Steam-turbine engine low-pressure stage working blade |
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IPC classes for russian patent Steam-turbine engine low-pressure stage working blade (RU 2515582):
     
 Steam-turbine engine low-pressure stage working blade / 2506430
Steam-turbine working blade 20 comprises aerodynamic part 42 with root part 44 attached to one end of the latter. Shank 40 with slot lock and skewed axial inlet extends from root part 44. End part 46 is attached to aerodynamic part 42, opposite the root part 44. Band 48 is made integral with end part 46. Band 48 has first flat part 52, second flat part 54 and recess 56 arranged laterally between said first and second flat parts. Recess 56 is located below first flat part 52 at first end whereat first flat part and recess 56 adjoin and ups to second flat part 54 at second end whereat second flat part and recess adjoin. Second flat part 54 is elevated above first flat part 52. Band 48 is located at 10 to 30 degrees relative to end part 46.
 System to prevent wear of tip airfoil shroud platform of turbine blade / 2456460
System to prevent wear of the tip airfoil shroud platform of the turbine blade comprises a turbine blade slot formed on the surface of the tip airfoil shroud platforms, and a rigid tube, mounted in the slot and has a durable outer surface. The tip airfoil shroud platform contacts the neighbour tip airfoil shroud platform when the turbine works at the contact surface. The contact surface has an interface that has a profile in the form of letter "Z". The tip airfoil shroud platform urther comprises a cut-off tooth, forming a ledge that runs along the middle of the upper surface of the tip airfoil shroud platform. The interface includes the middle surface of contact corresponding to the middle section of the profile in the form of letter "Z". The middle surface of contact has a substantially rectangular shape which substantially corresponds to the form of cross-section of a shearing tooth.
 Turbo machine wheel / 2433278
Turbo machine wheel comprises disk made integral with vanes, and damping elements. Flanges are made on edges of every vane. Damping element is arranged in gap provided between flanges of adjacent vanes. Damping element is made up of roll of micro wire mesh soldered to said flanges.
 Turbine wheel / 2433277
Turbine wheel comprises vanes made integral therewith and having flanges on its edges, as well as damping elements. Vane flanges are arranged in zone of vane outer edges. Damping element is made up of plate secured to lower surface of one of flanges of each vane. Flexible plate has free end arranged behind the plate of adjacent vane.
 Procedure for assembly of multitude of turbine wheel blades (versions) and also unit of turbine wheel and blades / 2399772
Procedure for assembly of multitude of blades on turbine wheel consists in preliminary twisting band and aerodynamic profile of each blade in response to tangential assembly force applied to tight fit contact surfaces of bands. Thereby rotary set off is transmitted to aerodynamic profile facilitating successive turn of aerodynamic profile into a final unit with edges of neighbour blades bought in contact one with another and with surfaces of dove tail of neighbour blades into contact one with another. In another version of assembly of multitude of turbine wheel blades there is made a lug on the band of each blade whereupon a removable clamp is secured on each lug of the band of each blade. The clamp and lug of corresponding neighbour blades have mainly complementary surfaces inclined at acute angle relative to tangential direction. Further, for preliminary twisting the band and aerodynamic profile of the blade there is wedged the clamp on the band of each blade positioned opposite to inclined surface of the lug on the band of the neighbour blade, which preliminary has been installed on the rim of the turbine wheel. Another invention of the group refers to a unit of turbine wheel and blades consisting of multitude of blades, of the lug positioned on the band of each blade, and of the removable clamp secured to each lug and equipped with a projecting part in tangential direction overlapping a part of the preliminary assembled lug of the turbine wheel blade. Neighbour bands have tightly fit contact surfaces. At least one lug and projecting part of the clamp have inclined surface in contact with another lug and projecting part of the clamp for preliminary twisting the assembled band and aerodynamic profile.
 Impeller of rotary flow machine and aircraft engine / 2380545
Impeller of rotary flow machine comprises rotor and ring. The former accommodates blades extending radially therefrom and having root parts attached to the rotor and ends. Aforesaid ring is arranged concentrically to rotor to cover blade ends so that the ring and blades are overlapped if seen in radial direction. With rotor running, ring is driven by blades. Blade radial size and ring ID are selected so that there is a clearance between blade ends and ring in radial direction with rotor dead. Impeller is designed to allow, at a certain rpm, an interaction between blades and ring to transfer a portion of or all force from blades to rotor when the ring revolves. Another invention of the set covers aircraft engine incorporating above described impeller.
