Case for gas turbine engine

A turbine exhaust case comprising:

• an inner ring extending along an axis;
• an outer ring extending at least partially about the inner ring;
• and a plurality of circumferentially spaced apart struts extending radially between the inner ring and the outer ring with respect to the axis, wherein each strut of the plurality of struts comprises:
• an airfoil section extending in a spanwise direction between the inner ring and the outer ring, extending in a chordwise direction between a leading edge and trailing edge to define a chord length, and extending in a thickness direction between a first side and a second side to define a chord width;
• a leading portion is defined by an exterior surface of the airfoil section between the leading edge and a widest location of the airfoil section relative to the thickness direction, and a trailing portion between the widest location and the trailing edge;
• a respective exterior contour is established by the exterior surface for each span position between a 0% span position and a 100% span position;
• and a plurality of dimples are defined in the exterior surface, at least one dimple of the plurality of dimples is separated from the leading edge by a first distance of no more than 5% of a second distance between the leading edge and the trailing edge along the exterior contour, wherein the plurality of dimples extend across a localized region of the exterior surface, a remainder of the exterior surface defines a second region free of any dimples, and a ratio of the localized region to the second surface area is between 1:2 and 1:4;
• and wherein each dimple of the plurality of dimples in the localized region has a surface area, and a ratio of a sum of the surface area of each dimple within the localized region to a total area of the localized region is between 1:3 and 1:4.

A gas turbine engine comprising:

• a compressor section;
• a turbine section;
• and
• a stator case comprising:
• an inner ring extending along an engine axis;
• an outer ring extending at least partially about the inner ring;
• and
• a plurality of circumferentially spaced apart struts extending radially between the inner ring and the outer ring with respect to the axis, wherein each strut comprises:
• an airfoil section extending in a spanwise direction between the inner ring and the outer ring, extending in a chordwise direction between a leading edge and trailing edge to define a chord length, and extending in a thickness direction between a first side and a second side to define a chord width;
• a leading portion is defined by an exterior surface of the airfoil section between the leading edge and a widest location of the airfoil section relative to the thickness direction, and a trailing portion between the widest location and the trailing edge;
• a respective exterior contour is established by the exterior surface for each span position between a 0% span position and a 100% span position;
• a plurality of dimples is defined in the exterior surface in the leading portion;
• and
• two or more dimples of the plurality of dimples are defined along the leading edge;
• wherein the plurality of dimples extend across a localized region of the exterior surface, each dimple in the localized region has a surface area, and a ratio of a sum of the surface area of each dimple within the localized region of the leading portion to a total area of the region is between 1:4 and 1:3.