A jet engine for propelling aircraft, capable of providing thrust from rest to high speeds is provided. The engine has an axial compressor (16) or several axial compressors located on the same plane and is driven by a gas generator. At the outlet of the turbine there is a gasification chamber (23) into which more fuel is injected. Combustion of the gases from the gasification chamber is performed in two combustion chambers (18) with a rectangular cross-section, separated by a central body (10). The exhaust of the gases is performed in nozzles, each with a square convergent/divergent cross-section (19) and (21). The cross-section of the throats (26) can be adjusted by means of two mobile elements (20). The final section of the central body (10) forms a wedge-shape (27), enabling the continued expansion of the exhaust gases.

A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.

A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.

A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a closure for closing the inlet so as to prevent ingress of debris; and a fastening attachable to an aircraft-mounted launcher and configured such that the cover remains attached to the aircraft on launch of the missile.

A cover for an intake of an air-breathing engine in a missile is disclosed. The cover comprises a closure for closing the inlet so as to prevent ingress of debris; and a fastening attachable to an aircraft-mounted launcher and configured such that the cover remains attached to the aircraft on launch of the missile.

A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.

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.

A motor and fuel-powered hybrid system of a rocket thruster is disclosed, which mainly provides power through a motor and a fluid fuel injector. In particular, at the beginning stage of the rocket lift-off, the motor drives the compressor to provide power to send the rocket into air. When the speed and height of the rocket gradually increase, the fuel is ignited to give power to keep propelling the rocket, thereby reducing the fluid fuel that needs to be carried on the rocket, increasing the rocket's loading space and enhancing the carrying capacity.

A hybrid airbreathing rocket engine module (70) comprises an air intake arrangement (62) configured to receive air and a heat exchanger arrangement (63) configured to cool air from the air intake arrangement (62); a compressor (64) configured to compress air from the heat exchanger arrangement (63); and one or more thrust chambers (65). The air intake arrangement (62), the compressor (64), the heat exchanger arrangement (63), and the one or more thrust chambers (65) are arranged generally along an axis (69) of the engine module (70). The heat exchanger arrangement (63) is arranged between the compressor (64) and the one or more thrust chambers (65).

A hybrid airbreathing rocket engine module (70) comprises an air intake arrangement (62) configured to receive air and a heat exchanger arrangement (63) configured to cool air from the air intake arrangement (62); a compressor (64) configured to compress air from the heat exchanger arrangement (63); and one or more thrust chambers (65). The air intake arrangement (62), the compressor (64), the heat exchanger arrangement (63), and the one or more thrust chambers (65) are arranged generally along an axis (69) of the engine module (70). The heat exchanger arrangement (63) is arranged between the compressor (64) and the one or more thrust chambers (65).