Method of forming reactive forces of motion from air-dynamic part of jet and device for realization of this method

FIELD: engines and pumps.

SUBSTANCE: method is carried out by means of transverse extrusion of the required air mass for a combustion chamber from accelerating air column by jet from the channel formed by a blade rotor in a cylindrical body with subsequent replacement of accelerated air mass onto newly formed air mass with subsequent replacement of already cut part of reactive jet on column of air, which is carried out in the blind position of the channel by the lateral filling of the released space with air from the surrounding space through a screw window of a body in the period of its movement for getting into the jet from the other side. Lateral extrusion of the air mass from its volume is possible at the formation of a considerable internal pressure from the head of the jet to the counter-acting force of the resistance to acceleration of the free air mass in the channel, which requires the absence of the initial movement in the associated direction and its excess in the volume, which are allocated for the traction force increase.

EFFECT: increased efficiency of the air-jet engine by the steady supply of air mass under any operating conditions with a concomitant increase in traction force.

2 cl, 6 dwg

 



 

Same patents:

FIELD: engines and pumps.

SUBSTANCE: method to produce thrust consists in supply of a fuel mixture into a chamber, realisation of a detonation process of fuel burning in an intermittent mode. The outer wall of the chamber is closed with a microporous plate, which is arranged between two perforated metal plates. The microporous plate is made into several layers from different materials and with different porosity, with twisting capillaries, the fuel mixture is supplied under pressure. The detonation process of fuel combustion is realised near the outer wall, for instance, with a laser beam.

EFFECT: method considerably simplifies and cheapens process of thrust production, makes it possible to create universal devices.

4 cl, 1 dwg

FIELD: power engineering.

SUBSTANCE: method for recirculation of combustion products in a pulsating combustion chamber consists in mixing of a fuel and air mixture with combustion products in the volume of the combustion chamber, by installation of a front device at the inlet to the combustion chamber. In the range of operation with the air excess ratio of up to α≈10, air coming via the front device into the combustion chamber from the inlet system is used for ejection of the combustion products by the front device from the peripheral wall area of the combustion chamber into the flow of air at the inlet to the combustion chamber with the purpose of their further mixing. The front device of the pulsating combustion chamber comprises elements of mixture formation intensification and a body deepened into the combustion chamber for the distance of 0.3-1.5 of its hydraulic diameter. Elements of mixture formation intensification are made in the form of hollow semi-open petals installed radially in cuts inside the body and having a closed well-streamlined edge at the side of air inlet from the inlet system and a rear edge open towards the combustion chamber and an upper edge in radial direction via a cut in the front device body. The angle of inclination of the front edge of petal elements of intensification to the axis of the inlet system channel is 90-30°, and ends of petal intensification elements are free and do not cross in the centre, forming a radial beam structure with a free central passage near the axis of the front device.

EFFECT: invention increases efficiency of a working process of a pulsating combustion chamber with simultaneous provision of high parameters of environmental compatibility and manufacturability of a device.

8 cl, 11 dwg

FIELD: aircraft engineering.

SUBSTANCE: proposed aircraft engine comprises combustion chamber, resonant tube, air-fuel mix intake multi-ejector system, fuel injection nozzle, fuel system, superheater coil arranged at aircraft tail side. Fuel is fed from fuel system into air-fuel mix intake multi-ejector system. Outlet of said air-fuel mix intake multi-ejector system is communicated with combustion chamber front part at aircraft nose part. Fuel injection nozzle is arranged at inlet of said air-fuel mix intake multi-ejector system. Exhaust gases from resonant tube is directed opposite aircraft flight path. Said resonant tube is arranged outside the combustion chamber while superheater coil is located there inside. Axes of resistant tube, combustion chamber and air-fuel mix intake multi-ejector system are arranged in parallel. Exhaust gases are released from combustion chamber with 180 degrees turn relative to engine motion vector.

EFFECT: decreased overall dimension of air breather.

13 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises supersonic air intake, supersonic mixing chamber, supersonic combustion chamber, supersonic outlet nozzle, fuel-air mix igniter, and fuel feed system. Fuel feed system comprises manifolds and pylons with fuel channels and nozzles mounted in supersonic mixing chamber. Engine incorporates also gas-air stage channel arranged between supersonic air intake and supersonic mixing chamber. Fuel feed system pylons are arranged at gas-air stage channel outlet. Fuel-air mix continuous-operation igniter is arranged in supersonic combustion chamber crosswise recess. Fuel feed system channels are exposed to be shutoff by gas-dynamic means.

