Nozzle guide assembly of radial-flow turbine |
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IPC classes for russian patent Nozzle guide assembly of radial-flow turbine (RU 2306425):
    
 Steam turbine intake hole and method of its modification / 2302533
Pair of ports of intake hole is arranged at opposite sides of steam turbine casing to provide passing of steam in opposite directions along circumference in ring-shaped steam chamber to first stages of turbine through axial opposite outlet holes. Parts of chamber in upper and lower casings has cross sections decreasing in common direction along circumference from sections of intake hole for steam to provide uniform flow of steam relative to chamber in common inner direction and through axial outlet holes and near holes.
 Steam turbine flow path / 2296228
Invention is aimed at increasing economy of first non-controlled stages of steam turbines with nozzle steam distribution. According to invention flow path of known steam turbine containing nozzle box assembly accommodating nozzle blades, controlled stage working wheel, diaphragm of first non-controlled stage with fitted-in nozzle blades, working wheel and chamber formed between said wheel of controlled stage and diaphragm of first non-controlled stage is furnished with convex-concave screen installed before nozzle assembly of diaphragm provided with perforations, convex part being arranged opposite to nozzle assembly and pointed into chamber, and concave part is extended in radial direction towards rotor axis. Holes of perforation are of different size. Diameter of holes in part far from rotor axis is at least twice as small as diameter of holes located close to rotor axis.
 Turbine adjustable nozzle assembly / 2294439
Invention can be used in transport gas-turbine engines and turbocompressors of internal combustion engines. Proposed adjustable nozzle assembly of turbine has vanes with turnable axles arranged between housing. Turnable axles are sectional, being made of material with memorized shape effect. Iron and nickel-based alloys are used as memorized shape effect materials in which martensite transformation takes place at different temperatures.
 Gas turbine stator / 2278274
Proposed stator of gas turbine has housing with channel to pass gases, ring member arranged around stator housing at a distance in radial direction and functionally coupled with housing, and intermediate members holding ring member at a distance from stator housing in radial direction. Intermediate member are arranged over circumference of ring member at distance from each other and are provided with movable member. Said movable member thrusts against stator housing or ring member with possibility of displacement. At least one of intermediate members features elastic properties in direction of stator radius, and at least one other intermediate member has no such properties.
 Device to control position of blades with adjustable angle of setting / 2272913
Proposed device to control position of blades with adjustable angle of setting in turbomachine has tie-rod, mating devices, locking devices and means for holding said tie-rod on said root of blade for combined turning without play. Mating devices forming hinge joint between first end part of tie-rod and rotary ring are provided with pin passing through first through hole made in first end part of tie-rod and getting into radial socket in rotary ring. Said pin is held in position by locking with ports to pass pins and installed for displacement on rotary ring. Locking devices used to hold second end part of tie-rod on root of adjustable blade are provided with locking screw passing through second through hole made in second end part of tie-rod and getting into groove in root of adjustable blade.
 Axial-flow turbine stator blade / 2272151
Proposed blades of axial-flow turbine stator has channel expanding into cone to pass flow of gas through turbine. Blade is provided with flat at its root which is connected with stator housing with provision of tight fit and reliable locking of joint. Stator blade root is made in form of hollow profile with radially inner flat of blade root which is made to suit contour of channel to pass flow of gas through turbine and radially outer flat of blade root arranged at a distance inner flat from and made to suit contour of stator housing, and also side wall or two, mainly parallel, side walls. Outer flat is provided with at least one hole to accommodate corresponding attachment part by means of which said is secured on stator housing.
 Turbine nozzle box of gas-turbine engine / 2260700
Proposed nozzle box of turbine of gas-turbine engine has nozzle vanes with trunnions and ring projections. Inner ring with ring groove is fixed on inner flanges of nozzle vanes in which vane ring projection is fitted. One of flanges of inner ring is furnished with axially extended ring bead with radial slot in which trunnion of vane nozzle is arranged. Difference between distance from axis of bolt of fastening flange of inner ring and inner surface of ring projection of nozzle vane and distance between axis of bolt of fastening flange of inner ring and outer machined surface of nozzle vane trunnion is greater than zero.
