Fuel supply circuit and cooling method

FIELD: aviation.

SUBSTANCE: invention relates to a power supply circuit (6) for supplying a rocket motor (2) with at least the first liquid fuel. The mentioned power supply circuit comprises at least one buffer tank (20) for the first liquid fuel and the first heat exchanger (18), which is embedded in the mentioned buffer tank (20) and suitable for connecting to the cooling circuit (17) for cooling at least one power source to cool the mentioned heat source by transferring the heat to the first fuel.

EFFECT: improved cooling of aircraft heat sources.

11 cl, 3 dwg

 



 

Same patents:

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering and can be used in spacecraft engines. Power plant comprises cryogenic tank with shield-vacuum heat insulation and channel with heat exchanger, flow control valve, booster pump, intake with capillary accumulator with heat exchanger and throttle and hydropneumatic system with pipeline. Channel cross-section sizes comply with maximum outer sizes of heat exchanger cross-section.

EFFECT: cooling of cryogenic component in capillary accumulator.

3 dwg

FIELD: chemistry.

SUBSTANCE: invention relates to propellants for liquid, solid fuel and hybrid rocket engines, containing oxidiser and combustibles. Propellant oxidiser contains boron nitrate. Propellant contains saod oxidiser and combustibles, such as pure or bound boron, for instance boranes (diborane), beryllium borohydrate, boron carbide, borides of metals. In addition to large release of hydrogen born reacts with released nitrogen with formation of boron nitride and heat release 252.6 kJ/mol.

EFFECT: obtaining propellant oxidiser, which contains boron nitrate.

4 cl

FIELD: machine building.

SUBSTANCE: hollow one-piece blank with bottom is pressed from a bar section, local bulges are provided on the bottom on the outer and/or inner side. The following operations are performed: machining of the blank internal and external surfaces, rotary drawing with thinning with permissible deformation degree, thermal treatment and finishing machining. The local bulges shall exceed the minimal thickness of the shell by at least 10 times.

EFFECT: improved strength characteristics.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises control over jet engine thrust vector, fuel flow running out from combustion chamber along Laval nozzle, lengthwise duplex control electromagnets mounted at nozzle outer expanded section, current MHD-generator installed at the nozzle throat, current stabiliser and rectifier and aircraft control system that controls said electromagnets. Control over jet engine thrust vector is ensured by deflection of plasma flow running out from combustion chambers with respect to nozzle mirror axis by electromagnetic field induced by control electromagnets. Plasma flow is known to consist of positively charge ions and electrons. Note here that bulk of ions is several orders of magnitudes higher than that of electrons. This defines the thrust vector by the direction of positive ion flow.

EFFECT: simplified design of aircraft, decreased weight, higher reliability of engine and aircraft.

4 cl, 2 dwg

FIELD: power engineering.

SUBSTANCE: propellant comprises fuel and oxidant. Versions of the fuel contain fuel and oxidant at the following ratios of components: beryllium boron hydride - 35.26%+-10%, ammonium dinitramide - 56.52%+-10%, beryllium - 8.22%+-5% or lithium boron hydride - 36.45%+-10%, ammonium dinitramide - 51.93%+-10%, lithium - 11.62%+-5%, or aluminium boron hydride - 24.1%+-10%, ammonium dinitramide - 58.84%+-10%, aluminium - 17.06%+-5%.

EFFECT: jet engine with such fuel from gases releases only pure hydrogen.

3 cl

FIELD: engines and pumps.

SUBSTANCE: rocket propellant comprises fuel and oxidiser. Rocket propellant features the following composition at the following ratio of components in wt %: beryllium borane - 34.63±10, ammonia dinitramide - 55.50±10, beryllium hydride - 9.87±5, or beryllium borane - 23.78±10, ammonia dinitramide - 76.22±10, or lithium borane - 35.85±10, ammonia dinitramide - 51.06±10, lithium hydride - 13.09±5, or aluminium borane - 23.66±10, ammonia dinitramide - 57.76±10, aluminium hydride - 18.58±5, or decaborane - 39.64±10, ammonia dinitramide - 60.36±10. Other versions are produced using the reaction with ammonia (wt %): beryllium borane - 44.61±10, ammonia dinitramide - 35.75±10, ammonia - 19.63±5. All said reactions can be realised with the help of the other oxidiser, that is, nitrogen hexaoxide, N3O6.

EFFECT: emission of pure hydrogen solely.

11 cl

Rocket propellant // 2513850

FIELD: chemistry.

