Abstract: A gas turbine engine and air intake assembly comprises an intake passage extending between an inlet highlight at a first end and an upstream face of a fan at a second end and comprising in flow series an intake lip, a most upstream portion of which defines the intake highlight and a most downstream portion of which defines a throat, a diffuser with sectional area broadening towards the fan; and a straight conditioning duct, arranged immediately upstream of the fan. The camber line of the intake passage intersects the engine main axis at an intersecting point upstream of the fan at an intersecting point and the camber line is parallel to the engine main axis in the straight conditioning duct.