Carbon-carbon composite material. RU patent 2520281.
 Cooling system of liquid-propellant engine chamber / 2511942In a cooling system of a liquid-propellant engine chamber, which includes a cylindrical combustion chamber and a nozzle containing in its turn convergent and divergent parts and a critical section between them, which are made in the form of an external cover, an internal cover with the main fins of constant thickness, which form a cooling circuit, and at least one barrier belt with tangential openings and a manifold, inside which an annular part is installed, according to the invention, the annular part is trapezoid-shaped and has a trapezoid-shaped cavity, and inlet and outlet openings are made on end faces of the annular part at an angle to the combustion chamber axis. The barrier belt can be made at the connection point of the combustion chamber and the nozzle in the middle of the nozzle convergent part. There can be made two barrier belts. |
 Fluid-gas jet engine / 2511877Invention relates to aerospace engineering and may be used in clustered rocket bodies as a correction engine. Proposed engine comprises tank filled with working fluid and having the bore in cover, chamber and jet nozzle. Working fluid phase splitter is arranged inside the engine chamber, at tank outlet. Control valve with spring and electromagnet is arranged downstream of said splitter. This engine incorporates the device to heat working fluid in area adjoining the tank outlet. Fluid-gas engine generates jet thrust by outflow of water steam formed at gas vaporisation from liquid phase. |
 Liquid propellant rocket engine chamber / 2497013Proposed engine chamber combustion chamber with regenerative cooling, throat and nozzle, 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. |
 Method of determining unit pulse of solid fuel / 2494394Method involves measuring the reaction force of gasification products when burning a sample of solid fuel, armoured on the side surface, wherein the reaction force and time for complete combustion of the sample of solid fuel placed in a constant volume explosion apparatus are measured, at pressure in the range of (0.5-1.5)MPa, generated by an inert gas, e.g. nitrogen or argon, wherein the volume of the explosion apparatus and the mass of the sample are in a given ratio, and the value of the unit pulse of is determined using a calculation formula. |
 Liquid propellant engine / 2494274Liquid-propellant engine comprises at least one gas generator, at least one turbo pump unit, feed and adjustment members, circular regenerative-cooling chamber with shaped center body accommodating aforesaid units, mixing head including case, oxidiser feed unit, mainly oxygen feed, primary fuel feed unit, extra fuel feed unit and fire plug 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. |
 Device to suppress transverse forces by separation of reactive jet acting at jet engine nozzle, and jet engine nozzle / 2493413Device to suppress transverse forces includes orientation devices installed on a jet engine nozzle and comprising the first unit forming a traction rod, the second unit forming a fixation link, and a driving unit. The first end of the traction rod is hingedly fixed on the nozzle. The first end of the fixation link is hingedly fixed on the combustion chamber, and the second end is hingedly fixed to the second end of the traction rod. The first end of the driving unit is hingedly fixed on the fixed structure of an aircraft, and the second end is hingedly fixed to the second end of the fixation link. Each traction rod comprises a rigid element fixed to both ends of the traction rod, an element, which is longitudinally deformed under action of compression or extension force, and facilities to disconnect the rigid element from the traction rod ends. The longitudinally deformed element is rigidly connected to two ends of the traction rod and comprises a tube stretching in the longitudinal direction of the traction rod and equipped with multiple circumferential slots. The other invention of the group relates to a jet engine nozzle, comprising the above device for suppression of transverse forces. |
 Liquid propellant rocket engine / 2493412Liquid propellant rocket engine comprises at least one gas generator, at least one turbopump set, elements of power supply and control, a circular regeneratively cooled chamber with a profiled central body, in the inner cavity of which there are listed units installed, a mixing head, comprising a body, a unit of oxidant supply, mostly, oxygen, a unit of main fuel supply, a unit of additional fuel supply, a unit of a flame bottom. In the specified units along concentric circumferences there are coaxial jet nozzles installed, which create central and peripheral areas. The specified coaxial jet nozzles include a hollow tip, which connects the oxidant cavity with the combustion zone, a bushing covering the tip with a gap and connecting the cavity of the first fuel with the combustion zone. In tips of at least nozzles of the central zone in the outlet part there are radially arranged slots made in the form of alternating ledges and grooves, besides, radially arranged slots are made so that the perimeter of the central part of the jet limited with beam generatrices makes not more than 3s, beam length is 2.3…2.5s, where s - beam thickness, at the same time the number of beams is equal to three, besides, in the bushing, between ledges of the tip, there are channels, the output part of which opens to the combustion zone, and the input one connects with the additional fuel cavity. |
