Aircraft engine struts with stiffening protrusions

An inlet case for an aircraft engine, comprising:

• a conduit annularly extending around a central axis, the conduit having an inlet oriented in a substantially radial direction and an outlet oriented in a substantially axial direction, the conduit defined between a first wall and a second wall, each of the first wall and the second wall having a gaspath side facing the conduit and an opposed side facing away from the conduit;
• struts circumferentially distributed around the central axis, the struts extending across the gaspath, a strut of the struts having an airfoil including a leading edge, a trailing edge, a first end secured to the first wall, and a second end secured to the second wall, the airfoil having a chord line connecting the leading edge to the trailing edge, wherein the volume of each strut is defined in part by each of the first wall, the second wall, the leading edge, and the trailing edge;
• and
• protrusions extending from a baseline surface of the opposed side of the first wall and external to the respective volume of each strut, the protrusions being circumferentially distributed around the central axis and being circumferentially spaced apart from one another, the protrusions increasing a thickness of the first wall, a protrusion of the protrusions overlapping a location where the leading edge or the trailing edge meets the gaspath side of the first wall, the protrusion extending from a first protrusion end to a second protrusion end in a direction of an airflow in the gaspath, the first protrusion end and the second protrusion end located on the baseline surface, the first protrusion end being upstream of the leading edge or downstream of the trailing edge relative to the airflow, the second protrusion end being downstream of the leading edge and upstream of the trailing edge, the protrusion intersected by a projection of the chord line on the opposed side of the first wall.