86 results about "Regenerative cooling" patented technology

The invention belongs to the field of engines, and particularly relates to a dual-fuel regenerative cooling system and method. The cooling system comprises a combustion chamber, an ammonia supply device and a kerosene supply device; three layers of cooling flow channels are arranged in the wall face of the combustion chamber, the output ends of the three layers of cooling flow channels are arranged in the combustion chamber, and the three layers of cooling flow channels comprise a first cooling channel, a second cooling channel and a third cooling channel which are sequentially arranged from inside to outside. The ammonia supply device is connected with the input ends of the first cooling channel and the second cooling channel; the kerosene supply device is connected with the input ends of the third cooling channel and the second cooling channel; and ammonia or kerosene is introduced into the second cooling channel in a time-sharing manner. Through the three-layer cooling channel design and the fuel switchable function, the effects of fuel cooling, thermal protection, cracking hydrogen production and combustion organization are improved at the same time.

The invention provides a regenerative cooling channel structure and an engine, and relates to the technical field of engine thermal protection, the regenerative cooling channel structure comprises a first channel and a second channel which are arranged between the outer wall face and the inner wall face of a combustion chamber at intervals in the radial direction, and an inlet and an outlet of the first channel are located at the inlet end and the outlet end of the combustion chamber correspondingly; an inlet and an outlet of the second channel are located at the outlet end and the inlet end of the combustion chamber respectively. An outlet of the first channel communicates with an inlet of the second channel, and a coolant flows into the first channel through the inlet of the first channel, then flows into the second channel through an outlet of the first channel and the inlet of the second channel in sequence and then flows into the combustion chamber through an outlet of the second channel. The flowing direction of the coolant in the first channel is consistent with the flowing direction of gas in the combustion chamber to form downstream cooling, the flowing direction of the coolant in the second channel is opposite to the flowing direction of the gas in the combustion chamber to form countercurrent cooling, the flowing speed and flow distribution of the coolant are improved, the heat transfer deterioration phenomenon is restrained, and the cooling effect is effectively improved.

The utility model relates to the technical field of hydrogen drying devices, in particular to a low-pressure, low-dew-point and low-pressure-drop hydrogen drying device which comprises an adsorption tower which comprises a tower A and a tower B, after water is cooled and separated through a regeneration cooler and a regeneration gas-water separator, the hydrogen enters an adsorption tower A through V1 to absorb water and dry to meet the requirement, the hydrogen is discharged out of the tower and passes through V7 to reach a gas using point, a small part of about 20% of gas is divided from dry gas at an outlet and is electrically heated to 180 DEG C, and the gas is sent to a tower B through V6 to regenerate and activate an adsorbent; hydrogen absorbing moisture is discharged from the tower and enters a gas inlet cooler and a gas inlet gas-water separator through a V4, the temperature of the cooled and dehydrated hydrogen is greatly increased after the cooled and dehydrated hydrogen is pressurized by a booster pump, the cooled and dehydrated hydrogen is converged with hydrogen at an inlet and then passes through a regeneration cooler and a regeneration gas-water separator, the cooled and dehydrated hydrogen returns to the adsorption tower A to adsorb moisture, and first-step pressurized reflux drying is completed; and similarly, hydrogen is adsorbed from the tower B, is subjected to split-flow heating regeneration, passes through the tower A, is pressurized and then flows back to the tower B again.

The invention relates to the technical field of engine thermal management, and particularly provides an active cooling method for coupling rotational flow cooling and regenerative cooling, which comprises the following steps: arranging a rectangular auxiliary inlet channel on the side wall of a rectangular main inlet channel of a regenerative cooling channel, and constructing a rotational flow regenerative cooling channel; when the rectangular main inlet channel performs regenerative cooling, coolant induced rotational flow is injected into the rectangular auxiliary inlet channel, and the rotational flow strength is regulated and controlled by adjusting the ratio of the flow of the coolant induced rotational flow to the total flow; and a cooling process simulation model is constructed, and the cooling effect of the rotational flow regeneration cooling channel is analyzed based on simulation calculation data. By means of the innovative rotational flow regeneration cooling channel design, controllable rotational flow is introduced into a traditional regeneration cooling channel, and the problems that a scramjet engine combustion chamber is insufficient in heat transfer in the extremely high-temperature environment and the fuel chemical heat sink utilization rate is low are solved. And fluid mixing is enhanced through rotational flow, a thermal boundary layer is destroyed, the fuel pyrolysis reaction is optimized, and efficient heat exchange is achieved.

