Uber-cooled turbine section component made by additive manufacturing

Patent metadata

Field	Value
Publication number	US-9393620-B2
Application number	US-201213714561-A
Country	US
Kind code	B2
Filing date	Dec 14, 2012
Priority date	Dec 14, 2012
Publication date	Jul 19, 2016
Grant date	Jul 19, 2016

Abstract

A gas turbine airfoil having internal cooling passages is formed by additive manufacturing. Layers of superalloy powder are fused by an energy beam using a two-dimensional pattern providing unmelted areas forming passageways therein. Layers of the powder are added and fused using sufficient two-dimensional patterns to form the entire airfoil with the desired pattern of internal cooling passages. After completion of the formation of the airfoil, it may be hot isostatic pressed, directionally recrystallized, bond coated, and covered with a thermal barrier layer.

First claim

The invention claimed is:

1. A method of making a turbine section component of a gas turbine engine, the method comprising:
forming the component by additive manufacturing using superalloy powder to form the component with internal cooling passages located proximate an exterior surface of the component, at least some of the internal cooling passages within 0.050 inches to 0.010 inches of the exterior surface;
hot isostatic pressing the part to enhance mechanical properties, producing an initial plurality of grains resulting in an equiaxed grain structure in the part;
directional recrystallizing the part to introduce a directional grain structure and reduce the initial plurality of grains to a final plurality of directional grains in the part;
forming a bond coat on the surface; and
depositing a thermal barrier layer on the bond coat;
wherein a number of the final plurality of directional grains is less than 30.

2. The method of claim 1 , wherein forming the component by additive manufacturing includes:
loading a STL file into a fusing unit having a build plate, the STL file having slices defining the component with internal cooling passages for air flow therein;
placing a layer of superalloy powder on the build plate in the fusing unit;
directing an energy beam to the powder on the build plate to fuse selectively the powder in a shape of a two-dimensional slice from the STL file;
dropping the build plate by a distance equal to the thickness of one layer; and
adding a new layer of powder to the existing layer and fusing the powder in the shape of the next two-dimensional slice from the STL file and repeating with additional layers of powder until all the two-dimensional slices from the STL file have been used to form an airfoil in a plurality of layered passageways filled with un-fused powder.

3. The method of claim 2 , wherein the fusing unit is selected from an Electron Beam Melting unit and a Direct Metal Laser Sintering unit.

4. The method of claim 2 , wherein the STL file is formed by converting a CAD file of the airfoil and slicing the CAD file into thin slices of about 50μ to about 70μ thick.

5. The method of claim 2 , which further includes the step of removing unfused powder and verifying that the internal cooling passages are open.

6. The method of claim 1 , wherein the superalloy powder is selected from multi-crystal and single crystal powders.

7. The method of claim 1 , wherein the internal cooling passages in the airfoil have a shape selected from at least one of ellipsoidal, serpentine, layered, stacked and labyrinth.

8. The method of claim 1 , wherein the passages in the component have a diameter no larger than about 0.015 inches (0.0381 cm).

9. A method of forming an airfoil having internal cooling passages, the method comprising:
loading a STL file into a fusing unit having a build plate, the STL file having slices defining a gas turbine airfoil having internal cooling passages
placing a layer of superalloy powder on the build plate in the fusing unit;
directing an energy beam to the powder on the build plate to fuse the powder in the shape of a two-dimensional slice from the STL file;
adding a new layer of powder to the existing layer and fusing the powder in the shape of a next two-dimensional slice from the STL file and repeating with additional layers of powder until all the two-dimensional slices from the STL file have been used to form the airfoil with a plurality of internal cooling passages filled with un-fused powder; and
removing un-fused powder from the internal cooling passages; and
directionally recrystallizing the airfoil after verifying that the internal passages are open, thereby reducing an initial plurality of grains to a final plurality of directional grains in the airfoil;
wherein a number of the final plurality of directional grains is less than 30.

10. The method of claim 9 , wherein the fusing unit is selected from an Electron Beam Melting unit and a Direct Metal Laser Sintering unit.

11. The method of claim 9 , wherein the STL file is formed by converting a CAD file of the airfoil and slicing the CAD file into thin slices, the CAD file thin slices being about 50μ to about 70μ thick.

12. The method of claim 9 , wherein the superalloy powder is selected from multi-crystal and single crystal powders.

13. The method of claim 9 , wherein the passages in the airfoil have a shape selected from at least one of ellipsoidal, serpentine, layered, stacked and labyrinth.

14. The method of claim 9 , wherein the passages are washed with an abrasive slurry after verifying the passages are open to reduce surface roughness.

15. The method of claim 9 , wherein the passages in the airfoil have a diameter no larger than about 0.015 inches (0.0381 cm).

16. A gas turbine airfoil having internal cooling passages, the airfoil comprising:
an additive manufacturing superalloy airfoil body having a plurality of internal cooling passages, at least some of the internal cooling passages with a cross sectional dimension no larger than about 0.015 inches (0.0381 cm), and disposed within 0.050 inches to 0.010 inches of the exterior surface;
wherein the airfoil body is formed of a directional recrystallized superalloy having a final plurality of directional grains;
wherein a number of the final plurality of directional grains is less than 30.

17. The airfoil of claim 16 , wherein the internal cooling passages contain trips.

Assignees

• United Technologies Corp

Inventors

• Bales Daniel A
• Klucha Agnes
• Dolansky Gregory M

Classifications

• B22F10/68

  Cleaning or washing · CPC title

• B22F10/66

  by mechanical means · CPC title

• B22F10/64

  by thermal means (control of energy beam parameters for post heating B22F10/364) · CPC title

• B22F10/62

  by chemical means · CPC title

• B22F10/28

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