Various layered gas turbine engine component constructions

Patent metadata

Field	Value
Publication number	US-9341118-B2
Application number	US-95115210-A
Country	US
Kind code	B2
Filing date	Nov 22, 2010
Priority date	Dec 29, 2009
Publication date	May 17, 2016
Grant date	May 17, 2016

Abstract

A gas turbine engine component is disclosed having a construction that permits a working fluid to flow from one side of the component to the other. In one embodiment the construction includes multiple layers, and in one particular embodiment the construction includes three layers. One or more layers can have different properties. Additionally, one or more layers of the construction can include a cellular structure. In one embodiment the component is a gas turbine engine combustor liner.

First claim

What is claimed is:

1. An apparatus comprising:
a gas turbine engine component composition having a first foamed material portion located on a hot side of the component, a second foamed material portion coupled with the first foamed material portion, and a third foamed material portion coupled with the second foamed material portion and located on a cold side of the composition, the first foamed material portion, the second foamed material portion, and the third foamed material portion each having a plurality of pores arranged along their thicknesses between the hot side and the cold side, the first foamed material portion, the second foamed material portion, and the third foamed material portion structured to permit the passage of a cooling working fluid between the cold side and the hot side to provide transpiration cooling, wherein the second foamed material portion has a higher porosity than the first foamed material portion and the third foamed material portion, and the first foamed material portion includes a cellular configuration having a working fluid passage formed therethrough and wherein the first foamed material portion is a support structural portion that provides strength to the gas turbine engine component composition, wherein the first foamed material portion and second foamed material portion of the gas turbine engine component construction are sufficiently rigid to maintain a shape of the component construction.

2. The apparatus of claim 1 , wherein the working fluid passage is defined by the cellular configuration.

3. The apparatus of claim 2 , wherein the cellular configuration is an open cellular configuration.

4. The apparatus of claim 1 , wherein the first foamed material portion has a density of pores the same as a density of pores of the third foamed material portion.

5. The apparatus of claim 1 , wherein the first foamed material portion is metallic or ceramic.

6. An apparatus comprising:
a combustor liner having a thickness that includes a first foamed material member, a second foamed material member, and a third foamed material member, the first foamed material member adjacent the second foamed material member, and the second foamed material member adjacent the third foamed material member, and the foamed material members arranged to permit a cooling flow to pass from the first foamed material member to the second foamed material member to the third foamed material member, the first foamed material member, the second foamed material member, and the third foamed material member are each free of a substrate or other structure that aids in maintaining a shape of the combustor liner such that the strength of the combustor liner is solely provided by the first foamed material member, the second foamed material member, and the third foamed material member, and wherein a porosity of the second foamed material member is greater than a porosity of the first foamed material member and a porosity of the third foamed material member.

7. The apparatus of claim 6 , wherein the second foamed material member is positioned between a hot side of the combustor liner and the first foamed material member.

8. The apparatus of claim 7 , where the first foamed material member has a higher thermal conductivity than the second foamed material member.

9. The apparatus of claim 6 , wherein the second foamed material member has a lower density than the first foamed material member.

10. The apparatus of claim 6 , wherein the second foamed material member forms a structural support for the combustor liner.

11. The apparatus of claim 6 , wherein the first foamed material member is formed of a metal or a ceramic.

12. A method comprising:
providing a relatively cold side foamed material layer having open cells of a gas turbine engine component and a relatively hot side foamed material layer having open cells of a gas turbine engine component;
locating the relatively cold side foamed material layer of the gas turbine component adjacent to the relatively hot side foamed material layer of the gas turbine engine component to create a layered foamed material construction;
coupling the relatively cold side foamed material layer having open cells to the relatively hot side foamed material layer having open cells, wherein the coupling is performed after the providing and includes forming a cooling passage between the relatively cold side foamed material layer to the relatively hot side foamed material layer, wherein the coupling results in the component having a shape solely maintained by the structural strength of the relatively cold side foamed material layer and the relatively hot side foamed material layer; and
coupling a third foamed material layer to the layered foamed material construction, wherein the third foamed material layer is of greater porosity than the relatively hot side foamed material and the relatively cold side foamed material, the coupling a third foamed material layer including connecting the cooling passage between the relatively cold side foamed material layer to the relatively hot side foamed material layer with a passage within the third foamed material layer.

13. The method of claim 12 , wherein the coupling a third foamed material layer includes coupling the third foamed material layer on a hot side of the relatively hot side foamed material, the relatively hot side foamed material layer having a porosity higher than the relatively cold side foamed material layer.

Assignees

• Bastnagel Philip M
• Rice Edward Claude
• Rolls Royce Corp

Inventors

• Bastnagel Philip M
• Rice Edward Claude

Classifications

• F01D25/145

  Thermally insulated casings · CPC title

• Y10T29/49229

  Prime mover or fluid pump making · CPC title

• F23R3/007

  constructed mainly of ceramic components · CPC title

• F23R2900/03041

  Effusion cooled combustion chamber walls or domes · CPC title

• F23R3/002

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title