Ceramic matrix composite (CMC) hollow blade and method of forming CMC hollow blade

Patent metadata

Field	Value
Publication number	US-10443410-B2
Application number	US-201715624893-A
Country	US
Kind code	B2
Filing date	Jun 16, 2017
Priority date	Jun 16, 2017
Publication date	Oct 15, 2019
Grant date	Oct 15, 2019

Abstract

A ceramic matrix composite (CMC) hollow blade includes a CMC airfoil, which includes at least one airfoil CMC ply, at least one cavity CMC ply, and an insert. The airfoil CMC ply defines the contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side. The cavity CMC ply defines a cavity within the CMC airfoil. The insert is located between the first edge and the cavity. The insert is wrapped by a CMC ply such that the CMC ply extends along the insert from the first side of the CMC airfoil across the mean camber line of the CMC airfoil and to the second side of the CMC airfoil. The CMC ply terminates on the second side of the CMC airfoil.

First claim

What is claimed is:

1. A ceramic matrix composite (CMC) hollow blade comprising a CMC airfoil comprising:
at least one airfoil CMC ply defining a contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side, the second side extending from the first edge to the second edge;
at least one cavity CMC ply defining a cavity within the CMC airfoil of the CMC hollow blade; and
a first insert located between the first edge and the cavity, the first insert being wrapped by one of the at least one airfoil CMC ply and the at least one cavity CMC ply such that the one of the at least one airfoil CMC ply and the at least one cavity CMC ply, starting off a mean camber line of the CMC airfoil, extends along the first insert from the first side of the CMC airfoil across the mean camber line and to the second side of the CMC airfoil, the one of the at least one airfoil CMC ply and the at least one cavity CMC ply terminating at a ply end on the second side of the CMC airfoil off the mean camber line.

2. The CMC hollow blade of claim 1 , wherein the first side is a pressure side and the second side is a suction side.

3. The CMC hollow blade of claim 1 , wherein the first side is a suction side and the second side is a pressure side.

4. The CMC hollow blade of claim 1 , wherein the first edge is a leading edge and the second edge is a trailing edge.

5. The CMC hollow blade of claim 1 , wherein the first edge is a trailing edge and the second edge is a leading edge.

6. The CMC hollow blade of claim 1 further comprising a second insert between the second edge and the cavity.

7. The CMC hollow blade of claim 6 , wherein the second insert is wrapped by another of the at least one airfoil CMC ply and the at least one cavity CMC ply extending along the second insert from the first side of the CMC airfoil across a mean camber line of the CMC airfoil and to the second side of the CMC airfoil.

8. The CMC hollow blade of claim 1 , wherein the one of the at least one airfoil CMC ply and the at least one cavity CMC ply crosses the mean camber line between the first edge and the cavity at least twice.

9. The CMC hollow blade of claim 1 , wherein the one of the at least one airfoil CMC ply and the at least one cavity CMC ply is one of the at least one cavity CMC ply.

10. A method of forming a ceramic matrix composite (CMC) hollow blade, the method comprising:
laying up at least one cavity CMC ply defining a cavity within a CMC airfoil of the CMC hollow blade;
placing a first insert on the at least one cavity CMC ply; and
laying up at least one airfoil CMC ply around the at least one cavity CMC ply and the first insert, the at least one airfoil CMC ply defining a contour of the CMC airfoil including a first edge, a second edge opposite the first edge, a first side extending from the first edge to the second edge, and a second side opposite the first side, the second side extending from the first edge to the second edge;
wherein the first insert is located between the cavity and the first edge; and
wherein the first insert is wrapped by one of the at least one airfoil CMC ply and the at least one cavity CMC ply such that the one of the at least one airfoil CMC ply and the at least one cavity CMC ply, starting off a mean camber line of the CMC airfoil, extends along the first insert from the first side of the CMC airfoil across the mean camber line and to the second side of the CMC airfoil, the one of the at least one airfoil CMC ply and the at least one cavity CMC ply terminating at a ply end on the second side of the CMC airfoil off the mean camber line.

11. The method of claim 10 , wherein the first side is a pressure side and the second side is a suction side.

12. The method of claim 10 , wherein the first side is a suction side and the second side is a pressure side.

13. The method of claim 10 , wherein the first edge is a leading edge and the second edge is a trailing edge.

14. The method of claim 10 , wherein the first edge is a trailing edge and the second edge is a leading edge.

15. The method of claim 10 further comprising placing a second insert between the second edge and the cavity.

16. The method of claim 15 further comprising wrapping the second insert by another of the at least one airfoil CMC ply and the at least one cavity CMC ply extending along the second insert from the first side of the CMC airfoil across a mean camber line of the CMC airfoil and to the second side of the CMC airfoil.

17. The method of claim 10 , wherein the one of the at least one airfoil CMC ply and the at least one cavity CMC ply crosses the mean camber line between the first edge and the cavity at least twice.

18. The method of claim 10 , wherein the one of the at least one airfoil CMC ply and the at least one cavity CMC ply is one of the at least one cavity CMC ply.

19. The method of claim 18 , wherein the one of the at least one airfoil CMC ply and the at least one cavity CMC ply extends across the mean camber line more than twice.

20. The CMC hollow blade of claim 9 , wherein the one of the at least one airfoil CMC ply and the at least one cavity CMC ply extends across the mean camber line more than twice.

Assignees

• Gen Electric

Inventors

• De Diego Peter
• Kittleson Jacob John

Classifications

• C04B35/71

  Ceramic products containing macroscopic reinforcing agents (C04B35/66 takes precedence {; infiltration of a porous ceramic matrix with a material forming a non-ceramic phase C04B41/00, reaction infiltration with Si in order to form SiC C04B35/573, in order to form Si3N4 C04B35/591}) · CPC title

• F01D5/282 Primary

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

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• C04B35/622

  Forming processes; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products · CPC title

• F05D2240/304

  related to the trailing edge of a rotor blade · CPC title