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Gas turbine engine includes housing with a stator stage having blades with an adjustable setting angle, which are controlled by a drive ring coaxially enveloping the above housing. Movement of the ring is restricted by rotation only about the axis of the above housing and connected with knee levers to blades with an adjustable setting angle. The drive ring is connected to an adjacent individual drive unit in the form of a power drive and containing two sections forming a cylinder and a stock. The stock is hinged to the ring, and the cylinder is hinged to the above housing; with that, the hinge between the cylinder and the housing is located near the end of the cylinder, out of which the stock comes. |
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Turbine stator comprises outer case to support nearing props with fairing (7), cooled nozzle blades (14) with lower flanges (15) arranged downstream of gas flow (5). Inner radial rib (8) of every fairing (7) is arranged in U-like seal ring (9) fitted at cylindrical flange (11) of the support. U-like seal ring (9) has outer and inner C-cross-section ledges (12) and (13) directed towards nozzle blades (14). Said outer and inner C-cross-section ledges (12) and (13) make pin-hole joint with inner ring (16) fitted radially at lower flanges (15) of blades (14). Shell (22) of inner ring (16) has channels (23) for proportioned feed of cooling air into lower-pressure chamber (20). |
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Support stand for turbine diaphragm, support stand structure for turbine diaphragm and steam turbine Support stand (430) for a steam turbine diaphragm comprises the main vertical part (435) with a bulge (447), which passes from the specified part (435) substantially perpendicular to it. The bulge comprises the first bulge, stretching from the upper end of the main vertical part (435), and the second bulge stretching from the area near the lower end of the main vertical part (435). The first bulge is at a certain distance from the second bulge. The first and second bulges are designed for coupling with an appropriate slot (450), made in the turbine diaphragm. In the bulges there is a hole (455), which passes via them vertically and is designed to place a fastening element (460), stretching via the first and second bulges (447) to ensure vertical attachment of the main vertical part (435) and specified bulges (447) to the turbine diaphragm. |
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High temperature gas turbine comprises a labyrinth seal as per honeycomb block on the inner shoulder made with a baffle plate and with an internal air cavity of the nozzle blade being cooled. The air cavity at the nozzle blade outlet is connected to the perforation which leads to internal cavities of honeycomb block cells via a dosing hole in the baffle plate and via a distributing channel and axial channel system which are set in the inner shoulder circumferentially. The axial channels are additionally connected by perforation to the outer surface of the inner shoulder of the nozzle blade. |
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Blade with airfoil and axial turbomachine Blade with airfoil comprises an inner platform zone and an outer tip zone in the radial direction, and a front entrance edge and a rear exit edge, between the platform zone and the tip zone, in axial direction. The blade is fitted with a pressure side being concave in the radial direction between the inner platform zone and the outer tip zone, as well as with a back being convex in the radial direction between the inner platform zone and the outer tip zone. The blade width in the axial direction between the entrance edge and the straight exit edge is changed parabolically from the maximal width in the platform and tip zones to the minimal width at the section between the platform zone and the tip zone. The other invention of the group refers to an axial turbomachine comprising the group of the above blades with airfoil. |
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Housing of jet-turbine engine, and jet-turbine engine containing such housings Housing of a jet-turbine engine has the possibility of installing into it of a variety of blades and includes attachment devices of the end of each blade, which are located on the housing side opposite to blades. Attachment devices include a ring-shaped element passing around the housing, and the housing includes holes through which ends of blades pass for their interaction with attachment devices. The housing is made of long fibres connected with thermoplastic resin. The ring-shaped element is obtained by pultrusion and soaked with thermoplastic resin welded with thermoplastic resin of the housing; besides, the whole assembly is connected by means of hot pressing. The other invention of the group relates to a jet-turbine engine containing the above housing and many blades, each of which has an end connected to the housing. |
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Outlet straightener vane for the turbojet engine contains extended single-block front and back sections, and also external layer, joined together by hot pressing. The extended single-block front section is cut out from the pultruded profile, containing resin-impregnated fibres, and forms a front edge of the vane. The extended single-block back section is cut out from the pultruded profile, containing resin-impregnated fibres, and forms a back edge of the vane. The external layer is made on the basis of resin-impregnated fibres and located between the front and back edges with forming of lateral sides of the vane. The external layer overlaps the zones of the front and back edges. Another invention of the group relates to the turbojet engine containing multiple vanes, mentioned above, each of which is fixed on the housing. |