 Liquid propellant rocket engine / 2493411Liquid propellant rocket engine comprises at least one gas generator, at least one turbopump set, elements of power supply and control, a circular regeneratively cooled chamber with a profiled central body, in the inner cavity of which there are listed units installed, a mixing head, comprising a body, a unit of oxidant supply, mostly, oxygen, a unit of main fuel supply, a unit of additional fuel supply, a unit of a flame bottom. In the specified units along concentric circumferences there are coaxial jet nozzles installed, which create central and peripheral areas. The coaxial jet nozzles include a hollow tip, which connects the oxidant cavity with the combustion zone, a bushing covering the tip with a gap and connecting the cavity of the first fuel with the combustion zone, at the same time in tips of nozzles of the central zone in the outlet part there are radially arranged slots made in the form of alternating ledges and grooves, besides, in the bushing, between ledges of the tip, there are channels, the output part of which opens towards the combustion area, the inlet one connects with the cavity of additional fuel unit. |
 Liquid-propellant engine / 2490507Liquid-propellant engine (LPE) includes a gas generator, a turbo-pump unit, feed and control elements, a regeneratively cooled chamber with a shaped central body, in the inner cavity of which the above units are installed, a mixing head including a housing, a supply unit of oxidiser, mainly oxygen, a main fuel supply unit, and additional fuel supply unit an a fire bottom unit. In the above units there installed in concentric circles are coaxial uniaxial-jet injectors forming central and peripheral zones. The above coaxial uniaxial-jet injectors include a hollow tip attaching the oxidiser cavity to combustion zone, a sleeve enclosing the tip with a gap and attaching the first fuel cavity to combustion zone. In tips of at least injectors of central zone there are radially located slots in the outlet part, which are made in the form of alternating projections and cavities; radially located slots are made so that perimetre of central part of the jet, which is restricted with generatrixes of beams, is not more than 3s, and beam length - 2.3…2.5s, where s is beam thickness. Number of beams is equal to three. In the sleeve between projections of the tip there are channels, the outlet part of which opens to the cavity made in the sleeve housing, and the inlet part is connected to the additional fuel cavity; the above cavity in the sleeve housing is connected through tangential channels to an annular groove made on the sleeve end and connected to combustion zone. |
 Method of operating space engine running on gas fuel / 2488712Pre-gasified fuel components, helium gas from displacement system and aluminium powder are fed into prechamber for mixing. Further, made mix is fed via peripheral tangential swirler into combustion chamber on the side of nozzle cover. On gyrating along combustion chamber wall toward head section said mix protects combustion chamber walls against heat of active bed of flow part from engine axial section. Presence of helium decreases molecular weight of combustion products to add to engine specific pulse. To increase mix combustion temperature aluminium powder is added thereto. |
 Method for application of heat-protective and conductive coating on carbon fibres and fabrics / 2511146Method for application of heat-protective and conductive coating on carbon fibres and fabrics includes plasma spraying of cermet compound in the form of mechanical powder blend containing 5-15 wt % of nichrome, 15-5 wt % of zirconium dioxide, 70 wt % of aluminium, 10 wt % of aluminium-nickel, and 4-7 wt % of yttrium oxide as stabilising agent for zirconium dioxide. |
| Formation method of heat-resistant coatings on basis of nickel aluminide (nial) / 2507310 Invention can be used at production of heat-resistant and antifriction coatings on a part from carbon and alloy steels working under conditions of increased temperatures of up to 1600°C and dry friction. The coating is formed on steel parts by application of an aluminium layer by means of a liquid-phase method and performance of a diffusion annealing. Prior to application of the aluminium layer, a steel part is nickel-plated; after that, the aluminium layer of the technically pure aluminium melt is applied at the temperature of 800-850°C during 3-4 seconds, and diffusion annealing is performed at the temperature of 950-1100°C during 6-10 hours. |