 The cooled jet vane of a gas turbine / 2237811
 To allow the apparatus axial turbine / 2232902
The invention relates to low-flow turbines, which are widely used in power industry, shipbuilding
 Method of control centripetal turbine with vaneless guide assembly / 2298652
Invention relates to methods of control of centripetal turbine with vaneless guide assembly and it can be used in superchargers of internal combustion engines. Method is implemented by regulating discharge capacity of turbine by changing flow area of acceleration section of volute. Change of flow area of acceleration section of volute of vaneless guide assembly is provided by curvilinear translational movement of shaped element in direction of flow or counter direction of flow of gas getting into volute. Geometrical form, position and value of flow area of acceleration section of volute of vaneless guide assembly are determined by curvilinear translational movement of shaped element.
 Stator of compressor of gas-turbine engine / 2287064
Proposed stator of compressor of gas-turbine engine horizontally-split housing, turnable vanes of guide-vane assembly, control mechanism, lever secured on housing, and tie-rod. Control mechanism includes angular levers and rack, and tie-rod is adjustable in length. Turnable vanes of guide-vane assembly are installed in housing, are connected by levers with rings of drive and are connected through control mechanism to tie-rod hinge-connected to link of rack and short arm of additional lever. Long arm of additional lever is connected to hydraulic cylinder. Cross section of drive ring is H-section, and one of walls of drive rings is provided with slots to arranged ends of levers of turnable vanes. Sizes of slots are chosen to provide process clearance between each ring of drive and lever in process of assembling.
 Diffuser for control valve / 2272204
Control valve with diffuser comprises steam box with the side steam supply, lid, seat, valve, axle box, and rod. The diffuser is made of protecting ring shell mounted in the top section of the seat for permitting changing the direction of motion from the side steam flow direction to the direction along the axis of the valve and seat.
 Buchs control valve / 2218499
The invention relates to power engineering, in particular to the turbines, and represent one of the major parts of the distribution of steam turbine, designed to accommodate a spindle (stem) valve
 Control valve / 2183780
The invention relates to the field of power engineering and is intended for regulating the pressure of steam at the outlet of the turbine
 The control unit steam turbine / 2141565
The invention relates to paralegalism valve for steam turbines, containing situated in the housing of the valve insert is held in a sealing gasket of the valve spindle, sliding in the valve insert valve cone and located in the housing of the valve cone valve, and the hydraulic
 The control valve of a steam turbine / 2053372
The invention relates to a control device of a steam distribution turbines, and more specifically to the control valves of the steam turbine
 Combined locking-regulating valve / 2008440
The invention relates to the field of power engineering and can be used when designing the bodies of the steam distribution steam turbines, in particular turbines for nuclear, thermal or geothermal power stations
Diffuser for control valve / 2272204
Control valve with diffuser comprises steam box with the side steam supply, lid, seat, valve, axle box, and rod. The diffuser is made of protecting ring shell mounted in the top section of the seat for permitting changing the direction of motion from the side steam flow direction to the direction along the axis of the valve and seat.
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FIELD: mechanical engineering; radial-flow turbines. SUBSTANCE: proposed nozzle guide assembly of radial-flow turbine contains nozzle vanes, drive and adjusting device. Nozzle vanes are uniformly spaced around axle of turbine wheel and are installed by trunnions in turbine casing for adjustable turning in channel formed by walls of casing. Adjusting device is made in form of ring turn synchronizer engaging with nozzle vanes through guides secured on their trunnions. Each guide is made in form of bellcrank whose free ends are arranged in radial slots of turn synchronizer. Said turn synchronizer is made in form of two concentric disks, inner and outer ones, interconnected for relative turning, each disk being located by radial slots from free ends of bellcranks pointed to disk. EFFECT: increased accuracy of synchronous turning of vanes, reduced gas leakage in clearances along end faces of vanes, reduced wear of units caused by high-temperature dry friction. 5 cl, 2 dwg
