Turbine stator airfoil assemblies and methods for their manufacture

Patent metadata

Field	Value
Publication number	US-9289826-B2
Application number	US-201213621845-A
Country	US
Kind code	B2
Filing date	Sep 17, 2012
Priority date	Sep 17, 2012
Publication date	Mar 22, 2016
Grant date	Mar 22, 2016

Abstract

In accordance with an exemplary embodiment, a method of manufacturing a stator airfoil assembly includes forming an interior wall of a stator airfoil using an additive manufacturing technique, forming an exterior wall of the stator airfoil using the additive manufacturing technique, and forming a plurality of internal ribs between the interior wall and the exterior wall using the additive manufacturing technique. A cooling air circuit is formed in a space between the interior wall and the exterior wall. Further, the interior wall, the exterior wall, and the internal ribs are formed simultaneously as an integral structure by using the additive manufacturing technique.

First claim

What is claimed is:

1. A method of manufacturing a stator airfoil assembly, comprising:
forming an interior wall of a stator airfoil using an additive manufacturing technique;
forming an exterior wall of the stator airfoil using the additive manufacturing technique;
forming a flange over an outer radial wall cooling air opening of the stator airfoil using the additive manufacturing technique, wherein the flange is disposed radially over the opening such that the flange intersects with a radial projection of the opening and such that cooling air flows around the flange to enter into the airfoil; and
forming a plurality of internal ribs between the interior wall and the exterior wall using the additive manufacturing technique,
wherein a cooling air circuit is formed in a space between the interior wall and the exterior wall, and
wherein the interior wall, the exterior wall, and the internal ribs are formed simultaneously as an integral structure by using the additive manufacturing technique.

2. The method of claim 1 , wherein the additive manufacturing technique comprises direct metal laser sintering.

3. The method of claim 2 , wherein the interior wall, the exterior wall, and the internal ribs are formed of a high-temperature superalloy.

4. The method of claim 1 , wherein brazing or welding processes are not employed to form any of the interior wall, the exterior wall, or the internal ribs.

5. The method of claim 1 , wherein the flange comprises first, second, and third portions, wherein the first portion is connected with the outer radial wall and extends radially outward and away from the outer radial wall, wherein the second portion is connected with the first portion and extends from an outer radial end of the first portion axially rearward over the stator airfoil so as to pass through the radial projection of the opening, and wherein the third portion is connected with the second portion and extends form an axially rearward end of the second portion radially outward and away from the outer radial wall.

6. A stator airfoil assembly, comprising:
an airfoil exterior wall;
an airfoil interior wall disposed within the airfoil exterior wall and defining a cooling air flowpath between the interior wall and the exterior wall;
a flange disposed over an outer radial wall cooling air opening of the stator airfoil, wherein the flange is disposed radially over the opening such that the flange intersects with a radial projection of the opening and such that cooling air flows around the flange to enter into the airfoil; and
a plurality of internal ribs separating the interior wall from the exterior wall,
wherein the airfoil exterior, the airfoil interior, and the internal ribs are formed as an integral structure without any weld or braze joints connecting the airfoil exterior, the airfoil interior, or the internal ribs.

7. The stator airfoil assembly of claim 6 , wherein the airfoil exterior, the airfoil interior, and the internal ribs are formed using an additive manufacturing technique.

8. The stator airfoil assembly of claim 7 , wherein the additive manufacturing technique comprises direct metal laser sintering.

9. The stator airfoil assembly of claim 8 , wherein the interior wall, the exterior wall, and the internal ribs are formed of a high-temperature superalloy.

10. The stator airfoil assembly of claim 6 , wherein the flange comprises first, second, and third portions, wherein the first portion is connected with the outer radial wall and extends radially outward and away from the outer radial wall, wherein the second portion is connected with the first portion and extends from an outer radial end of the first portion axially rearward over the stator airfoil so as to pass through the radial projection of the opening, and wherein the third portion is connected with the second portion and extends form an axially rearward end of the second portion radially outward and away from the outer radial wall.

11. A stator airfoil assembly, comprising:
a hub endwall;
a tip endwall;
an airfoil disposed between the hub endwall and the tip endwall, the tip endwall including an opening to allow cooling air to flow into the airfoil; and
a flange of the tip endwall configured radially over the opening such that cooling air flows around the flange to enter into the airfoil, wherein the flange is disposed over the opening such that the flange intersects with a radial projection of the opening.

12. The stator airfoil assembly of claim 11 , wherein the hub endwall, the tip endwall, and the flange are formed as an integral structure without any weld or braze joints.

13. The stator airfoil assembly of claim 12 , wherein the hub endwall, the tip endwall, and the flange are formed using an additive manufacturing technique.

14. The stator airfoil assembly of claim 13 , wherein the additive manufacturing technique comprises direct metal laser sintering.

15. The stator airfoil assembly of claim 11 , wherein the hub endwall, the tip endwall, and the flange are formed of a high-temperature superalloy.

16. The stator airfoil assembly of claim 11 , wherein the flange comprises first, second, and third portions, wherein the first portion is connected with the tip end wall and extends radially outward and away from the tip end wall, wherein the second portion is connected with the first portion and extends from an outer radial end of the first portion axially rearward over the stator airfoil so as to pass through the radial projection of the opening, and wherein the third portion is connected with the second portion and extends form an axially rearward end of the second portion radially outward and away from the tip end wall.

Assignees

• Morris Mark C
• Godfrey Donald G
• Kington Harry Lester
• Honeywell Int Inc

Inventors

• Morris Mark C
• Godfrey Donald G
• Kington Harry Lester

Classifications

• B22F5/04 Primary

  of turbine blades · CPC title

• B22F10/60

  Treatment of workpieces or articles after build-up · CPC title

• B22F10/28

  Powder bed fusion, e.g. selective laser melting [SLM] or electron beam melting [EBM] · CPC title

• F05D2230/22

  by sintering · CPC title

• F01D5/147

  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 title