 Turbine rotor, device and method to produce it / 2375589
Turbine rotor comprises one or several rows of blades with root, airfoil portion and shroud shelf. The latter and root feature rhomboid shape. Shroud shelves of one row of blades make closed ring and, along rotor circumference, exceeds theoretical index pitch required, for shroud shelves to make said closed ring, by allowance value. Shroud shelf rhomboid sides oriented along rotor circumference are arranged at 90° to rotor lengthwise axis, minus angle of twist. Every blade of one row is arranged with shroud shelves and airfoil sections twisted along blade lengthwise angle at 90° to rotor lengthwise axis. Other invention of the set relates to method of producing turbine rotor that comprises fabricating blades with rhomboid shroud shelves. Rhomboid sides that pass along rotor circumference are arranged at 90° to rotor lengthwise axis, minus angle of twist. Every blade fitted into the slot, its shroud shelves and airfoil sections twisted along blade lengthwise angle at 90° to rotor lengthwise axis. Twisting force is exerted on shroud shelves with form closure and maintained unless the last blade on the row is fitted in its place. One more invention of the set relates to appliance intended for fabricating turbine rotor and comprising a clip with two walls to limit lengthwise slot and to embrace shroud shelves of two adjacent blades at their centers. One of said two walls, right across said lengthwise slot, has two inner-thread holes receiving coupling screw to be fitted opposite one of shroud shelves.
 Turbine blade end retaining element / 2351769
Turbine blade end retaining element comprises a base attached to the turbine blade. The said base incorporates Z-like recesses, sealing rails arranged on the base and cavities made in the base and abutting on the said sealing rails and Z-like recesses. The said cavities make a flexible contact surface on the turbine blades interfaces to allow a uniform load distribution between two blades.
 Steam or gas turbine rotor / 2347913
Proposed rotor of the steam or gas turbine comprises the blades arranged in several radial rows and made up of blade root fitted into the rotor, blade operating surface and rotary shroud. Open cuts are made in inclined surfaces of the aforesaid blade row shrouds. The cuts of adjacent shrouds form, in fact, a closed hollow space expanding radially along the rotor, first, to the maximum cross section and, then, narrows again. In every hollow space, a pin is fitted to move free. Note that the said pin maximum cross section is smaller than that of the hollow space and exceeds its minimum cross section. The said hollow space features a drop-like shape narrowing wedge-like from the maximum cross section. The angle at the wedge apex, formed by the inner surfaces of the hollows space cuts exceeds that at which the pin self-deceleration in the hollow space occurs.
 Turbine blade and gas turbine with this blade / 2332575
Turbine blade incorporates an edge and a platform arranged along the blade axis, the said platform being made on the blade edge base and crossing the blade axis. The platform is formed by the first spring-flexible sheet part fitting partially tightly on the thrust block furnished on the blade edge. The aforesaid part fits tightly on the following thrust block arranged on the adjacent turbine blade. The second invention of the set covers the gas turbine incorporating a flowing channel arranged along its axis and furnished with annular crosswise section for working medium and a second blades rim arranged after the first one along the turbine axis. The aforesaid rim incorporates a set of circular turbine blades entering radially the turbine blade flowing channel protected by this invention.
 Turbine assembly of turbo-pump unit / 2511964
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.
 Turbo-pump unit, and cold, hot and industrial water pumping method / 2511963
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.
 Gas turbine cermet blade / 2510463
Cermet blade has shaped ceramic shell and drive rod with inner and outer flanges arranged there inside. Said drive rod has flexible pins inclined to drive rod inner flange and staying in contact with inner surface of shaped ceramic shell to ensure stability of said shell and to damp its vibration. Plate spring is arranged between drive rod inner flange and lower thrust flange of said shell to compensate for shaped shell thermal expansion. To up reliability, detachable drive rod outer shell abuts, without clearance, on upper thrust flange of shaped ceramic shell and is secured to rod outer radius.