EFFECT: reduced calorific intensity at high supersonic speeds, self-controlled fuel feed, expanded range od speeds.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to electric power engineering and may be used as electric power source or drive of various transport facilities. Proposed power plant comprises heat engine with dynamotor fitted on its output shaft coupled with electric generator. Additionally, power plant incorporates wave reduction gearbox arranged between dynamotor and heat engine. Heat engine housing is shaped to barrel with disc shaft running in bearings. Disc outer surface accommodates paired opposed supersonic air intakes of air jet working circuits made up of inlet diffusers arranged tangentially on disc inner surface, combustion chambers and supersonic nozzles. Inlet diffusers are communicated with high-pressure liquid or gas fuel source via ejector with its active nozzle communicated with fuel source. Mixing chamber is composed of axially symmetric channel in the shaft communicated via radial pipelines arranged on disc inner surface with initial sections of inlet diffusers the walls of which have holes. Heat- and noise-resistant coating is applied on heat engine housing surface and disc inner surface.

EFFECT: simplified nonpolluting design, higher efficiency.

2 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed engine running on detonating fuel-air mixture comprises, at least, one fire tube with crosswise lower section moving relative to said tube to occupy two extreme positions. Note here that first position corresponds to detonation phase and second position corresponds to phase of feed into said chamber. Engine comprises also outer case around fire tube making peripheral annular chamber around tube lateral wall to allow air flow from engine intake. Fixed flow guides are arranged in said peripheral annular chamber to make flow channels and, at least, one moving unit is arranged in said chamber. Said moving unit is arranged in annular chamber and connected with moving lower part to displace along fire tube lateral wall. Note here that said moving unit may shut off one of flow channels to direct portion of airflow in direction of inlet and unlock said channel when its lower part stays in first position.

EFFECT: perfected design.

12 cl, 4 dwg

FIELD: propulsion engineering.

SUBSTANCE: impulse detonation rocket engine contains the burner section (the entrance of this section is using for portion supply of detonation fuel), the impulse sparking system and the locking device for burner section output at the moment of it's filling-up by detonation fuel; the draught asymmetrical nozzle and the locking device. The draught asymmetrical nozzle is mounted on the output of burner section and it contains Laval's nozzle as a channel. That channel is tapered and quick-divergent at the direction of detonation product's expiration. Locking device is performed as rotor valve, which is situated at the nozzle's critical cut and is performed as cylindrical drive body with a rotation axis that interpenetrates draught nozzle's critical cut perpendicular to its axis. The end-to-end channel with the inner profile (the profile coincides with draught nozzle circuit on the length of cylindrical body's transverse size) is performed in the cylindrical body in the direction of nozzle's axis. The rotation axis of the cylindrical body and the axis of draught nozzle are situated at the one plane. The engine also contains a laser impulse system for sparking by laser spark (that spark is generating in the burner section); the command spark impulse synchronous feeding and burner section output locking sensor, and the rotor valve, which has one entry connected to the laser system and the other entry connected to the rotor valve drive.

EFFECT: increased stability of engine performance and expanded range of its operation modes, decreased vibration capacity.

4 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises, in particular, cyclic ejection of combustion products and suction of atmospheric air. Circular vortex is generated at resonator tube inlet in combustion product cyclic ejection. This ups increase in rarefaction inside combustion chamber in blow cycle and, hence, intensifies filling said chamber with atmospheric air.

EFFECT: increased thrust of pulse duct.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises, in particular, cyclic ejection of combustion products and suction of atmospheric air. Two circular vortices are generated at a time in intake channel in suction cycle. This intensifies mass transfer and combustion to up pressure pulse amplitude and engine thrust.

