Impingement insert for a gas turbine engine

A gas turbine engine, comprising:

• a compressor section;
• a combustion section;
• a turbine section;
• a gas turbine engine component;
• an impingement insert positioned within the gas turbine engine component, the impingement insert comprising:
• an insert wall comprising an inner surface and an outer surface spaced apart from the inner surface;
• a nozzle extending at least one of outwardly from the outer surface of the insert wall and inwardly from the inner surface of the insert wall, the nozzle comprising an outer surface and a circumferential surface;
• wherein the insert wall and the nozzle collectively define a cooling passage extending therethrough;
• wherein the cooling passage comprises an inlet portion, a throat portion, a converging portion extending from the inlet portion to the throat portion, an outlet portion, and a diverging portion extending from the throat portion to the outlet portion;
• and
• wherein the cooling passage further comprises a cross-sectional shape, the cross-sectional shape comprising a semicircular portion and a non-circular portion, the non-circular portion of the cross-sectional shape comprising a first linear side and a second linear side, the first linear side and the second linear side coupled by a fillet portion.