The invention relates to the technical field of waste gas recycling, in particular to a refining agent regeneration method and system. The refining agent is used for removing impurities in polyolefin hydrocarbon raw materials, and the regeneration method comprises the following steps: sequentially and repeatedly purging and cooling the polyolefin refining agent by using nitrogen to respectively obtain first regeneration cooling exhaust gas and a purging refining agent; sequentially carrying out liquid separation and first pressure swing adsorption on the first regeneration exhaust gas to obtain a first hydrocarbon adsorption material; pressurizing and displacing the purging refining agent by using a polyolefin raw material to respectively obtain mixed exhaust gas and a regenerated refining agent; the mixed exhaust gas is subjected to liquid separation and second pressure swing adsorption in sequence, and a second hydrocarbon adsorption material is obtained; and desorbing the first hydrocarbon adsorption material and the second hydrocarbon adsorption material to obtain the polyolefin recycled material. According to the regeneration method, a three-stage coupling separation system of purging regeneration, liquid separation and pressure swing adsorption is constructed, and compared with a traditional thermal regeneration method, the recovery rate of hydrocarbon raw materials in regenerated exhaust gas of the refining agent can be increased only through pressure swing adsorption.

The invention discloses a combustion chamber regenerative cooling type turbofan engine system based on methanol fuel, relates to the technical field of aero-engines, and solves the problems that a traditional aero-engine is insufficient in cooling capacity and large in pollution. An air inlet channel, a fan, an air compressor system, a combustion chamber, a turbine system and an exhaust nozzle are sequentially communicated, and the outlet end of the exhaust nozzle is communicated with the atmosphere; the fan, the gas compressor system and the turbine system are connected through a shaft; a regeneration cooling channel is arranged in the combustion chamber, the methanol fuel tank is communicated with the regeneration cooling channel, methanol absorbs heat and evaporates in the regeneration cooling channel and is cracked to form mixed gas at the same time, and the mixed gas and air are combusted after being mixed. The regenerative cooling technology is applied to the turbofan engine, methanol serves as fuel and coolant, heat of a combustion chamber is absorbed to be evaporated and vaporized, meanwhile, the methanol is cracked to form mixed gas for combustion, dependence of a traditional engine on cooling air is reduced, the heat efficiency of the engine is improved, and meanwhile the combustion performance of methanol fuel is enhanced.

The invention provides an ammonia fuel cell power generation dual-fuel scramjet engine capable of achieving energy gradient utilization, belongs to the technical field of aircraft thermal protection and power generation, and solves the problems that a traditional airborne power generation system is difficult to use due to the high incoming flow Mach number in hypersonic flight, and coking is caused in a regeneration cooling channel of a fuel decomposition gas turbine. Ammonia and aviation kerosene generate high-temperature fuel gas in a combustion chamber of the scramjet engine to push the engine to generate thrust; high-temperature waste heat of the combustion chamber is recycled through the regeneration cooling channel, fuel is heated, a part of ammonia is decomposed, and decomposed gas drives a turbine generator to generate electric energy. According to the power generation system for gradient utilization of energy, factors such as actual use temperature and pressure are fully considered, the energy utilization efficiency is effectively improved, energy waste is reduced, and reasonable adaptation of energy is achieved, so that the power generation efficiency of the whole system is improved, and the electric energy requirement of a hypersonic aircraft is greatly met.