EFFECT: increased thrust of pulse duct.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: pulse gas-turbine engine comprises pulse gas-generator engine connected to compressor, and also to additional gas turbine or to jet engine nozzle. Engine also comprises gas-generator turbine having at least two combustion chambers, which are arranged with the possibility of rotation parallel to shaft, on one side, comprising inlet openings that exit for instance to distributor with ignition, control and monitoring devices, with systems of fuel or fuel-air mixture, air supply. Combustion chambers are joined to distributor with calibrated gap and, for instance, labyrinth seals. On the other side, combustion chambers comprises nozzles, for instance, in the shape of Laval nozzles arranged in the form of vanes bent aside opposite to rotation, coming out in axial direction to at least one crescent guide apparatus. Nozzle apparatus is arranged with clearance to nozzles of combustion chambers, along circumference of their rotation so that it comprises, at first along with nozzles rotation, bleed, and then nozzle apparatus that comes out to nozzles of combustion chamber. Between bleed and nozzle apparatus there is cutoff plate arranged with the possibility to cover nozzle of at least one combustion chamber. Between nozzle apparatus and bleed of crescent guide apparatus, along with rotation of combustion chamber nozzles, cutoff plate is also arranged, with the possibility to close nozzle of at least one combustion chamber during its rotation. In every crescent guide apparatus there is hole provided, which is connected to exhaust branch pipe coming out to nozzles, for instance, controlled, of additional gas turbine, or to nozzle, for instance, controlled, of jet engine.

EFFECT: invention increases reliability and efficiency factor of engine.

18 cl, 5 dwg

FIELD: mechanical engineering; engines.

SUBSTANCE: proposed pulsating detonation engine contains combustion chamber, reactor and detonation resonator made in form of separate modules and connected to each other with possibility of replacement. Air channel of second loop is arranged inside combustion chamber and reactor along longitudinal axis of engine.

EFFECT: possibility of use of proposed engine as model for carrying out different researches owing to possibility of variation of engine systems.

1 dwg

Pulsejet engine // 2279562

FIELD: jet engines.

SUBSTANCE: proposed pulsejet engine contains combustion chamber limited by side wall with air intake arranged at inlet and nozzle at outlet, fuel feed system with tank, injectors and fuel feed channel connecting tank with injectors, and ignition unit with electronic control unit and supply source. Side wall of combustion chamber is elastically pliable. Fuel feed channel from tank to injectors is laid directly around elastically pliable side wall of combustion chamber in form of solid space limited by outer rigid wall. Fuel feed channel is provided with inlet and outlet valves which are orientated to side of injectors.

EFFECT: improved reliability of combined operation of fuel feed system at knocking in combustion chamber.

4 cl, 5 dwg

FIELD: mechanical engineering.

SUBSTANCE: methods of operation of detonation power plant includes injection of fuel into initiating detonation pipe, initiating of fuel from one of end faces of detonation pipe, propagation of burning process along detonation pipe with change into detonation combustion at each working cycle. After initiating of next portion of fuel, forming of cumulative jet with higher pressure zone at bottom of chamber is provided owing to geometry and design of initiating detonation and cones which is ensured by synchronization of flows of detonation combustion products from several detonation pipes or cones and application of higher pressure zones orientated relative to axial line of chamber of detonation plant at angle from 0° to 90°.

EFFECT: increased specific power and efficiency.

10 cl, 33 dwg

FIELD: pulsating detonation engines.

SUBSTANCE: invention relates to pulsating detonation engines employing magnetohydrodynamic control of flow. Proposed engine contains pipe 12 with open front end 16 and open rear end 18 and fuel-air inlet 20 made in pipe 12 of front end 16. Igniter 24 is located in pipe 12 in place between front end 16 and rear end 18. Flow magnetohydrodynamic control system is arranged between igniter 24 and fuel-air inlet 20 to control detonation in pipe 12 before igniter 24. Flow magnetohydrodynamic control system employs magnetic and electric fields before igniter 24 to dissipate detonation combustion wave 34 propagating forward or at least reduce potential of ignition.

EFFECT: provision of operation of valve control or flow control system at high frequency for pulsating detonation engines, improved reliability.

30 cl, 7 dwg

FIELD: aircraft engineering.

SUBSTANCE: invention can be used in designing of flying vehicles of different application and aircraft engines. Proposed chamber of detonation combustion pulsejet engine has housing, ambient air intake, device for injecting oxidizer and fuel into chamber and device for initiating detonation combustion. Thrust wall of chamber is made movable, in form of piston for preliminary compression of ambient air. Chamber is provided with bypass channel to supply compressed air into detonation section of chamber, and piston reverse stroke spring pusher. Air intake has channel in compression section of chamber communicating the chamber with atmosphere.

