Infrared suppression exhaust duct system for a turboprop propulsion system for an aircraft

摘要

The invention is an exhaust duct system for an aircraft, the aircraft having at least one turboprop propulsion system mounted on the wing within a nacelle, the propulsion system having a circular shaped exhaust port generally aligned with the longitudinal axis of the aircraft. In detail, the invention includes a generally shallow S shaped duct having a longitudinal axis aligned with the longitudinal axis of the exhaust port. A duct includes a circular shaped inlet section, a rectangular exhaust port section and a transition section therebetween. The inlet has a larger diameter than the exhaust port of the propulsion system and is positioned there about. The inlet includes a plurality of flexible finger like members extending inward such that they are in slidable engagable with the external surface of the exhaust port. A first pair of struts are pivotally connected at the center of the rectangular exhaust port section by their first ends and extend upward and outward from the longitudinal axis of the duct with their second ends pivotally connected to the underside of the wing. A second pair of struts are pivotally connected to the sides of the transition section by their first ends and extend upward and rearwards from the inlet slightly outward and having second ends pivotally coupled to the underside of the wing.