Regeneratively cooled porous media jacket
The fluid and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is used to design a regeneratively cooled rocket or other high temperature engine cooling jacket. Cooling jackets comprising impermeable inner and outer walls, and porous media channels are disclosed. Also disclosed are porous media coolant jackets with additional structures designed to transfer heat directly from the inner wall to the outer wall, and structures designed to direct movement of the coolant fluid from the inner wall to the outer wall. Methods of making such jackets are also disclosed.
1. A rocket engine cooling jacket comprising:
a fluid-impermeable inner wall forming a contoured chamber and a combustion chamber;
a fluid-impermeable outer wall;
an open cell metal foam porous media matrix between the inner wall and the outer wall, wherein the porous media matrix includes an inlet configured to receive a coolant fluid at one end of the contoured chamber and an outlet configured to expel the coolant fluid at the other end of the contoured chamber into the combustion chamber.
2. The cooling jacket of claim 1 wherein the porous media matrix comprises structures providing multiple direct thermal connections between the inner wall and the outer wall.
3. The cooling jacket of claim 1 wherein the porous media matrix comprises structures directing mixing of the coolant fluid from the inner wall to the outer wall.
4. The cooling jacket of claim 3 wherein the porous media matrix structures directing mixing of the coolant fluid from the inner wall to the outer wall include microtubes.
5. The cooling jacket of claim 3 wherein the porous media matrix structures directing mixing of the coolant fluid from the inner wall to the outer wall include ribbon structures.
6. The cooling jacket of claim 1 wherein the porous media matrix follows the contour of the contoured chamber.
7. The cooling jacket of claim 1 wherein the porous media matrix comprises a microfluidic porous lithographic structure.
8. The cooling jacket of claim 1 wherein the porous media matrix is non-catalytic to the coolant fluid.
9. The cooling jacket of claim 1 wherein the porous media matrix includes aluminum.
10. The cooling jacket of claim 1 wherein the porous media matrix includes nickel.
11. The cooling jacket of claim 1 wherein the porous media matrix includes stainless steel.
12. The cooling jacket of claim 1 wherein the porous media matrix has a porosity of less than 80%.
13. The cooling jacket of claim 1 wherein the inner wall, porous media matrix, and outer wall are formed from stacked and aligned metal layers.
14. A rocket engine cooling jacket comprising:
a fluid-impermeable inner wall forming a cooling chamber and a combustion chamber;
a fluid-impermeable outer wall;
a porous media matrix between the inner wall and the outer wall, wherein the inner wall, porous media matrix, and outer wall are formed from stacked and aligned metal layers, and wherein the porous media matrix includes an inlet configured to receive a coolant fluid at one end of the cooling chamber and an outlet configured to expel the coolant fluid at the other end of the cooling chamber into the combustion chamber.
15. The cooling jacket of claim 14 wherein the porous media matrix comprises a microfluidic porous lithographic structure.
16. The cooling jacket of claim 14 wherein the porous media matrix comprises microfluidic porous metal foam.
17. The cooling jacket of claim 14 wherein the porous media matrix is non-catalytic to the coolant fluid.
18. The cooling jacket of claim 14 wherein the porous media matrix comprises open cell metal foam.
19. The cooling jacket of claim 14 wherein the porous media matrix includes aluminum.
20. The cooling jacket of claim 14 wherein the porous media matrix includes nickel.
21. The cooling jacket of claim 14 wherein the porous media matrix includes stainless steel.
22. The cooling jacket of claim 14 wherein the porous media matrix has a porosity of less than 80%.
23. A method of cooling a rocket engine comprising passing a fluid propellant coolant from a propellant tank through an inlet port, through an open cell metal foam porous media matrix that is disposed between an inner wall of the rocket engine that is fluid impermeable and an outer wall of the rocket engine that is fluid impermeable; and through an outlet port into the combustion chamber of the rocket engine.
24. The method of claim 23 wherein the porous media matrix has a porosity of less than 80%.
25. A method of cooling a rocket engine comprising passing a fluid propellant coolant from a propellant tank through an inlet port, through a microfluidic porous media matrix that is disposed between an inner wall of the rocket engine that is fluid impermeable and an outer wall of the rocket engine that is fluid impermeable, wherein the inner wall, porous media matrix, and outer wall are formed from stacked and aligned metal layers; and through an outlet port into the combustion chamber of the rocket engine.
26. The method of claim 25 wherein the porous media matrix has a porosity of less than 80%.