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Transition zone between secondary combustion and lp turbine of gas turbine Gas turbine connected with secondary combustion chamber contains a set of guide vanes of LP turbine installed downstream of the specified combustion chamber. Radially the external border of the secondary combustion chamber is made by the external wall segment secured on the supporting component radially installed outside. The hot gases flow is limited radially from outside, inside the guide vanes by the external platform secured on the support of the guide vane. Between the wall segment and the external platform there is radially continuing cavity with width from 1 to 25 mm in axial direction in the inlet area. The cavity inlet area has step element reducing the cavity width by 10% per step, and continuing in the cavity at right angle to the direction of the hot gas flow. Relatively to the step element the cavity width radially outside again increases to width of the inlet area by means of the step continuing in the cavity at right angle to the direction of the hot gas flow. |
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Nozzle assembly of gas reaction turbine Nozzle assembly of gas turbine contains external and internal housings, between which stator vanes are located. The nozzle assembly vanes are electrically isolated from each other and fitted with electric contacts. The electric contacts of vanes are connected through electric cables to unlike poles of DC power supply so that the vanes connected to unlike poles of DC power supply alternate between each other uniformly along the whole circle. |
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Transition duct of gas turbine engine and method of its manufacturing, and also gas turbine engine Transition duct for connection of a combustion chamber and a turbine part of a gas turbine engine comprises a shell including the first and second surfaces. The first and second surfaces of the shell are connected by piercing, and the shell of the transition duct is made at least from one sheet stamped into a shape that creates a transition duct with a double shell. The other invention of the group relates to a gas turbine engine comprising the above transition duct. When the above transition duct is manufactured, the shell is produced, which comprises the first and second surfaces, and connection is made by piercing to connect the specified surfaces. |
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Turbine outlet device comprises hollow aerodynamic profiled supports located after the runner of the last turbine stage as well as aerodynamic profiled contours. The contours are formed by the front and rear blades set between the supports with displacement in respect to each other. The mean lines of input zones of the contours and input zones of the profiled supports are turned to the turbine longitudinal axis by 20-40° in the direction of the rotation of the last turbine stage runner. The mean lines of the output zones of the contours are directed along the turbine longitudinal axis. The blades are set with displacement in respect to each other at the distance equal to 0.03-0.15 of the length of the front blade chord. Along the contour chord the blades are set in the position of matching the front of the exit edge of the front blade and the front of the leading edge of the rear blade or are displaced in respect to the latter. The number of the contours set between the supports is determined by the dependence protected by the present invention. |
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Device for repair of the flange including some ledges uniformly located in circle comprises hollow bent reinforcement part shaped to flange and flange reconditioning part. Reinforcement part can be secured at the flange sound ledges and has two perpendicular mirror planes. Flange reconditioning part is arranged at reinforcement part with the help of fasteners located in one of mirror planes of said reinforcement part. The other invention of the set relates to aircraft engine module including crankcase flange repaired with help of aforesaid device. One more invention relates to aircraft engine including aforesaid module. In flange repair, sound damaged ledge is cut to select the free ledge at the flange adjoining the cut-off ledge for reinforcement and reconditioning parts to be located thereat. Then, reinforcement and reconditioning parts are assembled for them to be secured at the flange via bores of the flange safe ledges and reinforcement part bores. |
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Turbine assembly of turbo-pump unit Turbine assembly of the unit includes a working medium - steam supply housing, a nozzle block with inclined nozzles, a turbine having a shaft with a runner, and a waste steam outlet housing located downstream of the turbine in the steam flow direction. The steam supply housing is equipped with a header including an axisymmetrical annular cover having the shape of a flattened fragment of a tore or a toroid. The turbine runner us made at least of one disc with blades. Blades are convex-concave as to width and have radial height comprising (0.05÷0.25) of the disc radius. The blade thickness is variable in the direction of steam flow with maximum in the middle part of the blade chord width. The chord width of the blade in the projection to a conditional chord plane attaching inlet and outlet side edges of the blade does not exceed radial height of the blade. The nozzles are made in the disc in the amount of 8÷15, located radially at equal distance with their longitudinal axes from the turbine axis and equally spaced in a conditional circumferential direction at equal angles determined in the range of (24÷45)°. Total number of blades exceeds by 2.6÷34.4 times the number of nozzles. |