The invention relates to the technical field of aero-engine combustion chamber design, in particular to a multi-layer mixing section structure of a pulse detonation combustion chamber. The multi-layer mixing structure is characterized in that the multi-layer mixing structure comprises a multi-layer mixing section arranged in a detonation pipe, an oil supply pipe is arranged on the detonation pipe, the multi-layer mixing section comprises an inner mixing ring and an outer mixing ring, and the inner mixing ring and the outer mixing ring form three Venturi type circulation channels through connecting structures; and a fuel nozzle connected with an oil supply pipe is arranged at the axis of the inner mixing ring. By means of the multi-layer mixing section, incoming flow air is divided into multiple jet flows, the mixing efficiency of fuel oil and air is improved, the mixing uniformity of the fuel oil and air is remarkably improved, and the mixing distance is shortened. Meanwhile, according to the regenerative cooling structure, a fuel oil channel is designed in a multi-layer mixing section, recycling of the wall face of the pulse detonation combustion chamber is achieved, meanwhile, the oil injection temperature is increased, the fuel oil and air mixing effect is improved, and the combustion efficiency is improved.

The application relates to a 3D printing-based abnormal cooling channel heat transfer evaluation method of a regenerative cooling engine, which comprises the following steps: determining an overheating area of a thrust chamber, obtaining node overheating temperature of an overheating position; carrying out heat transfer calculation of a normal cooling channel of the thrust chamber and obtaining a gas side theoretical normal wall temperature of the overheating position; assuming an initial coolant flow value of the overheating position, carrying out abnormal cooling channel heat transfer calculation to obtain a theoretical node overheating temperature; judging whether the theoretical node overheating temperature and the node overheating temperature meet a condition; if yes, taking the initial coolant flow value as a final coolant flow value; obtaining a coolant flow variation ratio alpha based on the final coolant flow value, obtaining a rated working condition flow of the abnormal cooling channel, carrying out abnormal cooling channel heat transfer calculation and evaluation, and outputting a rated abnormal cooling channel gas side wall temperature; and if the rated abnormal cooling channel gas side wall temperature is lower than a material temperature resistance limit of the thrust chamber, the rated working condition of a hot test is safe, and the test can be carried out.

This invention belongs to the field of ramjet technology and provides a wide-speed range ramjet fuel supply system and method driven by a pyrolysis oil-gas turbine. The system comprises a fuel tank, a centrifugal pump, a motor, an oil-gas turbine, a battery, an electromagnetic control module, fuel lines, a pyrolysis fuel vapor line, a combustion chamber, and a regenerative cooling channel on the outer wall of the combustion chamber. Through the connection between the centrifugal pump, the regenerative cooling channel, and the oil-gas turbine, the system utilizes the cracking of hydrocarbon fuel into small-molecule pyrolysis kerosene vapor to drive the turbine rotor to produce work. The motor then assists in starting the ramjet, thereby resolving the power generation challenges of the ramjet mode and alleviating thermal protection issues.

The invention relates to the technical field of heat recovery, in particular to a heat energy recovery management method, device, equipment and medium for a compression heat regeneration drying machine. The method comprises the steps that when high-temperature and high-humidity compressed air generated by an air compressor passes through a switching valve, an air guiding instruction is triggered; high-temperature and high-humidity compressed air is respectively guided to a first drying tower in an adsorption mode and a second drying tower in a regeneration mode; in the regeneration process of the second drying tower, preheating desorption is conducted on the drying agent in the second drying tower through high-temperature compressed air flowing through the first drying tower, and high-temperature regenerated gas is generated; the high-temperature regenerated gas is introduced into a regeneration cooler and exchanges heat with a cooling medium, so that the high-temperature regenerated gas is cooled and condensed, and liquid water is separated out; and the cooling medium after heat recovery is conveyed to a heat utilization unit, heat energy recycling is achieved, and operation parameters of the air compressor and the drying tower are coordinated in real time so as to maintain system pressure balance. The effect of improving the heat recovery efficiency during compression heat regeneration is achieved.

The utility model provides a system for increasing the temperature of a dry quenching calcium-based dry desulfurization agent, which belongs to the technical field of dry quenching desulfurization and comprises a dust removal system, a desulfurization system, an electric tracing band, a heat exchanger and a compressed air pipeline, the dust removal system comprises a dust removal cover, a low-temperature dust removal pipeline, a high-temperature dust removal pipeline, a heat storage cooler, a bag type dust collector, a dust removal fan and an exhaust funnel, the dust removal cover is arranged at the discharge port of the dry quenching body, and the dust removal cover, the low-temperature dust removal pipeline, the heat storage cooler, the bag type dust collector, dust removal air and the exhaust funnel are sequentially connected; the two ends of the high-temperature dust removal pipeline are respectively connected with the dry quenching body and the heat storage cooler; according to the system, when the calcium-based dry desulfurization system is under the working condition in winter, the purposes of enhancing the desulfurization effect, reducing the content of a desulfurizing agent and reducing the operation and maintenance cost are achieved.