SUBSTANCE: invention relates to rocket propellants for liquid, solid fuel and hybrid rocket engines. Rocket propellant contains fuel, which represent borazine, and oxidant. In presence of bound nitrogen in oxidant fuel additionally contains boron or its compounds, for instance, diborane, tetraborane, decaborane, beryllium borohydride, metal borides. As one of versions, rocket propellant contains as fuel 62.65±15.0% of borazine and oxidant oxygen 37.35±15.0%. As another version rocket propellant contains 34.56±13.0% of borazine, 51.52±13.0% of oxygen and 13.02±13.0% of boron. In all cases the sum of component ratios must constitute 100%.

EFFECT: invention makes it possible to obtain high energy fuel and reduce confuser of nozzle, that is, to lighten rocket engine.

4 cl

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises control over jet engine thrust vector, fuel flow running out from combustion chamber along Laval nozzle, lengthwise duplex control electromagnets mounted at nozzle outer expanded section, current MHD-generator installed at the nozzle throat, current stabiliser and rectifier and aircraft control system that controls said electromagnets. Control over jet engine thrust vector is ensured by deflection of plasma flow running out from combustion chambers with respect to nozzle mirror axis by electromagnetic field induced by control electromagnets. Plasma consists of positive-charge ions and negative-charge electrons. Note here that mass of ions is several orders of magnitude higher than that of electrons. This defines the thrust vector by the direction of positive ion flow.

EFFECT: simplified aircraft design, decreased weight and overall dimensions of jet engine.

2 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: liquid-propellant engine includes a combustion chamber, a gas generator and a turbopump unit with a turbine and pumps. The gas generator and the turbopump unit are installed above the combustion chamber in series one above another along its axis. The gas generator and the turbopump unit are made as one whole unit. As per the first version, the liquid-propellant engine includes the following in downward direction: a gas generator, a turbine, an oxidiser pump, a fuel pump, a multiplier and an additional fuel pump, and the turbine outlet is connected to the combustion chamber via a gas line. As per the second version, the liquid-propellant engine includes the following in downward direction: an additional fuel pump, a multiplier, a fuel pump, a gas generator and a turbine, and the turbine outlet is connected immediately to the combustion chamber.

EFFECT: increasing the rocket movement speed, improving its weight characteristics and increasing the flight range.

2 cl, 7 dwg

FIELD: transport.

SUBSTANCE: invention relates to rocketry. Proposed vehicle comprises body, rocket engine with axially symmetric supersonic nozzle and truncated cone-shaped jacket made of soft thin-wall material, closed on body side and exposed on nozzle side to fold along lengthwise axis. Cone smaller exposed base extends beyond nozzle edge. Case is made form heatproof dense fabric. Fabric of smaller exposed base is connected with heatproof rigid ring. Jacket larger closed base has annular tubular channel communicated on one side with flexible tubular channels from heat-resistant dense fabric bound with jacket fabric and located along jacket one generatrix extending from larger base to smaller one and provided with gauged outlets in rigid ring area and, on the other side, with high-temperature gas source. Folded jacket is attracted to body by cords from thermally unstable material jointed with jacket smaller base rigid ring and located opposite flexible tubular channel outlets.

EFFECT: decreased weight and increased thrust.

7 dwg

FIELD: engines and pumps.

SUBSTANCE: in a protection device of a liquid-propellant engine against static electricity, which includes conductive paths attached by means of screws and nuts with one end to installation elements on housings of pyro valves and with the other end to bosses on the engine frame, pyro cartridges screwed into pyro valves, earthing bosses on the frame, earthing conductors, in which according to the invention, between the threaded part of pyro cartridges and the mating thread of a pyro valve seat, a thread on the pyro valve body and a thread of a tube of a start-up ampoule of the gas generator, as well as in places of attachment of the paths and earthing there applied is current-carrying enamel reducing active resistance of an electric circuit and serving at the same time as a locking device of threaded connections, to structures of pyro valve assemblies there connected are pipelines to which electrical jumpers are fixed, which are connected to the engine frame by means of fasteners; on a transverse tie member of its frame there arranged are bosses with earthing conductors connected to them.

EFFECT: improving reliability of electrical circuits for removal of electrostatic electricity from a pyro device.

3 cl, 16 dwg

FIELD: engines and pumps.

