Abstract: Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber.

Abstract: Methods and systems for manipulating surface topology of additively manufactured fluid interacting structures, such as additively manufactured heat exchangers or airfoils, and associated additively manufactured articles, are disclosed. In one aspect, an article which interacts with a fluid is imparted with surface topology features which affect performance parameters related to the fluid flow. The topological features may be sequenced, combined, intermixed, and functionally varied in size and form to locally manipulate and co-optimize multiple performance parameters at each or selectable differential lengths along a flow path. The co-optimization method may uniquely prioritize selectable performance parameters at different points along the flow path to improve or enhance overall system performance.

Abstract: Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber.

Abstract: Methods and systems for manipulating surface topology of additively manufactured fluid interacting structures, such as additively manufactured heat exchangers or airfoils, and associated additively manufactured articles, are disclosed. In one aspect, an article which interacts with a fluid is imparted with surface topology features which affect performance parameters related to the fluid flow. The topological features may be sequenced, combined, intermixed, and functionally varied in size and form to locally manipulate and co-optimize multiple performance parameters at each or selectable differential lengths along a flow path. The co-optimization method may uniquely prioritize selectable performance parameters at different points along the flow path to improve or enhance overall system performance.

Abstract: Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber.

Abstract: Methods and systems for manipulating surface topology of additively manufactured fluid interacting structures, such as additively manufactured heat exchangers or airfoils, and associated additively manufactured articles, are disclosed. In one aspect, an article which interacts with a fluid is imparted with surface topology features which affect performance parameters related to the fluid flow. The topological features may be sequenced, combined, intermixed, and functionally varied in size and form to locally manipulate and co-optimize multiple performance parameters at each or selectable differential lengths along a flow path. The co-optimization method may uniquely prioritize selectable performance parameters at different points along the flow path to improve or enhance overall system performance.

Abstract: Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber.

Abstract: Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber.

Abstract: Methods and systems for manipulating surface topology of additively manufactured fluid interacting structures, such as additively manufactured heat exchangers or airfoils, and associated additively manufactured articles, are disclosed. In one aspect, an article which interacts with a fluid is imparted with surface topology features which affect performance parameters related to the fluid flow. The topological features may be sequenced, combined, intermixed, and functionally varied in size and form to locally manipulate and co-optimize multiple performance parameters at each or selectable differential lengths along a flow path. The co-optimization method may uniquely prioritize selectable performance parameters at different points along the flow path to improve or enhance overall system performance.

Abstract: Devices and methods of rocket propulsion are disclosed. In one aspect, a staged combustion liquid rocket engine with preburner and turbopump unit (TPU) integrated into the structure of the combustion chamber is described. An initial propellant mixture is combusted in a preburner combustion chamber formed as an annulus around a main combustion chamber, the combustion products from the preburner driving the turbine of the TPU and subsequently injected into the main combustion chamber for secondary combustion along with additional propellants, generating thrust through a supersonic nozzle. The preburner inner cylindrical wall is shared with the outer cylindrical wall of the engine's main combustion chamber and the turbine is axially aligned with the main combustion chamber.