The invention discloses an engine DPF regeneration cooling stage exhaust temperature safety control method and system, and relates to the technical field of diesel engine aftertreatment system control. According to the technical key points, linear controllable adjustment of exhaust flow is achieved through collaborative composite slope control, high-temperature heat stored in parts such as DOC, DPF and SCR of an aftertreatment system is released in order along with stable airflow and taken away at a constant speed, and severe temperature fluctuation and high-frequency thermal shock caused by sudden change of cold and hot airflow in the prior art are completely avoided; irreversible faults such as shedding of an SCR carrier catalytic coating, aging failure of a temperature sensor probe and thermal deformation air leakage of a sealing gasket are effectively avoided, and the thermal aging rate of a post-processing core component is reduced, so that the service life of the whole machine of a post-processing system is prolonged, the long-term operation reliability of the post-processing system is improved, and meanwhile, the equipment maintenance cost and shutdown loss of a terminal user are reduced.

The invention relates to a regenerative cooling engine abnormal channel heat transfer evaluation method based on 3D printing, and the method comprises the steps: determining an overheating region of a thrust chamber, and obtaining the node overheating temperature of an overheating position; heat transfer calculation of a normal cooling channel of the thrust chamber is carried out, and the theoretical normal wall temperature of the gas side at the overheating position is obtained; assuming an initial value of coolant flow at a superheat position, and carrying out heat transfer calculation of an abnormal cooling channel to obtain a theoretical node superheat temperature; judging whether the theoretical node overheating temperature and the node overheating temperature meet conditions or not; if yes, the coolant flow initial value serves as the final coolant flow; based on the final coolant flow, a coolant flow change proportion alpha is obtained, rated working condition flow of the abnormal cooling channel is obtained, heat transfer calculation evaluation of the abnormal cooling channel is carried out, and the rated abnormal cooling channel gas side wall temperature is output; and if the gas side wall temperature of the rated abnormal cooling channel is lower than the material temperature resistance limit of the thrust chamber, the rated working condition of the hot vehicle test is safe, and the test run can be carried out.

The invention relates to a thermodynamic component combined test, and provides a thermodynamic component combined test system and a test method in order to solve the problems that an afterburning cycle engine gas generator is large in propellant mass flow deviation, large in combustion product pollution, high in hot test run cost and the like. The test system comprises a fuel gas generator, a gas venturi tube and a thrust chamber which are coaxially connected; a first component access port is formed in the top of the fuel gas generator, a second component access port is formed in the side face of the fuel gas generator, the first component access port and the second component access port are used for accessing a first component propellant and a second component propellant respectively, and a plurality of fuel gas performance monitoring ports are formed in the side face of the gas venturi tube; a second component regeneration cooling access port is formed in the side surface of the outlet end of the thrust chamber and is used for regenerating and cooling a second component propellant and then accessing the second component propellant into the thrust chamber; the test method based on the test system can effectively improve the efficient, reliable and environment-friendly hot test run test between the fuel gas generator and the thrust chamber.

The present application relates to the technical field of aerospace engine, in particular to a liquid fuel engine thrust chamber needle bolt head regenerative cooling structure, comprising: a thrust chamber and a needle injection injector, the injector shell of the needle injection injector is arranged in the thrust chamber from the top of the thrust chamber, and the injector shell is located in the thrust chamber, at least one week main injection hole is arranged on the radial of the injector shell, the annular gap is formed between the injector shell and the top shell of the thrust chamber, and the end of the injector shell is provided with an inner recess structure in the thrust chamber; The first cooling flow channel and the second cooling flow channel are arranged in the injector shell above and below the main injection hole, and the outlet of the second cooling flow channel is connected with the rotational flow tangential hole; wherein, the liquid propellant in the propellant combination is injected into the injector shell, and the annular gap between the injector shell and the top shell of the thrust chamber is used for injecting another propellant in the propellant combination. The present application improves the combustion efficiency of the thrust chamber, and improves the specific impulse and the thrust-to-weight ratio of the engine.

