Granted Patent B2

US 12,331,657 · App. 18/314,499 · Granted Jun 17, 2025

Inventors: Nicholas Joseph Kray (Mason, OH); Elzbieta Kryj-Kos (Liberty Township, OH)

Assignee: General Electric Company

F01D5/282F05B2280/6003

Abstract

Claims (32)

1. A composite airfoil, comprising:

an airfoil core including a composite core comprising a three-dimensional, woven fiber network;

a wall completely surrounding the airfoil core, including a first set of stacked plies including a first type of ply having directional fibers extending in a first direction, and defining at least a portion of an exterior surface, the exterior surface extending between a leading edge and a trailing edge to define a chordwise direction and between a root and a tip to define a spanwise direction; and

at least one stiffener located in at least one pocket defined by the composite core and the wall, wherein the at least one stiffener is located at the at least one pocket, the at least one stiffener having a second set of stacked plies including a second type of ply having directional fibers extending in a pre-determined direction associated with a pre-determined stiffness of the at least one stiffener;

wherein the at least one stiffener is oriented relative to the spanwise direction so as to provide torsional stiffening.

2. The composite airfoil of claim 1 wherein the wall comprises at least one laminate skin defined by the first set of stacked plies and having a first stiffness and the at least one stiffener comprises a laminate stiffener defined by the second set of stacked plies and having a second stiffness.

3. The composite airfoil of claim 2 wherein the second set of stacked plies includes both the first type of ply and the second type of ply with a greater number of the second type of ply defining the second set of stacked plies.

4. The composite airfoil of claim 1 wherein the at least one stiffener is oriented with respect to the spanwise direction at an angle of between or equal to 30 degrees and 60 degrees.

5. The composite airfoil of claim 1 wherein the at least one stiffener is multiple stiffeners.

6. An airfoil for a turbine engine, which generates a hot gas fluid flow, the airfoil comprising:

a wall comprising a set of stacked plies and defining an exterior surface along which the hot gas fluid flow flows and extending between a leading edge and a trailing edge to define a chordwise direction and between a root and a tip to define a spanwise direction, the wall bounding an interior;

a composite core located within the interior and surrounded entirely by the wall;

at least one stiffener located between the composite core and the exterior surface, the at least one stiffener comprising laminate or one or more layers of plies; and

at least one pocket defined by the composite core and the wall, wherein the at least one stiffener is located at the at least one pocket.

7. The airfoil of claim 6 further comprising at least one laminate skin defining at least a portion of the exterior surface.

8. The airfoil of claim 7 wherein the at least one laminate skin is multiple laminate skins together defining the exterior surface.

9. The airfoil of claim 7 wherein the at least one stiffener is oriented with respect to the spanwise direction at an angle of between or equal to 30 degrees and 60 degrees.

10. The airfoil of claim 7 wherein the at least one laminate skin comprises a first set of directional fibers extending in a first direction defining a first stiffness and the at least one stiffener comprises a second set of directional fibers extending in a second direction defining a second stiffness.

11. The airfoil of claim 10 wherein the second stiffness is 5%, or more, stiffer than the first stiffness.

12. The airfoil of claim 10 wherein the first direction is different than the second direction.

13. The airfoil of claim 10 wherein the first direction is the same as the second direction.

14. The airfoil of claim 6 wherein the at least one stiffener is multiple stiffeners.

15. A composite airfoil, comprising:

an airfoil core;

a wall surrounding the airfoil core, the wall comprising at least one laminate skin defined by a first set of stacked plies and having a first stiffness, the first set of stacked plies including a first type of ply having directional fibers extending in a first direction, and the wall defining at least a portion of an exterior surface, the exterior surface extending between a leading edge and a trailing edge to define a chordwise direction and between a root and a tip to define a spanwise direction; and

at least one stiffener located between the airfoil core and the wall, the at least one stiffener comprising a laminate stiffener defined by a second set of stacked plies and having a second stiffness, the second set of stacked plies including both the first type of ply and a second type of ply with a greater number of the second type of ply defining the second set of stacked plies, and the second type of ply having directional fibers extending in a pre-determined direction associated with a pre-determined stiffness of the at least one stiffener;

wherein the at least one stiffener is oriented relative to the spanwise direction so as to provide torsional stiffening.

16. The composite airfoil of claim 15 wherein the second stiffness is 5%, or more, stiffer than the first stiffness.

17. The composite airfoil of claim 15 wherein the first direction is the same as the pre-determined direction.

18. The composite airfoil of claim 15 wherein the first direction is different than the pre-determined direction.

19. The composite airfoil of claim 15 , further comprising at least one pocket in one of the airfoil core or the at least one laminate skin, wherein the at least one stiffener is located in the at least one pocket.

20. The composite airfoil of claim 15 wherein the at least one stiffener is multiple stiffeners.

Assignments (1)

Continuity (1)

References Cited (19)