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US 6,640,546 B2Granted
Foil formed cooling area enhancement
AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Melvin Robert Jackson, Stephen Joseph Ferrigno, Ji-Cheng Zhao
Life of this patent
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Abstract
A wall structure for a gas turbine engine component is provided which comprises a wall having a first side facing a flow of hot gases and a second side exposed to a source of cooling fluid. The wall has a plurality of holes formed therethrough, and an outer layer disposed on the first side. The holes greatly increase the wetted surface area of the wall exposed to cooling flow.
Claims28
A wall structure for a gas turbine engine component, comprising:
- a wall having a first side facing a flow of hot gases and a second side exposed to a flow of cooling fluid, said wall,having a plurality of holes formed therethrough;
- and
- an outer layer disposed on said first side of said wall.
A combustor liner for a gas turbine engine, comprising:
- a circumferentially extending wall enclosing a combustion chamber, said wall having a first side facing a flow of hot gases and a second side exposed to a flow of cooling fluid, said wall having a plurality of holes formed therethrough;
- and
- an outer layer disposed on said first side of said wall.
A turbine airfoil, comprising:
- first and second spaced-apart walls extending from a leading edge of said airfoil to a trailing edge of said airfoil, wherein at least one of said walls has a first side facing a flow of hot gases and a second side exposed to a flow of cooling fluid, said one of said walls having a plurality of holes formed therethrough;
- and
- an outer layer disposed on said first side of said one of said walls.
Dependencies are inferred from the claim text.