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Turbo-pump unit, and cold, hot and industrial water pumping method Turbo-pump unit includes a turbine assembly with working medium inlet and outlet housings, a nozzle block and a single-stage turbine. The unit includes a pump assembly with a screw centrifugal impeller. The working medium supply housing is equipped with a manifold including an axisymmetrical tight annular cover. The large part of the cover has the shape of a longitudinally flattened fragment of a tore or a toroid. Turbine runner blades are convex-and-concave as to width, radial height of 0.05÷0.25 of the turbine runner disc radius. The blade thickness is accepted as variable in the direction of working medium flow vector with maximum in the middle part of the blade chord width. The chord width of the blade in the projection to a conditional chord plane attaching inlet and outlet side edges of the blade does not exceed radial height of the blade. The inter-blade channel is of a confuser-and-diffuser type in the direction of the steam flow vector with maximum constriction of flow cross sectional area determined in zone of maximum thickness of blades. Total number of turbine runner blades exceeds by 2.6÷34.4 times the number of nozzles in the nozzle block. |
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Blade with changeable installation angle for turbomachine module stator section includes an active part of the blade, on which sides there arranged are radially inner and outer flanges. Active part of the blade divides inner flange to the first part located on the side of the blade convex surface and the second part located on the side of the blade concave surface. The first part of inner flange has external outline overlapping the circle at a distance from which and inside which there located is a part of external outline of the second part of inner flange. The other inventions of the group relate to stator section unit including above blade, to stator sections including such unit, to turbomachine module, including such section, and to turbomachine including this module. During manufacturing of the blade with changeable installation angle, radially performed is an inner flange from round profile machined in a circumferential direction forming the second part of this flange. |
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Gas turbine engine distributor, gas turbine engine turbine and gas turbine engine Gas turbine engine distributor comprises inner and outer circular platforms connected by radial blades. Inner platform comprises circular elements made of abradable material arranged at sheet sectors that make a ring of L-, S- or C-shape-cross-section inside inner platform. Inner edges of every sheet sector is soldered or welded to inner platform while outer edges are secured to abradable element or at sheet ring secured at abradable element. Distributor inner platform is composed of cylindrical baffle divided in sections. Inner platform sectors are molded elements and support sealing plates soldered or welded to platform sector by one edge and, by another, edge staying in sliding contact with adjacent sector of the platform level with sheet sectors supporting abradable elements. Other inventions of the set relate to gas turbine engine turbine with above described distributor and to gas turbine engine incorporating said turbine. |
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Improvement of control ring of setting angle of turbo-machine fixed blades Turbo-machine includes a stage having blades with a variable setting angle, which are arranged in the housing in a circumferential direction. Each blade includes a control rod radially projecting on the housing outer side and connected by means of a lever to a common control ring coaxial to the above housing and installed with possibility of being rotated on the outside of the housing. Control ring includes two sections fixed with connection side jaws and with an insert on one and the other sides of the above sections at least near ends of the latter. Sections include side grooves into which the above connection jaws are installed. |
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Tightness between combustion chamber and nozzle guide vanes of turbine in gas-turbine engine Gas-turbine engine includes an annular combustion chamber, a sectoral turbine nozzle guide vanes located at the chamber outlet and sealing devices axially arranged between combustion chamber and nozzle guide vanes. Sealing devices include a circumferential seal with axial elasticity, which includes axial support devices on exit edge of the combustion chamber and exit circumferential edge that is of sectoral type. Each sector of exit edge is arranged in one line with sector of nozzle guide vanes and includes axial support devices on entry edge of the sector of the nozzle guide vanes. The other invention of the group refers to a seal packing for the above gas-turbine engine, which is made as a single part and contains two circumferential edges. One of the edges has radial slots setting the sectors between themselves, which has the possibility of free movement irrespective of each other. |
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Gas turbine engine transition compartment and gas turbine engine Gas turbine engine transition compartment comprises first and second ends and housing extending there between. Said housing comprises inner and outer surfaces and turbulence promoter. Turbulence promoter extends continuously in spiral and make an integral structure over the entire outer surface. It features semicircular cross-section and is configured so that first part of air flow descends in spiral around transition compartment while second part is forced over spiral turbulence promoter to facilitate cooling of said compartment. Besides, this invention covers the gas turbine engine comprising combustion chamber unit and transition compartment described above and attached to combustion chamber to extend therefore. |