EFFECT: possibility of using detonation combustion pulsejet engine at low flying speeds.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: method of thrust generation incorporates decomposition of hydrocarbon fuel in the presence of a catalyst to produce hydrogen-containing mix (synthesis gas) with subsequent burning of the synthesis gas mixed with oxygen-containing component. Combustion of synthesis gas is effected in cyclic detonation conditions at the rate of several cycles per second, the thrust being produced due to detonation products blowout. The synthesis gas for this detonating mix, prior to feeding it into the detonation combustion chamber, is produced by a catalytic conversion of liquid or gaseous hydrocarbon fuel, e.g. natural gas, methane, petroleum, kerosene etc. Hydrocarbon fuel is preliminary mixed with oxygen-containing component, and the catalytic conversion is effected using a catalytic converter that ensures hydrocarbon fuel conversion into the synthesis gas without using water.

EFFECT: higher specific thrust and power efficiency in decomposition of hydrocarbon fuel.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: method of increasing the vertical take-off jet engine thrust consists in using the reaction of gases thrown off the resonator pipe and ejecting atmospheric air. During the intake cycle, the gas resonator pipe backflow power is exploited by arranging a turning branch piece inside the ejector to form an extra lift on the ejector intake part. In compliance with the other version, during the intake cycle, the gas resonator pipe backflow power is exploited by arranging mechanical elements in the resonator pipe tail, the said elements representing wing profile screen mounted at a zero incidence to create extra lift.

EFFECT: increased vertical take-off jet engine thrust.

2 cl, 7 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed engine and its version incorporate at least one pulsed detonation chamber designed to cause detonation of fuel and oxidiser furnished with one exhaust side and incorporating a porous insert to be fitted into the pulsed detonation chamber inner space, nearby the outlet side, and a casing accommodating the aforesaid pulsed detonation chamber. In compliance with the second version the casing is furnished with a porous insert to be fitted into the pulsed detonation chamber inner space, downstream of the exhaust side.

EFFECT: attenuation of crosswise waves required to maintain detonation and/or increase in curvilinear shape of front impact wave along with decrease in its power.

11 cl, 15 dwg

FIELD: engines and pumps.

SUBSTANCE: hypersonic pulse detonating engine comprises casing, air intake, half-closed detonating combustion chamber, nozzle block, fuel system and control system. Air intake is arranged as annular. Central body is casing with fuel tank, heat exchanger and active thermal shielding. Half-closed detonating combustion chamber is formed by end wall of central body and internal wall of nozzle block. Air intake channel is connected to half-closed detonating combustion engine by adjusted annular slotted nozzle. Method of hypersonic pulse detonating engine functioning consists in preparation of fuel mixture, its supply to half-closed detonating combustion chamber, detonation of fuel mixture in pulse mode and generation of impulse. Prepared fuel mixture with coefficient of oxygen excess below 0.1 is supplied to half-closed detonating combustion chamber via end perforated wall. Fuel mixture with coefficient of oxygen excess more than 0.85 is sent to half-closed detonating combustion chamber via adjusted annular slotted nozzle periodically in pulse mode, and fuel mixture gas detonation is carried out in the range of frequencies from 200 to 27,000 Herz.

EFFECT: higher reliability of engine operation in hypersonic flight modes, and also thermal efficiency factor and specific impulse increase.

6 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: method for operation of supersonic pulse athodyd includes supply and combustion of fuel in supersonic flow in expanding channel of combustion chamber. Fuel supply and combustion is carried out in several expanding sections of combustion chamber in pulse periodic mode. Combustion chamber is made of expanding sections that are serially installed one after another with devices for pulse periodic supply of fuel into points of sections joint and via pylons that are available in flow of every section. Sections of combustion chamber are arranged so that inlet section of subsequent section is more than outlet section of the previous section. Amount and frequency of supplied fuel in every section of combustion chamber is specified based on condition of non-stationary flow supersonic speed maintenance in the whole of chamber channel.

EFFECT: invention is aimed at increase of pulse athodyd operation efficiency to increase Mach number of flight.

2 cl, 2 dwg

Up!