 Single-crystal turbine blade, turbomachine module and turbomachine / 2498082
Single-crystal blade of turbine impeller is manufactured by casting with directionally crystallisation and comprises a blade airfoil, an end structural component of the blade airfoil and a transition zone. The blade airfoil consists of leading and back edges, sides of C-tray and C-back, centre line and longitudinal axis. The end structural element of the blade airfoil comprises the end side of the blade airfoil on the side of the gas-air path with the end side forming an angle to the longitudinal axis of the blade airfoil. The transition zone is located between the blade airfoil and the end side of the blade airfoil and provides for the blade airfoil bulb. The transition zone stretches around the leading edge between the point placed at the blade airfoil back and at the end side of the above end structural element upstream in relation to the C-back and the point placed at the blade airfoil tray and at the end side of the above end structural element upstream in relation to the C-tray. Other inventions of the group relate to a turbomachine module and a turbomachine comprising the above mentioned blades.
 Blade with asymmetrical platform, rotor blade wheel, turbomachine and turbomachine nozzle diaphragm section / 2498081
Blade (10) for turbomachine rotor blade wheel comprises an aerofoil section and at least one platform on the end of the aerofoil. The blade (10) is made so that to be set together with many other essentially similar blades so as to form a ring. The platform surface is fitted by profile (80) on the suction surface side and by profile (85) on the pressure surface side, respectively along the suction surface or pressure surface. The suction surface profile (85) of the blade has a recessed section (I) of the pressure surface located in the axial direction in the upstream half of the aerofoil section. Most of the surface between the aerofoil profiles is provided by the movement of a linear segment based on the profiles (80, 85) of suction surface and pressure surface.
 Blower guide vane made of 3d composite / 2497674
Invention relates to production of turbine blower guide vane of composite material. Proposed method comprises making of fiber preform by 3D weaving of one part. Said preform comprises first part extending in one lengthwise axis to make preform for vane airfoil and second part located and lengthwise end forming the preform for vane support. Second part consists of first layer and second layer facing the latter and separated therefrom by separation without cutting in making of preform. Proposed method comprises bending said first and second layers so that each of them is located in plane perpendicular to lengthwise axis, in fact, in symmetry about each other relative to said first part so that firs layer first section overlaps second layer second section ahead of first part edge. This method comprises jointing the preform with the mould to compact the former by polymer female die.
 Blade for turbomachine impeller, area of turbomachine nozzle block, impeller and turbomachine / 2496986
Blade of a turbomachine impeller comprises an aerofoil section with a trough, a back, rear and front edges, and also a shelf stretching from one of ends of the aerofoil perpendicularly to its longitudinal direction. The blade together with many identical blades forms a ring. Aerofoil sections of the ring are installed radially. Adjacent shelves of the blades are combined in pairs to form a continuous surface between their aerofoil sections, connecting the trough of the aerofoil section with the back of the adjacent aerofoil section. The specified surface in the upper half of the aerofoil section along the flow comprises a ledge located closer to the trough than to the back and a sunk channel arranged between it and the trough. The ledge is separated from the trough by means of the specified sunk channel. Other inventions of the group relate to the area of the turbomachine nozzle block and to the impeller comprising the above blades. Another invention relates to a turbomachine comprising the specified impeller.
 Impeller blade of compressor with variable elliptical connection / 2495254
Impeller of turbomachine centrifugal compressor has at least one blade (24) connected to hub (26) of the impeller by means of fillet (27). Blade is continued along a chord formed between front edge (28) and rear edge of the blade. Fillet (27) has the shape that changes continuously along the chord. Fillet (27) represents section (P) of ellipse (E1). Fillet (27) is subject to the change by means of continuous change of lengths of ellipse axes.
 Compressor wheel with lightweight blades / 2494262
Compressor wheel with lightweight blades includes a disk and lightweight blades welded to it. A lightweight blade consists of two parts connected to each other by welding. In each part of the blade there made are cavities so that adjacent cavities form ribs with the apexes of which both parts of the blade are connected to each other in root area. Ribs in root area of the blade are oriented mainly radially in relation to the rotation axis. In middle and peripheral zones the ribs are bent so that ribs of one part of the blade intersect ribs of the other part of the blade, thus being connected to each other along contact platforms. Selection of geometrical dimensions, quantity and direction of ribs, quantity, shape and location of contact platforms is performed based on conditions of static and dynamic loading of blades and the wheel of the compressor.