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Guide stage of a gas-turbine engine compressor includes a row of blades with a variable setting angle. Each blade includes a bucket, an external cylindrical trunnion being a blade rotation axis and entering a seat of an external casing, and an internal cylindrical trunnion installed in a mounting place of the inner ring. The internal trunnion of each blade is arranged parallel to the blade rotation axis and at some distance from that axis and installed in the mounting seat of the ring by means of a ball hinge system. The hinge system includes a ball coupling put on the blade internal trunnion and installed into the ring mounting place. Ball coupling includes an internal element installed with possibility of axial shift to the side on the blade internal trunnion, and an external element entering the ring mounting seat. External element includes an external circular projection meant for arrangement between a radially internal end of the blade bucket and the annular projection of the inner ring. |
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Proposed module comprises low-pressure and high-pressure compressors with their shafts running in bearings, and radial pipes of inner chamber supercharging. Shafts are separated from inner chamber by labyrinth seals fitted on seal disc. Said disc is fitted at reducing housing. Supercharge pipe communicate said chamber with compressed air line extending through reducing housing. Pipe ends are tightly fitted in reducing housing radial pipelines and radial guides of deal disc bushes. Pipe ends can be locked in said radial pipes. Seal disc guide bushes feature radial size sufficient for said ends to displace between working position whereat radial outer ends are tightly fitted in reducing housing pipelines and mounting position whereat said radial ends extend from reducing housing pipelines. Another invention of the set covers above described inner chamber disc with guide bush radial ends are tapered. One more invention of this set covers turbo machine with above described compressor. |
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Proposed device comprises control lever, pin and two free spherical plain bearings. Upper end of said pin is engaged with control lever while lower end is connected with vane. First free spherical plain bearing is fitted on pin lower end while second one is arranged on pin upper end. Free spherical plain bearing comprises inner and outer racers to make one ball joint. Inner racer and pin interlocked. Another invention of this set covers stator comprising case, aforesaid control devices and vanes arranged in said case. Every vane is rigidly secured to pin while aforesaid bearings are fitted in case bore. Other inventions of the set relate to compressor with said stator and gas turbine engine with said compressor. |
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Sealing of hub cavity of outlet casing in gas turbine engine Outlet casing of gas turbine engine includes two coaxial internal and external cylindrical walls connected by means of radial posts, and a cylindrical casing. Cylindrical casing is connected to rear end of radially internal wall and restricts the hub cavity together with radially internal wall and waste gas passage space together with radially external wall. Cylindrical casing is provided on its front end with a radial annular part directed inside the gas turbine engine. Radial annular part of the casing is provided on its inner end with an annular shoulder interacting due to tight radial sliding with internal cylindrical wall of the outlet casing. The other invention of the group refers to cylindrical casing for the above outlet casing, which is provided on one of its ends with an annular flange, and on the other one with a radial annular part that is directed inwards. Radial annular part is provided on its inner end with a radial annular shoulder having a cylindrical collar. One more invention of the group refers to gas turbine engine containing the above outlet casing. |
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Clamping accessory (versions) for mechanical treatment of nozzle blade Nozzle blade comprises radial inner and outer walls with a section of an aerodynamic surface stretching between the inner and outer walls. The inner wall is made with a mounting element on its surface levelled with a longitudinal central axis via the nozzle blade. The first rotary fastening element of the clamping accessory is made as capable of engagement with the mounting element of the inner wall of the nozzle blade. In the other version the clamping accessory for mechanical treatment of the nozzle blade comprises universal mounting elements on the nozzle blade and the clamping accessory for mechanical treatment. The mounting element on the blade is arranged as capable of levelling the blade with the central axis of a machine, around which the blade rotates during mechanical treatment as the mounting element on the blade is engaged with the mounting element on the clamping accessory for mechanical treatment. |
