Exhaust nozzle for an engine of a flying craft
View Patent ↗Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned with slots 39 formed in the outlet ducts, and controlled means for adjusting the outflow of gas injected into the outlet ducts.
1. An exhaust nozzle for an engine of a flying craft, comprising:
a tubular body with two outlet ducts defining, in the upstream direction, a primary gas flow path divided, in the downstream direction, into two parallel secondary gas flow paths, wherein each of the two outlet ducts comprises a box for injecting gas into a corresponding secondary path, each box being attached to a lateral wall of a corresponding outlet duct in an intermediate space formed between downstream sections of the outlet ducts and each box having a window aligned with a slot formed in the lateral wall of the corresponding outlet duct, and an adjustment mechanism configured to adjust a direction of an outflow of gas injected through said window into the secondary path, wherein said adjustment mechanism is configured to adjust the direction of said outflow of gas between a direction perpendicular to said secondary path and a non-perpendicular direction oblique relative to said secondary path.
2. A nozzle according to claim 1 , wherein said adjustment mechanism comprises a flap pivotally mounted inside the box between a position in which the flap closes off the window and a position in which the flap opens the window, said flap being connected to an actuator situated outside the box.
3. A nozzle according to claim 2 , wherein the flap is pivotally mounted along an edge of the window by a pin having one end outside the box connected to the actuator and another end guided in a bearing mounted in the box.
4. A nozzle according to claim 2 , wherein, when the window is in the closed-off position, the flap provides a continuity of the inner surface of the outlet duct.
5. A nozzle according to claim 3 , wherein seals are mounted around the window between the box and the wall of the outlet duct and on the pivot pin of the flap.
6. A nozzle according to claim 1 , wherein each box is situated in a vicinity of the downstream end of the outlet duct.
7. A nozzle according to claim 1 , wherein the boxes for injecting gas into the outlet ducts are each supplied with pressurized gas via a pipe opening into the box in a direction substantially perpendicular to the axis of the engine and to the yaw axis of the flying craft and directed outwardly with respect to the axis of the engine.
8. A nozzle according to claim 7 , wherein, in each outlet duct, the injection of gas from the box is directed outwardly with respect to the axis of the engine.
9. A nozzle according to claim 1 , wherein the boxes are supplied with pressurized gas from an annular manifold that bleeds off said pressurized gas flow path.
10. A nozzle according to claim 1 , wherein said primary gas flow path has a circular cross section and each of said secondary gas flow paths has a substantially rectangular cross section.
11. A nozzle according to claim 1 , wherein each of said outlet ducts has only one sole box.
12. A nozzle according to claim 11 , wherein, in each outlet duct, the sole box is located on an inner lateral wall of the outlet duct relative to an axis of the engine.