High porosity abradable coating
AssigneeSolar Turbines Incorporated
InventorsBrent Allen Cottom, Michael Andrew Coe
Life of this patent
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Abstract
An abradable coating for a gas turbine engine includes a bond coat, an intermediate layer, and a porous layer. The bond coat includes a metal coating and a thickness from 0.152 millimeters to 0.229 millimeters. The intermediate layer includes a ceramic material and a thickness from 0.051 millimeters to 0.381 millimeters. The porous layer includes a porous ceramic material. The porous layer also includes a porosity greater than thirty-five percent of a volume of the porous layer. The porous layer further includes a thickness from 0.127 millimeters to 1.524 millimeters.
Claims20
An abradable coating for a gas turbine engine, comprising:
- a bond coat applied to a substrate, the bond coat including
- a metal coating, and
- a thickness from 0.152 millimeters to 0.229 millimeters;
- an intermediate layer applied to the bond coat, the intermediate layer including
- a ceramic material, and
- a thickness from 0.051 millimeters to 0.381 millimeters;
- and
- a porous layer applied to the intermediate layer, the porous layer including
- a porous ceramic material,
- a porosity greater than thirty-five percent of a volume of the porous layer, and
- a thickness from 0.127 millimeters to 1.524 millimeters.
An abradable coating for a shroud of a gas turbine engine located adjacent rotor blades, comprising:
- a bond coat applied to the shroud, the bond coat including
- an MCrAlY material and including a thickness from 0.152 millimeters to 0.229 millimeters;
- an intermediate layer applied to the bond coat, the intermediate layer including
- yttria stabilized zirconia and including a thickness from 0.051 millimeters to 0.381 millimeters;
- and
- a porous layer applied to the intermediate layer, the porous layer including
- yttria stabilized zirconia,
- a porosity between thirty-five percent to fifty percent of the volume of the porous layer, and
- a thickness of at least 1.016 millimeters.
A gas turbine engine, comprising:
- a rotor assembly including
- a rotor disk, and
- a plurality of rotor blades coupled to the rotor disk, each rotor blade of the plurality of rotor blades including an airfoil with a bare metal blade tip;
- a shroud located radially outward from the rotor assembly, the shroud including
- a surface located adjacent the blade tips of the plurality of rotor blades;
- and
- an abradable coating applied to the surface of the shroud, the abradable coating including
- a bond coat applied to the shroud, the bond coat including
- a metal coating,
- an intermediate layer applied to the bond coat, the intermediate layer including
- a ceramic material, and
- a porous layer applied to the intermediate layer, the porous layer including
- a porous ceramic material and including a porosity between thirty-five percent and fifty percent of the volume of the porous layer.
Dependencies are inferred from the claim text.