Airfoil, and method for manufacturing the same

Patent metadata

Field	Value
Publication number	US-10487667-B2
Application number	US-201414901910-A
Country	US
Kind code	B2
Filing date	Jul 1, 2014
Priority date	Jul 1, 2013
Publication date	Nov 26, 2019
Grant date	Nov 26, 2019

Abstract

A component for use in a gas turbine engine includes a first section, a second section, and a functionally graded section. The first section is made of a metal material. The second section is made of a ceramic material and/or a ceramic matrix composite material. The functionally graded section is disposed between the first section and the second section.

First claim

What is claimed is:

1. A component for use in a gas turbine engine, comprising:
an airfoil configured with a pressure side wall, a suction side wall, a rib and an aft cavity;
the pressure side wall and the suction side wall extending longitudinally between and connected at a leading edge and a trailing edge;
the rib extending laterally between the pressure side wall and the suction side wall;
the aft cavity extending laterally between the pressure side wall and the suction side wall, and the aft cavity extending longitudinally from the rib to the pressure side wall and the suction side wall at the trailing edge;
the airfoil comprising a first section consisting of a metal material, a second section consisting of a ceramic matrix composite material and a functionally graded section;
the first section forming the rib and a portion of the pressure side wall extending from the rib to the leading edge;
the second section forming a portion of the pressure side wall extending from the functionally graded section to the trailing edge; and
the functionally graded section forming a portion of the pressure side wall extending from the first section to the second section.

2. The component of claim 1 , wherein the functionally graded section is made of a combination of the metal material and the ceramic matrix composite material.

3. The component of claim 1 , wherein the metal material comprises a nickel-based superalloy.

4. The component of claim 1 , wherein the metal material comprises a cobalt-based superalloy.

5. The component of claim 1 , wherein the ceramic material comprises at least one of SiC, Si 3 N 4 , SiOxNy and Al 2 O 3 .

6. The component of claim 1 , wherein the ceramic material comprises at least one of C/SiC, SiC/SiC and SiC/C.

7. The component of claim 1 , wherein the functionally graded section includes at least one of a gradual variation in composition over a volume of the functionally graded section, or a gradual variation in structure over the volume, that results in a corresponding change in a property of the functionally graded section over the volume.

8. The component of claim 7 , wherein the property is melting point, strength or durability.

9. The component of claim 1 , wherein the component includes at least one of a forward cavity and a channel, through which a cooling fluid flow is operable to pass.

10. The component of claim 1 , wherein
the component is configured with a plurality of cooling apertures that permit a cooling fluid flow to pass there through to aid in cooling the component; and
the cooling fluid flow is operable to pass through at least one of the plurality of cooling apertures to minimize thermally-induced stress caused by differences in respective coefficients of thermal expansion of at least two of the first section, the second section and the functionally graded section.

11. The component of claim 10 , wherein at least one of the plurality of cooling apertures is disposed within a portion of the component in the first section proximate the functionally graded section.

12. The component of claim 1 , wherein the first section, the second section and the functionally graded section have different coefficients of thermal expansion relative to one another.

13. The component of claim 1 , wherein the component is included in a rotor blade.

14. The component of claim 1 , wherein the component is included in a guide vane.

15. The component of claim 1 , wherein
the airfoil is further configured with a channel wall, a forward cavity and a forward channel;
the channel wall extends from the rib;
the forward cavity is disposed forward of the aft cavity, and the forward cavity is defined between and by the rib and the channel wall; and
the forward channel is disposed proximate the leading edge of the component, and the forward channel is defined by the rib, the channel wall, the pressure side wall and the suction side wall.

16. The component of claim 15 , wherein the first section further forms the channel wall.

17. The component of claim 15 , wherein a plurality of cooling apertures extend through the rib to permit a cooling fluid flow to pass between the aft cavity and the forward channel.

18. The component of claim 15 , wherein a plurality of cooling apertures extend through the pressure side wall, and a plurality of cooling apertures extend through the suction side wall, to permit a cooling fluid flow passing within the forward channel to be discharged from the component.

19. The component of claim 1 , wherein
the first section further forms a portion of the suction side wall extending from the rib to the leading edge;
the second section further forms a portion of the suction side wall extending from the functionally graded section to the trailing edge; and
the functionally graded section further forms a portion of the suction side wall extending from the first section to the second section.

20. The component of claim 1 , wherein the portion of the pressure side wall formed by the functionally graded section extends from the rib to the second section.

21. A component for use in a gas turbine engine, comprising:
an airfoil configured with a pressure side wall, a suction side wall, a rib and an aft cavity;
the pressure side wall and the suction side wall extending longitudinally between and connected at a leading edge and a trailing edge;
the rib extending laterally between the pressure side wall and the suction side wall;
the aft cavity extending laterally between the pressure side wall and the suction side wall, and the aft cavity extending longitudinally from the rib to the pressure side wall and the suction side wall at the trailing edge;
the airfoil comprising a first section of a metal material, a second section of a ceramic matrix composite material and a functionally graded section;
the first section forming the rib and a portion of the suction side wall extending from the rib to the leading edge;
the second section forming a portion of the suction side wall extending from the functionally graded section to the trailing edge; and
the functionally graded section forming a portion of the suction side wall extending from the first section to the second section.

22. The component of claim 21 , wherein
the first section further forms a portion of the pressure side wall extending from the rib to the leading edge;
the second section further forms a portion of the pressure side wall extending from the functionally graded section to the trailing edge; and
the functionally graded section further forms a portion of the pressure side wall extending from the first section to the second section.

23. The component of claim 21 , wherein the portion of the suction side wall formed by the functionally graded section extends from the rib to the second section.

24. The component of claim 21 , wherein
the airfoil is further configured with a channel wall, a forward cavity and a forward channel;
the channel wall is formed by the first section and projects out from the rib;
the forward cavity is disposed forward of the aft cavity, and the forward cavity is defined between the rib and the channel wall; and
the forward channel is disposed proximate the leading edge of the component, and the forward channel is defined by the rib, the channel wall, the pressure side wall and the suction side wall.

25. The component of claim 21 , wherein
the first section consists of

Assignees

• United Technologies Corp

Inventors

• Slavens Thomas N
• Mironets Sergey
• Staroselsky Alexander
• Snyder Brooks E
• Martin Thomas J

Classifications

• F05D2300/2283

  of silicon · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title

• B23P15/04

  turbine or like blades from several pieces · CPC title

• F04D29/325

  for axial flow fans (blade mountings F04D29/34, blades F04D29/38) · CPC title