 Two-bladed vane with plates, turbine wheel and gas turbine engine comprising such vanes / 2492330
Gas turbine engine vane comprises the first blade, the second blade and at least one plate. Each of the first and second blade has inner and outer sides placed between the front and rear edges. The first and second blades are arranged near in such a manner that the inner side of the first blade is placed with its entire surface opposite to the inner side of the second blade. The plane connects the inner side of the first blade and the inner side of the second blade and is placed to the rear edge of the vane. The rear edge of the vane is formed with the rear edge of the first blade and the rear edge of the second blade. The rear edge of the first blade is levelled relative to the rear edge of the second blade and is arranged near. Other inventions of the group relate to a turbine wheel and a gas turbine engine, comprising the above vanes.
 Axial-flow turbine stage and multi-stage turbine / 2256081
Multi-stage turbine and axial-flow turbine stage comprise working wheels that rotate in the opposite directions, are arranged on individual shafts, and have blade cascades on the intermediate diameter, which terns the fluid flow at the angle ΔβCA = 180° - (β1I + β2EFF), where β1I is the blade cascade inlet angle, β2EFF is the effective angle of the blade cascade output. The blade cascade of the first upstream working wheel turns the fluid not more than by 15°. Between the wheels, power is transmitted via a reduction gear. Between the shafts and the common shaft, power is transmitted through a conical reduction gear.
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FIELD: engines and pumps. SUBSTANCE: steam turbine (10) working blade (20) comprises airfoil section (42). Blade butt section (44) is secured to one end of airfoil section (42). Dovetail part (40) extends from butt section (44) and includes skewed part (40) with axial twist that features skew angle equal to 19 degrees. Rim section (46) is attached to airfoil section (42) at the end opposite the butt section (44). Airfoil shroud platform (48) is made integral with rim section part (46). Airfoil shroud platform (50) is secured to airfoil section (42) mid part between airfoil ends. Working blade (20) features outlet circular cross-section making about 4.43 m2 or larger. Airfoil section (42) features length making about 68.1 cm or larger. EFFECT: optimum aerodynamics and mechanical characteristics. 9 cl, 7 dwg
The level of technology The present invention, in General, refers to the working blade of a steam turbine, and more specifically to a working blade optimized form, suitable for operation at high operating speeds for use in the last stage of the section of the low pressure steam turbine. Flowing a portion of the steam turbine for the passage of the steam flow, in General, formed by the stationary casing and the rotor. In such a turbine many fixed blades fixed in the housing at the periphery and passes inside the turbine passage section for the passage of the steam flow. Similarly, many of rotor blades attached to the rotor at the periphery and passes out in the flow-through portion of the turbine for flow of steam. The stationary vanes and rotor blades are arranged in alternating rows so that the number of stationary blades and a number of blades, located directly downstream, form a step. The stationary vanes serve to direct the steam flow so that it passes between the rotor blades located downstream of a number under the proper angle. The airfoil blades extract energy from the steam, thereby producing the energy necessary to actuate the rotor and the load associated with it. With the passage p. the current of steam through the steam turbine, its pressure drops after each subsequent stage until until it reaches the desired outlet pressure. Thus, the steam parameters, such as temperature, pressure, speed, and moisture content will vary from row to row as steam expansion in the turbine passage section for the passage of the steam flow. Therefore, in each row of rotor blades using the blade having the shape of an aerodynamic surface that is optimized in accordance with the steam parameters affecting the number of blades. Rotor blades (see, for example, the patent of the Russian Federation 2264541, IPC F01D 5/26, 20.11.2005) design, also taking into account, in addition to steam, centrifugal load, perceived by the blades during operation. In particular, the large centrifugal loads acting on the rotor blades due to high speed rotation of the rotor, which leads, in turn, to the appearance of stresses in the rotor blades. The problem of design of rotor blades is to reduce the concentration of stresses in them, especially in the back section of the low pressure steam turbine where the blades are large and more weight due to the large size and subjected to the voltage associated with corrosion due to moisture present in the steam flow. This problem associated with the design of rotor blades for the section of the low pressure turbine, is exacerbated in the result is in the shape of the airfoil blades, in General, are defined: the forces acting on the rotor blades; their mechanical strength; resonant