Turbine engine with a blade

A blade for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow, comprising:

• a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow;
• and
• a plurality of cooling holes each comprising a passage extending between an inlet at the cooled surface and an outlet at the heated surface, the outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a straight-line distance, the passage defining a centerline forming a first angle (θ) with the heated surface, a top wall, and a bottom wall each extending from the inlet toward the outlet, and a layback surface defining at least a portion of the outlet, extending from the bottom wall to the heated surface, the layback surface forming a second angle (β) with the bottom wall and a third angle (Δ) with the heated surface, wherein for any range of angle values (α):
• (αlow<α<αhi):
• for at least a first cooling hole of the plurality of cooling holes αhi+αlow<θ, and αlow<Δ<αhi;
• and
• for at least a second cooling hole of the plurality of cooling holes αhi+αlow>θ, and αlow<β<αhi;
• wherein the distances for each of the plurality of cooling holes is maintained within 5% of each other as the first angle (θ) increases regardless of the location of the cooling hole on the blade, and
• wherein the sum of the low and high angle values is equal to a switch value (θs), αhi+αlow=θs.