Thermal barrier coating system for turbine components

• US 6,670,046 B1
• Filed: 08/31/2000
• Issued: 12/30/2003
• Est. Priority Date: 08/31/2000
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Westinghouse Power Corporation
• Inventors: Xia, John Yuan
• Primary Examiner(s): Jones, Deborah
• Assistant Examiner(s): MCNEIL, JENNIFER C
• Application Number:
  US09/651,935
• Time in Patent Office: 1,216 Days
• Field of Search: 428/469, 428/472, 428/116, 428/117, 427/453, 427/566, 427/585, 427/593, 416/241.B, 416/241.R, 416/224, 416/229.R, 416/248, 416/229.A
• US Class Current: 428/469
• CPC Class Codes: C23C 28/044 coatings specially adapted for cutting tools or wear applications
• CPC Class Codes: C23C 30/00 Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process C23C26/00, C23C28/00 take precedence
• CPC Class Codes: C23C 4/00 Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge build-up welding B23K, e.g. B23K5/18, B23K9/04
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: Y10T 428/24149 Honeycomb-like
• CPC Class Codes: Y10T 428/24157 Filled honeycomb cells [e.g., solid substance in cavities, etc.]

Abstract

A composite thermal barrier coating system includes a first composite thermal barrier coating over a portion of a substrate, and a second deposited thermal barrier coating over edge portions of the substrate. The first composite coating is relatively thick and preferably includes friable graded insulation comprising an abradable honeycomb metallic structure filled with high thermal expansion ceramic hollow spheres in a phosphate bonded matrix. The second deposited edge coating is relatively thin and preferably comprises an electron beam physical vapor deposited thermal barrier coating comprising ZrO₂ and Y₂O₃. The friable graded insulation may be manufactured to thicknesses in excess of current thermal barrier coating systems, thereby imparting greater thermal protection. Superior erosion resistance and abrasion properties are also achieved. The composite thermal barrier coating system is useful on combustion turbine components such as ring seal segments, vane segment shrouds, transitions and combustors.

Claims

1. A thermal barrier coating system, comprising:

a metal substrate;

a first composite ceramic-comprising thermal barrier coat over a first portion of the substrate capable of withstanding temperatures in excess of 1500°

F.;

a second ceramic-comprising thermal barrier coating over at least an edge portion of the substrate adjacent a periphery of the first composite thermal barrier coating and capable of withstand temperature in excess of 1500°

F.; and

wherein the first composite thermal barrier coating is embedded in a recessed portion of the metal substrate.

2. The thermal barrier coating system of claim 1, wherein the first composite thermal barrier coating is embedded in the substrate a distance of from about 10 to about 80 percent of the thickness of the first composite thermal barrier coating.

3. The thermal barrier coating system of claim 1, wherein the first composite thermal barrier coating is embedded in the substrate a distance of from about 20 to about 50 percent of the thickness of the first composite thermal barrier coating.

4. A thermal barrier coating system, comprising:

a metal substrate;

a first composite ceramic-comprising thermal barrier coating over a first portion of the substrate capable of withstanding temperatures in excess of 1500°

F.;

a second ceramic-comprising thermal barrier coat over at least an edge portion of the substrate adjacent a periphery of the first composite thermal barrier coating, and capable of withstanding temperatures in excess of 1500°

F.;

wherein a peripheral region of the first composite thermal barrier coating has a thickness less than the thickness of the remainder of the first composite thermal barrier coating; and

wherein the peripheral region is tapered at an angle of from about 5 to about 10 degrees measured from a plane defined by the underlying metal substrate.

5. A method of making a composite thermal barrier coating system, comprising:

covering a portion of a metal substrate with a first composite ceramic-comprising thermal barrier coating capable of withstanding temperatures in excess of 1500°

F.; and

depositing a second ceramic-comprising thermal barrier coating over at least an edge portion of the substrate adjacent a periphery of the first composite thermal barrier coating and capable of withstanding temperatures in excess of 1500°

F.; and

wherein the first composite thermal barrier coating is embedded in a recess in the metal substrate, and has a thickness greater than a thickness of the second deposited thermal barrier coating.

6. A thermal barrier coating system, comprising:

a metal substrate;

a first composite ceramic-comprising thermal barrier coating over a portion of the substrate capable of withstanding temperatures in excess of 1500°

F.;

a second ceramic-comprising thermal barrier coating over a second portion of the substrate and generally adjacent the first portion of the substrate and capable of withstanding temperatures in excess of 1500°

F.; and

wherein the first composite thermal barrier coating comprises a metal support structure including honeycomb having open cells.

7. The thermal barrier coating system of claim 6, wherein the cells are filled with a ceramic filler material comprising a ceramic matrix with ceramic particles contained therein.

8. A thermal barrier coating system for a combustion turbine engine ring segment, the thermal barrier coating system comprising:

a first thermal barrier coat disposed over a non-rubbing portion of the ring segment to a first thickness; and

a second thermal barrier coating disposed over an abrasion portion of the ring segment to a second thickness greater than the first thickness, the second thermal barrier coating comprising a metal support structure extending through at least a portion of the second thickness for supporting the second thickness of thermal barrier coating.

9. The thermal barrier coating system of claim 8, wherein the metal support structure comprises a metal structure bonded to the abrasion portion of the ring segment and defining a plurality of open cells.

10. The thermal barrier coating system of claim 9, wherein the non-rubbing portion of the ring segment comprises an edge surrounding the abrasion portion of the ring segment.

11. The thermal barrier coating system of claim 8, wherein the metal support structure comprises a metal structure broad onto the abrasion portion of the ring segment and defining a honeycomb of open cells.

12. The thermal barrier coating of claim 8, further comprising:

a recessed region formed in the ring sent for receiving the second thermal barrier coating; and

the first thermal barrier coating being disposed over a non-recessed portion of the ring segment adjacent the recessed portion.

13. The thermal barrier coating of claim 12, wherein a depth of the recessed portion is from 10-80% of the second thickness.

14. The thermal barrier coating of claim 12, wherein a depth of the recessed portion is from 20-50% of the second thickness.

15. The thermal barrier coating system of claim 8, further comprising a peripheral region of the second thermal barrier coating comprising a tapered thickness.

16. A thermal barrier coating system comprising:

a first thermal barrier disposed over a first portion of a substrate, the first thermal barrier comprising a metal support structure bonded to a generally planar portion of the substrate and extending through at least a portion of a thickness of the first thermal barrier for supporting the first thermal barrier from the substrate; and

a second thermal barrier disposed on an edge portion of the substrate adjacent the first portion.