SUBSTANCE: invention can be used to integrate four chambers, turbopump unit and other units into integral engine unit to transmit generated thrust to rocket body. Rocket engine frame comprises mounting and bottom frames, struts, supports, bosses with locating bores, bosses to secure the engine to rocket and angle pieces of box-cross-section. Said frame is composed by all-welded spatial frame. Geometrical axes of frame struts connecting sand mounting and bottom frames intersect at one point with support bosses and supports to make triangles. Struts are jointed to support bosses and supports by plates and ribs. Crossbars to mount frames are jointed by bolts and nuts to bottom frame supports. Support on smaller crossbar is furnished with plate with pads welded thereto to mounted pyro and temporary retainers. Steering drives fasteners are arranged at the frame edges. Besides, part-through bores are drilled in frame supports to mount assembly equipment. Two spaced apart supports are arranged at bottom frame where larger crossbar is mounted. Bores for rigging arrangement to be mounted are made on smaller crossbar side at box-cross-section angle piece between struts and mounting frame. Locating bores in support bosses feature high-quality surfaces for studs. Part-through bores for retainer washer lugs are made at support boss ends. Locking through bores are made at skirts of supports. Besides, bores are made in walls at struts bottom sides to fill inner cavities of struts with foam. Support bosses of mounting frame and frame bottom structure support are machined to makes them parallel.

EFFECT: higher stiffness, enhanced performances, decreased weight.

6 cl, 17 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed rocket engine has four chambers secured at the frame, turbopump unit secured thereto. Said unit comprises turbine, oxidiser and fuel pumps, heat protection, lines for oxidiser and fuel feed to gas generator and combustion chamber. In compliance with this invention, said frame is an all-welded 3D structure composed by fender and bottom frames interconnected by rods. Note here that crossbars with bearings are secured to bottom frame, journals of chambers being fitted in said bearing to turn about swing axis. Besides, the engine comprises four bent oxidiser gas feed lines with their common manifold connected with turbine outlet. Other eight bends are connected to appropriate heads of the chambers. Note here that sets of flexible pipes with bellows are arranged in said lines perpendicular to said swing axis. Said bellows are connected with fixed part of the line by one butt and, by opposite one, with movable part incorporated with unit of chambers swinging in one plane.

EFFECT: more efficient control over thrust vector, higher specific thrust pulse, perfected design.

12 cl, 28 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed attachment comprises rib with yoke and four extra threaded bosses with threaded ears, arc with four extra threaded bosses with threaded ears and lugs, braces, bosses, fasteners, lock nuts and clamp. Thrust plate with bolt is secured at said yoke. Threaded bush for mounting extra braces is fitted at lug threaded section and cotter-pinned thereat.

EFFECT: higher stiffness of attachment.

4 cl, 14 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed method comprises production of outer and inner shells, assembly of shell rings, soldering, making of bypass holes of the cooler in one or several commutator rings and welding of one or several commutators with commutator rings. In compliance with this invention, combustion chamber nozzle is soldered prior to making of bypass holes of the cooler in commutator rings or at making said holes not to the entire commutator ring wall depth. Then, after soldering in commutator rings, cooler bypass holes are made to the entire commutator ring wall depth. Commutators with tips are soldered to the nozzle. Note here that said holes are drilled either mechanically or by EDM process.

EFFECT: higher quality of soldered joint, ruled out clogging of commutator ring bypass holes and cooling circuit grooves.

2 cl, 4 dwg

FIELD: power industry.

SUBSTANCE: invention can be used at designing of atomisers and mixing heads of liquid-propellant engines. A coaxial spray atomiser includes a housing with a hollow tip, in the outlet part of which there are radially located slots made in the form of alternating projections and cavities, and attaching an oxidiser cavity to a combustion zone, a bushing enclosing the tip with a gap and attaching the cavity of the first combustible to the combustion zone. Radially located slots are made so that perimetre of a central part of the jet, which is restricted with generatrixes of beams, is not more than 3s, and beam length is 2.3…2.5s, where s - beam thickness; with that, the number of beams is equal to three; in the bushing between the tip projections there are the channels, the outlet part of which opens to the combustion zone, and the inlet one is connected to the cavity of the second combustible.

