Liquid-propellant rocket engine chamber with controlled nozzle

FIELD: engine devices and pumps.

SUBSTANCE: chamber comprises a cooled part of nozzle and an uncooled header of carbon-carbon composite material, steering assemblies and a frame, according to the invention, in the uncooled header, there are niches in which several sections of a detachable earth nozzle are disposed, having rotation shafts tangential in the area of the joint of uncooled header cooled part of the nozzle, mounted in brackets fixed to the cooled part of nozzle and connected by steering units to the engine frame.

EFFECT: increasing the efficiency and reliability of work along the entire rocket flight path.

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: invention relates to rocket engineering and can be used at creation of rocket engine nozzles, namely at development of a design of nozzles of liquid-propellant engines, which have a radiation-cooled nozzle extension. The rocket engine nozzle has a contour in the form of an axially doubled bell with a fracture of a contour line between two bell shapes. Fracture of the contour of the rocket engine nozzle is made in the form of an arc of a circle, the beginning and the end of which is determined with its contact points of contours of the first and the second bell shapes. Contour of the second bell shape is shaped as per a curve of the second order with an inclination angle to the symmetry axis of the rocket nozzle at the point of the fracture end of the rocket nozzle contour, which is larger than the inclination angle increased by 8° of the contour of the first bell shape to the symmetry axis of the rocket nozzle at the beginning point of the contour fracture.

EFFECT: invention allows decreasing evaluation temperature of the end part of the rocket engine nozzle at minimum reduction of effective specific thrust impulse.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry, particularly, to increase in rocket and aircraft engine thrust. Rocket engine supersonic nozzle thrust is increased by forcing the external medium into nozzle inside via set of holes and initiating the interaction between nozzle and working fluid. Forcing of external medium inside the nozzle is executed at overexpansion at pressure p"а">p"н". Working fluid is forced from nozzle inside to outside bottom at underexpansion at p"а"<p"н" via nozzle end section. The latter is made of high-temperature gastight material with exposed porosity. High-porosity permeable cellular material represents carbon-carbonic composite, or ceramic composite, or refractory metal alloy, or fibrous and channel-tubular material.

EFFECT: higher mean specific pulse, uniform blow-in/blow-out of working fluid, controlled altitude characteristics of rocket nozzle.

5 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocketry and can be used in production of rocket engine with expansion nozzle. Rocket engine nozzle comprises bell and folding adapter composed by tabs articulated with said bell by expander for changing of tabs from folded position to working position. Folded tab generatrix drawn through the plane of tab mirror plane is parallel with bell generatrix drawn through the same plane. Another invention of the set relates to rocket engine expansion gear including elements of articulation of tabs with nozzle bell that make the pantographs interconnecting the adjacent tabs. Every pantograph comprises lengthwise beam connected with each of two adjacent tabs by two articulated plates while every tab is connected with bell by guide elements.

EFFECT: simplified design of nozzle and its drive, decreased weight, higher reliability.

3 cl, 11 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed nozzle comprises case, subsonic and supersonic parts and seal-and-start device with afterburner tube and support. Flat swirler is arranged in said afterburner tube perpendicular to its axis at a distance from outlet cross-section at rigid mounts. Lengthwise axes of the latter are located in planes extending through afterburner tube axis. Flat swirler is provided with one or several bores and lining with low ablation temperature fitted at its front end surface.

EFFECT: decreased scatter of internal ballistic parameters at acceleration.

3 cl, 1 dwg

FIELD: machine building.

SUBSTANCE: rotating nozzle bell housing from composite materials comprises a shell with a shape of truncated cone with two attachment flanges near the large and small bases, and also main frame with embedded details for interaction with nozzle rotating mechanisms. The shell in the zone of frame installation is designed with a ring belt with the end surface fixing the frame position in an axial direction, and is integrated with the frame in a single-piece design with formation of ring space between the external surface of the belt and internal surface of the frame. In the ring space the embedded details interacting with the nozzle rotating mechanisms are embedded. The lateral surface of the frame from the side of the large base of the shell is designed with a strengthened ring edge formed by fabric bend around the hard disk (which is the part of its structure) from material compatible to the frame material, and is formed as a flange for embedding the housing into the system of nozzle components.

EFFECT: invention allows to improve the reliability of rotating nozzle bell, and to decrease its mass and labour input.

2 cl, 3 dwg

FIELD: motors and pumps.

