RussianPatents.com
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Heat resistant component. RU patent 2436866. |
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FIELD: metallurgy. SUBSTANCE: heat resistant component contains main part of TiAl of inter-metallic compound having friction surface rubbing against another component and resistant to abrasion coating. Coating is applied on friction surface and is formed by sedimentation in discharge of material of a consumable electrode of metal resistant to abrasion. EFFECT: raised resistance. 14 cl, 11 dwg, 3 tbl
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Rear suspension assembly of aircraft engine with double eye, and power plant containing such assembly / 2435968 Engine suspension assembly located between engine and its attachment post includes the first fixing device and two eyes in the form of a triangle with three holes made in each of them and forming oblique triangle. The first fixing device has the possibility of being attached to the post and is equipped with two eye lugs, each of which includes four mounting holes located opposite each other and aligned along one line. The first fixing device and each eye are connected to each other by means of connecting pins located in two holes of each eye and in the appropriate holes of the fixing device. The third hole made in the eye is meant for attachment to the fork located on the engine side. Each eye has double design made of two parts of identical shape and attached to each other in the direction perpendicular to the holes. The other invention of the group refers to the power plant of aircraft, which contains attachment post and engine connected to the post by means of the above suspension assembly. |
Air cleaning device for gas turbine installation / 2435051 Air cleaning device for gas turbine installation consists of air receiving chamber, of air filters arranged in tiers in air receiving chamber and of system for cycle air heating. A section of exhaust pipe located opposite an air intake chamber is used as a source of heat in the system of cycle air heating. A screen with flanges adjoining weather shield is set over the section of the pipe. Ribs are welded on the same section of the pipe. Removable panels are assembled between the same section of the pipe and the air receiving chamber and under the base of the air receiving chamber. |
Rotor drive of auxiliary unit of gas-turbine engine, support of units for gas-turbine engine, and gas-turbine engine / 2434151 Rotor drive of auxiliary unit, which is installed on support of units of gas-turbine engine, which contains rotor shaft drive means, includes tubular shaft rotated with the above means and supported with the first and the second support bearings rigidly connected to the support of the units. Rotor shaft is installed coaxially with tubular shaft, and engagement device with rotation is provided between rotor shaft and tubular shaft. Rotor shaft is supported with the third support bearing rigidly connected to the support of the units. The first and the second support bearings have the size which is less than size of the third support bearing. The other invention of the group refers to the support of gas-turbine engine units, which contains the gears rotating the above drive. One more invention of the group refers to gas-turbine engine containing the shaft and power take-off devices on the shaft, rotary gears of the above support of the units. |
Method of applying cermet coat slurry on turbine stator inner surface / 2433208 Slurry is applied by pouring into stator inner cavity through inlet branch pipe in amount sufficient for complete immersion of guide naves in slurry. Inlet branch pipe is sealed to turn turbine stator about its axis through angle at which inlet branch pipe stays at its bottom position. Then, turbine stator is turned clockwise about axis perpendicular to its axis through angle of inclination to horizon at which slurry does not flows out of turbine stator with inlet branch pipe and guide vanes unsealed. Thereafter, turbine stator is turned about said axis counter clockwise to drain slurry. Now with slurry drained, turbine stator is rotated about its axis with turbine in horizontal position, unless slurry layer water glare disappears. |
Air intake housing design / 2433073 Invention relates to aircraft engineering, namely, to turbojet aircraft nacelle. Proposed nacelle comprises air intake to direct airflow towards turbojet blower and central structural element 5 that includes housing 9 embracing said blower and jointed to air intake. Noise absorbing appliance 13 is arranged on a part of said air intake to envelope said housing. Note here that clearance 14 is allowed for between said appliance and housing. |
Control method of gas turbine engine with afterburner / 2432478 Control method of gas turbine engine with afterburner consists in the fact that fuel consumption in afterburner is controlled by measured air temperature at engine entrance, air pressure after compressor, engine control lever position and fuel consumption in main combustion chamber (main fuel consumption). Measured engine control lever position and gas pressure differential at engine turbine allow controlling hydraulic cylinders of jet nozzle doors actuator. Additionally the measured engine control lever position, air pressure after compressor and air temperature at engine inlet help to form specified value of start-up fuel consumption in afterburner. Start-up fuel consumption is directed into afterburner, "hot streak" device is switched on and afterburner ignition is controlled by measured gas temperature in afterburner. If there is no afterburner ignition the start-up fuel consumption and "hot streak" device are switched off, the specified value of start-up fuel consumption is changed with 5% increment and the process of afterburner start-up is repeated. It is done till afterburner ignition is fixed. If changing of specified fuel consumption exceeded 50% and there is no afterburner ignition, the process is stopped and unscheduled engine regulation is performed. |