EFFECT: increasing completeness of mixture formation.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed method consists in feeding fuel components in combustion chamber via coaxial aligned-jet nozzle communicating oxidiser chamber with combustion zone and including sleeve covering with clearance the nozzle to communicate fuel zone with combustion zone arranged in mixing head in concentric circles to make central and peripheral zones. Note here that at first stage mode oxygen is fed into combustion chamber via hollow nozzle with developed outlet surface of aligned-jet nozzle while hydrogen is fed via shaped gap between said nozzle and said sleeve and kerosene is fed via channels made in said sleeve. Note also that outlet section of said channels opens into combustion chamber while their outlet communicates with kerosene unit chamber. Besides said chamber in said sleeve is connected with circular groove made at sleeve end and connected with combustion zone. Note here that at second and further stages oxygen is fed into combustion chamber via hollow nozzle with developed outlet surface of aligned-jet nozzle while hydrogen is fed via shaped gap between sais nozzle and said sleeve. Proposed nozzle comprises casing with hollow atomiser. Outlet of the latter has radial grooves composed by alternating recesses and ledges communicating oxidiser chamber with combustion zone, sleeve to house said atomiser with clearance and to connect hydrogen chamber with combustion zone. Note that said radial grooves are arranged so that perimetre of jet central part confined by generating lines of beams does not exceed 3s while beam length makes 2.3…2.5s, where s is beam thickness. Note also that the channels made between atomiser ledges with outlets open sleeve chamber and inlets communicated with kerosene chamber. Note also that the sleeve between nozzle ledges has channels with outlets open to fire zone.

EFFECT: better fuel mix mixing.

2 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed method consists in feeding fuel components in combustion chamber via coaxial aligned-jet nozzle communicating oxidiser chamber with combustion zone and including sleeve covering with clearance the nozzle to communicate fuel zone with combustion zone arranged in mixing head in concentric circles to make central and peripheral zones. Note here that at first stage mode oxygen is fed into combustion chamber via hollow nozzle with developed outlet surface of aligned-jet nozzle while hydrogen is fed via shaped gap between said nozzle and said sleeve and kerosene is fed via channels made in said sleeve. Note also that outlet section of said channels opens into combustion chamber while their outlet communicates with kerosene unit chamber. In operation at second and further stages oxygen is fed into combustion chamber via nozzle with developed outlet surface of aligned-jet nozzle while hydrogen is fed via shaped gap between said nozzle and said sleeve.

EFFECT: better fuel mix mixing.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: method to supply fuel components into a chamber of a three-component liquid propellant rocket engine, preferably, oxygen-kerosene-hydrogen, consists in supply of the specified components into the chamber via coaxial jet nozzles, comprising a hollow tip, which connects an oxidant cavity with a combustion zone, a bushing covering with a gap the tip and connecting the cavity of fuel with the combustion zone, arranged in a mixing head along concentric circumferences and forming central and peripheral areas. At the mode of the first stage oxygen into the cavity of the combustion chamber is supplied via the hollow tip with developed triradial outlet surface of the coaxial jet nozzle, hydrogen - via a profiled gap between the tip and the bushing of the specified nozzle, kerosene - via channels, which are made in the bushing. Besides, the outlet profile of the specified channels is made as equidistant to the tip profile. The outlet part of specified channels opens into the cavity of the combustion chamber, and the inlet one is connected with the cavity of the kerosene unit; at the mode of the second and subsequent stages oxygen into the cavity of the combustion chamber is supplied via the hollow tip with the developed outlet surface of the coaxial jet nozzle, and hydrogen - via the profiled gap between the tip and the bushing of the specified nozzle.

EFFECT: improved completeness of mixture formation.

2 cl, 2 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises gas generator, turbo pump unit, feed and adjustment assemblies, mixing head including housing, unit to feed oxidiser, mainly, oxygen, primary fuel feed tank, extra fuel feed tank and fire bottom unit. Coaxial aligned-jet nozzles making central and peripheral zones are arranged in said units in concentric circles. Said coaxial aligned-jet nozzles include hollow tip communicating oxidiser zone with fire zone, sleeve covering said tip with clearance to communicate the primary fuel unit with fire zone. Note here that tips of at least central zone nozzles have radial grooves at their outlets composed of alternating ledges and recesses. Note also that the sleeve between tip ledges has channels with outlets open to fire zone and inlets communicated with extra fuel unit chamber. Note that outer profile of said channels is equidistant with tip profile.

EFFECT: better fuel mix mixing.

5 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket engines. A turbine pump, in which a pump impeller is connected to one end of a rotary shaft, and a turbine is connected to the other end of the rotary shaft. The turbine pump is made so that the equivalent area between the efficiency curve of the turbine produced on the basis of a conditional expression, in which the number of rotations of the rotary shaft is maintained as permanent regardless of the pump flow speed and efficiency curve of the actual machine turbine, becomes the working area. A rocket engine is considered, using a turbine pump, which is made so that the equivalent area between the efficiency curve of the turbine produced on the basis of a conditional expression, in which the number of rotations of the rotary shaft is maintained as permanent regardless of the pump flow speed and efficiency curve of the actual machine turbine, becomes the working area.

EFFECT: invention provides for reduced moment of inertia of a turbine pump and improves speed of response of a rocket engine of a turbine pump type.

5 cl, 10 dwg

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