Turbine abradable air seal system

Patent metadata

Field	Value
Publication number	US-9938849-B2
Application number	US-201415026755-A
Country	US
Kind code	B2
Filing date	Sep 17, 2014
Priority date	Oct 2, 2013
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

An air seal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.

First claim

What is claimed is:

1. A seal system for a rotor blade assembly of a gas turbine engine, the seal system comprising:
a substrate;
a bond coat disposed on the substrate;
a ceramic interlayer disposed inboard of the bond coat;
an erosion resistant thermal barrier coating (E-TBC) layer inboard of the ceramic layer; and
an abradable layer disposed inboard of the erosion resistant thermal barrier coating (E-TBC) layer, wherein a transition layer is formed between the erosion resistant thermal barrier coating (E-TBC) layer and the abradable layer, the transition layer having a mixture of properties of the erosion resistant thermal barrier coating (E-TBC) layer and the abradable layer.

2. A seal system as recited in claim 1 , wherein the bond coat is metallic having a thickness of 1.27×10 −4 to 2.286×10 −4 meters (5 to 9 mils).

3. A seal system as recited in claim 1 , wherein the ceramic interlayer is 2.54×10 −6 to 7.62×10 −5 meters (0.1 to 3.0 mils) thick.

4. A seal system as recited in claim 1 , wherein the abradable layer is a porous, erosion resistant layer having a thickness of 5 to 50 mils (1.27×10 −4 to 1.27×10 −3 meters).

5. A seal system as recited in claim 1 , wherein the substrate layer is metallic.

6. A method for forming an air seal system for a rotor blade assembly of a gas turbine engine comprising:
applying a bond coat onto a substrate
applying a ceramic interlayer onto the bond coat;
applying an erosion resistant thermal barrier coating (E-TBC) layer onto the interlayer.
applying a transition layer inboard of the erosion resistant thermal barrier coating layer (E-TBC); and
applying an abradable layer inboard of the transition layer and the erosion resistant thermal barrier coating (E-TBC) layer.

7. A method as recited in claim 6 , wherein applying the bond coat includes high velocity oxygen fuel (HVOF) spraying a metallic bond coat material onto the substrate.

8. A method as recited in claim 6 , wherein applying the bond coat includes diffusion heat treating the bond coat and substrate at 1975° F. (1079° C.) in a protective atmosphere.

9. A method as recited in claim 6 , wherein applying the ceramic interlayer includes air plasma spraying a ceramic interlayer material onto the bond coat while the substrate and bond coat are held at an elevated temperature.

10. A method as recited in claim 6 , wherein applying the erosion resistant thermal barrier coating (E-TBC) layer includes air plasma spraying erosion resistant thermal barrier coating (E-TBC) layer material onto the ceramic interlayer.

11. A method as recited in claim 6 , wherein applying the abradable layer includes air plasma spraying abradable layer material onto the erosion resistant thermal barrier coating (E-TBC) layer.

Assignees

• United Technologies Corp

Inventors

• Strock Christopher W
• Lutjen Paul M
• Bruskotter Michael J

Classifications

• F05D2220/32

  in gas turbines · CPC title

• C23C28/32

  including at least one pure metallic layer · CPC title

• F16J15/40

  by means of fluid · CPC title

• F01D11/122 Primary

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F05D2240/55

  Seals · CPC title