An improved rocket engine system including a rotating detonation rocket engine, and three propellants. The propellants consist of at least one oxidizer and at least one fuel. A third propellant, a fuel or oxidizer or inert fluid, is injected to control the detonation characteristics. The improved rocket engine system may further include at least one additional rocket engine (pump provides pressure for multiple engines). The improved rocket engine system may further include multiple turbopump shafts for independent control of the propellants.

An improved rocket engine system including a rotating detonation rocket engine, and three propellants. The propellants consist of at least one oxidizer and at least one fuel. A third propellant, a fuel or oxidizer or inert fluid, is injected to control the detonation characteristics. The improved rocket engine system may further include at least one additional rocket engine (pump provides pressure for multiple engines). The improved rocket engine system may further include multiple turbopump shafts for independent control of the propellants.

A combustion chamber suitable in particular for use in an engine comprises a combustion space, a combustion space wall delimiting the combustion space, and a plurality of cooling channel webs extending from a surface of the combustion space wall which faces away from the combustion space and separating mutually adjacent cooling channels from one another. The cooling channel webs are each provided with a projection extending from an end face of the cooling channel webs which faces away from the combustion space. Furthermore, the combustion chamber comprises a plurality of cover elements, wherein each cover element extends along a longitudinal axis of a cooling channel delimited by two mutually adjacent cooling channel webs between the projections of the mutually adjacent cooling channel webs and is form-fittingly connected to the projections of the two mutually adjacent cooling channel webs in order to cover the cooling channel.

Concurrent rocket engine pre-conditioning and tank filling is disclosed. A disclosed example apparatus includes an inlet valve to supply a rocket propellant tank that is associated with a rocket engine with rocket propellant, and a flow director to direct at least a portion of a flow of the rocket propellant from the inlet valve to a chill line of the rocket engine to thermally condition the rocket engine as the rocket propellant tank is being filled with the rocket propellant.

An example turbo-pump for a rocket is provided. The example turbo-pump includes a turbine. A first chamber, coupled to the turbine, receives oxidizer fluid resulting in the oxidizer fluid leaving the first chamber at a faster rate to a reaction chamber. A select amount of the oxidizer fluid enters the turbine. A second chamber, coupled to the turbine, receives fuel resulting in the fuel leaving the second chamber at a faster rate to the reaction chamber. A select amount of the fuel enters the turbine. A plurality of pipes is positioned around the turbine. The plurality of pipes is configured to distribute cooling fluid around the turbine to lower the kinetic energy of the select amount of the fuel and the oxidizer fluid within the turbine.

A thrust chamber liner includes a metallic combustion chamber having an annular protrusion extending radially away from an exterior surface of the combustion chamber adjacent to its injector opening. A metallic nozzle is coupled to the combustion chamber at its throat opening. A composite material encases the exterior surface of the combustion chamber, but is only bonded to the annular protrusion.

A liquid rocket engine cools a thruster body by pumping propellant through cooling channels integrated in the thruster body between internal and external surfaces. One or more of the cooling channel surfaces has a variable depth along a thrust axis to mix propellant flow and destroy thermal stratification, such as a depth that varies with a repeated contiguous sinusoidal form along the thrust axis. Fuel passed through the cooling channels injects from the combustion chamber wall towards a central portion of the combustion chamber to cross impinge with oxygen injected at the combustion chamber head so that a toroidal vortex forms to enhance propellant mixing.

A liquid rocket engine cools a thruster body by pumping propellant through cooling channels integrated in the thruster body between internal and external surfaces. One or more of the cooling channel surfaces has a variable depth along a thrust axis to mix propellant flow and destroy thermal stratification, such as a depth that varies with a repeated contiguous sinusoidal form along the thrust axis. Fuel passed through the cooling channels injects from the combustion chamber wall towards a central portion of the combustion chamber to cross impinge with oxygen injected at the combustion chamber head so that a toroidal vortex forms to enhance propellant mixing.

An air-breathing rocket engine in certain embodiments comprises an outer shell and an interior portion situated entirely within the front end of the outer shell. The interior portion includes a funnel-shaped intake and an annular primary combustion chamber between the inner front wall of the shell and the outer surface of the funnel-shaped intake. The intake has a central aperture that is in fluid communication with the throat and exhaust areas within the outer shell. A second circumferential gap is formed between the outer surface of the front inner wall and the inner surface of the front end of the outer shell and is in fluid communication with the throat and exhaust areas within the outer shell. One or more injector ports and one or more ignition ports are situated at the front end of the second circumferential gap.

An air-breathing rocket engine in certain embodiments comprises an outer shell and an interior portion situated entirely within the front end of the outer shell. The interior portion includes a funnel-shaped intake and an annular primary combustion chamber between the inner front wall of the shell and the outer surface of the funnel-shaped intake. The intake has a central aperture that is in fluid communication with the throat and exhaust areas within the outer shell. A second circumferential gap is formed between the outer surface of the front inner wall and the inner surface of the front end of the outer shell and is in fluid communication with the throat and exhaust areas within the outer shell. One or more injector ports and one or more ignition ports are situated at the front end of the second circumferential gap.