Typical podded engines, such as those used on airliners, have identical installations for each engine. The engine components and nacelle components are interchangeable. By utilizing interchangeable parts for all engines on an aircraft, manufacturing costs are decreased, part storage is minimized, and maintenance is facilitated since parts can be cross-utilized between engines and engine nacelles. However, for aircraft with internally mounted engines, the engine outlets may be shaped and unique according to the engine mounting location. At a minimum, engines mounted within the wing or fuselage on one side of the aircraft may each utilize convergent/divergent engine nozzles that are unique to that side and/or position, and are a mirror image of the components utilized with engines mounted in the opposite wing or fuselage side.
For example, engine nozzle apertures corresponding to internally mounted engines on one side of an aircraft may include swept components and saw tooth configurations that minimize radar signatures. The corresponding components on the opposite side of the aircraft may be configured as a mirror image to the engine nozzle apertures on the first side of the aircraft. In these situations, two distinct sets of engine components must be designed, produced, stored and maintained. Because the features of the engine components may differ according to engine mounting location, different engines may also require unique software to control the engine performance. For these reasons, engines may require unique configuring prior to installation according to the characteristics of the nozzle and nozzle aperture that is unique to that engine position, increasing the time and cost associated with maintaining the aircraft.
It is with respect to these considerations and others that the disclosure made herein is presented.