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Steam turbine and method of moisture removal from flow path in steam turbine Steam turbine comprises a diaphragm consisting of an inner ring, an outer ring and airfoils stretching between them. The airfoil comprises at least one channel of moisture removal, stretching along a part of the airfoil length and having at least one inlet hole, which communicates by the flow with the steam path passing through a row of airfoils and between adjacent airfoils, and at least one channel of inlet, stretching along a part of the length of the airfoil along the axis downstream at least one channel of the moisture removal channel and comprising at least one outlet hole for inlet of steam into the steam path. In the outer ring of the diaphragm there is an outer cavity, which represents a cavity for separation of steam/moisture. Steam and moisture removed via a channel of moisture removal arrive into the cavity. The cavity communicates along the flow with the channel of steam inlet for repeated inlet of steam separated in the cavity, into the steam path. |
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Compressor for repeated air pumping; turbomachine Compressor includes a housing containing compression stages with an impeller in each of them. Inlet stator located before the first stage includes blades with an adjustable inclination angle and rotation axes passing through the housing, and a repeated air pumping circuit. Repeated air pumping circuit includes spray holes passing through some blades of inlet stator and opening to inner part near their rotation axes at the compressor inlet. Holes are opened to incoming flow of compressor at a tangent to the housing. Each stationary blade includes a base of round shape with rotation axes projecting outwards from its centre. Base is arranged in a seat in external casing of the housing, and the above spray holes pass at an angle through the base. In external casing of the housing there is a hole opening to a ring-shaped cavity passing around the rotation axis and formed radially to external surface of inlet stator, external casing of the housing, a flat ring-shaped gasket and a bushing forming a bearing of the rotation axis. The hole passes between ring-shaped cavity and inner part of the housing. The other invention of the group refers to turbomachine containing the above compressor. |
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Turbine output device contains profiled supports of the casing located in flow-through part downstream turbine wheel of last stage. The middle lines of profile output areas of supports are directed along the turbine longitudinal axis. The middle lines of profile input areas of supports are turned to turbine longitudinal axis by 20-40° towards rotation of turbine wheel of last stage. |
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Lever for bringing into rotation of turbomachine stator blade with adjustable setting angle includes the first attachment zone on driven element of lever, the second attachment zone on stator blade with adjustable setting angle and the third zone of elongated shape between the first and the second zones. At least in one section of surface at least of one of the above zones of lever there laid is laminated vibration damping element. Laminated element includes at least one layer of viscoelastic material, which is in contact with the above surface section, and one counter layer of stiff material. Other inventions refer to turbomachine and compressor of gas-turbine engine, which contains at least one above described lever for bringing into rotation of stator blade with adjustable setting angle. |
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Scroll distributor and turbine hereto Turbine scroll distributor comprises case and connector. Said case completely covers the area around annular channel coiled around turbine rotor and cylindrical channel extending from annular channel to rotational axis to reach the rotor. Connector retains to case relative to retaining part to allow the case to expand and contract radially from rotational axis crossing its center. Said connector has ledge, slot and recess. Ledge is arranged on either case or retaining part to extends in one direction along radial line. Slot is made in another element. It is open in another direction along said radial line to extend in circumferential direction relative to rotational axis. Said ledge enters said slot. Said recess is composed by cutout in one wall that shapes slot in one direction along said radial line. Ledge penetrates through said recess in displacement along rotational axis relative to said wall. |
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Moist-steam turbine nozzle blade cascade Moist-steam turbine nozzle blade comprises body. Said body is arranged between inlet and outlet edges and features convex and concave surfaces. Medium section of concave surface is covered by guide plate to make a channel and injected steam exhaust slot located on body outflow edge side. Medium section of body concave surface and guide plate on channel and injected steam exhaust slot side are provided with heat-insulation layer. |
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Turbine nozzle assembly includes blade with internal and external side walls, external ring and flow divider with horizontal elongation. Boundary of transition between external ring and external side wall has enveloped/enveloping transition boundary or radial locking mechanism. Boundary of transition between horizontal elongation and internal side wall has radial locking mechanism or enveloped/enveloping transition boundary. Radial locking mechanism includes an enveloped step projecting along the axis out of the side wall and provided with a flange on its radial side in the form of the second enveloped step projecting along the axis to side wall. Enveloped/enveloping transition boundary includes radial enveloping groove on side wall and mating radial enveloped step. Where the enveloped/enveloping transition boundary is located on rear edge of side wall, it is connected by means of a butt weld located throughout the length of enveloped/enveloping transition boundary. Axial length of enveloped/enveloping transition boundary is approximately less than 1/4 of axial length of alignment between side wall and external ring or horizontal elongation. |
