US 11,739,650 B2 · Hybrid airfoil coatings

Abstract

The disclosure describes articles and techniques that include an airfoil having a hybrid coating system to provide improved particle impact resistance and improve CMAS attack resistance on the pressure side of the airfoil and improved thermal load protection on the suction side of the airfoil. An example article for a gas turbine engine may include a substrate, and a hybrid environmental barrier coating (EBC) including a relatively dense EBC layer on a first portion of the substrate and a relatively porous EBC layer on a second portion of the substrate, where the first portion of the substrate is different from the second portion of the substrate, and wherein at least a portion of the relatively porous EBC layer overlaps at least a portion of the relatively dense EBC layer in an overlap region.

Claims12

Dependent claims

A turbine blade for a gas turbine engine, the turbine blade comprising:

a substrate comprising an airfoil having a leading edge, a suction side and a pressure side, each of the suction side and the pressure side extending from a stagnation point toward a trailing edge of the airfoil;
and
a hybrid environmental barrier coating (EBC) on the substrate, the hybrid EBC comprising:
a first EBC layer having a first porosity;
and
a second EBC layer having a second porosity, wherein the second porosity is greater than the first porosity, wherein at least a portion of the second EBC layer overlaps at least a portion of the first EBC layer in an overlap region between the stagnation point and an aerodynamic throat of the airfoil, wherein the first EBC layer extends from the overlap region, over the leading edge over the airfoil and along the pressure side, and wherein the second EBC layer extends from the overlap region along the suction side.

3 more elements

Dependencies are inferred from the claim text.

Hybrid airfoil coatings

Life of this patent

Hybrid airfoil coatings

Life of this patent

Abstract

Claims12