SYSTEM AND METHOD FOR REDUCTION OF TURBINE EXHAUST GAS IMPINGEMENT ON ADJACENT AIRCRAFT STRUCTURE

Systems and methods for the protection of a surface adjacent to an exhaust system are presented herein. The system may comprise an ejector, an ejector inlet, and a ejector shroud, and a shroud outlet. The ejector may include the exhaust nozzle of an engine. The should outlet is in fluid communicatio...

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Bibliographische Detailangaben
Hauptverfasser:	Lerg, Bryan, Pierluissi, Anthony, Sutterfield, David
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	Systems and methods for the protection of a surface adjacent to an exhaust system are presented herein. The system may comprise an ejector, an ejector inlet, and a ejector shroud, and a shroud outlet. The ejector may include the exhaust nozzle of an engine. The should outlet is in fluid communication with the atmosphere. The adjacent surface may partially bound a region proximate to and downstream of the shroud outlet. The system may further comprise a plurality of forced mixing lobes that extend from the engine exhaust nozzle in a region spaced apart from the adjacent surface. The distribution of the lobes may be asymmetric in the cross section of the ejector shroud proximate to the shroud outlet.