| 摘要 |
A variable area two-stage ejection nozzle exhaust system for a turbojet engine having an afterburner. wherein, a primary nozzle has spherical segments contained within a spherical shell housing which spherical segments are pivotally adjustable in response to augmented and non-augmented engine operation to provide for an efficient exhaust nozzle exit area choke plane; and a secondary nozzle with aerodynamically actuated trailing edge flaps for varying the secondary exhaust nozzle exit area in response to primary nozzle pressure variations and airplane Mach number. Also provided within the primary nozzle are separate clamshell type blocker doors which, in combination with fluid flow turning vanes incorporated into the primary nozzle wall, turn the fluid flow to obtain reverse thrust from the turbojet engine.
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