Seal hook mount structure with overlapped coating

Patent metadata

Field	Value
Publication number	US-9181877-B2
Application number	US-201213731180-A
Country	US
Kind code	B2
Filing date	Dec 31, 2012
Priority date	Sep 27, 2012
Publication date	Nov 10, 2015
Grant date	Nov 10, 2015

Abstract

A seal is positioned radially outwardly of a compressor blade. The seal has a seal hook facing in a downstream direction. A seal mount has a mount hook for receiving the seal hook in a gap. The hook face in an upstream direction. The seal mount has an upstream portion extending from an upstream end into the gap. The mount hook extends into a web which extends in a downstream direction. A thermal barrier coating on the upstream portion of the seal mount extends to a downstream end. There is a thermal barrier coating on a radially inner surface of the mount hook, and along the web to a downstream coating end. An upstream end of the coating on the inner surface of the hook being formed axially upstream of the downstream end of the coating on the upstream portion.

First claim

The invention claimed is:

1. A compressor section for use in a gas turbine engine, comprising:
a compressor blade for rotating about an axis;
a seal positioned radially outwardly of said compressor blade, and said seal having a seal hook facing in a downstream direction;
a seal mount, said seal mount having a mount hook for receiving said seal hook in a gap, and said mount hook facing in an upstream direction, with said seal mount having an upstream portion extending from an upstream end into said gap, said mount hook then extending into a web which extends in a downstream direction; and
a thermal barrier coating on said upstream portion of said seal mount from an upstream end and extending to a downstream end, and there being thermal barrier coating on a radially inner surface of said mount hook, and along said web with an upstream end of said coating on said radially inner surface of said hook being formed axially upstream of said downstream end of said coating on said upstream portion.

2. The compressor section as set forth in claim 1 , wherein at least a portion of said gap is not provided with thermal barrier coating.

3. The compressor section as set forth in claim 1 , wherein a flow control feature is positioned upstream of said seal.

4. The compressor section as set forth in claim 1 , wherein a second seal hook is positioned at a downstream end of said seal, and said seal mount having a second mount hook, with said second seal hook received in said mount hook.

5. The compressor section as set forth in claim 4 , wherein said second mount hook also faces in an upstream direction.

6. A gas turbine engine comprising:
a fan, a compressor section, a combustion section and a turbine section;
said compressor section including a compressor blade for rotating about an axis;
a seal positioned radially outwardly of said compressor blade, and said seal having two seal hooks, said seal hooks both facing in a downstream direction;
a seal mount, said seal mount having a mount hook for receiving said seal hook in a gap, and said mount hook facing in an upstream direction, with said seal mount having an upstream portion extending from an upstream end into said gap, said mount hook then extending into a web which extends in a downstream direction; and
a thermal barrier coating on said upstream portion of said seal mount from an upstream end extending to a downstream end, and there being thermal barrier coating on a radially inner surface of said upstream one of said mount hooks, and along said web to a downstream coating end, with an upstream end of said coating on said inner surface of said hook being formed axially upstream of said downstream end of said coating on said upstream portion.

7. The gas turbine engine as set forth in claim 6 , wherein at least a portion of said gap is not provided with thermal barrier coating.

8. The gas turbine engine as set forth in claim 6 , wherein a flow control feature is positioned upstream of said seal.

9. The gas turbine engine as set forth in claim 6 , wherein a second seal hook is positioned at a downstream end of said seal, and said seal mount having a second mount hook, with said second seal hook received in said mount hook.

10. The gas turbine engine as set forth in claim 9 , wherein said second mount hook also faces in an upstream direction.

11. The gas turbine engine as set forth in claim 6 , wherein said turbine section includes a fan drive turbine for driving said fan, and there being a gear reduction between said fan drive turbine and said fan.

12. The gas turbine engine as set forth in claim 11 , wherein said fan delivering air into a bypass duct, and into said compressor section.

Assignees

• United Technologies Corp

Inventors

• Travis Brittany
• Maalouf Fadi S
• Firnhaber Michael C

Classifications

• F01D11/08 Primary

  for sealing space between rotor blade tips and stator (specially-shaped blade tips therefor F01D5/20) · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title

• F04D29/526

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

• F04D29/5853

  heat insulation or conduction · CPC title

• F04D29/644

  especially adapted for elastic fluid pumps · CPC title