The invention relates to a high-heat-mass-ratio cooling flow distribution resistance reduction structure and method based on boundary layer disturbance, and belongs to the technical field of aerospace propulsion active thermal protection. The problem that a traditional flow distribution method of a regenerative cooling parallel channel is too high in flow resistance is solved. Comprising a flow distribution structure, a plurality of channels are arranged in the flow distribution structure, and disturbance structures are arranged in the channels. Through the disturbance structures arranged on the channels, the flow deviation between the channels connected in parallel can be remarkably reduced, and the hidden danger of high-temperature damage is completely eradicated. Compared with a traditional flow distribution method such as a throttling hole and a flow guide plate, the flow resistance loss brought by the flow distribution method is greatly reduced.

The invention discloses a dual-mode low-emission combustion chamber matched with a standing vortex evaporation tube and a method. The combustion chamber comprises a multi-channel diffuser, an inner casing, an outer casing, a flame tube and a high-energy ignition electric nozzle. The flame tube comprises an outer ring wall plate, an inner ring wall plate, a single-concave-cavity structure, a cap cover, a cross flame supporting plate and M * N evaporation pipes. The trapped vortex combustion chamber is combined with two low-emission advanced combustion organization technologies of RQL and LPP, different combustion modes are adopted in different states or different areas in the whole flight cycle so as to adapt to the oil-gas ratios in different states, and the pollutant emission in the whole working condition range is reduced. And meanwhile, the M * N evaporation pipes can also be used for solving the problem that multiphase fuel oil is difficult to supply normally under the aviation kerosene phase state change caused by fuel oil regenerative cooling.

The application discloses a bidirectional gradient dot matrix sandwich regenerative cooling channel and a parameterized design method thereof, and belongs to the technical field of thermal protection of liquid rocket engines. The cooling channel comprises an outer wall, an inner wall and a dot matrix sandwich layer arranged between the outer wall and the inner wall. The dot matrix strut has a flow direction gradient along the flow direction of the cooling working medium and a normal gradient along the normal direction of the wall surface. The parameterized design method comprises the following steps: S1, constructing a normalized heat flow factor; S2, establishing a flow direction gradient strut diameter distribution; S3, determining a minimum strut diameter in a low heat flow area and checking; S4, constructing a normal gradient and determining a hot wall end diameter and a draft angle distribution; and S5, determining a cold wall end diameter and checking. The method can match the strut heat exchange capacity with the non-uniform heat flux density distribution on the gas side, and form normal gradient struts with thick hot wall ends and thin cold wall ends, so that the hot spot temperature is reduced, the temperature uniformity is improved, the pressure drop increase of the channel is controlled, and the lightweight advantage is maintained.

The utility model discloses a cold accumulation type cooling device, which belongs to the technical field of cooling equipment, and comprises a refrigeration module, an inner circulation module, a temperature control circulation module and an outer circulation module, the refrigeration module can introduce a refrigerant into an evaporator to absorb heat; the inner circulation module comprises a first pump body and a cold storage box, and the first pump body can supply cold storage fluid in the cold storage box to the evaporator; the temperature control circulation module comprises a second pump body and a first heat exchanger, the first heat exchanger is provided with a first heat exchange flow channel and a second heat exchange flow channel, the second pump body can introduce cold storage fluid into the first heat exchange flow channel, and the cold storage box can collect the cold storage fluid flowing through the evaporator and the first heat exchanger; the outer circulation module comprises a buffer box and a third pump body, the second heat exchange flow channel is connected with the buffer box, the third pump body can supply cooling liquid of the buffer box to the load end, the cooling liquid flowing through the load end is sequentially led into the second heat exchange flow channel and the buffer box, and the electric power and cost can be reduced.

Systems and methods for use in multi-stage regenerative cooling cycles that leverage an ejector as the motivating force to sub-cool a single refrigerant in a multi-stage regenerative cooling cycle. The multi-stage regenerative cooling cycle is more efficient than conventional muti-stage cooling cycles due to the placement of the ejector, which enables each stage to operate at a higher evaporating pressure and lower compression ratio.

