Engine hot section component and method for making the same

Patent metadata

Field	Value
Publication number	US-9677180-B2
Application number	US-201113336394-A
Country	US
Kind code	B2
Filing date	Dec 23, 2011
Priority date	Dec 30, 2010
Publication date	Jun 13, 2017
Grant date	Jun 13, 2017

Abstract

One embodiment of the present invention is a unique engine hot section component having a coating system operative to reduce heat transfer to the hot section component. Another embodiment is a unique method for making a gas turbine engine hot section component with a coating system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines, hot section components and coating systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

First claim

What is claimed is:

1. A method for manufacturing a gas turbine engine hot section component, the method comprising:
selecting a first radiation barrier coating composition comprising tantalum oxide for a first refraction index;
selecting a second radiation barrier coating composition comprising mullite for a second refraction index different from the first refraction index;
performing a surface finish enhancing treatment on the gas turbine engine hot section component; and
after performing the surface finish enhancing treatment, applying a plurality of pairs of alternating layers of the first radiation barrier coating composition and the second radiation barrier coating composition onto the gas turbine engine hot section component.

2. The method of claim 1 , wherein applying the plurality of pairs of alternating layers of the first radiation barrier coating composition and the second radiation barrier coating composition comprises applying a layer of the first radiation barrier coating composition to the gas turbine engine hot section component and applying a layer of the second radiation barrier coating composition to the layer of the first radiation barrier coating composition.

3. The method of claim 1 , wherein applying the plurality of pairs of alternating layers of the first radiation barrier coating composition and the second radiation barrier coating composition comprises applying a layer of the second radiation barrier coating composition to the gas turbine engine hot section component and applying a layer of the first radiation barrier coating composition to the layer of the second radiation barrier coating composition.

4. A method for manufacturing an engine hot section component, the method comprising:
applying a thermal barrier coating (TBC) to the engine hot section component;
performing a surface finish enhancing treatment on the TBC, wherein the surface finish enhancing treatment enhances reflective properties of the TBC; and
after performing the surface finish enhancing treatment on the TBC, applying a plurality of pairs of alternating layers of a first radiation barrier coating composition and a second radiation barrier coating composition onto the TBC, wherein the first radiation barrier coating composition comprises tantalum oxide and has a first refraction index, and wherein the second radiation barrier coating composition comprises mullite and has a second, different refraction index.

5. The method of claim 4 , wherein the TBC includes Yttria-Stabilized Zirconia (YSZ).

6. The method of claim 4 , further comprising applying a bond coat to the engine hot section component prior to applying the TBC.

7. The method of claim 6 , wherein the bond coat is an MCrAlY bond coat, and where M=Co, Ni or Co/Ni.

8. The method of claim 4 , further comprising applying an adhesion aid to the TBC prior to applying the first radiation barrier coating.

9. The method of claim 8 , wherein the adhesion aid includes at least one of alumina, mullite, a silicate, or zircon.

10. The method of claim 8 , further comprising performing a surface finish treatment on the adhesion aid prior to applying the first radiation barrier coating, wherein the surface finish treatment enhances reflective properties of the adhesion aid.

11. The method of claim 4 , wherein the first radiation barrier coating is applied using large area filtered arc deposition (LAFAD) processing with ion assisted arc deposition (IAAD).

12. The method of claim 4 , wherein the first radiation barrier coating is applied using directed vapor deposition (DVD) processing.

13. The method of claim 12 , wherein an inert gas is used to transport a first radiation barrier coating material to the component to apply the first radiation barrier coating.

Assignees

• Naik Subhash K
• Teague Charles J
• Loebig James Carl
• Rolls Royce Corp
• Rolls-Royce North America Tech Inc

Inventors

• Naik Subhash K
• Teague Charles J
• Loebig James Carl

Classifications

• F05D2300/611

  Coating · CPC title

• Y02T50/67

  Cross-Sectional Technologies · mapped topic

• C23C28/3215

  at least one MCrAlX layer · CPC title

• F05D2300/504

  Reflective properties · CPC title

• F01D5/288

  Protective coatings for blades · CPC title