Fire containment coating system for titanium

Patent metadata

Field	Value
Publication number	US-9834835-B2
Application number	US-201514624817-A
Country	US
Kind code	B2
Filing date	Feb 18, 2015
Priority date	Feb 18, 2015
Publication date	Dec 5, 2017
Grant date	Dec 5, 2017

Abstract

A coated substrate comprises: a metallic substrate; a bondcoat atop the substrate; and a ceramic barrier coat atop the bondcoat. The bondcoat has a combined content of one or more of molybdenum, chromium, and vanadium of at least 50 percent by weight.

First claim

What is claimed is:

1. A coated substrate comprising:
a metallic substrate;
a bondcoat atop the substrate; and
a ceramic barrier coat atop the bondcoat,

wherein:
the bondcoat comprises by weight at least 50.0 percent said molybdenum and at least 6 percent nickel.

2. The coated substrate of claim 1 wherein:
the metallic substrate is a titanium-based substrate.

3. The coated substrate of claim 2 wherein:
the metallic substrate comprises aluminum and vanadium.

4. The coated substrate of claim 1 wherein:
the metallic substrate is a steel substrate.

5. The coated substrate of claim 1 wherein:
the ceramic barrier coat comprises at least 50 weight percent zirconia.

6. The coated substrate of claim 1 wherein:
the ceramic barrier coat comprises yttria-stabilized zirconia.

7. The coated substrate of claim 1 wherein at a location along the substrate:
the bondcoat has a thickness of 25.4 micrometer to 0.41 millimeter; and
the ceramic barrier coat has a thickness of 0.10 millimeter to 1.27 millimeter.

8. The coated substrate of claim 1 wherein:
the substrate has a melting point of at most 1660° C.; and
the bondcoat has a melting point of at least 1550° C.

9. The coated substrate of claim 1 wherein:
the substrate has a melting point; and
the bondcoat has a melting point greater than the melting point of the substrate.

10. The coated substrate of claim 1 wherein:
the substrate has a melting point; and
the bondcoat has a melting point at least 25° C. greater than the melting point of the substrate.

11. A method for manufacturing the coated substrate of claim 1 , the method comprising:
applying the bondcoat by air plasma spray.

12. The method of claim 11 further comprising:
applying the ceramic barrier coat by air plasma spray.

13. A coated substrate comprising:
a metallic substrate;
a bondcoat atop the substrate; and
a ceramic barrier coat atop the bondcoat,

wherein:
the bondcoat comprises by weight at least 54 weight percent vanadium.

14. The coated substrate of claim 13 wherein:
the bondcoat comprises by weight at least 6.0 weight percent aluminum.

15. A gas turbine engine case half comprising:
a metallic substrate;
a bondcoat atop the substrate; and
a ceramic barrier coat atop the bondcoat,

wherein:
the bondcoat has a combined content of one or more of molybdenum, chromium, and vanadium of at least 50 percent by weight; and
the bondcoat and the ceramic barrier coat are along an inner diameter (ID) surface of the case half.

16. A gas turbine engine comprising:
a compressor case comprising:
a metallic substrate;
a bondcoat atop the substrate; and
a ceramic barrier coat atop the bondcoat, wherein the bondcoat has a combined content of one or more of molybdenum, chromium, and vanadium of at least 50 percent by weight;

a blade outer air seal stage carried by the compressor case; and
a stage of blades surrounded by the stage of blade outer air seals.

17. The gas turbine engine of claim 16 wherein one or both of:
the blades each have a titanium alloy substrate; and
the blade outer air seal stage has titanium alloy substrates.

18. The gas turbine engine of claim 16 wherein:
the bondcoat and barrier coat are on an inner diameter (ID) surface of the compressor case.

19. The gas turbine engine of claim 18 wherein:
an inner diameter (ID) surface of the compressor case surrounds the blade outer air seal stage.

20. The gas turbine engine of claim 16 wherein:
the bondcoat comprises by weight at least 50 weight percent said chromium.

21. The gas turbine engine of claim 16 wherein:
the bondcoat comprises by weight at least 6.0 percent nickel.

22. The gas turbine engine of claim 16 wherein:
the bondcoat comprises by weight at least 10.0 percent cobalt.

23. The gas turbine engine of claim 16 wherein:
the metallic substrate is a titanium-based substrate.

Assignees

• United Technologies Corp

Inventors

• Strock Christopher W
• Bintz Matthew E

Classifications

• C23C28/3455

  with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer · CPC title

• C23C28/347

  with layers adapted for cutting tools or wear applications · CPC title

• C22C27/04

  Alloys based on tungsten or molybdenum · CPC title

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F05D2300/2118

  Zirconium oxides · CPC title