Patent ID: 8539748

Claim:
A method for assembling a turbine engine including a compressor, said method comprising: coupling an inlet to a gas turbine engine, the inlet extending circumferentially about a centerline of the inlet over a predetermined segment angle that is less than 360° and the inlet including: a bullet nose, a nacelle spaced radially outwardly from the bullet nose such that an entry passage is defined between the bullet nose and the nacelle, an inertial particle separator (IPS) positioned within the entry passage and oriented downstream of the bullet nose to define a dirty fluid channel and a clean fluid channel, wherein the dirty fluid channel is positioned downstream from a convex section of the bullet nose and is configured to receive particles separated from the fluid by inertia caused by the fluid flowing past the convex section of the bullet nose, and a first surface that is defined by the segment angle, the segment angle selected such that the first surface matingly engages a surface of a fuselage of an aircraft when the inlet is installed on the aircraft; and coupling the first surface flush against the fuselage of the aircraft to reduce drag.