Damping of vibration of a combustion chamber by resonators
Device for damping oscillations of a combustion chamber that includes at least one resonator connected to a pre-chamber in a vibration-damping manner. The pre-chamber is connected to a combustion chamber in a vibration-damping manner via at least one passage channel. This abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.
1. A device for damping oscillations of a combustion chamber comprising:
at least one resonator structured arranged to dampen vibrations in fluid communication with a pre-chamber,
an injector head having at least one passage channel, an open area and at least one injector element, the injector element extended through the open area to supply fuel to the combustion chamber.
wherein the pre-chamber is connected to the combustion chamber to dampen vibrations via the at least one passage channel.
2. The device of claim 1 , wherein the combustion chamber adjoins the injection head.
3. The device of claim 2 , wherein the injection head conducts the fuel flow into the combustion chamber.
4. The device of claim 3 , wherein the pre-chamber is arranged upstream of the at least one injection element.
5. The device of claim 3 , wherein the pre-chamber is arranged an area of the at least one injection element.
6. The device of claim 1 , wherein the at least one passage channel is part of the injection element.
7. The device of claim 1 , wherein the combustion chamber is part of a rocket engine.
8. A system for damping oscillations, the system comprising:
a combustion chamber;
an injection head having at least one injector tube to inject fuel to the combustion chamber;
a pre-chamber supply the fuel to the injection head; and
at least one resonator structured and arranged to dampen vibrations of the combustion chamber and comprising one of:
an opening in fluid communicating with the pre-chamber; and
an opening in fluid communicating with an open area of the injection head.
9. The system of claim 8 , wherein the combustion chamber comprises an outlet arranged opposite the injection head.
10. The system of claim 8 , wherein the opening communicating with the pre-chamber comprises a circumferential opening.
11. The system of claim 8 , wherein the at least one resonator is annular shaped.
12. The system of claim 8 , wherein the at least one resonator comprises a sleeve which extends into the open area of the injection head.
13. The system of claim 8 , wherein the at least one resonator comprises a sleeve oriented along a direction of gas flow and which extends into the open area of the injection head.
14. The system of claim 8 , wherein the at least one resonator comprises a plurality of sleeves at least one of oriented along a direction of gas flow and extending into the open area of the injection head.
15. The system of claim 8 , wherein the at least one resonator comprises a radially oriented opening communicating with the pre-chamber.
16. The system of claim 8 , wherein the at least one resonator comprises a plurality of radially oriented openings communicating with the pre-chamber.
17. The system of claim 8 , wherein the at least one resonator comprises a radially oriented opening communicating with the open area of the injection head.
18. The system of claim 8 , wherein the at least one resonator is one of:
integrally formed in a side wall of the pre-chamber;
integrally formed in an end wall of the pre-chamber; and
integrally formed in a side wall of the injection head.
19. A system for damping oscillations of a rocket engine, the system comprising:
a combustion chamber;
an injection head having at least one injector tube to inject fuel to the combustion chamber;
a pre-chamber supply the fuel to the injection head; and
at least one resonator structured and arranged to dampen vibrations of the combustion chamber and comprising one of:
an opening in fluid communicating with the pre-chamber; and
an opening in fluid communicating with an open area of the injection head.