A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

A method of controlling a gas turbine engine includes the steps of: detecting a shaft break event in a shaft connecting a compressor of the gas turbine engine to a turbine of the gas turbine engine; and in response to this detection, activating a shaft break mitigation system which introduces a fluid into a gas flow of the gas turbine engine downstream of the turbine, or increases an amount of a fluid being provided into the gas flow of the gas turbine engine downstream of the turbine, whereby the fluid reduces an effective area of a nozzle for the gas flow so as to reduce the mass flow rate of the gas flow through the turbine.

An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.

An afterburner arrangement comprising: an internal casing and an external casing defining a bypass pathway between them; a mounting strut forming a structural connection between the internal casing and the external casing; and A plurality of fuel nozzles associated with the mounting strut, wherein the mounting strut at least partly houses a corresponding plurality of fuel pathways to provide fuel to the respective fuel nozzles.

The present vertical lift vehicle system can include a single internal combustion engine, a single propeller, and a plurality of small ducts. The small ducts can connect to a single main duct acting as a combustion chamber, wherein the combustion chamber combines air from the small ducts with propane, wherein when ignited the contents of the main duct produce added thrust to the vehicle as it exits the main duct.

An aft section structure of a jet engine with an axis is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; spray bars, each of the spray bars extending radially within the duct and comprising trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.

An aft section structure of a jet engine with an axis is comprised of a casing defining a duct around the axis and opened axially fore and aft; a cone tapering aftward at a first angle with the axis and having a pointed end; guide vanes, each of the vanes radially extending from the cone to the casing and comprising a pressure side at a second angle with a plane containing the axis; spray bars, each of the spray bars extending radially within the duct and comprising trailing sides, each of the trailing sides being directed aftward at a third angle with a plane containing the axis; and flame holders, each of the flame holders extending radially within the duct and comprising one or more interior sides, each of the interior sides being directed aftward at a fourth angle with a plane containing the axis.

A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.

A confluence structure of an aircraft bypass turbine engine which includes a confluence plate with a downstream end supported by a portion that is movable in the direction of the axis by a control mechanism which can optionally be adjusted in flight. A mobile portion of a sleeve delimiting the secondary stream on the outside, and an inner projection of the outer casing can also slide axially in certain embodiments. This provides a wide range of options for modifying the gas dilution and operating conditions of the engine.