Low permeability high pressure compressor abradable seal for bare Ni airfoils having continuous metal matrix

Patent metadata

Field	Value
Publication number	US-10145258-B2
Application number	US-201514689492-A
Country	US
Kind code	B2
Filing date	Apr 17, 2015
Priority date	Apr 24, 2014
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

An air seal in a gas turbine engine comprising a substrate. A bond coating layer is adhered to the substrate. An abradable layer is adhered to the bond coating layer. The abradable layer comprises a metal matrix discontinuously filled with a soft ceramic material.

First claim

What is claimed is:

1. A seal comprising:
an abradable layer, the abradable layer comprising a metal matrix discontinuously filled with soft ceramic material clad with a metal, wherein the metal cladding comprises discrete elemental layers.

2. The seal of claim 1 , further comprising:
a substrate coupled to said abradable layer.

3. The seal of claim 1 , wherein the substrate is metallic.

4. The seal of claim 1 , further comprising:
a bond coating layer adhered to the substrate;
said abradable layer adhered to said bond coating.

5. The seal of claim 1 , wherein the metal matrix is discontinuously filled with at least one of a hexagonal boron nitride and a hexagonal boron nitride agglomerate.

6. The seal of claim 1 , wherein said metal matrix is discontinuously filled with a soft phase material.

7. The seal of claim 1 , wherein said abradable layer includes a metal fraction of from 10 V % to 36 V %.

8. A gas turbine engine comprising:
a first structure;
a second structure rotating relative to the first structure, wherein one of the first structure and second structure comprises a substrate; and
an abradable layer adhered to the substrate, the abradable layer comprising a metal matrix discontinuously filled with soft ceramic material clad with a metal, wherein the metal cladding comprises discrete elemental layers.

9. The gas turbine engine of claim 8 , wherein the substrate is an outer case, and the other rotating structure is a blade tip, wherein the blade tip is arranged adjacent the outer case without any intervening, separable seal structure.

10. The gas turbine engine of claim 9 , wherein the metal matrix is discontinuously filled with a hexagonal boron nitride agglomerate.

11. The gas turbine engine of claim 8 , wherein said metal matrix is discontinuously filled with a soft phase material.

12. The gas turbine engine of claim 8 , further comprising:
a bond coating layer adhered to the substrate; and
said abradable layer adhered to said bond coating layer.

Assignees

• United Technologies Corp

Inventors

• Strock Christopher W

Classifications

• F05D2300/2282

  of boron · CPC title

• F05D2260/95

  Preventing corrosion · CPC title

• F05D2230/42

  by hot isostatic pressing · CPC title

• F05D2230/312

  by plasma spraying · CPC title

• F05D2230/30

  with deposition of material · CPC title