Gas turbine engine impact liner

Patent metadata

Field	Value
Publication number	US-10113559-B2
Application number	US-201514850438-A
Country	US
Kind code	B2
Filing date	Sep 10, 2015
Priority date	Oct 14, 2014
Publication date	Oct 30, 2018
Grant date	Oct 30, 2018

Abstract

A gas turbine engine impact liner is disclosed. The impact liner may include a base sheet, a plurality of stanchions extending from the base sheet, and a plurality of supports, each being operatively associated with one of the plurality of stanchions.

First claim

What is claimed is:

1. An impact liner for a gas turbine engine, comprising:
a base sheet;
a perforated sheet spaced a distance from the base sheet;
a plurality of stanchions extending from the base sheet; and
a plurality of supports, each of the supports being operatively connected to one of the plurality of stanchions at a first end of the support, each support extending from a stanchion and coupled to the perforated sheet at a second end of the support opposite the first end, each support including a chamber formed therein interactive with the perforated sheet to act as a Helmholtz resonator.

2. The impact liner of claim 1 , wherein the supports further include a plurality of trusses extending from an inner wall.

3. The impact liner of claim 1 , wherein the supports further include nodes.

4. The impact liner of claim 2 , wherein the supports further include nodes and wherein the trusses meet at the nodes.

5. The impact liner of claim 3 , wherein the supports are coupled to the stanchions at the nodes.

6. The impact liner of claim 4 , wherein the supports are coupled to the stanchions at the nodes.

7. A gas turbine engine, comprising:
a compressor section;
a combustor section downstream of the compressor section;
a turbine section downstream of the combustor section; and
a fan section upstream of the compressor section, the fan section including an impact liner, the impact liner including:
a base sheet;
a perforated sheet spaced a distance from the base sheet;
a plurality of stanchions extending from the base sheet; and
a plurality of supports, each of the supports being operatively connected to one of the plurality of stanchions at a first end of the support, each support extending from a stanchion and coupled to the perforated sheet at a second end of the support opposite the first end, each support including a chamber formed therein interactive with the perforated sheet to act as a Helmholtz resonator.

8. The gas turbine engine of claim 7 , wherein the supports further include a plurality of trusses extending from an inner wall.

9. The gas turbine engine of claim 7 , wherein the supports further include nodes.

10. The gas turbine engine of claim 8 , wherein the supports further include nodes and wherein the trusses meet at the nodes.

11. The gas turbine engine of claim 9 , wherein the supports are coupled to the stanchions at the nodes.

12. The gas turbine engine of claim 10 , wherein the supports are coupled to the stanchions at the nodes.

13. A method for making an impact liner, comprising:
injection molding a stanchion-support combination, the stanchion-support combination having a first surface and a second surface and including:
a plurality of stanchions extending from the base sheet; and
a plurality of supports, each of the supports being operatively connected to one of the plurality of stanchions;

adhering the first surface to a base sheet;
adhering the second surface to a perforated sheet spaced a distance from the base sheet, each support of the stanchion-support combination including a chamber formed therein interactive with the perforated sheet to act as a Helmholtz resonator.

14. The method of claim 13 , the stanchion-chamber combination being comprised of thermoplastic.

15. The method of claim 13 , the base sheet being comprised of metal or metal alloy.

16. The method of claim 13 the perforated sheet being comprised of metal or metal alloy.

Assignees

• United Technologies Corp

Inventors

• Turner Matthew A
• Kling Colin J
• Topol David A

Classifications

• F04D29/325

  for axial flow fans (blade mountings F04D29/34, blades F04D29/38) · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2300/43

  Synthetic polymers, e.g. plastics; Rubber · CPC title

• F05D2300/17

  Alloys · CPC title