Patent ID: 9696036
Date: 2017-07-04
CPC Classifications: B23P,F23R

Claim:
1. A combustion chamber tile of a gas turbine comprising: a basic element including a first surface on a first side thereof and a second surface on a second side thereof opposite the first side and also including an effusion cooling hole extending through the basic element from the first surface to the second surface, a ceramic surface coating applied to the first surface, the effusion cooling hole including an inlet opening adjacent the first side of the basic element and extending substantially at a right angle to the first surface over part of a length of the effusion cooling hole, the effusion cooling hole inside the basic element including a straight section adjacent the first side and then an offset section extending from the straight section toward the second side, the effusion cooling hole including a shoulder opposite the inlet opening in an area of a beginning of the offset section, the shoulder being inclined away from the first surface in a direction away from the effusion cooling hole to form a recessed portion in the effusion cooling hole recessed away from the first surface for accumulating a portion of the ceramic surface coating.