Apparatus for desuperheating high temperature, high velocity steam
A desuperheating spray chamber for use in a rocket exhaust recovery system for a nuclear thermal propulsion rocket, including a substantially-cylindrical outer tank with an upper end including an entrance port and two exhaust ports, a substantially-cylindrical shroud extending downwardly from an inner surface of the upper end of the tank, an annular inner spray ring that is both disposed within and concentric with the shroud; and an annular outer spray ring that is disposed between a side wall of the outer tank and the shroud, the annular outer ring being concentric with the shroud.
1. A desuperheating spray chamber for use in a rocket exhaust recovery system for a nuclear thermal propulsion rocket, comprising:
a substantially-cylindrical outer tank with an upper end including an entrance port and two exhaust ports disposed thereon;
a substantially-cylindrical shroud extending downwardly from an inner surface of the upper end of the tank, wherein the shroud is concentric to the entrance port about a longitudinal center axis of the outer tank;
an annular inner spray ring that is both disposed within and concentric to the shroud about the longitudinal center axis; and
an annular outer spray ring that is disposed between a side wall of the outer tank and the shroud, the annular outer ring being concentric to the shroud about the longitudinal center axis.
2. The spray chamber of claim 1 , further comprising a drain assembly in fluid communication with a bottom end of the outer tank.
3. The spray chamber of claim 1 , further comprising a manway extending radially-outwardly from the side wall of the outer tank.
4. The spray chamber of claim 3 , further including ports extending radially-outwardly from the side wall of the outer tank for receiving instrumentation.
5. The spray chamber of claim 1 , further comprising a first set of nozzles disposed on the inner spray ring.
6. The spray chamber of claim 5 , wherein each nozzle of the first set of nozzles has a spray axis that defines one of an obtuse and an acute angle with respect to the longitudinal center axis of the outer tank.
7. The spray chamber of claim 5 , further comprising a second sent of nozzles disposed on the outer spray ring, each nozzle of the second set of nozzles having a spray axis that is parallel to the longitudinal center axis of the outer tank.
8. A desuperheating spray chamber for use in a rocket exhaust recovery system for a nuclear thermal propulsion rocket, comprising:
a substantially-cylindrical outer tank with an upper end including an entrance port and at least one exhaust port disposed thereon;
a substantially-cylindrical shroud extending downwardly from an inner surface of the upper end of the tank;
an inner spray ring that is disposed within the shroud about a longitudinal center axis of the outer tank; and
an outer spray ring that is disposed between a side wall of the outer tank and the shroud, and is concentric to the shroud.
9. The spray chamber of claim 8 , further comprising a drain assembly in fluid communication with a bottom end of the outer tank.
10. The spray chamber of claim 8 , further comprising a manway extending radially-outwardly from the side wall of the outer tank.
11. The spray chamber of claim 10 , further including ports extending radially-outwardly from the side wall of the outer tank for receiving instrumentation.
12. The spray chamber of claim 8 , further comprising a first set of nozzles disposed on the inner spray ring.
13. The spray chamber of claim 12 , wherein each nozzle of the first set of nozzles has a spray axis that defines one of an obtuse and an acute angle with respect to the longitudinal center axis of the outer tank.
14. The spray chamber of claim 12 , further comprising a second set of nozzles disposed on the second outer spray ring.
15. The spray chamber of claim 14 , wherein each nozzle of the second set of nozzles has a spray axis that is parallel to the longitudinal center axis of the outer tank.