Propellant feed circuit and a cooling method
The invention relates to the aerospace field, and in particular to the field of vehicles propelled by rocket engines. In particular, the invention relates to a feed circuit ( 6 ) for feeding a rocket engine ( 2 ) at least with a first liquid propellant, the feed circuit including at least one first heat exchanger ( 18 ) suitable for being connected to a cooling circuit ( 17 ) for cooling at least one heat source in order to cool said heat source by transferring heat to the first propellant, and, in addition, downstream from said first heat exchanger, a branch passing through a second heat exchanger.
1. A feed circuit for feeding a rocket engine at least with a first liquid propellant, including at least one first heat exchanger connected to a cooling circuit for cooling at least one source of heat, wherein the feed circuit includes a first tank and a connection from the first tank that passes through said at least one first heat exchanger to a thrust chamber, and wherein the feed circuit further includes a branch branching off downstream from said at least one first heat exchanger and passing through a second heat exchanger positioned within a second tank before returning to the first tank.
2. The feed circuit according to claim 1 , comprising a buffer tank for said first liquid propellant, said at least one first heat exchanger being incorporated in the buffer tank.
3. The feed circuit according to claim 1 , wherein said first liquid propellant is a cryogenic liquid.
4. The feed circuit according to claim 3 , wherein said first liquid propellant is liquid hydrogen.
5. The feed circuit according to claim 1 , including a pump upstream from said at least one first heat exchanger.
6. An assembly comprising a feed circuit for feeding a rocket engine at least with a first liquid propellant in a first tank and a heat source, wherein the feed circuit includes at least one first heat exchanger connected to a cooling circuit for cooling the heat source; wherein the feed circuit includes a first tank and a connection from the first tank that passes through the at least one first heat exchanger for supplying the first liquid propellant to a thrust chamber; and wherein the feed circuit further comprises a branch branching off downstream from said at least one first heat exchanger and passing through a second heat exchanger positioned within a second tank before returning to the first tank.
7. The assembly according to claim 6 , wherein said heat source is a fuel cell.
8. A vehicle comprising a rocket engine with at least one feed circuit for feeding the rocket engine at least with a first liquid propellant, the vehicle further including a first tank containing the first liquid propellant, wherein the at least one feed circuit includes at least one first heat exchanger connected to a cooling circuit; a heat source provided with the cooling circuit connected to said at least one first heat exchanger of the at least one feed circuit, the at least one feed circuit includes the first tank, a connection from the first tank that passes through said at least one first heat exchanger to a thrust chamber; and a second heat exchanger positioned within a second tank, and wherein the at least one feed circuit further comprises a branch branching off downstream from said at least one first heat exchanger and passing through the second heat exchanger before returning to the first tank.
9. The vehicle of claim 8 , wherein the second tank includes a second liquid propellant that is different than the first liquid propellant.