 Structural element with catalytic surface, method of its production and application / 2490063Invention relates to structural element. Proposed structural element has catalytic surface 12. Note here that said catalytic surface consists of metallic surface sections 14 and surface components 13 of MnO2 in contact with the former. Note also that portion of said surface components 13 of MnO2 with respect to the sum of metallic surface components and surface components 13 of MnO2 varies from 10% to 60%. Invention covers also the method of making catalytic surface 12 of structural element. Besides, it covers application of structural element for decreasing ozone content in gas flowing over catalyst surface. |
| Method for producing matrix, matrix and method of producing microstructure relief of light-diffusing panel and its use / 2453631 Method of manufacturing a matrix to produce a microstructure relief on the surface of a light-diffusing panel includes creation of a model of the surface with preset microstructure relief by applying an adhesive on a sheet of acid-resistant material, placing over it a layer of a mixture made of fractions of hard crystalline rocks, applying a metallic coating to create an electrical contact with subsequent formation of galvanic metallic sediment, which is separated from the model and the metal matrix with a preset microsructure relief is shaped. The method of producing a microstructure relief on the surface of a light-diffusing panel is characterised by the fact that the surface of the light-diffusing panel with a microstructure relief is formed by die casting and a casting mould is used to place a matrix containing on its surface a copy of the preset microstructure relief produced by the above method. |
 Device for diffusive metallisation in medium of fusible liquid metal solutions / 2423546Device consists of heating chamber with external heaters wherein there is located bath with metal solution. A sluice chamber is located at the same level with the heating chamber. Above the heating and sluice chambers there is located a manipulation chamber connecting the heating and sluice chambers. In the manipulation chamber there are arranged a rotor device of transfer of coated items, loading-unloading device whereon there are fixed coated items, heat-protecting screens and sealing water-cooled disks ensuring sluice chamber sealing. |
 Method of anti-friction strengthening treatment of inner cylinder surfaces / 2355555Invention deals with engineering industry technology, namely with methods of anti-friction strengthening treatment of inner cylinder surfaces. Process tool with anti-friction bars and deforming elements is rotated and moved reciprocating. Coating application on part surface is performed by its rubbing with anti-friction bars and part surface deformation with coating by deforming elements in a form of balls and rollers. Coating application is performed with the help of suspension composed of fine powder and binding agent. Suspension is supplied by channels of process tool simultaneously with the beginning of deforming element operation. Deforming element radius is 1.5…2.0 mm. Hold down pressure of deforming elements towards processed surface is 160…500N. Rotation velocity of process tool is 20…40 m/min. Reciprocating movement speed of process tool is 10…20 m/min. Hold down pressure of anti-friction bars towards treated surface is 160…500N. |
 Method for making nanostructured metal plate / 2354751Ceramic substrate is placed on melted lead or eutectic Pb-Bi surface with dissolved deposited metal. Then the ceramic substrate surface is cooled to ensure temperature gradient 600-700°C between the melt and its surface. Further it is kept in the inert gas medium until nanostructured metal plate of the required thickness is deposited on the ceramic substrate surface. Thereafter the plate is removed from the substrate. |
 Method of nanostructured metal layer formation on steel plate surface / 2354750Deposited metal is dissolved in melted lead or eutectic Pb-Bi, with a temperature gradient 500-600°C ensured between the melt with the dissolved metal and a steel plate surface pre-coated with lead by steel plate cooling. Then metal is deposited on the steel plate surface in inert gas medium due to the temperature gradient between the melt surface and the sheet surface. The thickness of prepared nanostructured layer is controlled by process time. |
 Manufacturing method of functional surface / 2353706Invention relates to method of manufacturing of functional surface and can be used in mechanical engineering, for instance, for forming of reflecting and other metal-containing coatings. It is implemented gas-dynamic sputtering by powder material with rains size 0.01-50 mcm from chosen materials and material in the form of spheroidized particles with size 70-300 mcm made of steel and other solid magnetic medium It is used feedback system between coating thickness and density of evaporated material flow and/or velocity of travel sputtering spot of evaporation relative to detail surface. Evaporated powder material is tagged rate providing connection to the surface and to particles of treated material - rate, providing impact moulding of evaporated material. It is implemented surface finish by programmable mechanical operation till nominal dimensions of its profile and roughness. Process is implemented with simultaneous pumping out, catching and separation of materials particles. Temperature of surface and gas powder flow of evaporated material is lower the temperature of recrystallisation soft component of evaporated powder material. |
