An aircraft ejector nozzle includes a plug assembly (26) located between upper and lower cowlings (18, 20) and upright sidewalls (22). The plug assembly (26) includes separable upper and lower diverters (28, 30). Each diverter includes multiple subsections pivotably attached end-to-end. In one embod
An aircraft ejector nozzle includes a plug assembly (26) located between upper and lower cowlings (18, 20) and upright sidewalls (22). The plug assembly (26) includes separable upper and lower diverters (28, 30). Each diverter includes multiple subsections pivotably attached end-to-end. In one embodiment, first, second, and third subsections (90, 92, 94) are provided. Stationary ejectors (40, 42) located in the cowlings (18, 20) input ambient airflow (44) into an exhaust stream (32). Preferably the ejectors (40, 42) include mixing components (46). Upper and lower aft flaps (48, 50) further tailor the exhaust path shape. An actuation assembly (52) moves the diverters (28, 30) and aft flaps (48, 50) between their various positions. One actuation assembly embodiment includes a number of rotatable disks (118, 120, 132, 134, 142) for guiding the upper and lower diverters (28, 30) and the aft flaps (48, 50). In a first plug assembly configuration the diverter forward ends (84) are positioned together and the diverter aft ends (86) are positioned together. The first configuration forces exhaust (32) around the diverters (28, 30). In a second plug assembly configuration the diverter forward ends (84) are positioned apart and the diverter aft ends (86) are positioned apart. The second configuration forces exhaust (32) between the diverters (28, 30) while simultaneously covering the ejectors (40, 42). Acoustic linings (100) are provided at various locations within the nozzle and are exposed to the exhaust flow only during noise suppression configurations, thus minimizing liner wear and contamination.
대표청구항▼
[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] An aircraft engine ejector nozzle for optimizing engine performance and suppressing engine noise by altering an exhaust airflow, the nozzle comprising:(a) upper and lower cowlings
[ The embodiments of the invention in which an exclusive property or privilege is claimed are defined as follows:] [1.] An aircraft engine ejector nozzle for optimizing engine performance and suppressing engine noise by altering an exhaust airflow, the nozzle comprising:(a) upper and lower cowlings extending between an upright sidewalls, at least one of the upper and lower cowlings including an ejector for directing ambient air into the exhaust airflow; and(b) a reconfigurable plug assembly extending between the upright nozzle sidewalls, the upper and lower cowlings located above and below the plug assembly respectively, the plug assembly comprising separable upper and lower diverters each having an inner surface, an outer surface, a forward end, and an aft end, the upper and lower diverters being positioned in a generally opposed longitudinal relation, the reconfigurable plug assembly having at least two distinct configurations, the first configuration comprising positioning the diverter forward ends together and the diverter aft ends together in order to form a bifurcated exhaust path defined between the cowlings and the diverter outer surfaces and the second configuration comprising positioning the diverter forward ends apart and the diverter aft ends apart to form an exhaust path defined by the upper and lower diverter inner surfaces;(c) an actuation assembly for moving the plug assembly between the at least two distinct configurations.
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이 특허에 인용된 특허 (12)
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