| 摘要 |
A variable nozzle that discharges the exhaust gas of an aeronautic gas turbine engine, along the axis thereof, from the fore end to the aft end of the aircraft, is comprised of an exhaust duct (3) guiding the exhaust gas toward the aft end, a plurality of primary flaps (5) arranged to define a primary flow path (15) converging toward the aft end, each axially supported, so as to be rotatable, by the exhaust duct that adjusts the opening of the primary flow path, and each comprising a first section (53) and a second section (55) that forms an angle outward in the radial direction relative to the first section; and a plurality of secondary flaps (7) arranged to define a secondary flow path (17) in communication with the first flow path and capable of forming a fan shape towards the aft end, the plurality of secondary flaps each axially supported to be rotatable, by the second section of the primary flaps that adjust the opening of the secondary flow path. |