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Guide vane turning mechanism of axial turbine or compressor includes housing with case with turning vanes, which is installed into it. Levers connected in movable manner to the ring resting on the case are fixed on vane trunnions. Mechanisms comprising the shaft installed in the sleeve attached to the housing and levers on the shaft ends are located on both sides of the housing. Levers are hinged to the ring on one end of the shaft and to hydraulic actuator on the other end. On one of the hydraulic actuators there installed is spool valve through which oil is supplied from turbine or compressor control system to its pressure cavity connected by means of a pipe to pressure cavity of the second hydraulic actuator. |
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Gas turbine engine fast expansion plasma-enriched transition duct System of plasma-enriched fast expansion duct comprises gas turbine engine transition duct and conical plasma generator to generate comical plasma along duct outer wall. Said transition duct has inlet and outlet downstream of duct inlet, duct conical radially inner and outer walls arranged in axil direction between duct inlet and outlet. |
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Blade of gas turbine engine, and high pressure turbine and gas turbine engine, which contain it Blade (10), mostly of high pressure turbine of gas turbine engine, includes ribs (50) formed on inner side near rear edge (42). On larger part of rear edge, in zones in which the operating temperature of blades is especially increased, ends of ribs near rear edge are arranged closer to rear edge and/or section of ribs has larger surface area. Grooves (60) are formed between in-series located ribs (50). Air injection holes (41) are made in those grooves. |
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Stator of turbine plant includes casing, stage of guide vanes with adjustable setting angles, actuating rim and a guide. Guide vanes are moved by means of the actuating rim installed on outer side of casing and connected to vanes by means of rods. Guide projects above external surface of casing and is rigidly fixed on the latter. Three blocks of rollers to move along the guide are located in circumferential direction of rim at equal distances from each other. Each block of rollers is connected to rim so that each block of rollers is directed radially relative to the rim. Each block of rollers includes at least two rollers interacting with the guide, and each roller is installed on radial axis installed immediately on the rim. Other inventions of the group refer to compressor and turbine plant, which contain the above stator. |
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Gas turbine engine blade assembly and gas turbine stator with said assembly Turbine blade assembly comprises cases of low- and high-pressure sides with front edge, rear edge and convex or concave surface there between to form radial outer and inner edges as well as radial inner and outer deck. Every case has inner and outer flanges extending from outer and inner edges, respectively. Radial inner deck comprises multiple lengthwise grooves to receive radial inner flanges of cases of low- and high-pressure sides. Radial outer deck comprises multiple lengthwise grooves to receive radial outer flanges of cases of low- and high-pressure sides. Another invention relates to gas turbine stator comprising blade assembly and radial inner and outer decks. Blade assembly comprises blade, radial inner and outer face plugs and clamping element arranged there between. Blade extends radially between said plugs and comprises cases of low- and high-pressure sides. Clamping element supports cases of low- and high-pressure sides in definite relative orientation and relative to inner and outer face plugs. Radial inner deck comprises lengthwise groove to accommodate radial inner face plug while radial outer deck comprises lengthwise groove to receive radial outer plug. |
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Sleeve of blade hinge with adjustable setting angle, which is installed into the cavity in turbomachine ring, includes tubular housing around longitudinal axis and devices preventing the rotation in the ring cavity. Tubular housing of sleeve has the first conical annular projection located on one of its ends and the other conical annular projection located on the opposite end. Conical surfaces formed with the first and the second annular projections face each other. Devices preventing the sleeve rotation in the ring cavity include the plate having at least one surface for establishment of flat contact with the corresponding surface of the plate for prevention of rotation of the neighbouring sleeve. One more invention of the group refers to turbomachine ring containing multiple cavities to arrange the hinge and multiple sleeves made as described above. Other inventions of the group refer to turbomachine compressor and turbomachine, each of which includes at least one of the above said rings. |
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Stator blade of gas turbine engine with adjustable setting angle, and gas turbine engine Stator blade of gas turbine engine with adjustable setting angle includes blade continued on one side with turning support by means of which it is installed with possibility of being rotated in the hole of case of gas turbine engine, and platform. Platform is provided between blade and turning support perpendicular to the direction formed with blade and turning support. The platform plane lying opposite to the blade includes the first and the second zones; at that, the first zone is subject to intense friction with wall of case due to transverse forces applied to the blade, and thickness of platform in the second zone has been decreased in comparison to thickness of platform in the first zone. The other invention of the group refers to gas turbine engine containing at least one above described stator blade. |