Control method of gas turbine engine with afterburner / 2432478 Control method of gas turbine engine with afterburner consists in the fact that fuel consumption in afterburner is controlled by measured air temperature at engine entrance, air pressure after compressor, engine control lever position and fuel consumption in main combustion chamber (main fuel consumption). Measured engine control lever position and gas pressure differential at engine turbine allow controlling hydraulic cylinders of jet nozzle doors actuator. Additionally the measured engine control lever position, air pressure after compressor and air temperature at engine inlet help to form specified value of start-up fuel consumption in afterburner. Start-up fuel consumption is directed into afterburner, "hot streak" device is switched on and afterburner ignition is controlled by measured gas temperature in afterburner. If there is no afterburner ignition the start-up fuel consumption and "hot streak" device are switched off, the specified value of start-up fuel consumption is changed with 5% increment and the process of afterburner start-up is repeated. It is done till afterburner ignition is fixed. If changing of specified fuel consumption exceeded 50% and there is no afterburner ignition, the process is stopped and unscheduled engine regulation is performed. |
Method of cooling gas turbine rotor by continuous power conversion by endothermic reaction / 2430251 Air is compressed in compressor to be fed into combustion chamber for fuel combustion. Resulted hot gas is fed for expansion to active gas power turbine to drive compressor. Converted fuel with increased absolute calorific power is afterburnt in endothermic reaction of initial fuel in steam reforming reactor. Parallel thermal cycle is conducted wherein heated mix of water with hydrocarbon fuel is fed via turbine hollow shaft into reaction chamber. Reaction chamber comprises porous carbon metal container arranged inside pressure gas turbine that stays in contact with power turbine or makes an integral part thereof. Reactor is rotated to compress said mix partially during endothermic reaction. Mix is partially heated by turbine cooling and by waste gas heat and, then, is discharged via jet nozzles to generate extra torque. |
Method of cooling gas turbine rotor by continuous power conversion by endothermic reaction / 2430251 Air is compressed in compressor to be fed into combustion chamber for fuel combustion. Resulted hot gas is fed for expansion to active gas power turbine to drive compressor. Converted fuel with increased absolute calorific power is afterburnt in endothermic reaction of initial fuel in steam reforming reactor. Parallel thermal cycle is conducted wherein heated mix of water with hydrocarbon fuel is fed via turbine hollow shaft into reaction chamber. Reaction chamber comprises porous carbon metal container arranged inside pressure gas turbine that stays in contact with power turbine or makes an integral part thereof. Reactor is rotated to compress said mix partially during endothermic reaction. Mix is partially heated by turbine cooling and by waste gas heat and, then, is discharged via jet nozzles to generate extra torque. |
Prop-fan engine / 2430250 Proposed engine comprises gas generator with compressor and rear prop fan coupled with power turbine 8 via reduction gear 13 surrounded by acicular air and gas chambers. Radial and axial deflectors 21, 22 are arranged in air chambers 19 of posts 16 and air chamber 20 of housing 15 to make oil chamber 23 of reduction gear 13. Ring reflector 30 is arranged on housing ahead of rear support housing flange joint 24 with deflector 22 and reduction gear housing 25. Said ring deflector 30 makes annular slot-like cavity 31 with its outlet communicated with compressor. Ring deflector outlet is provided with nozzle 32 to blow flange joint 24. |
Engine with supercharger (versions) / 2401388 Proposed engine 1 comprises supercharger 40 consisting of compressor 41 with multiple vanes fitted on the shaft of turbine 42, at least one device 44 providing step motion of multiple vanes 45 and turbine angular speed transducer 62 to recognise rotation of device 44 providing step motion of multiple vanes 45 and rotation of multiple vanes 45, which is connected with MCU 60. Engine 1 incorporates also turbine angular speed computing device to computer turbine angular speed letting multiple pulses per one revolution of turbine shaft. |