The invention relates to the technical field of hydrogen purification, in particular to a multi-dryer alternative selective hydrogen purification system, which comprises an impurity removal assembly, a gas-water separation component, a deoxidization piece connected with the gas-water separation component, and a hydrogen cooling piece connected with the deoxidization piece; a plurality of groups of drying assemblies are arranged, and each group of drying assembly comprises a regeneration cooling piece connected with the hydrogen cooling piece and a drying part connected with the regeneration cooling piece; and the switching assembly is arranged between the hydrogen cooling piece and the multiple sets of drying assemblies, different working states formed by the multiple sets of drying box bodies are utilized, so that different levels of operation is conducted on hydrogen purification, and the hydrogen purification efficiency and the purification yield are improved.

The invention belongs to the technical field of thermal protection of aircrafts, and particularly discloses a novel regenerative cooling channel with a longitudinal embedded corrugated plate and an application of the novel regenerative cooling channel with the reinforced cooling, the novel regenerative cooling channel comprises a regenerative cooling channel body and the corrugated plate, and the corrugated plate is longitudinally arranged in the regenerative cooling channel body. And the corrugated plate is perpendicular to the heating surface of the regeneration cooling channel and divides the interior of the regeneration cooling channel into two independent sub-channels. Through reasonable construction and layout of the corrugated plates, mixing between fluids and convective heat exchange between the fluids and the heating wall surface can be enhanced, a thermal boundary layer is periodically destroyed, and heat transfer resistance is reduced, so that the heat transfer capacity of a regenerative cooling system is effectively improved, and the temperature of high-temperature parts of an aircraft is effectively reduced.

The application belongs to the field of engine cooling, and particularly relates to a dual-working fluid regenerative cooling system and method. The dual-working fluid regenerative cooling system comprises a dual-working fluid regenerative cooling module, an ammonia cracking product separation module and an energy comprehensive utilization module. The dual-working fluid regenerative cooling module comprises an ammonia supply device, a kerosene supply device and a double-layer regenerative cooling channel. The ammonia cracking product separation module comprises a membrane separator and a pressure swing adsorption unit. The energy comprehensive utilization module comprises a power generation device connected with the nitrogen-rich gas outlet. The application builds a closed-loop system integrating efficient thermal management, stable combustion and energy efficient utilization by means of ammonia and kerosene dual-working fluid cooling, ammonia cracking hydrogen production and nitrogen-rich gas power generation.

The invention relates to the field of ramjet kerosene shunting and regenerative cooling, and discloses a ramjet regenerative cooling kerosene shunting device which comprises an annular piece, a plurality of kerosene flow channel inlets, a plurality of kerosene flow channel outlets formed in the other side of the annular piece, an annular confluence groove and a plurality of flow channels formed in the annular piece. The annular confluence groove is communicated with an outlet of each kerosene flow channel through the shunting channel; wherein the shunting channel comprises a convergence section, a throat channel and an expansion section, the convergence section comprises a rapid convergence section and a saturation pressure section, and the expansion section comprises a primary expansion section, an equal-diameter channel and a secondary expansion section. According to the invention, through the arrangement of the shunting channel, when kerosene passes through the convergence section of the shunting channel, the fluid speed is accelerated, the pressure is reduced, and the static pressure at the throat part is reduced to the saturated vapor pressure, the liquid is sharply vaporized, so that the flow of the kerosene after passing through the expansion section is kept stable, and the kerosene flow in each cooling channel connected with the downstream is uniform and kept stable; the regeneration cooling effect of each area is ensured.

A method for predicting flow instability of supercritical pressure fuel of a regenerative cooling channel belongs to the field of aero-engines and comprises the following steps: acquiring a flow instability boundary of a regenerative cooling channel structure through numerical calculation; calculating a quasi-supercooling degree and a quasi-phase change number of the to-be-predicted working condition point; calculating a corresponding damping factor according to the quasi-supercooling degree and the quasi-phase change number of the to-be-predicted working condition point; and comparing the damping factor corresponding to the to-be-predicted working condition point with 0, and predicting whether the working condition point is a stable working condition point or an unstable working condition point according to a comparison result. According to the method, the fuel cracking reaction is considered when the flow instability boundary is constructed, and the applicable temperature of the obtained flow instability boundary comprises the cracking temperature zone, so that the stability of the working condition point in the cracking temperature zone can be accurately predicted. Besides, the prediction method provided by the invention is applicable to a single-tube cooling channel and a multi-connected cooling channel, has wider engineering applicability, and realizes accurate and efficient prediction of the supercritical pressure fuel flow instability of the regenerative cooling channel.

