Turbine abradable air seal system
AssigneeRaytheon Technologies Corporation
InventorsChristopher W. Strock, Paul M. Lutjen, Michael J. Bruskotter
Life of this patent
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Abstract
An air scal system for a rotor blade assembly of a gas turbine engine includes a substrate. An optional ceramic interlayer may be disposed on an optional bond coat deposited on the substrate. An erosion resistant thermal barrier coating (E-TBC) layer is disposed on the ceramic interlayer (if present) or on the bond coat, or on the substrate. An abradable layer is disposed on the erosion resistant thermal barrier coating (E-TBC) layer.
Claims13
A seal system for a rotor blade assembly of a gas turbine engine, the seal system comprising:
- a substrate;
- a bond coat disposed on the substrate;
- an erosion resistant thermal barrier coating (E-TBC) layer inboard of the ceramic layer;
- and
- an abradable layer consisting of porous yttria stabilized zirconia (YSZ) or a ceramic filled with hexagonal boron nitride and disposed inboard of the erosion resistant thermal barrier coating (E-TBC) layer wherein a transition layer is formed between the erosion resistant thermal barrier coating (E-TBC) layer and the abradable layer, the transition layer having a mixture of properties of the erosion resistant thermal barrier coating (E-TBC) layer and the abradable layer.
A method for forming an air seal system for a rotor blade assembly of a gas turbine engine comprising:
- applying a bond coat onto a substrate;
- applying an erosion resistant thermal barrier coating (E-TBC) layer onto the interlayer;
- applying a transition layer inboard of the erosion resistant thermal barrier coating layer (E-TBC);
- and
- applying an abradable layer consisting of porous yttria stabilized zirconia (YSZ) or a ceramic filled with hexagonal boron nitride inboard of the transition layer and the erosion resistant thermal barrier coating (E-TBC) layer.
Dependencies are inferred from the claim text.