Thrust orienting nozzle
View Patent ↗The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzle and comprising at least one of following two piloting means: a means of dividing the principal flow into each of the two half-nozzles, and a means of orienting the thrust vector produced by each of the two half-nozzles. The invention applies in particular to the yaw control of an aircraft without a vertical tail unit.
1. A thrust orienting nozzle for an aerospace vehicle, comprising:
a channel configured to guide a principal propulsion gas flow downstream from at least one gas generator;
a first symmetric channel configured to guide a first portion of the principal propulsion gas flow from the channel to a first half-nozzle;
a second symmetric channel configured to guide a second portion of the principal propulsion gas flow from the channel to a second half-nozzle;
the first half-nozzle configured to eject the first portion of the principal propulsion gas flow, the first half-nozzle including a first throat and first divergent walls downstream of the first throat, the first divergent walls including a first internal side and a first external side;
the second half-nozzle configured to eject the second portion of the principal propulsion gas flow, the second half-nozzle including a second throat and second divergent walls downstream of the second throat, the second divergent walls including a second internal side and a second external side; and
at least one of the following two piloting means, including
a) a means of dividing the principal propulsion gas flow into each of the half-nozzles, and
b) a means of orienting the thrust vector produced by each of the two half-nozzles,
wherein the at least one of the two piloting means being fluid injection means downstream of the first symmetric channel and the second symmetric channel and within the first half-nozzle and the second half-nozzle.
2. The thrust orienting nozzle according to claim 1 , wherein said first half-nozzle and said second half-nozzle are configured to orientate a thrust vector in yaw for the aerospace vehicle.
3. The thrust orienting nozzle according to claim 1 , wherein said first half-nozzle and said second half-nozzle are configured to orientate a thrust vector in pitch for the aerospace vehicle.
4. The thrust orienting nozzle according to claim 2 , wherein the nozzle comprises two pairs of half-nozzles, including
a first pair of half-nozzles for the orientation of the thrust vector in yaw, and
a second pair of half-nozzles for an orientation of a thrust vector in pitch for the aerospace vehicle,
wherein the first pair of half-nozzles includes the first half-nozzle and the second half-nozzle, and the second pair of half-nozzles includes a third half-nozzle and a fourth half-nozzle.
5. The thrust orienting nozzle according to claim 1 , wherein the means of dividing the principal propulsion gas flow comprises the fluid injection means in the throat of each of the half-nozzles.
6. The thrust orienting nozzle according to claim 5 , wherein the gas generator is a turbojet, and the fluid injection means are supplied with air drawn off from a compressor of the at least one gas generator,
wherein the fluid injection means are disposed on the first internal side of the first half-nozzle and the second internal side of the second half-nozzle, the first internal side being longer than the first external side as measured downstream from the first throat, the second internal side being longer than the second external side as measured downstream from the second throat.
7. The thrust orienting nozzle according to claim 6 , wherein the air is continuously drawn off from the compressor.
8. The thrust orienting nozzle according to claim 1 , wherein the means of orienting a thrust vector produced by the first half-nozzle and a thrust vector produced by the second half-nozzle are constituted by the fluid injection means disposed in at least one of the first divergent walls of and in at least one of the second divergent walls.
9. The thrust orienting nozzle according to claim 8 ,
wherein the fluid injection means are disposed on the first internal side of the first half-nozzle and the second internal side of the second half-nozzle, the first internal side being longer than the first external side as measured downstream from the first throat, the second internal side being longer than the second external side as measured downstream from the second throat.
10. The thrust orienting nozzle according to claim 1 , wherein the at least one gas generator includes a turbine, and the first half-nozzle and the second half-nozzle are arranged to mask the turbine.
11. The thrust orienting nozzle according to claim 1 , wherein the principal propulsion gas flow is generated by two gas generators and the thrust orienting nozzle comprises a means of orientation of a thrust vector produced by each of the half-nozzles.
12. A turbomachine, comprising:
turbomachinery configured to create a principal propulsion gas flow;
a channel configured to guide the principal propulsion gas flow downstream from the turbomachinery;
a first symmetric channel configured to guide a first portion of the principal propulsion gas flow from the channel to a first half-nozzle;
a second symmetric channel configured to guide a second portion of the principal propulsion gas flow from the channel to a second half-nozzle;
the first half-nozzle configured to eject the first portion of the principal propulsion gas flow, the first half-nozzle including a first throat and first divergent walls, the first divergent walls including a first internal side and a first external side;
the second half-nozzle configured to eject the second portion of the principal propulsion gas flow, the second half-nozzle including a second throat and second divergent walls, the second divergent walls including a second internal side and a second external side; and
at least one of the following two piloting means, including
a) a means of dividing the principal propulsion gas flow into each of the half-nozzles, and
b) a means of orienting the thrust vector produced by each of the two half-nozzles,
wherein the at least one of the two piloting means being fluid injection means, and two half-nozzles includes the first half-nozzle and the second half-nozzle, and
wherein the fluid injection means are disposed on the first internal side of the first half-nozzle and the second internal side of the second half-nozzle, the first internal side being longer than the first external side as measured downstream from the first throat, the second internal side being longer than the second external side as measured downstream from the second throat.
13. The thrust orienting nozzle according to claim 1 , wherein the aerospace vehicle is a drone, the first internal side being longer than the first external side as measured downstream from the first throat, and the second internal side being longer than the second external side as measured downstream from the second throat.
14. The thrust orienting nozzle according to claim 1 , wherein
the first divergent walls also includes an upper wall and a lower wall, and the upper wall and the lower wall are opposite to each other and parallel to each other.