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US 2010/0247291 A1Published application
Gas turbine engine article having columnar microstructure
AssigneeUnited Technologies Corporation
InventorsSusan M. Tholen, Philip R. Belanger, Christopher W. Strock
Life of this patent
Estimating the term…
Abstract
A gas turbine engine article includes a substrate extending between two circumferential sides, a leading edge, a trailing edge, an inner side for resisting hot engine exhaust gases, and an outer side. A gaspath layer is bonded to the inner side of the substrate and includes a metallic alloy having a columnar microstructure.
Claims16
A gas turbine engine article comprising:
- a substrate extending between two circumferential sides, a leading edge, a trailing edge, an inner side for resisting hot engine exhaust gases, and an outer side;
- and
- a gaspath layer bonded to the inner side of the substrate, the gaspath layer comprising a metallic alloy having a columnar microstructure.
A gas turbine engine comprising:
- a compressor section;
- a combustor fluidly connected with the compressor section;
- and
- a turbine section downstream from the combustor, the turbine section having a seal that includes a substrate extending between two circumferential sides, a leading edge, a trailing edge, an inner side for resisting hot engine exhaust gases from the combustor, and an outer side, and a gaspath layer bonded to the inner side of the substrate, the gaspath layer comprising a metallic alloy having a columnar microstructure.
1 more element
A method of processing a gas turbine engine article, comprising:
- forming a gaspath layer comprising a metallic alloy having a columnar microstructure;
- and
- bonding the gaspath layer to an inner side of a substrate that extends between two circumferential sides, a leading edge, a trailing edge, the inner side for resisting hot engine exhaust gases, and an outer side.
Dependencies are inferred from the claim text.