Component, gas turbine component and method of forming

• US 10,119,473 B2
• Filed: 05/20/2015
• Issued: 11/06/2018
• Est. Priority Date: 05/20/2015
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Lin, Dechao, Kottilingam, Srikanth Chandrudu, Diao, Xiaoxue, Thomas, Nicholas
• Primary Examiner(s): Sung, Gerald L
• Assistant Examiner(s): Breazeal, William
• Application Number:
  US14/717,074
• Publication Number:
  US 20160341127A1
• Time in Patent Office: 1,266 Days
• Field of Search: 138120, 138155-157, 138145
• CPC Class Codes: F02C 7/222 Fuel flow conduits, e.g. manifolds
• CPC Class Codes: F05D 2230/50 Building or constructing in particular ways
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment manufacture with deposition of material F05D2230/30
• CPC Class Codes: F05D 2260/95 Preventing corrosion coating or surface treatment F05D2230/90
• CPC Class Codes: F05D 2300/1723 Nickel-Copper alloy, e.g. Monel

Abstract

Components are disclosed which include a first component section and a second component section joined to form a hollow structure defining a plenum having an interior surface, wherein the component sections each include mating ridges joined together along the length of the plenum, and a corrosion-resistant cladding layer including a corrosion-resistant material overlaying the interior surface of the plenum. In one embodiment, the component is a gas turbine combustor fuel manifold. A method of forming the components includes applying corrosion-resistant segments including a corrosion-resistant material to each of the surfaces of the component sections, and joining the component sections to form the component, wherein joining the component sections includes fusing the corrosion-resistant segments into the corrosion-resistant cladding layer, and joining the mating ridges of the component sections.

Claims

1. A component, comprising:

a first component section and a second component section joined to form a hollow structure, wherein;

the hollow structure is an annulus;

the hollow structure defines a plenum including an interior surface, a width and a length, the length being greater than the width and extending along a circumferential path of the hollow structure;

the first component section includes a first substrate material and the second component section includes a second substrate material;

the first component section includes a first mating ridge and a second mating ridge extending radially outward relative to the circumferential path;

the second component section includes a third mating ridge and a fourth mating ridge extending radially inward relative to the circumferential path;

the first mating ridge is joined to the third mating ridge along the length of the plenum; and

the second mating ridge is joined to the fourth mating ridge along the length of the plenum; and

a corrosion-resistant cladding layer including a corrosion-resistant material,

wherein the corrosion-resistant cladding layer overlays the interior surface of the plenum and the corrosion-resistant cladding layer includes a first corrosion-resistant segment overlaying the first component section fused to a second corrosion-resistant segment overlaying the second component section, and

wherein the component is a gas turbine component.

2. The component of claim 1, wherein the component is a gas turbine manifold.

3. The component of claim 2, wherein the gas turbine manifold is a combustor fuel manifold or a combustor gas manifold.

4. The component of claim 1, wherein the first substrate material and the second substrate material each, independently, is selected from the group consisting of steel, carbon steel, low-alloy steel, Cr—

Mo steel, and combinations thereof.

5. The component of claim 4, wherein the first substrate material and the second substrate material are each independently carbon steel or Cr—

Mo steel.

6. The component of claim 1, wherein the corrosion-resistant material is selected from the group consisting of a nickel-based alloy, a stainless steel, or combinations thereof.

7. The component of claim 1, wherein the corrosion-resistant cladding layer includes a thickness of between 0.005 inches to 0.05 inches.

8. A gas turbine component, comprising:

a first component section and a second component section joined to form a combustor fuel manifold, wherein;

the combustor fuel manifold is an annulus;

the combustor fuel manifold defines a plenum including an interior surface, a width and a length, the length being greater than the width and extending along a circumferential path of the combustor fuel manifold;

the first component section includes a first substrate material and the second component section includes a second substrate material;

the first component section includes a first mating ridge and a second mating ridge extending radially outward relative to the circumferential path;

the second component section includes a third mating ridge and a fourth mating ridge extending radially inward relative to the circumferential path;

the first mating ridge is joined to the third mating ridge along the length of the plenum; and

the second mating ridge is joined to the fourth mating ridge along the length of the plenum; and

a corrosion-resistant cladding layer including a corrosion-resistant material,

wherein the corrosion-resistant cladding layer overlays the interior surface of the plenum and the corrosion-resistant cladding layer includes a first corrosion-resistant segment overlaying the first component section fused to a second corrosion-resistant segment overlaying the second component section.

9. The gas turbine component of claim 8, wherein the first substrate material and the second substrate material each, independently, is selected from the group consisting of steel, carbon steel, low-alloy steel, Cr—

Mo steel, and combinations thereof.

10. The gas turbine component of claim 8, wherein the corrosion-resistant material is selected from the group consisting of a nickel-based alloy, a stainless steel, or combinations thereof.

11. The gas turbine component of claim 8, wherein the corrosion-resistant cladding layer includes a thickness of between 0.005 inches to 0.05 inches.

12. A method of forming a component, comprising:

providing a first component section and a second component section, wherein;

the first component section includes a first substrate material and the second component section includes a second substrate material;

the first component section includes a first mating ridge, a second mating ridge and a first surface between the first mating ridge and the second mating ridge; and

the second component section includes a third mating ridge, a fourth mating ridge, and a second surface between the first mating ridge and the second mating ridge;

applying a first corrosion-resistant segment including a corrosion-resistant material to the first surface and a second corrosion-resistant segment including the corrosion-resistant material to the second surface; and

joining the first component section and the second component section to form the component defining a plenum including an interior surface, a width and a length, the length being greater than the width, wherein joining the first component section and the second component section includes;

an additive root pass depositing corrosion-resistant material between the first corrosion-resistant segment and the second corrosion-resistant segment;

fusing the first corrosion-resistant segment and the second corrosion-resistant segment into a corrosion-resistant cladding layer, wherein the corrosion-resistant cladding layer overlays the interior surface of the plenum;

joining the first mating ridge to the third mating ridge along the length of the plenum; and

joining the second mating ridge to the fourth mating ridge along the length of the plenum,

wherein the component is a gas turbine component.

13. The method of claim 12, wherein the component is a gas turbine manifold.

14. The method of claim 13, wherein the gas turbine manifold is a combustor fuel manifold or a combustor gas manifold.

15. The method of claim 12, wherein the applying the first corrosion-resistant segment and the second corrosion-resistant segment includes affixing the first corrosion-resistant segment to the first surface and affixing the second corrosion-resistant segment to the second surface, wherein affixing includes a technique selected from the group consisting of welding, brazing, or a combination thereof.

16. The method of claim 15, wherein at least one of the first corrosion-resistant segment and the second corrosion resistant segment includes a plurality of sub-segments, each of which plurality of sub-segments is separately affixed to one of the first surface and the second surface.

17. The method of claim 12, wherein joining the first component section and the second component section includes a technique selected from the group consisting of welding, brazing, or a combination thereof.

18. The method of claim 12, wherein the corrosion-resistant material is selected from the group consisting of a nickel-based alloy, a stainless steel, or combinations thereof.

19. The method of claim 12, wherein the first substrate material and the second substrate material each, independently, is selected from the group consisting of steel, carbon steel, low-alloy steel, Cr—

Mo steel, and combinations thereof.

20. The method of claim 12, wherein joining the first component section and the second component section forms a hollow structure, and the hollow structure is an annulus.