Seal coating

Patent metadata

Field	Value
Publication number	US-2016201498-A1
Application number	US-201514883289-A
Country	US
Kind code	A1
Filing date	Oct 14, 2015
Priority date	Dec 15, 2014
Publication date	Jul 14, 2016
Grant date	—

Abstract

A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.

First claim

1 . A method of forming a coating comprising:
disposing a substrate having a plurality of protrusions on a seal; depositing a topcoat over the protrusions; creating a wear pattern in the topcoat; and converting the topcoat.

2 . The method of claim 1 , wherein the seal is a blade outer air seal.

3 . The method of claim 1 , wherein the topcoat comprises a thermally insulating ceramic material having a porosity between 5 and 70 volume percent.

4 . The method of claim 1 , wherein the topcoat comprises segmented portions defining a plurality of faults extending from the plurality of protrusions through the topcoat.

5 . The method of claim 1 , wherein depositing the topcoat over the plurality of protrusions forms a surface having a plurality of dimples.

6 . The method of claim 5 , wherein creating a wear pattern comprises rubbing a blade tip against the topcoat during an initial rub event.

7 . The method of claim 6 , wherein rubbing the blade tip against the topcoat during the initial rub phase forms a channel depth that is less than a depth of the plurality of dimples.

8 . The method of claim 7 , wherein the wear pattern allows for approximately equal wear to the blade tip and the seal.

9 . The method of claim 1 , converting the topcoat comprises running an engine to expose the seal to a surface temperature of at least 1950° F. (1066° C.).

10 . A turbine section comprising:
a casing; a plurality of blades within the casing; a substrate deposited on the casing having a plurality of protrusions; and an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat.

11 . The turbine of claim 10 , wherein the plurality of protrusions extend from the substrate towards the plurality of blades.

12 . The turbine of claim 10 , wherein the plurality of protrusions extend from the substrate at a substantially uniform height of at least 0.01 inches (0.0254 centimeters).

13 . The turbine of claim 10 , wherein the plurality of faults are gaps located between the plurality of protrusions.

14 . The turbine of claim 10 , wherein the plurality of protrusions forms a grid on the substrate.

15 . The turbine of claim 14 , wherein the topcoat comprises a plurality of dimples corresponding to a shape of the grid on the substrate.

16 . The turbine of claim 10 , wherein the unconverted topcoat comprises a thermally insulating ceramic material.

17 . The turbine of claim 10 , wherein the unconverted topcoat provides a wear pattern configured to allow approximately equal wear to a blade tip a seal.

18 . A method of forming a coating in a turbine, the method comprising:
applying the coating to a seal in the turbine; creating a channel in the coating during an initial rub event; and converting the coating during a high-temperature event, wherein converting the coating comprises preserving the channel created during the initial rub event.

19 . The method of claim 18 , wherein creating a channel in the coating comprises rapidly accelerating the turbine during a green run, causing rubbing of a blade tip against the coating.

20 . The method of claim 18 , wherein the high-temperature event comprises running an engine to expose the seal to a surface temperature above 1950° F. (1066° C.).

Assignees

• United Technologies Corp

Inventors

• Farris John R
• Mccaffrey Michael G

Classifications

• F01D11/12 Primary

  using a rubstrip, e.g. erodible. deformable or resiliently-biased part · CPC title

• F01D11/122

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

• F01D25/005

  Selecting particular materials · CPC title

• B05D3/007

  After-treatment · CPC title

• C23C4/11

  Oxides · CPC title