# US 8,413,419 B2 · Regeneratively cooled porous media jacket > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,413,419 B2 - Document ID: US8413419B2 - Status: Granted - Kind: B2 - Application number: 12/633,770 - Filed: 2009-12-08 - Published: 2010-08-19 - Granted: 2013-04-09 - Earliest claimed: 2008-12-08 - Assignees: Firestar Engineering, LLC - Applicants: Greg Mungas; David J. Fisher; Adam Pollok London; Jack Merrill Fryer - Inventors: Greg Mungas; David J. Fisher; Adam Pollok London; Jack Merrill Fryer - Web page: https://patentgrep.com/patent/US8413419B2 ## CPC - F02K 9/00: Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof - F02K 9/34: Casings; Combustion chambers; Liners thereof - F02K 9/40: Cooling arrangements {(for nozzles F02K9/972)} - F02K 9/64: having cooling arrangements - F02K 9/972: {Fluid cooling arrangements for nozzles (F02K9/64 takes precedence)} - F05D 2260/20: Heat transfer, e.g. cooling - Y10T 29/49346: Rocket or jet device making - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) 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. ### Claim 3 (depends on 1) 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. ### Claim 4 (depends on 3) 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. ### Claim 5 (depends on 3) 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. ### Claim 6 (depends on 1) The cooling jacket of claim 1 wherein the porous media matrix follows the contour of the contoured chamber. ### Claim 7 (depends on 1) The cooling jacket of claim 1 wherein the porous media matrix comprises a microfluidic porous lithographic structure. ### Claim 8 (depends on 1) The cooling jacket of claim 1 wherein the porous media matrix is non-catalytic to the coolant fluid. ### Claim 9 (depends on 1) The cooling jacket of claim 1 wherein the porous media matrix includes aluminum. ### Claim 10 (depends on 1) The cooling jacket of claim 1 wherein the porous media matrix includes nickel. ### Claim 11 (depends on 1) The cooling jacket of claim 1 wherein the porous media matrix includes stainless steel. ### Claim 12 (depends on 1) The cooling jacket of claim 1 wherein the porous media matrix has a porosity of less than 80%. ### Claim 13 (depends on 1) The cooling jacket of claim 1 wherein the inner wall, porous media matrix, and outer wall are formed from stacked and aligned metal layers. ### Claim 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. ### Claim 15 (depends on 14) The cooling jacket of claim 14 wherein the porous media matrix comprises a microfluidic porous lithographic structure. ### Claim 16 (depends on 14) The cooling jacket of claim 14 wherein the porous media matrix comprises microfluidic porous metal foam. ### Claim 17 (depends on 14) The cooling jacket of claim 14 wherein the porous media matrix is non-catalytic to the coolant fluid. ### Claim 18 (depends on 14) The cooling jacket of claim 14 wherein the porous media matrix comprises open cell metal foam. ### Claim 19 (depends on 14) The cooling jacket of claim 14 wherein the porous media matrix includes aluminum. ### Claim 20 (depends on 14) The cooling jacket of claim 14 wherein the porous media matrix includes nickel. ### Claim 21 (depends on 14) The cooling jacket of claim 14 wherein the porous media matrix includes stainless steel. ### Claim 22 (depends on 14) The cooling jacket of claim 14 wherein the porous media matrix has a porosity of less than 80%. ### Claim 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. ### Claim 24 (depends on 23) The method of claim 23 wherein the porous media matrix has a porosity of less than 80%. ### Claim 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. ### Claim 26 (depends on 25) The method of claim 25 wherein the porous media matrix has a porosity of less than 80%.