Anti-torque nozzle system with internal sleeve valve for a rotorcraft
The system of the present application includes a duct for receiving airflow from within a duct portion of a tailboom. The airflow is a mixture of fan driven air and engine exhaust. The system includes a fixed nozzle assembly with an anti-torque nozzle, a pro-torque nozzle and a thrust nozzle. A rotating sleeve valve is located within the fixed nozzle assembly. The rotating sleeve valve located within the fixed nozzle assembly and is configured to selectively redirect airflow into one or more of the anti-torque nozzle, the pro-torque nozzle and the thrust nozzle.
1. A propulsive anti-torque system for an aircraft, the propulsive anti-torque system comprising:
a fixed nozzle assembly comprising:
an anti-torque nozzle;
a pro-torque nozzle;
a thrust nozzle;
a diverter in fluid communication with a duct located inside a tailboom, the diverter having a forward sleeve opening so as to receive mixed air from the duct, the diverter located forward of the fixed nozzle assembly;
a rotating sleeve valve disposed within the fixed nozzle assembly so as to receive the mixed air downstream from the diverter, the rotating sleeve valve comprising:
a scoop portion having a curved shape concave to the flow of air configured to redirect the mixed air from the diverter into at least one of: the anti-torque nozzle, the pro-torque nozzle, and the thrust nozzle;
an actuator configured to selectively rotate the rotating sleeve valve such that the mixed air is redirected in the fixed nozzle assembly.
2. The propulsive anti-torque system according to claim 1 , wherein the diverter portion is approximately concentric with the duct.
3. The propulsive anti-torque system according to claim 1 , wherein the airflow through the thrust nozzle produces a forward thrust vector on the aircraft.
4. The propulsive anti-torque system according to claim 1 , wherein the airflow through the anti-torque nozzle produces an anti-torque vector, thereby producing a torque on the aircraft.
5. The propulsive anti-torque system according to claim 1 , wherein the airflow through the pro-torque nozzle produces a pro-torque vector, thereby producing a torque on the aircraft.
6. The propulsive anti-torque system according to claim 1 , wherein the airflow through the anti-torque nozzle and the thrust nozzle produces a resultant force which is a combination of an anti-torque vector and a thrust vector.
7. The propulsive anti-torque system according to claim 1 , wherein the airflow is pressurized by an engine and a fan.
8. The propulsive anti-torque system according to claim 1 , wherein the anti-torque nozzle comprises:
at least one anti-torque vane for directing the airflow in an anti-torque producing direction.
9. The propulsive anti-torque system according to claim 1 , wherein the pro- torque nozzle comprises:
at least one pro-torque vane for directing the airflow in a pro-torque producing direction.
10. The propulsive anti-torque system according to claim 1 , wherein the thrust nozzle comprises:
at least one thrust vane for directing the airflow in a thrust producing direction.
11. The propulsive anti-torque system according to claim 1 , wherein the rotating sleeve valve further comprises:
a sleeve vane located in the scoop portion so as to increase the aerodynamic efficiency of the scoop portion in turning the airflow into at least one of: the anti-torque nozzle, the pro-torque nozzle, and the thrust nozzle.
12. An aircraft comprising:
an engine which provides power to a main rotor system;
a fan;
a duct within a tailboom, wherein the duct acts as a conduit to provide airflow to a propulsive anti-torque system, the airflow being a mixture of compressed air from the fan and exhaust from the engine;
a propulsive anti-torque system located near an aft end of the tailboom, the propulsive anti-torque system comprising:
a fixed nozzle assembly comprising:
an anti-torque nozzle;
a pro-torque nozzle;
a thrust nozzle;
a diverter in fluid communication with the duct, the diverter having a forward sleeve opening so as to receive mixed air from the duct, the diverter located forward of the fixed nozzle assembly;
a rotating sleeve valve disposed within the fixed nozzle assembly so as to receive the mixed air downstream from the diverter, the rotating sleeve valve comprising:
a scoop portion having a curved shape concave to the flow of air configured to redirect the mixed air from the diverter into the thrust nozzle and at least one of: the anti-torque nozzle and the pro-torque nozzle;
an actuator configured to selectively rotate the rotating sleeve valve such that selectively rotating the rotating sleeve valve redirects airflow into at least one of: the anti-torque nozzle, the pro-torque nozzle, and the thrust nozzle.
13. The aircraft according to claim 12 , wherein the airflow through the thrust nozzle produces a forward thrust vector on the aircraft.
14. The aircraft according to claim 12 , wherein the airflow through the anti-torque nozzle produces an anti-torque vector, thereby producing a torque on the aircraft.
15. The aircraft according to claim 12 , wherein the airflow through the pro-torque nozzle produces a pro-torque vector, thereby producing a torque on the aircraft.
16. The aircraft according to claim 12 , wherein the airflow through the anti-torque nozzle and the thrust nozzle produces a resultant force which is a combination of an anti-torque vector and a thrust vector.
17. The aircraft according to claim 12 , wherein the airflow is pressurized by an engine and a fan.