Nozzle for pump and pneumatic spraying of fuel / 2378529 Invention is related to design and operation of internal combustion engine. Nozzle for pump and pneumatic spraying of fuel comprises cylindrical shell open at the top and bottom and arranged with circular ledge, press flange arranged as a whole with shell, body cover, cone valve with groove in upper part, valve seat with ledge, rod with hole for the whole length of rod, fixators-limiters of vertical shifts, hollow nozzle piston, having free space inside, nozzle cylinder, spraying disks with holes, which produce perforated labyrinth, nut of disks fixation, nozzles for compressed air and fuel inlet, electrically driven valves of compressed air and fuel control and supply, oval ledge on piston head, axial compressor, compressed air receiver, fuel tank. Nozzle drive is executed by means of electrically driven valves action at its piston for valve opening and closing and at fuel for its spraying by compressed air or overpressure of the fuel itself without compressed air, valve is connected with the help of thread to rod and is inserted top down into body till ledge stop at seat and in body. Fixators-limiters that limit value of vertical shifts in opening and closing of valve enter groove of valve and are screwed into threaded holes in valve seat. Size of fixators that protrude into groove is less than width of groove on valve. Limiter of piston stroke is inserted into body. Lower support part of body is installed with the possibility of free traveling inside nozzle body and is arranged with larger diametre compared to other part of piston stroke limiter, spring is installed on it, which rests on lower support part of piston stroke limiter by lower end, and touches lower plane of nozzle piston by upper end. Nozzle cylinder is inserted into body, rests on piston stroke limiter and is pressed by body cover. Pressing force of cover acts through cylinder to limiter of piston stroke and at valve seat. Piston space hosts spraying disks with holes, one of which has its whole area as perforated, the second disk has holes only in the centre, and the first on top has holes along periphery. Thread is cut in upper part of piston, and nut that presses disks is screwed into this thread. There are two threaded holes in cylinder cover, and compressed air nozzle is screwed in one of them, and fuel inlet nozzle is screwed into the other one. Holes with thread and holes in nozzles represent fuel supply and air supply channels. Electrically driven valve for control and supply of fuel is installed on pipeline for fuel supply, directly near nozzle for fuel supply. Electrically driven valve for supply and control of compressed air is installed on air duct. |
Single-chamber multicylinder internal combustion engine with movement of pistons in opposite direction to each other / 2362893 Invention refers to propulsion engineering. Technical result is increase of engine efficiency and enhancement of its adjustment. Substance of the invention consists that in an engine, one combustion chamber for a number of working cylinders with actuating pistons is used, and therefore the whole cubic capacity of the claimed engine fits one combustion chamber. Besides, potential considerable consolidation of inlet gas supplied to the working cylinders is implemented. This ensures to combust enhanced cyclic fuel charge, thereby to perform more engine running without increasing in thermal loss. Enhancement of engine adjustment is provided by application of main circulation systems with adjustable stroke of the actuating pistons in the claimed ICEs, as well as by application of a movement phase variation device of the actuating pistons. |
Method of setting and adjusting compressor internal combustion engine supercharging pressure and system to this effect / 2338913 Method comprises adjusting supercharging pressure by a throttling device and includes the following operations, i.e. setting and adjusting the driving reduction gear set gear ratio relative to the ratio initial value and throttling the air flow by a throttle arranged ahead of the compressor, in the suck-in pipe. Note here that the supercharging system is set up by selecting an appropriate increased gear ratio of the reduction gear and the throttle throat cross-section, invariable in the engine operation. Note also that the aforesaid increased gear ratio of the reduction gear is constant in adjusting the supercharging parameters, while the throttle throat cross-section is varied depending upon the engine operating conditions. The proposed system incorporates an internal combustion engine, a driving reduction gear, a supercharging compressor, a throttling device. The driving reduction gear features a gear ratio increased relative to its initial value, while the throttling device is arranged ahead of the compressor in the suck-in pipe in throttling a low-pressure air flow. |
Air pump for vehicles / 2338900 Invention relates to air pumps for vehicles, particularly, to supercharging air pump. The proposed device incorporates air pump, for example, impeller 2 coupled with output shaft 4 of vehicle transmission with its input shaft being coupled to the vehicle engine in operation. The aforesaid input and output shaft 6 and 4 are coupled with appropriate gears of a three-way differential planetary gear set. The 3rd gear and input shaft 6 are linked to rotors 20 and 22, while the terminals of stators 24 and 26 are interconnected via controller 27 wired in the circuit to control electric power flux between the aforesaid components. |