 Method for making thin-wall decorative articles by electric-arc metallization / 2309196Method comprises steps of forming pattern of article for making according to it rough mold; performing sand blasting of working surface of rough mold; depositing onto its surface layer of alloy being material of decorative article; releasing deposited layer from rough mold due to difference of thermal expansion factors of materials of deposited layer and substrate. |
 System and method for making reinforcing element integral with sandwich metal fibre sheet / 2501710Claimed inventions relate to integral structures and methods of their production. Proposed structure comprises sandwich metal fibre sheet with metallic and nonmetallic layers, extreme inner metallic layer and extra layer bonded to extreme inner metallic layer by friction welding with mixing. Reinforcing element is made integral with said extreme inner metallic layer. In compliance with first version, proposed method comprises preparation of sandwich metal fibre sheet with nonmetallic and metallic layers and extreme inner layer and bonding extra to the latter by friction welding with mixing to obtain welded semis. In compliance with second version, it includes machining of welded semis to shape outer surface of said extreme inner layer, placing nonmetallic and metallic layers thereon to obtain sandwich metal fibre sheet, machining said welded semis to shape said inner extreme metallic layer and machining of reinforcing element. |
FIELD: chemistry.
SUBSTANCE: invention relates to composite materials, particularly carbon-carbon composite material, and can be used in making liquid-propellant engines. The carbon-carbon composite material with a protective silicon carbide coating has a sealing layer. The protective coating is coated with a sealing layer of nickel, niobium or molybdenum metal.
EFFECT: high durability and reliability of the obtained material.
1 dwg
The invention relates to the field of high-temperature composite materials.
Known carbon-carbon composite material with a protective coating of silicon carbide material (see "Model combustion chamber liquid-propellant rocket engine", described in the patent for useful model RU 93468 U1, published 27.04.2010 year).
By its characteristics and the achieved result, this material is closest to the claimed and taken as a prototype.
The disadvantage of this material is low durability and low reliability due to leaks protective coating.
When working known device of oxidant of high-temperature gas-dynamic flow penetrates through the cracks and pores of the protective coating of silicon carbide and reacts with the carbon-carbon composite material, causing oxidation and destruction of well-known material and devices.
The technical result of the invention consists in increasing the durability of the material and structural safety.
This technical result is achieved in a carbon-carbon composite material with a protective coating of silicon carbide, according to the invention of the fact that the protective coating applied layer of metal: - of Nickel, or niobium, or molybdenum, having a melting point above the maximum operating temperature of a composite material.
Below, with reference to the attached picture, a description of the invention.
Carbon-carbon composite material contains, for example, woven frame made of carbon fiber carbon matrix (layer 1) and protective coating (layer 2).
The claimed material is made with a sealing layer 3 of metals: Nickel, or niobium, or molybdenum, on the protective covering 2, that allows to cover cracks and pores in the protective coating without weakening the structure of the latter.
Sealing layer 3 can be done by any method available (plating, sputtering in vacuum, etc.)
During operation of the proposed material, for example, in the design of the combustion chamber liquid-propellant rocket engine sealing layer 3 will prevent the penetration of oxidant of high-temperature gas-dynamic flow to the protective coating 2 through cracks and pores and hence carbon-carbon layer 1 composite material, preventing oxidation and destruction of the latter.
Thus, the claimed carbon-carbon composite material is compared with the prototype higher durability and reliability in conditions of operating at high temperatures in the environment oxidizer and restrictions on weight.
Carbon-carbon composite material containing protective coating of silicon carbide, wherein the protective coating applied sealant layer of metal, selected from Nickel, niobium or molybdenum.