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Device for attachment of guide vanes of turbine, turbine and aircraft engine with such equipment Device for attachment of guide vanes of turbine, which is fixed on support that in its turn is installed on stabilising part, contains slot connection devices for connection to slot of the support edge with stabilising edge of stabilising part, retention part for retention in slot of support edge and stabilising edge and retention devices for prevention of relative rotation of support edge and stabilising edge. Retention devices include at least one groove having semispherical shape in its section and made on plane of support edge, and at least one groove having semispherical shape in its section and made on plane of stabilising edge. Grooves are arranged one opposite another and form retention hole at installation of both edges into the slot. The other invention of the group refers to turbine containing the above device for attachment of guide vanes. One more invention refers to aircraft engine containing the above turbine and/or the above device for attachment of guide vanes. |
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Guide unit for air flow at inlet of combustion chamber of gas turbine engine Straightening unit includes two coaxial shells between which the blades passing mainly in radial direction are arranged. Diffuser includes two coaxial walls representing rotation bodies and connected to each other by means of radial partitions. One of the shells of straightening unit is made in the form of single part with one wall of diffuser, which represents rotation body. The other shell of straightening unit is connected to and fixed on the other diffuser wall representing rotation body. Blades of strengthening unit are rigidly connected through one end to one shell of straightening unit and are located at some distance with a small gap from the other shell on the other end. |
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Here is disclosed device for fixation of stationary blade in circular carter of fan of turbo-machine, wherein blade consists of head formed with platform with front and back ends, blade body and blade root. The circular carter has a circular slot made in its internal wall and front and back boards. The back board of the circular slot is made in form of a groove with and axial orifice directed forward, while a back end of the platform is inserted into the said back board. The blade has a section of the platform between the blade root and the front end containing a through hole wherein there is installed a fastener holding the platform in the circular slot. Another invention of the group refers to two-circuit turbo-reactive engine with a front fan containing a set of stationary blades forming a straightener blade at output of a rotor of the fan wherein the blades are maintained inside the carter by means of the above said device. One more invention of the group refers to the procedure of assembly of the stationary blade of the above said turbo-reactive engine consisting in installation of the blade root in the orifice of the carter of the primary circuit, in inclining the blade for insertion of the back end of the platform into the back groove of the circular slot and in turning the blade around the groove inserting the front end of the platform into a circular slot. Further, the platform is secured on the carter by means of fasteners. |
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Active turbine nozzle assembly Proposed nozzle assembly comprises nozzle including acceleration section and outlet section wherein nozzle outlet section on skew edge plane has mean flexure radius equal to mean radius of turbine wheel cascade. Nozzle acceleration section is made up of axially symmetric nozzle and curved widening channel. Channel width is constant and equals the diameter of axially symmetric nozzle outlet section. Channel height smoothly increases from axially symmetric nozzle outlet section to maximum value at outlet section of nozzle assembly. Axially symmetric nozzle axis is directed along tangent to a circle of the mean curvature radius of said widening channel. Axially symmetric nozzle section does not exceed the height of turbine cascade vane height. Surface of widening channel is formed by two cylindrical coaxial surfaces with mean radii of curvature equal to mean radius of nozzle outlet section on skew edge plane, and two sesquilinear surfaces conjugated therewith, diameter of said surfaces being equal to that of axially symmetric nozzle outlet section. |
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Control system of stages of rotating blades of stator of compressor of gas turbine engine Control system of stages of rotating blades of stator of compressor of gas turbine engine includes drive shaft including driving arm connected through a rod to power cylinder of control mechanism, and the arm connected through a rod to sensor of setting angle of rotating blades. Driving arm includes outer and inner arms connected at two points by means of the first and the second fasteners. Inner arm has the possibility of being rotated relative to the second fixture in case of damage of the first fixture. Rods of power cylinder and sensor have the possibility of being moved in parallel planes, and sensor is directly connected to automatic control system of gas turbine engine. |
