Compressor scroll spigot fit load interface

An aircraft engine comprising:

• a shaft extending along a central engine axis;
• a bearing housing including one or more bearings rotationally supporting one or more rotors on the shaft;
• an engine casing;
• a scroll housing surrounding the shaft and housing a centrifugal impeller, the scroll housing including a scroll outer wall and a scroll housing annular body with a spigot-receiving cavity defined in the scroll housing annular body, the scroll housing operatively coupled to the engine casing;
• and
• a scroll coverplate operatively coupled to the scroll housing and to the bearing housing, the scroll coverplate having a scroll coverplate annular body with a spigot protruding axially from the scroll coverplate annular body, the spigot received in the spigot-receiving cavity;
• wherein a load-bearing path is defined between the shaft and the engine casing through the bearing housing, the scroll coverplate, the spigot, the spigot-receiving cavity, and the scroll housing;
• and
• wherein the scroll housing includes a radially outer scroll wall that is asymmetrically shaped about a circumference of the scroll housing annular body, and the spigot-receiving cavity is disposed radially inwardly of the radially outer scroll wall.