frequency and thermodynamic characteristics. The consideration of these factors leads to restrictions when choosing the shape of the airfoil blades. Thus, the optimum shape of the airfoil blades for the given number is a matter of compromise between the mechanical and aerodynamic parameters associated with the form. Disclosure of inventions According to one aspect of the present invention proposed blade of a steam turbine that contains the plot of the aerodynamic surface, the section of the shank, attached to one end area of the aerodynamic surface section in the form of a swallow's tail, protruding from the shank section, and the section in the dovetail includes a beveled portion in the form of a dovetail with axial winding having a bevel angle of around 19°, the section of the crown attached to the plot of the aerodynamic surface on the end opposite the section of the shank, the retaining shelf, made in one piece as part of a section of the crown, shelf, attached to the intermediate section of the site aerodynamic the surface between its ends, with lop the TKA has an output under the square component 4,43 m2or more. The plot of the aerodynamic surface preferably has a length, which is about to 68.1 cm or more. Banding shelf preferably has a flat section extending from the leading edge area of the aerodynamic surface at a specified distance from it to the rear edge section of the aerodynamic surface, while retaining the shelf has a width decreasing, essentially, from the end located at a specified distance from the front edge to the place that is located essentially in the center of the back edge and front edge, with the width of the retaining shelf increases from the center to the trailing edge, and the width of the retaining shelves at the end located at a specified distance from the front edge, and the width of the retaining shelf at the rear edges are essentially the same. The blade preferably further comprises sealing the teeth, protruding upward from the retaining shelf, thus sealing the tooth passes from the end located at a specified distance from the front edge, essentially through the center to the trailing edge. Banding regiment preferably passes through the suction side of the plot aerodynamic surface at the end located at a given distance from the leading edge to approximately the center, and through the store is well injection site aerodynamic surface from the center to the rear edge. According to another aspect of the present invention proposed section low-pressure steam turbine, containing a number of rotor blades of the last stage of a steam turbine arranged around the impeller of the turbine, each of the multiple blades of the last stage of a steam turbine contains a plot of the aerodynamic surface having a length, comprising about 68,1 cm or more, the section of the shank, attached to one end area of the aerodynamic surface section in the form of a swallow's tail, protruding from the shank section, and the section in the dovetail includes a beveled portion in the form of a dovetail with axial winding having a bevel angle of around 19°, the section of the crown attached to the plot of the aerodynamic surface on the end opposite the section of the shank, the retaining shelf, made in one piece as part of a section of the crown, shelf, attached to the intermediate section of the site aerodynamic surface between its ends, and many blades of the last stage of a steam turbine has an output under the area constituting about 4,43 m2or more. Many of rotor blades of the last stage of the steam turbine is preferably configured to actuate at a speed component from approximately the 1500 rpm to about 3600 rpm Banding shelves set of rotor blades of the last stage of the steam turbine is preferably installed with a nominal gap between adjacent shroud shelves. The shelves of each of the multiple blades of the last stage of a steam turbine is preferably made so that you have a gap between them, which is closed when the number of blades of the last stage of a steam turbine of a given operating speed. Brief description of drawings Figure 1 is a perspective view in partial section of a steam turbine; Figure 2 is a perspective view of the working blades of a steam turbine according to one variant of implementation of the present invention; Figure 3 is a perspective view, on an enlarged scale of a part in the dovetail with axial winding, shown in the working blade is presented in figure 2, according to one variant of implementation of the present invention; Figure 4 is a perspective view of the retaining shelves used in the working blade is presented in figure 2, according to one variant of implementation of the present invention; Figure 5 is a perspective view, which shows the relative location of adjacent shroud shelves according to one variant of implementation of the present invention; IG is a perspective view of the shelves, used with the working blade is presented in figure 2, according to one variant of implementation of the present invention; and Fig.7 is a perspective view, which shows the relative location of adjacent shelves according to one variant of implementation of the present invention. Detailed description of the invention The