| 摘要 |
PURPOSE: To vector a thrust in a pitch or yaw direction within a convergent divergent exhaust nozzle for an aircraft gas turbine engine by pivoting deflector flaps on the top and bottom pivotal flaps of the exhaust nozzle for later appropriate extension. CONSTITUTION: An aircraft gas turbine engine includes a vectorable two-dimensional convergent divergent exhaust nozzle 22 connected to another engine part by a connecting duct. The exhaust nozzle 22 is constituted of a convergent section 24, a divergent section 30 and a throat part 34 between both these sections 24 and 30. The convergent section 24 is made up of a top wall 18T and a bottom wall 18B, which are respectively provided at their rear ends with a top primary flap 26T set on a pivot 28T and a bottom primary flap 26B set on a pivot 28B, which are further respectively provided at their rear ends with a secondary flap 32T set on a pivot 36T and a secondary flap 32B set on a pivot 36B. The secondary flaps 32T and 32B are mounted with respective left deflector flaps 70TL and 70BL and right deflector flaps 70TR and 70BR all pivoted on a hinge 60 or the like for pivotal motion by rotary actuators 56. |
