Aircraft components with porous portion and methods of making

Patent metadata

Field	Value
Publication number	US-9903275-B2
Application number	US-201414192332-A
Country	US
Kind code	B2
Filing date	Feb 27, 2014
Priority date	Feb 27, 2014
Publication date	Feb 27, 2018
Grant date	Feb 27, 2018

Abstract

A component including a porous portion which may be permeable or impermeable to air, and a method for making. In one example, the component is a cooled wall segment for a gas turbine engine, including a body defining a contact surface configured to be in contact with circulating hot gas and an outer surface configured to be in contact with cooling air. The body includes a first portion with at least one retention element, and a porous second portion made of a porous material permeable to air, containing a plurality of interconnected pores, and having a porosity greater than that of the first portion. The second portion is engaged to the first portion, defines at least part of the contact surface, and defines at least part of a fluid communication between the outer surface and the contact surface through the interconnected pores. The wall segment may be for example a heat shield or shroud segment. Methods of forming components are also discussed.

First claim

The invention claimed is:

1. A method of forming a cooled wall segment for a gas turbine engine through a powder injection molding process, the method comprising:
forming a green body of the wall segment, including:
forming a first portion from a first feedstock, the first portion defining at least one retention element of the body, and
forming a second portion from a second feedstock, wherein a surface of the second portion is exposed to define at least part of a contact surface of the body configured to be in contact with hot gas circulating through the gas turbine engine; and

debinding and sintering the green body, such that the second feedstock defines a porous material permeable to air and containing a plurality of interconnected pores, and such that the first feedstock defines a material less porous than the material defined by the second feedstock.

2. The method as defined in claim 1 , debinding and sintering the green body includes interconnecting the first and second portions.

3. The method as defined in claim 1 , wherein forming the second portion includes disposing the second portion as a coating on the first portion to define at least part of the contact surface.

4. The method as defined in claim 1 further comprising applying a thermal barrier coating to the cooled wall segment.

5. The method as defined in claim 1 , wherein the second portion has a lower density than the first portion.

6. The method as defined in claim 1 , wherein the second feedstock defines the porous material with a porosity of equal to or less than 70%.

7. The method as defined in claim 1 , wherein the second feedstock defines the porous material with a porosity of equal to or more than 70%.

8. The method as defined in claim 1 , wherein the material defined by the first feedstock is impermeable to air.

9. A method of forming an aircraft-based component, the method comprising:
metal-injection molding to form a green body, the body including a first portion molded from a first feedstock and a second portion molded from a second feedstock, wherein the first feedstock produces a first material having a density of 96.5% or more of a theoretical density of the corresponding forged material and the second feedstock produces a second material having a porosity of equal to or more than 7%.

10. The method of claim 9 wherein a surface of the second portion is exposed to define at least part of an exterior surface of the body.

11. The method of claim 9 wherein the second material is permeable to air and comprising a plurality of interconnected pores.

12. The method of claim 9 wherein the second material is impermeable to air.

13. The method of claim 9 further comprising enclosing the second portion within the first portion by a third portion, the third portion extending over the second portion and cooperating with the first portion to enclose the second portion.

14. The method of claim 9 wherein the third portion is molded from the first feedstock.

15. The method of claim 9 further comprising debinding and sintering the green body.

16. The method of claim 9 further comprising applying a thermal barrier coating to the component.

17. The method of claim 9 wherein the second portion has a lower density than the first portion.

18. The method of claim 9 , wherein the second material has a porosity of equal to or less than 70%.

19. The method of claim 9 , wherein the second material has a porosity of equal to or more than 70%.

20. The method of claim 9 , wherein the aircraft-based component is a shroud segment for a gas turbine engine, wherein metal injection molding to form the green body includes forming the first portion to define an open cavity, filling the open cavity with the second portion, enclosing the second portion with a third portion made of the first feedstock, the third portion extending over the second portion and cooperating with the first portion to close the open cavity; and the method further comprises debinding and sintering the green body while the second portion supports the third portion to prevent collapse of the third portion within the cavity.

21. The method as defined in claim 9 wherein the first material is impermeable to air.

Assignees

• Pratt & Whitney Canada

Inventors

• Campomanes Marc
• Scalzo Orlando
• Bouthillier Alain

Classifications

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F05D2260/203

  by transpiration cooling · CPC title

• F05D2230/22

  by sintering · CPC title

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• F01D25/12

  Cooling · CPC title