An assembly is provided for a gas turbine engine. This engine assembly includes an exhaust nozzle extending circumferentially about an axial centerline. The exhaust nozzle extends axially along the axial centerline to a trailing edge. The exhaust nozzle extends radially between an exterior inner surface and an exterior outer surface. The exhaust nozzle includes an inner skin, an outer skin and an internal cavity. The inner skin forms the exterior inner surface and includes a plurality of perforations. The internal cavity is disposed radially between the inner skin and the outer skin. The internal cavity is fluidly coupled with the perforations.
Engine exhaust nozzle with acoustic attenuation
2024-12-10
Patent
Electronic Resource
English
IPC: | F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS |
Turbine engine exhaust nozzle performance
AIAA | 1973
|Jet Engine Exhaust Nozzle Flow Effector
NTRS | 2011
|