Rocket engine turbopump with coolant passage in impeller central hub
Disclosed herein are various technologies pertinent to rocket engines, including injector, thrust chamber, and electrical turbopump devices that may be combined to provide a more efficient rocket engine. The electrical turbopump impeller includes a coolant bypass port fluidically connected with a coolant passage that passes through the impeller central hub and allows some of the propellant that is acted on by the impeller to bypass the impeller outlet and instead be flowed into the electrical turbopump housing so that the diverted propellant may be used to cool the various components housed within the housing such as the electric motor bearings, stator, rotor, and electronics.
1. A system comprising:
a first turbopump comprising an impeller and an electric motor, wherein:
the impeller has a central hub having a plurality of coolant paths extending through the central hub and a plurality of vanes extending from the central hub,
a first turbopump inlet is configured to receive a liquid, and
the impeller is configured to drive a first portion of the liquid to a first turbopump outlet and a second portion of the liquid through the plurality of coolant paths, into a cooling volume containing the electric motor, and out of one or more coolant outlets; and
a thrust chamber operably coupled to the first turbopump outlet.
2. The system of claim 1 , wherein the electric motor is controllable to vary a pumping rate of the liquid.
3. The system of claim 1 , wherein the system comprises:
a first propellant source operably coupled to the thrust chamber via the first turbopump; and
a second propellant source operably coupled to the thrust chamber via a second turbopump, wherein the system is configured to produce a mixture of a first propellant and a second propellant in the thrust chamber.
4. The system of claim 3 , wherein the first turbopump and the second turbopump are electrically controllable to vary the mixture of the first propellant and the second propellant.
5. The system of claim 3 , wherein the first turbopump and the second turbopump are controllable in real-time to optimize a combustion of the mixture of the first propellant and the second propellant.
6. The system of claim 1 , wherein the system comprises:
a first propellant source;
a first propellant supply line configured to supply a first propellant from the first propellant source to the first turbopump inlet; and
one or more coolant return lines configured to re-introduce the first propellant that passes out of the one or more coolant outlets to the first turbopump inlet.
7. The system of claim 1 , wherein the system comprises:
a first propellant source;
a first propellant supply line configured to supply a first propellant from the first propellant source to the first turbopump inlet; and
one or more coolant return lines configured to re-introduce the first propellant that passes out of the one or more coolant outlets into the first propellant supply line.
8. The system of claim 1 , wherein:
the liquid is a fuel,
the fuel that exits the first turbopump outlet is directed through a plurality of coolant flow passages, and
the plurality of coolant flow passages is defined by a plurality of walls between an interior skin of the thrust chamber and an exterior skin of the thrust chamber.
9. The system of claim 8 , wherein the fuel that is directed through the plurality of coolant flow passages passes into and through an injector manifold.
10. The system of claim 9 , wherein an oxidizer flows over the injector manifold without being mixed with the first portion of the liquid.
11. A method comprising:
actuating an electric motor to drive a first turbopump, the first turbopump including an impeller having a central hub with a plurality of coolant paths extending through the central hub and a plurality of vanes extending from the central hub;
providing a liquid to a first turbopump inlet;
driving, via the impeller, a first portion of the liquid to a first turbopump outlet, wherein a thrust chamber is operably coupled to the first turbopump outlet; and
driving, via the impeller, a second portion of the liquid through the plurality of coolant paths, through a cooling volume containing the electric motor, and out of one or more coolant outlets.
12. The method of claim 11 , wherein the method comprises controlling the electric motor to vary a pumping rate of the liquid.
13. The method of claim 11 , wherein the method comprises:
pumping a first propellant to a combustion chamber via the first turbopump; and
pumping a second propellant to the combustion chamber via a second turbopump.
14. The method of claim 13 , wherein the method comprises electrically controlling the first turbopump and the second turbopump to vary a mixture of the first propellant and the second propellant within the combustion chamber.
15. The method of claim 14 , wherein the method comprises electrically controlling the first turbopump and the second turbopump in real-time to optimize a combustion of the mixture of the first propellant and the second propellant.
16. The method of claim 11 , wherein the method comprises re-introducing the liquid that passes out of the one or more coolant outlets to the first turbopump inlet.
17. The method of claim 11 , wherein the method comprises re-introducing the liquid that passes out of the one or more coolant outlets to a source of the liquid.
18. The method of claim 11 , wherein the liquid is a fuel, and wherein the method comprises directing the fuel that exits the first turbopump outlet through a plurality of coolant flow passages defined by a plurality of walls between an interior skin of the thrust chamber and an exterior skin of the thrust chamber.
19. The method of claim 18 , wherein the method comprises directing the fuel that is directed through the plurality of coolant flow passages into and through an injector manifold.
20. The method of claim 19 , wherein the method comprises:
directing an oxidizer over and around the injector manifold; and
mixing, within the thrust chamber, the fuel that flows through the injector manifold with the oxidizer.
21. A system comprising:
a first turbopump comprising an impeller having a central hub with a plurality of coolant paths extending through the central hub and a plurality of vanes extending from the central hub, an electric motor and control electronics, wherein:
the control electronics are configured to operate the electric motor to cause the impeller to pump a first propellant during a rocket flight,
a first portion of the first propellant is directed toward a combustion chamber through operation of the impeller, and
a second portion of the first propellant is directed, through operation of the impeller, through the plurality of coolant paths and into and through a cooling volume containing the electric motor, thereby cooling the electric motor and the control electronics.
22. The system of claim 21 , wherein the electric motor is controllable to vary a pumping rate of the first propellant.
23. The system of claim 21 , wherein the system comprises:
a first propellant source that supplies the first propellant to the first turbopump; and
a second propellant source that supplies a second propellant to a second turbopump.
24. The system of claim 23 , wherein the first turbopump and the second turbopump are configured to vary a mixture of the first propellant and the second propellant.
25. The system of claim 24 , wherein the first turbopump and the second turbopump operate in real-time to optimize a combustion power.
26. The system of claim 21 , wherein the system comprises one or more coolant return lines configured to re-introduce the second portion of the first propellant into the first turbopump.
27. The system of claim 21 , wherein the system comprises:
a first propellant source that supplies the first propellant to the first turbopump via a supply line; and
one or more coolant return lines configured to re-introduce the second portion of the first propellant into the supply line.
28. The system of claim 21 , wherein the first portion of the first propellant is directed through a plurality of coolant flow passages of a thrust chamber, wherein the plurality of coolant flow passages is defined by a plurality of walls between an interior skin of the thrust chamber and an exterior skin of the thrust chamber.
29. The system of claim 28 , wherein the first portion of the first propellant that is directed through the plurality of coolant flow passages passes into an injector.
30. The system of claim 29 , wherein a second propellant flows over the injector before entering the combustion chamber.