Porous laminated material

• US 4,296,606 A
• Filed: 10/17/1979
• Issued: 10/27/1981
• Est. Priority Date: 10/17/1979
• Status: Expired due to Term

• Current Assignee: Allison Engine Company, Inc.
• Original Assignee: General Motors Corporation (Motors Liquidation Co. GUC Trust)
• Inventors: Reider, Samuel B.
• Primary Examiner(s): Garrett, Robert E.
• Application Number:
  US06/085,818
• Time in Patent Office: 741 Days
• Field of Search: 60/754, 416/219 C, 219/101-107
• US Class Current: 60/754
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence

Abstract

A porous, laminated metal fabrication includes first and second porous walls, each having laminae therein with a free edge portion across at least one end thereof; each of the first and second walls including an outer lamina with a first preformed hole pattern therein, each of the first and second walls further including an inner lamina having a second preformed hole pattern therein combined to form a tortuous air flow path through the first and second walls for cooling the metal therein; and each of the lamina in the laminae including a solid metal annulus therein of uniform density for welding; the annulus being located between the hole patterns and the free edge portions to define a weldable region between the first and second walls having an axial width limited to the axial width of the solid metal annulus whereby air flow through the first and second walls will flow freely throughout the full extent of all the performed hole patterns therein so as to maintain full coolant flow from exteriorly of the porous laminated fabrication to an inner surface thereon.

Claims

1. A porous laminated metal fabrication for a high temperature gas turbine engine component comprising first and second walls each having plural lamina with a free edge portion thereon, each of said first and second walls having a first lamina with a surface having a first preformed hole pattern therein, each of said first and second walls including a second lamina bonded to said first lamina, said second lamina having a surface with a second preformed hole pattern therein to form a tortuous air flow path through said first and second walls for cooling the metal therein, said wall holes directing coolant flow to form an air barrier on one of the lamina surfaces, each of said lamina having a solid metal section formed therein between said holes and said edge portions to define a weldable region of uniform metal density throughout a predetermined width between said first and second walls, a weld in said weldable region connecting said edge portions and having a width limited to the width of said region of uniform metal density whereby air flow through the first and second walls is free to flow through the full extent of all the preformed hole patterns in said lamina thereby to maintain full coolant flow therethrough during gas turbine engine operation.

2. A porous laminated metal combustor comprising first and second walls each having plural lamina with a free edge portion thereon, each of said first and second walls having an outer lamina with a first preformed hole pattern therein, each of said first and second walls including an inner lamina having a plurality of preformed holes therein to form a tortuous air flow path through said first and second walls for cooling the metal therein, said inner wall holes directing coolant flow into a combustion chamber to form an air barrier on the inside surface of the combustor in surrounding relationship to the combustion chamber therein, each of said lamina having a solid metal ring formed therein between said holes and said edge portions to define a weldable region of uniform metal density throughout a predetermined width between said first and second walls, a weld in said weldable region having a width limited to the width of said region of uniform metal density whereby air flow through the first and second walls is free to flow through the full extent of all the preformed hole patterns in said laminae thereby to maintain full coolant flow from exteriorly of the combustor assembly to the inside surface thereof during gas turbine engine operation.

3. A porous laminated metal combustor comprising a wall having plural lamina, said wall having a first lamina with a first preformed hole pattern and a second lamina having a second preformed hole pattern therein to form a tortuous air flow path through said lamina for cooling the metal therein, said wall having another hole therein, said second lamina holes directing coolant flow into a combustion chamber to form an air barrier on the inside surface of the combustor in surrounding relationship to the combustion chamber therein, said other hole directing air to penetrate into the chamber to a greater depth than that of said air barrier, each of said lamina having a solid metal ring formed therein around said other hole to define an annular region of uniform metal density for diffusion bonding between said first and second lamina, said annular region having a width limited to that required to control thermally induced stress at the edge of said other hole without restricting flow through the full extent of all the preformed holes in said lamina thereby to maintain full coolant flow from exteriorly of the combustor assembly to the inside surface thereof during gas turbine engine operation.