14results about "Ram jet engines" patented technology

An air-breathing turbojet engine (301) for a hypersonic vehicle is shown. The engine comprises a pump for pumping a cryogenic fuel, an inlet (302) configured to compress inlet air by one or more shocks, a cooler (303) to cool the compressed inlet air using the cryogenic fuel, and a turbo-compressor (304) to compress the air further. A precooler (311) between the inlet (302) and the cooler (303) cools compressed inlet air using compressed air from the turbo-compressor (304). A combustor (305) receives compressed cooled air from the turbo-compressor and a first portion of the cryogenic fuel for combustion. A first turbine (306) expands and is driven by combustion products, and a second turbine (307) 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 (309) receives combustion products from the first turbine and the second portion of the cryogenic fuel from the second turbine for combustion therein.

This invention provides a solid powder combustion power system, including a combustion power unit and an atomizing device. The combustion power unit consists of a powder inlet flange, a first-stage combustion chamber, an igniter assembly, and a tail nozzle connected coaxially in sequence. The atomizing device delivers solid powder into the combustion chamber via a pipeline through the powder inlet flange. The first-stage combustion chamber includes a water spray flange, a water inlet flange, and a connecting flange. Inner and outer pipes are installed between the water inlet flange and the connecting flange to form an annular sealed cooling water supply chamber, with the inner cavity of the inner pipe serving as the combustion chamber. The water inlet flange has a water inlet channel, and the water spray flange has a water spray channel with a water mist nozzle. The two are connected via a water supply channel with a switch valve, allowing water to be sprayed into the combustion chamber as needed. The igniter ignites the solid powder within the chamber, and the tail nozzle has a flame outlet for energy output. This system employs an integrated water-cooled structure on the combustion chamber wall, ensuring uniform cooling and facilitating installation and maintenance. The cooling water achieves uniform wall cooling and can also be sprayed into the combustion chamber to generate combustible gas, improving combustion efficiency and energy release.

The present disclosure relates to the technical field of engines, and particularly provides a wide-speed-range ramjet engine and a combined power device. The ramjet engine comprises a ram channel, a front-section strut fuel injector, a front-section cavity flame stabilizer, a rear-section strut fuel injector, a rear-section cavity flame stabilizer and a high-temperature jet flame stabilizer combination. The ram channel comprises, in sequence, an air inlet channel, a separation section, a front section of a scramjet combustion chamber, a rear section of the scramjet combustion chamber and a divergent nozzle. The front-section strut fuel injector and the front-section cavity flame stabilizer are sequentially arranged on the inner wall of the front section of the scramjet combustion chamber along the front-rear direction. The rear-section strut fuel injector and the rear-section cavity flame stabilizer are sequentially arranged on the inner wall of the rear section of the scramjet combustion chamber along the front-rear direction. The high-temperature jet flame stabilizer combination is arranged on the inner wall of the divergent nozzle close to the rear section of the scramjet combustion chamber. The present disclosure can reduce the comprehensive technical difficulty of combining a high-speed turbine engine with a scramjet engine.

The application provides a series type double combustion chamber rotating detonation ramjet engine and a working method, which comprises a combustion chamber outer shell, an air inlet channel, a separation section, a first stage combustion chamber, a first stage contraction section, a second stage combustion chamber, a second stage contraction section, an outlet nozzle, a combustion chamber center body, a first stage fuel injection cavity, a second stage fuel injection cavity, a first stage fuel injection hole, a second stage fuel injection hole, a center body front support and a center body rear support. The application is aimed at the rotating detonation combustion organization flow characteristics under high or low Mach number working conditions, realizes the compatibility of high or low Mach number rotating detonation combustion working conditions in the same flow channel, and thus widens the working Mach number range of the rotating detonation ramjet engine. Considering the large difference in the combustion back pressure transmission distance under the high / low incoming flow Mach number working conditions, the two combustion chambers are arranged in series, and the combustion organization working mode is reasonably arranged, so that the combustion back pressure transmission problem under the wide incoming flow Mach number condition can be solved.

The present application relates to the technical field of ramjet propulsion and energetic materials, and discloses a skeleton composite fuel and a ramjet engine, which comprises a continuous combustible metal skeleton and an oxygen-deficient combustible filling phase, and the mass of the continuous combustible metal skeleton accounts for 50%-90% of the total mass of the fuel; the continuous combustible metal skeleton is used for forming a defined space, serving as a structural bearing unit and participating in a combustion reaction, and the oxygen-deficient combustible filling phase refers to a mixture that cannot maintain stable and complete combustion by itself under the condition of no external oxidizing medium; the oxygen-deficient combustible filling phase is filled in the defined space of the continuous combustible metal skeleton to form a closed structure or a quasi-closed structure that is not connected to the inside and outside of the matrix, and then the combustion reaction interface is located on the surface of the fuel during the working process. The fuel metal content can be improved, the unity of structural bearing and controllable reaction interface can be realized, and problems such as low metal content and difficulty in realizing effective coupling combustion with external oxidizing medium can be solved.

