Gas turbine engine with inertial particle separator

An inertial particle separator (IPS) for fluid communication with an engine inlet of an aircraft engine, the IPS defining a longitudinal direction, a lateral direction normal to the longitudinal direction, and a vertical direction normal to both of the longitudinal direction and the lateral direction, comprising:

• a main duct having an inlet fluidly connected to an environment outside of the aircraft engine, the main duct having a first segment and a second segment, the first segment extending longitudinally away from the inlet and vertically toward an elbow, the second segment extending vertically and longitudinally away from the elbow, the main duct having a concave side and a convex side;
• two inlet ducts communicating with the main duct and extending from the concave side of the main duct, the two inlet ducts extending laterally away from one another and vertically away from the elbow;
• and
• a bypass duct communicating with the main duct and extending from the convex side of the main duct at a junction between the two inlet ducts and the main duct, an intersection between the bypass duct and the main duct defining a splitter, the bypass duct extending along the longitudinal direction and laterally between the two inlet ducts, the two inlet ducts and the bypass duct extending vertically away from one another.