil defines an overall airfoil height between the airfoil base and airfoil tip, the plurality of composite plies including a first discontinuous ply including

a first ply segment,

a second ply segment,

a first butt joint disposed at a predetermined break location between the first ply segment and the second ply segment along a first fragment profile to frangibly attach the first and second ply segments, wherein the first butt joint is positioned at a first break height, the first break height being greater than 25% of the overall airfoil height, and

a second butt joint extending through the airfoil along a second fragment profile, wherein the second butt joint is positioned at a second break height, the second break height being greater than 75% of the overall airfoil height, and

the plurality of composite plies including at least one inner continuous ply extending unbroken from the airfoil base to the airfoil tip,

wherein the airfoil defines a first airfoil fragment extending from the airfoil base to the first fragment profile, a second airfoil fragment extending from the first fragment profile to the second fragment profile, and a third airfoil fragment extending from the second fragment profile to the airfoil tip, and wherein the airfoil is configured to separate into the fragments following an extreme impact event.

2. The airfoil of claim 1, wherein the plurality of composite plies includes a second discontinuous ply, the first and the second butt joints being staggered in the spanwise direction.

3. The airfoil of claim 1, wherein at least one of the first butt joint or the second butt joint extends at least partially along the chordwise direction.

4. The airfoil of claim 1, wherein the first ply segment includes a first composite material and the second ply segment includes a second composite material, the first composite material being different from the second composite material.

5. The airfoil of claim 1, wherein at least one of the first butt joint or the second butt joint extends at least partially in the spanwise direction.

6. The airfoil of claim 1, wherein at least one of the first butt joint or the second butt joint comprises a resin material.

7. The airfoil of claim 2, wherein the at least one inner continuous ply extends unbroken from the airfoil base to the airfoil tip and between the first and the second discontinuous plies.

8. A gas turbine engine defining a central axis, the gas turbine engine comprising:

an engine shaft extending along the central axis;

a compressor attached to the engine shaft and extending radially about the central axis;

a combustor positioned downstream of the compressor to receive a compressed fluid therefrom;

a turbine mounted on the engine shaft downstream of the combustor to provide a rotational force to the compressor; and

a fan section including a plurality of radially-extending fan blades operably connected to the engine shaft, each fan blade including an airfoil comprising a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base, wherein the airfoil defines an overall airfoil height between the airfoil base and airfoil tip, the plurality of composite plies including a first discontinuous ply including

a first ply segment,

a second ply segment,

a first butt joint disposed at a predetermined break location between the first ply segment and the second ply segment along a first fragment profile to frangibly attach the first and second ply segments, wherein the first butt joint is positioned at a first break height, the first break height being greater than 25% of the overall airfoil height, and

a second butt joint extending through the airfoil along a second fragment profile, wherein the second butt joint is positioned at a second break height, the second break height being greater than 75% of the overall airfoil height, and

the plurality of composite plies including at least one inner continuous ply extending unbroken from the airfoil base to the airfoil tip,

wherein the airfoil defines a first airfoil fragment extending from the airfoil base to the first fragment profile, a second airfoil fragment extending from the first fragment profile to the second fragment profile, and a third airfoil fragment extending from the second fragment profile to the airfoil tip, and wherein the airfoil is configured to separate into the fragments following an extreme impact event.

9. The gas turbine engine of claim 8, wherein the plurality of composite plies includes a second discontinuous ply, the first and the second butt joints being staggered in the spanwise direction.

10. The gas turbine engine of claim 8, wherein at least one of the first butt joint or the second butt joint extends at least partially along the chordwise direction.

11. The gas turbine engine of claim 8, wherein at least one of the first butt joint or second butt joint extends uninterrupted from the trailing edge to the leading edge.

12. The gas turbine engine of claim 8, wherein at least one of the first butt joint or the second butt joint extends at least partially in the spanwise direction.

13. The gas turbine engine of claim 8, wherein at least one of the first butt joint or the second butt joint comprises a resin material.

14. The gas turbine engine of claim 9, wherein the at least one inner continuous ply extends unbroken from the airfoil base to the airfoil tip and between the first and the second discontinuous plies.