Abstract: The subject of the invention is a detonation rocket engine comprising an annular detonation chamber (5) connected to the Aerospike nozzle (4) and lines (2, 3) for supplying propellant components connected to the detonation chamber (5). The detonation chamber (5) has a bottom (9) connecting the inner wall (10) and the outer wall (11) between which the outlet (6) is formed. At the outlet (6) of the detonation chamber (5) there are at least three evenly distributed centring elements (1) connecting the inner wall (10) and the outer wall (11) of the detonation chamber (5), with cooling channels (7) connected to one of the lines (2, 3) supplying the propellant components to the detonation chamber (5).

Abstract: A fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine includes a spray nozzle, a gaseous carrier, a fuel mixing and evaporation chamber and an injector nozzle. During operation, both a liquid fuel and the gaseous carrier are supplied to the fuel mixing and evaporation chamber of the injector through the spray nozzle, where they are mixed and evaporated as a result of elevated temperature, and the mixture reaches the combustion chamber. The gaseous carrier is air or, flue gas, at elevated pressure and temperature and having a composition that prevents the initiation of flame combustion, and the gaseous carrier has an oxygen content low enough to prevent the initiation of combustion, even under conditions of elevated pressure and temperature.

Abstract: The invention relates to a fuel injector for injecting an over-enriched fuel and air mixture to the combustion chamber of an internal combustion engine, is characterised in that it comprises: a hydrocarbon liquid fuel spray nozzle, at least one supply of a gaseous carrier, a fuel mixing and evaporation chamber and an injector nozzle to the engine combustion chamber (C.C.), configured such that, during operation, liquid fuel is supplied and heated and compressed gaseous carrier are supplied to the fuel mixing and evaporation chamber of this injector through the spray nozzle, where they are mixed and evaporated as a result of elevated temperature, and the mixture of evaporated fuel with a hot gaseous carrier with low oxygen content thus formed reaches the combustion chamber (C.C.

Abstract: A detonation engine which creates thrust by generating a detonation wave, wherein the overall engine structure is simplified, and continuous output can be obtained, comprises: a rotational flow generation device which generates rotational flow about an axis in a mixed gas of air and fuel or of oxygen and fuel; a detonation chamber arranged downstream from the rotational flow generation device, formed in a ring-shape radially extended and continuous in the circumferential direction, which continuously combusts in the circumferential direction the mixed gas in which the rotational flow is generated to generate detonation waves, and draws it in from the radial inside and exhausts it to the radial outside; and a nozzle which is connected to the detonation chamber, and jets the high temperature and pressure combustion gas generated by the detonation waves flowing from the detonation chamber, to the rear while expanding it, and converts it into thrust.

Abstract: A detonation engine which creates thrust by generating a detonation wave, wherein the overall engine structure is simplified, and continuous output can be obtained, comprises: a rotational flow generation device which generates rotational flow about an axis in a mixed gas of air and fuel or of oxygen and fuel; a detonation chamber arranged downstream from the rotational flow generation device, formed in a ring-shape radially extended and continuous in the circumferential direction, which continuously combusts in the circumferential direction the mixed gas in which the rotational flow is generated to generate detonation waves, and draws it in from the radial inside and exhausts it to the radial outside; and a nozzle which is connected to the detonation chamber, and jets the high temperature and pressure combustion gas generated by the detonation waves flowing from the detonation chamber, to the rear while expanding it, and converts it into thrust.