Turbine engine having an airfoil with a set of cooling holes

A turbine engine comprising:

• an engine core extending along an engine centerline and including a compressor section and a turbine section in serial flow arrangement;
• an airfoil having an internal cooling passage defined by an inner surface, the inner surface having a first portion and a second portion;
• and
• a turbulator located within the internal cooling passage and extending from the first portion of the inner surface into the internal cooling passage, the turbulator comprising:
• a front face spaced from the first portion and the second portion;
• an upstream face extending between the front face and the inner surface;
• a downstream face extending between the front face and the inner surface opposite the upstream face;
• a turbulator nose located at a most upstream curved portion on the upstream face of the turbulator;
• a cavity width (A) is defined as a distance measured across the internal cooling passage between portions of the inner surface that extend through an interior of the airfoil between a first side and a second side, wherein the cavity width is measured in a chordwise direction defined by a camber line in a reference plane defined with respect to the turbulator nose;
• a cavity height (B) is defined as a distance measured across the internal cooling passage defined by the inner surface between the first portion of the inner surface to the second portion of the inner surface, wherein the cavity height is measured along a line intersecting the turbulator nose and perpendicular to the chordwise direction in a reference plane defined with respect to the turbulator nose;
• a cavity aspect ratio (C) is defined as a ratio of the cavity height to the cavity width, wherein the cavity aspect ratio is in a range from 0.1 to 10, inclusive of endpoints;
• a turbulator nose radius is defined as a radius of curvature of a turbulator nose measured along the upstream face, wherein the radius of curvature is in a range from 0.0127 centimeters to 1.905 centimeters (0.005 inches to 0.75 inches), inclusive of endpoints;
• and
• a turbulator height is defined as a greatest distance measured perpendicular to the first portion of the inner surface to the front face of the turbulator, wherein the turbulator height is in a range from 0.0127 centimeters to 0.1524 centimeters (0.005 inches to 0.06 inches), inclusive of endpoints.