In a jet engine having a core that sources a first flow of fluid and a component (such as a fan, a pump, and/or a bleed line) that sources a second flow of fluid, and where the first flow of fluid will typically have, at least during ordinary operation, a higher temperature than the second flow of fluid, at least one flow aperture formed by a first passageway to receive at least a portion of the aforementioned second flow of fluid, wherein that first passageway is comprised of at least one material that (by design and intent) deflects as a function of temperature such that a flow of the second flow of fluid through the at least one flow aperture is thereby desirably modulated.

A high efficiency hydrogen fuel system for an aircraft at high altitude which utilizes compressors to compress air to a sufficiently high pressure for the fuel cell. Liquid hydrogen is compressed and then utilized in heat exchangers to cool the compressed air, maintaining the air at a temperature low enough for the fuel cell. The hydrogen is also used to cool the fuel cell as it is also depressurized prior to its entry in the fuel cell cycle. A water condensation system allows for water removal from the airstream to reduce impacts to the atmosphere. The hydrogen fuel system may be used with VTOL aircraft, which may allow them to fly at higher elevations. The hydrogen fuel system may be used with other subsonic and supersonic aircraft, such as with asymmetric wing aircraft.

An air-breathing turbojet engine for a hypersonic vehicle is shown. The engine comprises a pump for pumping a cryogenic fuel, an inlet configured to compress inlet air by one or more shocks, a cooler to cool the compressed inlet air using the cryogenic fuel, and a turbo-compressor to compress the air further. A precooler cools the compressed inlet air using compressed cooled air from the turbo-compressor. A combustor receives compressed cooled air from the turbo-compressor and a first portion of the cryogenic fuel for combustion. A first turbine expands and is driven by combustion products, and a second turbine expands and is driven by a second portion of the cryogenic fuel. The first turbine and the second turbine drive the turbo-compressor via a shaft. An afterburner receives combustion products from the first turbine and the second portion of the cryogenic fuel from the second turbine for combustion therein.

A supersonic jet aircraft and a method of operating the same. The supersonic jet aircraft having at least three turbofan engines and an engine management computer. A first engine of the at least three turbofan engines is configured to be de-activatable during flight to move from an operational state in which it provides thrust to an operational state in which it stops providing thrust. Other engines of the at least three turbofan engines are configured to provide sufficient thrust to the supersonic jet aircraft when the first engine is de-activated such that the aircraft can perform a supersonic climb operation and/or a supersonic cruise operation.

This invention is focus on how to make a quieter supersonic flight. Several techniques and methods have been crafted to solve the noise problem of the sonic boom. Sonic boom is propagated from aircraft to the ground, so add interference media between them to block the noise wave could reduce the sonic boom level. Using special designed wings could also reduce noise wave. Part of the special wings design is inspired from the bird flock's flight. Using active shock wave to blow away the air at the windward front of the aircraft or using holes at the fuselage bottom to flow away the air underneath the fuselage could reduce the noise wave propagated to travel to the ground.

An engine comprises an air intake arrangement configured to receive air; a heat exchanger arrangement arranged downstream of the air intake arrangement, configured to cool the air, and comprising a plurality of heat exchanger modules; and one or more turbomachinery components configured to receive cooled air from the heat exchanger arrangement. The plurality of heat exchanger modules are arranged to be generally centred on and to be arranged along a longitudinal axis of the engine. At least one of the plurality of heat exchanger modules is arranged to at least partially overlap with at least one other one of the plurality of heat exchanger modules relative to the longitudinal axis of the engine.

A propulsion system includes a main gas turbine engine adapted for generating propulsive thrust during subsonic and supersonic flight operations and a supplementary propulsion unit adapted for generating additional thrust. The supplementary propulsion unit has an air intake and an exhaust for gas accelerated by the supplementary propulsion unit to provide the additional thrust and is adapted to generate the additional thrust during a limited range of subsonic flight operations, and to be dormant during other flight operations. The propulsion system has housing for the supplementary propulsion unit, including intake and exhaust covers which are moveable between deployed and stowed configurations. During the limited range of subsonic flight operations the intake and exhaust cover are moved to the deployed configuration to open the intake and the exhaust. During other flight operations the intake and exhaust cover are moved to the stowed configuration to close the intake and the exhaust.

An air-breathing turbojet engine (101) for a hypersonic vehicle is shown. The engine comprises a pump for pumping a cryogenic fuel, an inlet (102) configured to compress inlet air by one or more shocks, a cooler (103) to cool the compressed inlet air using the cryogenic fuel, and a turbo-compressor (104) to compress the air further. A combustor (105) receives compressed cooled air from the turbo-compressor and a first portion of the cryogenic fuel for combustion. A first turbine (106) expands and is driven by combustion products, and a second turbine (107) expands and is driven by a second portion of the cryogenic fuel. The first turbine and the second turbine drive the turbo-compressor via a shaft. An afterburner (109) receives combustion products from the first turbine and the second portion of the cryogenic fuel from the second turbine for combustion therein.

An assembly is provided for an aircraft propulsion system. This aircraft propulsion system assembly includes a nacelle inlet structure. The nacelle inlet structure includes an inner inlet opening, an outer inlet opening and a rotating structure. The rotating structure extends circumferentially about the inner inlet opening. The rotating structure is configured to rotate about an axis between a first position and a second position. The rotating structure at least partially closes the outer inlet opening in the first position. The rotating structure at least partially opens the outer inlet opening in the second position.

An air direction arrangement for an aircraft. The air direction arrangement contains an inlet opening and an inlet channel connected thereto and which is at least partially surrounded by an outer wall. The inlet channel is configured to guide air to an engine of the aircraft. The outer wall contains at least one outlet channel and at least one outlet element. The outlet element is configured to selectively release or close the outlet channel for an air flow from the inlet channel into the environment of the aircraft. The air direction arrangement contains a heat exchanger in the outlet channel to discharge thermal energy to the air flow which is flowing from the inlet channel into the environment of the aircraft.