following describes at least one implementation of the present invention with reference to its use in the steam turbine during operation. In addition, the following describes at least one implementation of the present invention with reference to the nominal size, including a set of nominal sizes. However, specialists in the art it should be clear that, following the ideas described in this application, the present invention can similarly be applied in any appropriate turbine and/or engine. In addition, specialists in the art should understand that, guided by the ideas expressed in this application, the present invention can similarly be applied at different scales, starting from the nominal size and/or dimensions. Figure 1 shows a perspective view in partial section of a steam turbine 10. The steam turbine 10 includes a rotor 12, which includes a shaft 14, and multiple distributed in the axial is upravlenii wheels 18. To each of the impeller 18 is mechanically attached set of rotor blades 20. More specifically, blades 20 are in series, passing around the periphery of each impeller 18. Many stationary blades 22 passes around the periphery of the shaft 14, and they are arranged in the axial direction between adjacent rows of rotor blades 20. The stationary vanes 22 interact with the rotor blades 20 for forming stage of the turbine and education flow-through part of the turbine for the passage of the steam flow through the turbine 10. Steam turbine works in the following way: steam 24 is supplied to the inlet 26 of the turbine 10 and passes through the stationary vanes 22. The stationary vanes 22 are sent 24 pairs downstream to the working blade 20. Pairs 24 passing through the other stages, transmitting force to the working blades 20 and causing rotation of the shaft 14. At least one end of the turbine 10 can pass in the axial direction of the rotor 12 and may be attached to the load or equipment (not shown), for example, but not limited to, the generator and/or other turbine. Accordingly, a large block of a steam turbine may actually contain multiple turbines attached coaxially to the same shaft 14. Such a unit may, for example, contain a high-pressure turbine connected to the medium-pressure turbine, which is connected to the low-pressure turbine. In one embodiment of the present invention, is shown in figure 1, the turbine 10 includes five steps. Five steps indicated by the positions L0, L1, L2, L3 and L4. Level L4 is the first step and the smallest (in radial direction) of the five stages. The L3 stage is the second stage and the next stage in the axial direction. Step L2 is the third stage, and she is depicted in the middle among the five speed manual transmission. Level L1 is the fourth and penultimate stage. Level L0 is the last stage and the largest (in radial direction). It should be understood that the five steps shown only as one example, and the low pressure turbine may contain more or less than five degrees. Figure 2 shows a perspective view of the working blade 20 of the steam turbine according to one variant of implementation of the present invention. Blade 20 has side 30 and discharge side 32 of the suction, which are connected together at a leading edge 34 and trailing edge 36. The chord of the working blade is the distance measured from the rear edge 36 to the leading edge 34 at any point in the radial direction along the length 38 in the radial direction. In the example embodiment of the invention, the length 38 in the radial direction, or the length of the blade, approximately SOS is to place 68,1 see Although the length of the blades in the example embodiment, is approximately 68,1 cm, specialists in the art it should be clear that the ideas proposed in this application is applicable to various size nominal size. For example, a specialist in the art can multiply the size of the working blade 20 on scale factors, for example by 1.2 to 2.0 and 2.4, for the production of a working blade length 81,8 cm, to 136.4 cm and of 163.7 cm, respectively. The working blade 20 comply with part 40 in the form of a dovetail, section 42 of the aerodynamic surface and section 44 of the shank passing between them. Section 42 of the aerodynamic surfaces is divided in a radial direction outward from section 44 of the shank section 46 of the crown. Banding shelf 48 perform in one piece as part of the section 46 of the crown. The shelf 50 is attached to the intermediate section of the site 42 aerodynamic surface between the section 44 of the shank and section 46 of the crown. In the example embodiment of the invention, the part 40 in the form of a dovetail, section 42 of the aerodynamic surface section 44 of the shank, section 46 of the crown of the retaining shelf 48 and the shelf 50 perform for one of the 12% chromium stainless steel. In the example embodiment, and is gaining a working blade 20 attached to the impeller 18 (1) of the turbine through the part 40 in the form of a dovetail, and blade passes radially outward from the impeller 18. Figure 3 shows a perspective view, on an enlarged scale of part 40 in the form of a dovetail, as shown in the working blade is presented in figure 2, according to one variant of implementation of the present