Hybrid airfoil for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-9835033-B2
Application number	US-201514659718-A
Country	US
Kind code	B2
Filing date	Mar 17, 2015
Priority date	Mar 26, 2012
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

A hybrid airfoil according to an exemplary aspect of the present disclosure includes, among other things, a leading edge portion made of a first material, a trailing edge portion made of a second material, and an intermediate portion between the leading edge portion and the trailing edge portion made of a non-metallic material. A rib is disposed between the leading edge portion and the intermediate portion. A protrusion of one of the rib and the intermediate portion is received within a pocket of the other of the rib and the intermediate portion.

First claim

What is claimed is:

1. A hybrid airfoil, comprising:
a leading edge portion made of a first material;
a trailing edge portion made of a second material;

an intermediate portion between said leading edge portion and said trailing edge portion, said intermediate portion made of a non-metallic material;
a rib disposed between said leading edge portion and said intermediate portion, wherein said rib includes a metallic structure; and
a protrusion of one of said rib and said intermediate portion is received within a pocket of the other of said rib and said intermediate portion.

2. The hybrid airfoil as recited in claim 1 , wherein said first material is a metallic material and said second material is a non-metallic material.

3. The hybrid airfoil as recited in claim 1 , wherein said first material and said second material are both metallic materials.

4. The hybrid airfoil as recited in claim 1 , wherein said non-metallic material is one of a ceramic material and a ceramic matrix composite (CMC) material.

5. The hybrid airfoil as recited in claim 1 , wherein each of said leading edge portion, said trailing edge portion and said intermediate portion extend between an inner platform and an outer platform.

6. The hybrid airfoil as recited in claim 5 , wherein said rib extends between said inner platform and said outer platform.

7. The hybrid airfoil as recited in claim 1 , wherein said intermediate portion includes an oxide material including at least one of silica, alumina, zirconia, yttria and titania.

8. The hybrid airfoil as recited in claim 1 , wherein said intermediate portion includes a non-oxide material including at least one of a carbide, a boride, a nitride, and a silicide.

9. A hybrid airfoil, comprising:
a leading edge portion made of a first material;
a trailing edge portion made of a second material;
an intermediate portion between said leading edge portion and said trailing edge portion, said intermediate portion made of a non-metallic material;
a rib disposed between said leading edge portion and said intermediate portion; and
a protrusion of one of said rib and said intermediate portion is received within a pocket of the other of said rib and said intermediate portion;
wherein a portion between said leading edge portion and said intermediate portion includes a pocket that receives another non-metallic portion.

10. The hybrid airfoil as recited in claim 9 , comprising an intermediate bonding layer disposed between said leading edge portion and said another non-metallic portion.

11. A hybrid airfoil, comprising:
a leading edge portion made of a first material;
a trailing edge portion made of a second material;
an intermediate portion between said leading edge portion and said trailing edge portion,
said intermediate portion made of a non-metallic material;
a rib disposed between said leading edge portion and said intermediate portion; and
a protrusion of one of said rib and said intermediate portion is received within a pocket of the other of said rib and said intermediate portion;
wherein said leading edge portion and said trailing edge portion include radial cooling passages and said intermediate portion excludes radial cooling passages.

12. A hybrid airfoil, comprising:
a metallic portion;
a first non-metallic portion connected to said metallic portion; and
a pocket formed in said metallic portion and configured to receive a second non-metallic portion, wherein said first non-metallic portion and said second non-metallic portion are either ceramic materials or ceramic matrix composite (CMC) materials.

13. The hybrid airfoil as recited in claim 12 , wherein said first non-metallic portion is an intermediate portion of said hybrid airfoil.

14. The hybrid airfoil as recited in claim 12 , wherein said second non-metallic portion is disposed between a leading edge portion and a rib of said hybrid airfoil.

Assignees

• United Technologies Corp

Inventors

• Mironets Sergey
• Pietraszkiewicz Edward F
• Staroselsky Alexander
• Zelesky Mark F

Classifications

• F01D5/147 Primary

  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

• F01D5/282

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

• F01D5/28

  Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion · CPC title

• F05D2240/122

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

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title