초록 ▼

An aircraft axisymmetric exhaust nozzle (36) is provided for reducing noise in an intermediate bypass ratio turbofan engine. The nozzle (36) includes a plurality of chute ejectors (38) placed equal distances about the circumference of a nozzle outer structure (46). A translatable centerbody (52) is

An aircraft axisymmetric exhaust nozzle (36) is provided for reducing noise in an intermediate bypass ratio turbofan engine. The nozzle (36) includes a plurality of chute ejectors (38) placed equal distances about the circumference of a nozzle outer structure (46). A translatable centerbody (52) is located within the outer structure (46). The annular space between the outer structure (46) and the centerbody (52) defines a convergent-divergent exhaust duct (56). Each chute ejector (38) includes an inlet ramp (70) rotatably connected to the outer structure (46) along a ramp forward end (78). Each inlet ramp (70) moves between opposed stationary side panels (39) that extend inwardly from the outer structure interior surfaces (50). The side panels (39) are located in longitudinal planes and are triangular in shape. Nozzle aft flaps (114) are used to form the rearmost portions of the nozzle (36). During noise suppression, the inlet ramp (70) is rotated inwardly to allow ambient air (40) to enter the exhaust duct (56) at aspiration ratios of less than 40% of the engine exhaust. When noise suppression is not needed, the inlet ramp (70) is rotated outwardly to a position that is flush and pressure sealed with the outer structure exterior surface (48).

대표청구항 ▼

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follow:] [1.] A noise suppression exhaust nozzle for an intermediate bypass ratio aircraft engine, the nozzle comprising:(a) an axisymmetric outer structure having interior sidewalls and a center

[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follow:] [1.] A noise suppression exhaust nozzle for an intermediate bypass ratio aircraft engine, the nozzle comprising:(a) an axisymmetric outer structure having interior sidewalls and a centerbody located within the sidewalls, the area between the centerbody and the sidewalls defining a convergent-divergent exhaust duct for passage of nozzle exhaust;(b) a plurality of chute ejectors positioned circumferentially about the nozzle outer structure, each chute ejector having an open position and a closed position, each chute ejector comprising opposed stationary side panels extending radially inward from the outer structure sidewalls, the stationary side panels including a wedge crest facing adjacent chute ejectors such that the combined wedge crests of adjacent chute ejectors provides a small throat for the engine exhaust; each chute ejector further comprising an inlet ramp positioned between the stationary side panels, the inlet ramp being rotatably connected to the outer structure; and(c) an actuation mechanism connected to the plurality of chute ejector inlet ramps and the outer structure, the actuation mechanism for moving the inlet ramps between their open and closed positions, whereby aspirated air is induced into the plurality of chute ejectors when the inlet ramps are in the open position, the aspirated air combining with engine exhaust.