invention. In this embodiment, the portion 40 in the dovetail includes a beveled portion in the form of a dovetail with axial winding, a bevel angle of approximately 19°, and which is introduced into the mating groove made in the impeller 18 (1) of the turbine. In one embodiment, the beveled part of the dovetail with axial winding has a "trehrozhkovuju" form, containing six contact surfaces made with the possibility of interaction with the impeller 18 (1) of the turbine. The beveled part of the dovetail with axial winding is preferred to achieve a distribution of the average and local stresses; for protection during speeding, and adequate limits of low cycle fatigue (MCU); and for the accommodation of section 44 of the shank of the working blades. Figure 3 also shows that the part 40 in the form of a dovetail contains restraint in the axial direction of the hook 41, which prevent movement of the working blade 20 in the axial direction. Specialists in this the field of technology should be clear, that the beveled part of the dovetail with axial winding may contain more or less than three hooks. In addition to describing additional details of the part 40 in the form of a dovetail figure 3 in an enlarged scale shows the transition region, in which a portion 40 in the dovetail is from section 44 of the shank. In particular, figure 3 shows the radius 52 of the curves in the place in which section 44 of the shank enters the platform 54 part in the dovetail. In the example embodiment of the invention the radius 52 of the curves contains many radii through which made a smooth transition from section 42 of the airfoil to the platform 54. Figure 4 shows a perspective view of the section 46 of the crown and of the retaining shelf 48 according to one variant of implementation of the present invention. Banding shelf 48 increases rigidity and improves the damping characteristics of the working blade 20. On the outer surface of the retaining shelf 48 may be located o-prong 56. Sealing the tooth 56 acts as a sealing means for restricting the flow of steam for the outer part of the working blade 20. Sealing the teeth 56 may be in the form of one edge or can be formed from a variety of edges, set the TBA straight or angled teeth, or one or more teeth of various sizes (for example, in the form of a labyrinth type seal). Banding shelf 48 (figure 4) has a flat section extending from the leading edge 34 at a specified distance from it to the rear edge 36. Banding shelf 48 has a width essentially decreasing from the end located at a specified distance from the front edge 34, 58, located essentially in the center relative to the rear edge 36 and the front edge 34. The width of the retaining shelf 48 increases from the center 58 to the rear edge 36. The width of the retaining shelf 48 at the end located at a specified distance from the front edge 34, and the width of the retaining shelf 48 at the rear edges 36 are essentially the same. In addition, figure 4 shows that the o-prong 56 protrudes upward from the retaining shelf 48 and sealing the tooth 56 is held from the end located at a specified distance from the front edge 34, essentially through the center 58 to the rear edge 36. Figure 4 also shows that the banding shelf 48 passes through the side 32 of the suction at the end located at a specified distance from the front edge 34, approximately to the center 58, and through the side 30 of the discharge from the center 58 to the rear edge 36. Figure 5 shows a perspective view, which shows the relative location of adjacent shroud shelves 48 according to one VA is Ianto implementation of the present invention. In particular, figure 5 shows the banding shelves 48 during the initial installation. Banding shelves 48 carry out so that they had a gap 60 between adjacent shroud webs 48 during the initial installation and/or at zero speed. As shown in the drawing, the sealing teeth 56 are also slightly offset from each other at zero speed. During the rotation of the impeller 18 (1) of the turbine rotor blades 20 begin to unfold. As it approaches the speed of rotation of the blades 20 to the operating level rotor blades to spin under the action of centrifugal force, the gaps 60 are closed and the seal teeth 56 are aligned with each other so that a nominal gap between adjacent shroud shelves and blades 20 form one continuously connected design. The mutual connection of the retaining shelves provides increased rigidity of rotor blades, improved damping of the blades and improved seal at the outer radial regions of rotor blades 20. In the example embodiment of the invention the working speed of rotation of the blades 20 is 3600 rpm, however, specialists in the art it should be clear that the ideas suggested in donnezac, applicable to various scales from this nominal level. For example, a specialist in the art can multiply operation level speed scale factors, for example 1.2, 2.0 and 2.4GHz for the manufacture of rotor blades, which could be used when the rotation speeds of 3000 rpm, 1800 rpm and 1500 rpm, respectively. Figure 6 shows a perspective view of the shelves 50, used according to one variant of implementation of the present invention. Shelf 50 (6) are located on the side 30 and discharge side 32 of the suction of the working blade 20. In this embodiment of the invention, the shelves 50 are triangular in shape and protrude outward from the sides 30 and discharge from the side 32 of the suction. 