| 摘要 |
<p>PURPOSE: To attempt maximization of thrust control by having each of right and left sidewalls support a rotatable disk and engaging each disk with upper and lower flaps free to rock relating to a two-dimensional exhaust nozzle in a gas turbine engine which drives and propels aircrafts. CONSTITUTION: A two-dimensional exhaust nozzle 1 is equipped with right and left sidewalls 2, 3 and upper and lower built-up flaps 5, 6. An exhaust gas conducting tube 7 with an inlet 8 and an outlet 9 is defined by the built-up flaps 5, 6. Each of the built-up flaps 5, 6 is equipped with divergent flaps 10, 39 pivotally attached to the rearward edges of tapered flaps 14, 43 by hinges 15, 44 and each of the hinges 15, 44 is attached to the rearward edges of disks 16, 45 which pivot by way of a link function 17 through an actuator 18 of the tapered flaps 14, 43. Furthermore, each of the flaps 10, 39 within groove-like tracks 19, 46 installed, is engaged with drive pins 21, 48 provided in disks 22, 49 of each of the divergent flaps 10, 39.</p> |
