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US 8,079,806 B2Granted
Segmented ceramic layer for member of gas turbine engine
AssigneeUnited Technologies Corporation
InventorsSusan M. Tholen, Christopher W. Strock
Life of this patent
Estimating the term…
Abstract
A turbine seal member for use in a gas turbine engine includes a turbine seal substrate having a gas-path side and a ceramic layer disposed on the gas-path side that includes a plurality of mechanical indentations.
Claims27
A turbine seal member for use in a gas turbine engine, comprising:
- a turbine seal substrate having a gas-path side;
- and
- a ceramic layer disposed on the gas-path side of the turbine seal substrate, the ceramic layer having a plurality of mechanical indentations that taper from a surface of the ceramic layer to an apex with a corresponding plurality of compacted ceramic regions adjacent the apexes.
A turbine seal member for use in a gas turbine engine, comprising:
- a turbine seal substrate having a gas-path side;
- and
- a ceramic layer disposed on the gas-path side of the turbine seal substrate, the ceramic layer having a plurality of mechanical indentations, wherein each of the plurality of mechanical indentations tapers from a surface of the ceramic layer to an apex, and includes microcracks extending from each of the mechanical indentations.
A turbine seal member for use in a gas turbine engine, comprising:
- a turbine seal substrate having a gas-path side;
- and
- a ceramic layer disposed on the gas-path side of the turbine seal substrate, the ceramic layer having a plurality of pyramidal indentations that taper from a surface of the ceramic layer to an apex and a corresponding plurality of compacted ceramic regions adjacent the apexes of the pyramidal indentations.
A method of controlling internal stresses of a ceramic layer of a turbine seal member, comprising:
- mechanically indenting the ceramic layer to form a plurality of mechanical indentations for altering the internal stresses to form stress relief cracks.
Dependencies are inferred from the claim text.