Engine exhaust system with directional nozzle
An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The secondary duct has a portion selectively rotatable relative to the remainder of the secondary duct for directing the exhaust gas vector. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct.
1. An exhaust system for an aircraft having an airframe and an engine with an exhaust exit, the exhaust system comprising:
a primary exhaust duct adapted to communicate exhaust gas from the engine exhaust exit and configured for movement with the engine;
a secondary exhaust duct in communication with the primary exhaust duct and adapted to be movably mounted to the airframe, the secondary duct having a portion selectively rotatable relative to the remainder of the secondary duct;
a drag link connecting the secondary duct to the primary duct, the drag link being configured to maintain coaxial alignment between the primary duct and the secondary duct and to allow axial movement of the secondary duct relative to the primary duct; and
a slip joint positioned between the primary duct and the secondary duct, the slip joint being configured to allow axial movement of the secondary duct relative to the primary duct and configured to prevent vertical and lateral movement of the secondary duct relative to the primary duct.
2. The exhaust system according to claim 1 , further comprising:
at least one strut adapted to connect the secondary duct to an airframe.
3. The exhaust system according to claim 1 , wherein the rotatable portion of the secondary duct is curved.
4. The exhaust system according to claim 1 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct.
5. The exhaust system according to claim 1 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct;
wherein the actuator is adapted to be operated to prevent overheating of components near the secondary duct.
6. The exhaust system according to claim 1 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct;
wherein the actuator is adapted to be operated to reduce the infra-red signature of the secondary duct.
7. An aircraft engine system, comprising:
an engine having an exhaust exit;
a primary exhaust duct in fluid communication with the exhaust exit and configured for movement with the engine;
a secondary exhaust duct in fluid communication with the primary exhaust duct and adapted to be movably mounted to the airframe, the secondary duct having a portion selectively rotatable relative to the remainder of the secondary duct;
a drag link connecting the secondary duct to the primary duct, the drag link being configured to maintain coaxial alignment between the primary duct and the secondary duct and to allow axial movement of the secondary duct relative to the primary duct; and
a slip joint positioned between the primary duct and the secondary duct, the slip joint being configured to allow axial movement of the secondary duct relative to the primary duct and configured to prevent vertical and lateral movement of the secondary duct relative to the primary duct.
8. The engine system according to claim 7 , further comprising:
at least one strut adapted to connect the secondary duct to an airframe.
9. The exhaust system according to claim 7 , wherein the rotatable portion of the secondary duct is curved.
10. The exhaust system according to claim 7 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct.
11. The exhaust system according to claim 7 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct;
wherein the actuator is adapted to be operated to prevent overheating of components near the secondary duct.
12. The exhaust system according to claim 7 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct;
wherein the actuator is adapted to be operated to reduce the infra-red signature of the secondary duct.
13. An aircraft, comprising:
an airframe;
an engine having an exhaust exit;
a primary exhaust duct in fluid communication with the exhaust exit and configured for movement with the engine;
a secondary exhaust duct in fluid communication with the primary exhaust duct and adapted to be movably mounted to the airframe, the secondary duct having a portion selectively rotatable relative to the remainder of the secondary duct;
a drag link connecting the secondary duct to the primary duct, the drag link being configured to maintain coaxial alignment between the primary duct and the secondary duct and to allow axial movement of the secondary duct relative to the primary duct; and
a slip joint positioned between the primary duct and the secondary duct, the slip joint being configured to allow axial movement of the secondary duct relative to the primary duct and configured to prevent vertical and lateral movement of the secondary duct relative to the primary duct.
14. The aircraft according to claim 13 , further comprising:
at least one strut adapted to connect the secondary duct to an airframe.
15. The aircraft according to claim 13 , wherein the rotatable portion of the secondary duct is curved.
16. The aircraft according to claim 13 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct.
17. The aircraft according to claim 13 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct;
wherein the actuator is adapted to be operated to prevent overheating of components near the secondary duct.
18. The aircraft according to claim 13 , further comprising:
an actuator selectively operable for rotating the rotatable portion of the secondary duct;
wherein the actuator is adapted to be operated to reduce the infra-red signature of the secondary duct.
19. An aircraft, comprising:
an airframe;
an engine having an exhaust exit;
a primary exhaust duct in fluid communication with the exhaust exit and configured for movement with the engine;
a secondary exhaust duct in fluid communication with the primary exhaust duct and adapted to be movably mounted to the airframe, the secondary duct having a portion selectively rotatable relative to the remainder of the secondary duct;
a drag link connecting the secondary duct to the primary duct, the drag link being configured to maintain coaxial alignment between the primary duct and the secondary duct and to allow axial movement of the secondary duct relative to the primary duct;
a slip joint positioned between the primary duct and the secondary duct, the slip joint being configured to allow axial movement of the secondary duct relative to the primary duct and configured to prevent vertical and lateral movement of the secondary duct relative to the primary duct; and
at least one strut connecting the secondary duct to the airframe; wherein the link and at least one strut cooperate to maintain a generally consistent relative alignment between the primary duct and the secondary duct.