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US 12,521,784 B2Granted
Systems, devices, and methods for spacecraft propulsion with a heat exchanger
AssigneePortal Space Systems Inc.
InventorsJeffery T. Thornburg, Prashaanth Ravindran
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Abstract
The present disclosure relates to systems, devices, and methods for spacecraft propulsion. In an embodiment, the present disclosure relates to an apparatus comprising a heat exchanger body defining a plurality of propellant channels configured to contain a propellant, a central cavity configured to contain a working fluid and fluidically connected to a plurality of working fluid channels that extend along a radial dimension of the apparatus, and a nozzle fluidically connected to the plurality of propellant channels and configured to expel the propellant.
Claims16
A heat exchanger for a spacecraft propulsion system constructed via an additive manufacturing process, comprising:
- depositing a first transverse layer of a refractory metal, the refractory metal of the first transverse layer forming a proximal most surface of the heat exchanger, the refractory metal of the first transverse layer defining an axial inlet to a cavity configured to contain a working fluid;
- the refractory metal of the first transverse layer defining a propellant inlet to a propellant feed channel configured to convey a propellant axially through the heat exchanger;
- depositing a second transverse layer of the refractory metal distal to the first transverse layer, the refractory metal of the second transverse layer radially surrounding the cavity configured to contain the working fluid, the refractory metal of the second transverse layer forming portions of walls that define a radial channel, the walls of the radial channel forming an inlet on the wall of the cavity configured to contain the working fluid, the radial channel configured to route the working fluid radially away from the cavity configured to contain the working fluid;
- depositing a third transverse layer of the refractory metal distal to the first transverse layer, the refractory metal of the third transverse layer forming portions of an outlet port of the radial channel on an exterior radial surface of the heat exchanger;
- depositing a fourth transverse layer of the refractory metal distal to the first transverse layer, the refractory metal of the fourth transverse layer defining a portion of the propellant feed channel that is configured to convey the propellant axially through the heat exchanger such that heat is transferred from the working fluid to the propellant via the refractory metal;
- and depositing a fifth transverse layer of the refractory metal distal to the first transverse, the refractory metal of fifth transverse layer forming a portion of a wall of a plenum coupled to an outlet of the propellant feed channel;
- and depositing a sixth transverse layer of the refractory metal above the fifth transverse layer in the axial direction, the refractory metal of the sixth transverse layer forming a portion of a wall of a nozzle configured to expel the propellant, the nozzle coupled to the plenum, the nozzle having a shape configured to generate a predetermined amount of thrust.
4 more elements
A heat exchanger for a spacecraft propulsion system constructed via an additive manufacturing process, comprising:
- depositing a first transverse layer of a refractory metal, the refractory metal of the first transverse layer radially surrounding and forming a portion of a wall of a central cavity, including a working fluid opening at a proximal end thereof in a proximal most surface of the heat exchanger, that occupies a central axis of the first transverse layer and is configured to contact and contain a working fluid, the refractory metal of the first transverse layer forming portions of walls that define a radial channel, the walls of the radial channel forming an inlet on the wall of the central cavity and an outlet on an exterior radial surface of the heat exchanger, the radial channel configured to contact and contain the working fluid as it flows from the central cavity, the radial channel configured to route the working fluid radially away from the central cavity to the outlet port;
- the refractory metal of the first transverse layer defining a portion of a propellant feed channel, including a propellant inlet to the propellant feed channel at a proximal end thereof in the proximal most surface of the heat exchanger, the propellant feed channel configured to convey a propellant axially through the heat exchanger such that heat is transferred from the working fluid to the propellant via the refractory metal;
- depositing a second transverse layer of the refractory metal above the first transverse layer in an axial direction, the refractory metal of the second transverse layer defining a further portion of the propellant feed channel;
- and depositing a third transverse layer of the refractory metal above the second transverse layer in the axial direction, the refractory metal of third transverse layer forming a portion of a wall of a plenum coupled to an outlet of the propellant feed channel;
- and depositing a fourth transverse layer of the refractory metal above the third transverse layer in the axial direction, the refractory metal of the fourth transverse layer forming a portion of a wall of a nozzle configured to expel the propellant, the nozzle coupled to the plenum, the nozzle having a shape configured to generate a predetermined amount of thrust.
2 more elements
Dependencies are inferred from the claim text.