Abstract: A turbopump for a rocket engine includes a radial pump having a wheel with vanes in a central body that is essentially rotationally symmetrical. The central body includes two separate outflow areas for one propellant component of the rocket engine, where a first portion of the propellant component is conveyed through a first of the outflow areas into a rocket combustion chamber and a second portion of the propellant component is conveyed through a second of the outflow areas into a gas generator. The first outflow area and the second outflow area have different geometric dimensions such that the propellant component in the first outflow area can be provided at a first propellant throughput and at a first exit pressure that differ from a second propellant throughput and a second exit pressure of the second outflow area.

Abstract: Embodiments of the invention relates to an injection element having an inner element with a first outlet opening and an outer element. The outer element includes at least one second outlet opening structured and arranged for receiving and injecting fuel in a combustion space, and arranged coaxially to the first outlet opening. The outer element further includes third outlet openings composed of bores structured and arranged for forming a cooling liquid film layer, wherein the bores are arranged coaxially to the first outlet opening and the at least one second outlet opening.

Abstract: Embodiments of the invention relates to an injection element having an inner element with a first outlet opening and an outer element. The outer element includes at least one second outlet opening structured and arranged for receiving and injecting fuel in a combustion space, and arranged coaxially to the first outlet opening. The outer element further includes third outlet openings composed of bores structured and arranged for forming a cooling liquid film layer, wherein the bores are arranged coaxially to the first outlet opening and the at least one second outlet opening.

Abstract: Device for damping oscillations of a combustion chamber that includes at least one resonator connected to a pre-chamber in a vibration-damping manner. The pre-chamber is connected to a combustion chamber in a vibration-damping manner via at least one passage channel. This abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

Abstract: The invention relates to an injection element (10), in particular for a rocket drive, with an inner element and an outer element arranged coaxially thereto (12, 14) for receiving and injecting fuel into a combustion space. According to the invention the outer element (14) has bores (16) for forming a cooling liquid film layer.