SUBSTANCE: invention can be used for the design of the liquid fuel rocket motor (LFRM) with turbopump fuel system designed without afterburning, with radiation-cooled camera nozzle attachment. LFRM includes turbopump unit (TPU) 1, gas-producer 2, exhaust line of TPU turbine 3, combustion chamber 4 with radiation-cooled nozzle attachment 5 and manifold 6 on the nozzle of the combustion chamber 4, connected with the exhaust line 3. Around the radiation-cooled attachment 5 the housing 7 is provisioned, the manifold 6 is located in the zone of joint of the radiation-cooled attachment 7 and regenerative-cooled parts of the nozzle of the camera 4 and is connected with the input of the annular cavity formed by the housing 7 and wall of the radiation-cooled attachment 7, the output of which is connected to ring-type supersonic nozzle 8, surrounding the radiation-cooled attachment 7. Meanwhile, for the material of the housing 7 dense heat-resistant fabric can be used.

EFFECT: improvement of reliability of the motor and increase of specific impulse.

2 cl, 1 dwg

FIELD: motors and pumps.

SUBSTANCE: nozzle consists of several independent trapezoidal ogival-shaped sectors, connection in axial direction. Forming of ogival profile of the package of internal and external walls of each sector is performed by explosion, on external surface of internal wall of each sector by milling the key grooves of variable width are made with formation of edges of cooling ducts, each internal wall of sector of ogival profile is cover by moulded thin external wall with their joining, then will the sectors are hydropneumatically tested, then their ends are subjected to machining and the sectors are welded by longitudinal profile welds in a ready nozzle with consequent non-destructive testing of welding joints and hydropneumatical testing of the sectors. The nozzle of the liquid fuel rocket motor can be made using another method - from several plane trapezoidal sectors. Meanwhile the milling of grooves in each sector and their connection are made plane. Moulding of ogival profile of the nozzle is made by explosive forming or by expanding punches. External and internal walls are joined by soldering or laser welding. The amount of sectors depends on the width of preform sheet and the nozzle diameter. Sectors are welded by laser or electron-beam welding.

EFFECT: obtaining of strength and reliable design of ogival-shaped large-sized nozzle irrespective of overall dimensions, the fabrication of which does not require unique equipment and significant capital investment.

9 cl, 10 dwg

Propelling device // 2532326

FIELD: engines and pumps.

SUBSTANCE: propelling device comprises a body, a cone-shaped combustion chamber, an exhaust pipe, two spring valves between the exhaust pipe and the combustion chamber, a control unit with hydraulic outlets.

EFFECT: invention makes it possible to increase reliability of operation of a jet engine without speed reduction.

1 dwg

FIELD: engines and pumps.

SUBSTANCE: in a supersonic part of an axisymmetric nozzle of a rocket engine there is an insert installed, which has length, output diameter and expansion degree less than the appropriate geometric parameters of the wall in the supersonic part of the nozzle. The insert takes two mounting positions - adjoins the wall of the supersonic part of the nozzle in process of flight in dense layers of atmosphere and is placed outside the area of aerodynamic interference with the rear edge of the wall in process of flight in low-density atmosphere. In the position designed for flight in low-density atmosphere the front edge adjoins the surface, which limits disturbances that reach the wall and the tangent to the generatrix of which passing via the edge of the output cross section of the nozzle, is directed at the angle μ=arctg1M21 to the tangent to the generatrix of the wall in the output section, where M - local Mach number near the wall in the output section of the nozzle.

EFFECT: increased nozzle traction at specified dimensions.

4 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to rocket engineering. A rocket engine with a sliding diffuser comprises a nozzle of gas escape leaving a combustion chamber, besides, the nozzle has a longitudinal axis (ZZ') and comprises the first part that determines the critical cross section of the nozzle and the first fixed section (12) of the diffuser, at least one second sliding section (16) of the diffuser, the cross section of which is more than the cross section of the first fixed section (12) of the diffuser, and a mechanism (18) of sliding of the second sliding section (16) of the diffuser, arranged outside the first and second sections (12, 16) of the diffuser. A heat protection shield (102) is built in between the sliding mechanism (18) and the first fixed section (12) of the diffuser. The heat protection shield (102) comprises a convex wall (104) on the side facing the first fixed section (12) of the diffuser.

EFFECT: invention provides for increased reliability of a rocket engine with a sliding diffuser by reduction of impact of heat radiation from a diffuser in process of rocket engine operation.

10 cl, 6 dwg

FIELD: rocket engine.

SUBSTANCE: proposed nozzle is made from carbon-to-carbon composite material; nozzle is provided with stationary bell mouth, extensible attachment mounted on load-bearing ring for locking the extensible attachment of collet. Load-bearing ring is provided with T-shaped slots in which collets are inserted. Collects are also made from carbon-to-carbon composite material and are secured by means of thermo-resistant adhesive.

EFFECT: enhanced tightness of nozzle at low mass of collet joint; enhanced operational reliability.

3 dwg

Up!