Patterned reduction of surface area for abradability

A gas turbine component comprising:

• a ceramic material defining a surface;
• an array of depressions in the surface, the depressions arranged in rows and columns defining a continuous labyrinth of walls oriented in two orthogonal directions, the walls being of substantially uniform thickness separating the depressions and making the depressions discontinuous from each other;
• and
• the ceramic material comprising hollow ceramic spheres in a ceramic matrix, the substantially uniform thickness of the walls comprising 0.5-1.5 times a maximum diameter of the hollow ceramic spheres.

A gas turbine component comprising:

• a ceramic material defining a surface;
• an array of cross-shaped depressions in the surface, the array of cross-shaped depressions comprising a first row of the cross-shaped depressions with a substantially uniform spacing between the depressions therein, a second row of the cross-shaped depressions with the substantially uniform spacing between the depressions therein, the second row offset diagonally from the first row, and a third row of the cross-shaped depressions with the substantially uniform spacing between the depressions therein, the third row offset diagonally from the second row;
• and
• a continuous labyrinth of walls separating and defining the cross-shaped depressions.