This invention discloses a combined power cycle system and method for cooling incoming air using ammonia-water, relating to the aerospace field. The system can switch between turbine-ramjet operating modes through an adjustable structure. Particularly during turbine-ramjet switching, ammonia-water is used to cool the high-temperature incoming air in the intake duct. The absorbed ammonia-water is then distilled to separate high-temperature ammonia gas and water. This invention combines heat exchanger precooling and jet precooling, effectively increasing the pressure ratio of the fan and compressor through multiple air cooling processes. This improves the compressor outlet gas temperature, thereby reducing compressor power consumption and providing greater thrust. Ammonia, as a supplementary fuel, has a higher specific impulse, addressing the thrust gap during engine mode transitions and effectively widening the operating speed range of the turbine engine.

This invention discloses a subsonic ramjet engine based on counter-rotating rotary detonation flame stabilization ignition, belonging to the field of subsonic ramjet engine flame stabilization ignition technology. It includes an intake cooling channel, an integrated fuel supply device, and a symmetrical rotary detonation flame stabilization device. The intake cooling channel cools the engine wall temperature; the integrated fuel supply device achieves high system integration, low flow resistance loss, and lightweight and convenient design; the symmetrical rotary detonation flame stabilization device uses a counter-rotating jet to assist in creating a stable low-speed recirculation zone in the main combustion chamber, thereby achieving flame stabilization. Furthermore, the continuously operating rotary detonation generator acts as a pre-combustion tube, providing forced ignition to the main combustion chamber. This highly integrated invention effectively cools the combustion chamber wall temperature of the subsonic ramjet engine, improves combustion stability, and significantly increases the ignition success rate of the main combustion chamber, thus providing an effective technical approach for subsonic ramjet engines to operate within a wide range of conditions.

Disclosed is an aircraft having a rocket-based combined cycle (RBCC) propulsion system including a rotating detonation rocket engine (RDRE) and an airbreathing jet engine. The RDRE is located within a throat area of the jet engine and is configured to be cooled by air bypassed from upstream of the jet engine.

The application discloses a time sequence control rotating detonation engine system combined with a turbojet engine, which comprises a turbojet engine, a shell sleeved on the periphery of the tail nozzle of the turbojet engine, a cylindrical base coaxially arranged on the inner side of the shell, and a fan-shaped detonation tube. A cover driven by an electromagnetic push rod is arranged at the top end of each detonation tube. A sequential ignition control device is arranged, and a fuel supply unit of the sequential ignition control device comprises an oil pump, a fuel coil pipe coiled in the cylindrical base, a common rail ring outside the shell, and a plurality of fuel injectors. A control unit adopts a mechanical time sequence controller, and through rotating a moving contact on an outer rotor, the mechanical time sequence controller sequentially connects static contacts on an electrode distributor, synchronously triggers electromagnetic push rods and fuel injectors of corresponding detonation tubes, and realizes multi-tube sequential cycle detonation. The application recovers exhaust heat energy to preheat fuel through a coaxial integrated structure, supplies air by using an ejecting effect, replaces a complex electronic system with a simple and reliable mechanical control, and realizes efficient, compact, wide working condition adaptation and thrust enhancement.

The application provides a real-time active oxygen supplementing regulation method and device for combustion of a scramjet engine, comprising the following steps: acquiring wall surface pressure data and flame self-luminous radiation data in a combustion chamber in real time; determining a current flame combustion state based on a flame combustion state discrimination criterion and the current acquired wall surface pressure data and flame self-luminous radiation data in the combustion chamber; and generating a corresponding control signal for the combustion chamber according to the current flame combustion state to realize active oxygen supplementing and combustion active regulation of the oxygen injection valve of the combustion chamber. The application can strengthen the combustion effect, improve the combustion efficiency, and improve the precision and stability of combustion control.

The disclosure discloses a fan variable flow path series turbine-based combined engine, which has two channels of a turbine engine and a ramjet engine. The turbine engine has two internal and external ducts, and contains components: inter-stage bleed fan, high-pressure compressor, main combustion chamber, high-pressure turbine, low-pressure turbine; the ramjet engine includes components: ramjet duct; after the turbine engine and the ramjet engine are connected in series to form a combined engine, the components used in common include: mixing chamber, afterburner / ramjet combustion chamber, integrated two-element nozzle of the ramjet duct. The fan variable flow path series turbine-based combined engine is provided with a front duct splitter ring, a fan inter-stage splitter ring, a duct conversion valve and a rear duct ejector structure. The engine adopts a framework design of double rotors, three ducts, mixed exhaust, main combustion chamber and afterburner / ramjet combustion chamber arranged in series, and the area ratio of the ramjet duct to the turbine duct is set to be small, and the overall cross-sectional area of the combined engine is small.