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Adjustment device of alignment of control ring of rotating blades of gas-turbine engine relative to cylindrical casing of crankcase includes control ring containing multiple threaded holes made in radial direction and multiple holders of blocks, each of which includes threaded bar screwed into one of threaded holes of the ring. On inner end of each block holder there installed is the block intended to come into contact with cylindrical casing. In addition, control ring includes multiple slots having tangential direction and passing through the ring in radial direction. Each slot is interconnected with one of threaded holes of the ring. Device has also compression means of each of the slots in longitudinal direction in order to lock the position of block holders. Other invention of the group refers to gas-turbine engine containing the above adjustment device of alignment of control ring of rotating blades. |
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Blade with variable setting angle for compressor of gas-turbine engine includes sleeve installed with possibility of rotation around guide roller of blade and intended for installation into housing of turbo machine. Connection between sleeve and guide roller is performed by a pair of nickel graphite/titanium; at that, guide roller consists of material on the basis of titanium, and sleeve is made from material on the basis of nickel and graphite. Sleeve has been made by agglomeration of powder on the basis of nickel and graphite. Other inventions of the group refer to gas-turbine engine and its compressor including the above blades with variable setting angle. |
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Procedure for fabrication of blade of guiding mechanism of steam turbine Procedure for fabricating blade of guiding mechanism of stem turbine consists in connection of padding with blade body by means of contact weld and electron-beam weld. The padding is connected with the blade body by contact welding at the exit edge of the blade, while slit channels are arranged between sections of contact welding along the exit edge of the blade. |
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Stator blade with alternate angle of assembly installed in case of gas-turbine motor consists of blade body, of platform, of fulcrum pin, of piece with disk and of at least one stop tongue. The disk of the piece with its one side is positioned on the platform and with its another side rests on a wall of the case directly or by means of a bushing. The piece is stationary in rotation relative to axis of the fulcrum pin. Each stop tongue is rigidly tied with the disk and interacts with a complementary surface corresponding to a flat made on the platform. The fulcrum pin consists of a ring-like yoke forming a bearing; in the disk of the piece there is made the central orifice large enough to ensure piece passing along the fulcrum pin. Another invention of the group refers to the gas-turbine motor containing at least a row of stator blades with alternate angle of assembly; the blades are installed in the case and are equipped with the above said piece interacting with a bushing positioned in a seat of the case. One more invention refers to the procedure for repair of the blade with alternate angle of assembly, platform of which has a worn part caused by friction with installed bushing. The procedure consists in mechanical treatment of this worn out part of the platform and in adding a piece to form the above said blade. |
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Jacket contains stationary coaxial circular rail projecting from external surface of this jacket. Also, at least three movable parts spaced one from another in circumferential direction can travel along this rail. Each movable part is connected with the driven ring by means of a radial guiding structure. For each movable part the radial guiding structure contains an element in form of a rod installed in radial direction into an orifice made in the said ring. The rod-shaped element is secured on the movable part. Another invention of the group refers to a compressor equipped with at least one above said row of the blades of the straightening device with alternate angles of assembly. One more invention refers to the gas-turbine motor incorporating the said compressor. |
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Bush for blade hinge with adjustable mounting angle for turbomachine installed in hole of turbomachine ring represents tubular frame with longitudinal axis and comprises at least three ribs. Shape of hole in turbomachine ring matches shape of bush, and ribs protrude along radius outside relative to longitudinal axis of tubular frame, pass along axis by its full height and are evenly distributed along its peripheral surface. Each rib of bush is arranged in the form of tubular rib, having substantially oval cross section. Other invention of group relates to ring of turbomachine having multiple holes, every of which is intended for location of guide hinge of blade with adjustable mounting angle, and multiple above specified bushes. Another two inventions relate to compressor of turbomachine and turbomachine, comprising at least one above specified ring. |
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Turbojet engine crankcase sheathing and turbojet engine Turbojet engine crankcase sheathing comprises two coaxial shells arranged one inside the other and rigidly jointed together by radial jackets that accommodate crankcase radial ducts. Sheathing inner shell lower edge is secured on crankcase element and rests axially on the other crankcase element by its upper edge. Sheathing, in free state, features axial size smaller than axial distance between attachment points of lower edge of inner shell and points of axial support of case of outer shell upper edge, when it is secured on crankcase. Another invention of proposed set relates to turbojet engine comprising above described crankcase sheathing. |
Another patent 2551293.