Patent ID: 8317129

Claim:
A universal convergent engine nozzle system, comprising: a plurality of distinct nozzle apertures, each distinct nozzle aperture configured for connection to a specific and different individual engine mounting location of a plurality of engine mounting locations within an aircraft, and comprising an upstream end configured for attachment to at least one universal convergent engine nozzle and a downstream end comprising an exit aperture through which an engine exhaust flow exits the distinct nozzle aperture; and a plurality of universal convergent engine nozzles, each universal convergent engine nozzle comprising a first end configured for attachment to an internally mounted aircraft engine; a second end configured for attachment to the upstream end of a distinct nozzle aperture corresponding to the specific engine mounting location of the internally mounted aircraft engine; and a convergent duct extending between the first end and the second end and configured to increase a velocity of the engine exhaust flow from the first end toward the second end to a nozzle throat, wherein all of the universal convergent engine nozzles are shaped and sized for mounting at all of a plurality of internal engine mounting locations within an aircraft such that each universal convergent engine nozzle is operative to route the engine exhaust flow from any internally mounted aircraft engine to the distinct nozzle aperture corresponding to the specific engine mounting location of the internally mounted aircraft engine.