7 shows a perspective view, which shows the relative location of adjacent shelves 50 according to one variant of implementation of the present invention. At zero speed of rotation between adjacent shelves 50 adjacent blades there is a gap 62. This gap 62 is closed when the impeller 18 (1) of the turbine starts to rotate when reaching the operating speed and swinging blades. The shelf 50 has an aerodynamic shape to reduce ventilation losses and improve overall efficiency. The stiffness of the blades and their damping characteristics also increases is raised by contact of the shelves 50 with each other when swinging blades. When swinging blades shroud shelves 48 and shelves 50 are in contact with their respective adjacent shelves. Many blades 20 behaves as one continuous coupled design, which has a high rigidity and superior damping characteristics compared to separate, not connected to the rotor blades. An additional advantage is that the blade 20 is experiencing reduced vibration voltage. The working blade according to aspects of the present invention is preferably used in the last stage or L0 section of the low pressure steam turbine. However, the working blade can also be used in other steps or other sections (for example, in sections of high or medium pressure). As mentioned above, one preferred length of the working blade 20 is about 68,1 see If the length of the working blades it can be output under the area of the last stage, which is about 4,43 m2. Due to this increased and improved output under the area it is possible to reduce the loss of kinetic energy arising from the release of steam from the last stage L0 blades. Due to lower losses provide an increased efficiency of the turbine. As noted above, specialists in the art should be PON the IDT, if the length of the working vanes scale, moving to a different length blades, then when this scaling is obtained from output under the square, which will also correspond to the chosen scale. For example, if you use a scale factor of 1.2, 2.0 and the 2.4 to obtain the length of the working blades, component 81,8 cm, to 136.4 cm and of 163.7 cm, respectively, will be obtained from output under the area, amounting to about 6.4 m2, 17.7 m2and 25.5 m2respectively. Although the invention has been specifically described and shown with reference to preferred implementation, specialists in the art will understand that can be made various changes and supplements of the invention. Thus, it should be understood that the appended claims cover all such changes and additions. 1. Blade (20) of a steam turbine, comprising: 2. The blade according to claim 1, in which area (42) of the aerodynamic surface has a length, which is about to 68.1 cm or more. 3. The blade according to claim 1, in which the retaining shelf (48) includes a flat section extending from the leading edge (34) of section (42) of the aerodynamic surface at a specified distance from it to the rear edge (36) of section (42) of the aerodynamic surface, while retaining shelf (48) has a width decreasing, essentially, from the end located at a given distance from the leading edge (34), located essentially in the center relative to the trailing edge (36) and leading edge (34), and the width banding shelves (48) increases from the center (58) to the trailing edge (36), and the width of the retaining shelves (48) at the end located at a given distance from the leading edge (34), and the width of the retaining shelves (48) at the trailing edge (36) are essentially the same. 4. The blade according to claim 3, additionally containing o zu the EC (56), protruding upward from the retaining shelves (48), thus sealing the tooth (56) runs from the end located at a given distance from the leading edge (34), essentially through the center (58) to the trailing edge (36). 5. The blade according to claim 3, in which the retaining shelf (48) passes through the side of (32) suction area (42) of the aerodynamic surface at the end located at a given distance from the leading edge (34), approximately to the center (58), and through the side of (30) discharge area (42) of the aerodynamic surface from the center (58) to the trailing edge (36). 6. Section low-pressure steam turbine (10), containing: 7. Section low-pressure according to claim 6, in which many blades (20) the last stage of a steam turbine configured to actuate at a speed component from about 1500 rpm to about 3600 rpm 8. Section low-pressure according to claim 6, in which the retaining shelves (48) sets of rotor blades (20) the last stage of the steam turbine is installed with a nominal gap (60) between adjacent shroud webs (48). 9. Section low-pressure according to claim 6, in which the shelves (50) of each of the sets of rotor blades (20) the last stage of the steam turbine is made so that you have clearance (62) between them, which closes when the set of rotor blades (20) the last stage of a steam turbine of a given operating speed.
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