The present invention proposes an active-passive composite staggered discrete slot structure hydrocarbon fuel supersonic air film cooling system. The inner side of the cooling ring is fitted with the wall of the engine combustion chamber, and a composite material structure is used on the fitting surface to meet its own thermal protection requirements. The hydrocarbon fuel flows into the stagnation chamber in the cooling ring from the regenerative cooling channel and uses the accelerating nozzle to achieve critical injection, while providing regenerative cooling for the cooling ring in the process. In order to make up for the defects of the lateral diffusion effect of the supersonic air film and ensure the structural strength of the combustion chamber, a staggered discrete slot air film injection method with full circumferential coverage of the combustion chamber is proposed. This cooling system realizes efficient regeneration / film composite cooling of the scramjet combustion chamber while ensuring its own thermal protection, effectively improving the performance of the hypersonic ramjet engine without affecting the engine size as much as possible.

The invention relates to the technical field of aero-engines, and provides a rotary detonation combustion chamber with a supercritical combined injection structure, the rotary detonation combustion chamber comprises an inner cylinder and an outer cylinder, the inner cylinder and the outer cylinder are respectively provided with a cooling cavity and an injection oil cavity, and efficient heat management is realized through a multi-stage regenerative cooling micro-channel. A combustion cavity, a throat and an air inlet cavity are formed in the space between the inner barrel and the outer barrel, fuel is mixed more evenly through the design of the spray hole sets, and the combustion efficiency and stability are improved. The opening and closing piece controls opening and closing of the spraying holes, and accurate oil supply under different working conditions is ensured. In addition, the gas flow characteristic is optimized through the gas inlet cone and the variable cross section design, and the overall performance is further improved. The effects of remarkably improving the combustion efficiency, reducing the uneven temperature distribution and improving the system stability are achieved.

This application provides an in-situ injection regeneration cooling system for ammonia-fueled combustion chambers, including a combustion chamber, a fuel supply assembly, and a control module. The combustion chamber includes a flame tube and a cooling channel. The fuel supply assembly includes a liquid ammonia storage tank, a direct injection pipeline, and a regeneration cooling pipeline. The direct injection pipeline is connected to the nozzle of the flame tube, and the regeneration cooling pipeline is connected to the cooling channel. The cooling channel is connected to the flame tube. A first flow regulating device is installed on the direct injection pipeline, and a second flow regulating device is installed on the regeneration cooling pipeline. A temperature monitoring device is installed in the area with the highest heat load in the cooling channel. The control method is that the control module adjusts the second flow regulating device according to the temperature obtained by the temperature monitoring device to regulate the cooling flow rate into the cooling channel. The control module calculates the difference between the total fuel flow rate and the cooling flow rate entering the flame tube according to the set total fuel flow rate and cooling flow rate, and controls the first flow regulating device according to the difference to regulate the injection flow rate into the flame tube.

The present invention discloses a controllable scramjet engine and its operating method, belonging to the field of scramjet engines. The engine comprises a supersonic combustion chamber, a controllable gas generator disposed on the outer wall of the supersonic combustion chamber, the output end of the controllable gas generator being connected to the input end of the supersonic combustion chamber via a regenerative cooling pipe disposed on the wall of the tail nozzle of the supersonic combustion chamber; the controllable gas generator comprises a main body, fuel filled within the main body, and an electric pyrolysis mechanism for pyrolyzing the fuel. Using the above-mentioned controllable scramjet engine and its operating method, pyrolysis gas is used as fluidizing gas to carry powdered fuel for injection, effectively enhancing the engine's specific impulse performance. The gas fuel can also serve as a pilot fuel, first burning to increase pressure and temperature, and then carrying a flow to eject high-energy powder particles, thereby solving the problem of short residence time of powdered fuel in the combustion chamber and low combustion efficiency.