Method of producing steam turbine vanes / 2433279 Proposed method consists in securing strip on vane leading edges, all along their length, said strip being made up of separate shaped stellite plates cut from solid shaped casting and butted together. One-piece stellite casting is divided into two or more sections. Said plates cut from one ingot section are arranged sequentially from vane apex starting from plates from mould closest to periphery. Plate face closest to mould periphery is arranged on vane apex side. |
System of heat insulation layers / 2433207 Proposed system (1) comprises first main side (2) to be located on boundary with structural part to be protected (30) and second main side (3) to be located on boundary with high-temperature ambient medium (4). System (1) has sections (5, 6) with different heat expansion factors. System first section (5) adjoining structural part to be protected (30) has first thermal expansion factor complying with that of structural part (30). At least, one second section (6) of system (1) has second, lower thermal expansion factor. System (1) is made up of joint between first ceramic heat insulation layer (8) facing aforesaid structural part, and second ceramic layer (9) facing high-temperature ambient medium (4). Note here that first and second protective layers (8, 9) are jointed together by plasma evaporation. System (1) consists of one of the following combinations of materials: 7YSZ/La2Hf2O7; 7YSZ/BaZrO3; 7YSZ/LaYbO3, where first value stands for material of first heat insulation layer (8), while second value designates material of second layer (9). Note also that 7YSZ is zirconium oxide stabilised by 7 wt % of yttrium oxide. |
Coating (versions), part of gas-turbine engine and protection method of part against damages related to sand effect / 2420612 Heat barrier coating consists of alternating layers of zirconium oxide, which is stabilised with yttrium oxide, and layers of material resistant to impact of molten silicates. External layer resistant to impact of molten silicates can be formed at least of one oxide chosen from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutecium, scandium, indium, zirconium, hafnium and titanium oxides, or can be formed of zirconium oxide stabilised with gadolinium oxide. Besides, metal bonding coating can be located between the base and system of heat barrier coating. |
Turbine blade for steam turbine and steam turbine with such blade / 2418956 Turbine blade for steam turbine consists of section of blade body containing fibrous composite material at least in separate areas and of section of root. Areas of the turbine blade containing fibrous composite material are surrounded with plastic protective layer preventing penetration of moisture into fibrous composite material during turbine blade operation. To control functions of the protective layer an electro-conducting layer or water-soluble chemical substances are installed between the protective layer and fibrous composite material. Another invention of the group refers to the steam turbine containing the above said turbine blade. |
Component of turbine (versions), turbine and procedure for turbine component coating / 2414603 Component of turbine consists of root, neck, platform and aerodynamic profile with external and internal surfaces defining cooling pass channels. According to one version the root of turbine component has one first coating, while the neck has the second coating. Also, composition of the first coating differs from the composition of the second coating. According to another version internal surface is covered with the first coating, while external surface is covered with the second coating; the first and second coating have different compositions. The third coating different from the first and the second one covers the platform and/or a lower side of the platform. The neck is covered with the fourth coating different from the third coating; the root is covered with the fifth coating different from the fourth coating. According to another one version the neck is covered with the first coating, a bottom of the platform is covered with the second coating; also, the first and the second coating are of different compositions. Internal surface is covered with the fourth coating, while the root is covered with the fifth coating corresponding in particular to a diffusion aluminide, aluminised layer, chromised layer or aluminised and chromised layer, also, the fifth coating differs from the fourth coating. Another invention of the group refers to a turbine containing the first step of working and guiding blades and the second step of working and guiding blades where the working blades of the first and second steps correspond to above said turbine components. Another invention of the group refers to procedure for coating the turbine component consisting in applying the first coating on all external and internal surfaces of the component, in applying the second coating on the first part of the coated component, and in applying the third coating on the second part of the coated component; also, the first, second and third coatings have different compositions. |
Procedure for increasing fretting resistance of items / 2390581 Invention refers to machine building and can be implemented for strengthening components of machines operating under conditions of fretting-corrosion. The procedure consists in modifying effect on material of surface layer of contacting sections of component in a friction pair by means of heating with electric arc. In a particular case of invention implementation heating with electric arc is performed at re-melting material. |
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