The invention relates to the turbines and can be used in turbomachines, in the heat transport in gas-turbine engines, gas turbine systems of supercharged internal combustion engines, power plants with gas turbine fuel cell. Known for directing nozzle apparatus radial turbines, representing the number of nozzle vanes, spaced equally around the axis of the turbine wheel and installed their pins in the turbine housing with the possibility of an adjustable rotation in the plane perpendicular to the axis of the impeller in the channel formed by the walls of the casing, in which the rotation of the blades is effected by exposure to a drive device for swinging the levers (leashes), mounted on the pivots of the blades, and which contain an adjustment device, for example, in the form of an annular synchronizer rotation formed by rods, articulated among themselves and with the rocker arm (patent RU 2125164, 1999) or, for example, in the form of a synchronizing ring, radial grooves in contact with the free ends of the levers(patent EP 0226444, 1987). The large number of joints between the blades and adjusting-driving device in the first similar causes errors in the rotation of the guide blades nozzle apparatus (NSA), and, consequently, reducing the efficiency of the article the interest of the turbine. In the second similar hosting a synchronizing ring with the rollers on the turbine housing requires large gaps in a couple of "roller-synchronizing ring to prevent jamming of the synchronizing ring due to the differential thermal movement of the synchronizing ring and the casing of the turbine, especially in transient conditions. A large gap causes errors in the rotation of the blades (NSA), and, as a consequence, the reduction efficiency of a stage of the turbine, and the possibility of failure when jamming of the synchronizing ring. The closest analogue (prototype) of the proposed solution is a guide to allow the apparatus radial turbine, patent RU 32532, 2003, which contains a number of nozzle vanes evenly positioned around the axis of the impeller, turbine, and set the pins in the turbine housing with the possibility of an adjustable rotation in the channel formed by the walls of the housing and the drive unit and the adjusting device in the form of an annular synchronizer turn, interconnected with deployme blades through fixed on their pivots leashes (regulating blade), the free ends of which are located in radial slots of the timing disk. In the prototype to improve the control precision NSA blades made of composite, consisting of rolling and NEPAD is mportant elements, articulated between an arc of a circle - this complicates the manufacture of the NSA. However, sufficient for improving the efficiency of a stage of the turbine level of control accuracy in the prototype is not ensured due based synchronization disk slidable in the recess of the housing of the turbine and consequently the dependence of the gap between them from thermal deformation of the turbine casing. The task implemented by the invention, aimed at the creation of the NSA, whose thermal deformation of the casing of the turbine does not affect the accuracy of regulation of the NSA-stage radial turbine, providing increased efficiency stage of the turbine, and improve reliability and long-term performance. The technical result to be obtained from use of the invention is to increase the accuracy of the synchronous rotation of the blades, reducing the flow of gas into the gaps on the ends of the rotary blades and the decrease in the intensity of wear from high temperature dry friction. To achieve a technical result in the pilot nozzle apparatus of the radial turbine containing the nozzle vanes are evenly positioned around the axis of the impeller, turbine, and set the pins in the turbine housing can be rotated in the channel formed by the walls of the casing, driving device and the adjusting device is on, in the form of an annular synchronizer turn, interconnected with deployme blades through fixed on their pivots leashes, the free ends of which are located in radial slots of the synchronizer, in contrast to known analogs each of these leashes made in the form of two shoulders arm, - synchronizer rotation is made in the form of two concentric disks: internal and external, linked with the possibility of mutual reversal, each of which is radial slots, addressed to him free ends of the levers. Additional differences are that: between facing each other with the surfaces of disks synchronizer placed at least three elements in the form of rolling elements such as rollers or balls; - forming the channel wall of the housing at the location to allow the blades are made with the possibility of axial displacement, for example spring-loaded in the direction of the blades; - jet blade interconnected with a movable wall of the housing through a bearing, and on the opposite wall through the bearing. The hosting disk synchronizer on the free ends of the two shoulders of the levers at different thermal deformation of the turbine casing and disks by moving the ends of the levers in the radial grooves of both drives is demonstrated to improve the accuracy of the synchronous rotation of the blades and increases the efficiency stage of the turbine, and keep working with the misalignment of the parts NSA and the turbine casing at transient conditions at various temperature deformations of parts of the NSA. Tucked up a wall, forming a channel at the location to allow the blades, providing a constant gap, not dependent thermal deformation of the turbine housing, which increases the efficiency stage of the turbine. The invention is illustrated by drawings, where figure 1 gives a General view of the NSA (cut), figure 2 - section a-a in figure 1. In the turbine housing 1 in channel 2 formed by the walls 3 and 4, placed evenly around the axis 5 of the impeller 6 nozzle vanes 7 installed its pins 8 in the housing 1 can be rotated relative to the axes of their pivots 8. On the free ends of the pins 8 secured leashes made in the form of two shoulders of the levers 9. For agreed joint rotation of the blades 6 has a synchronizer rotation consisting of two concentric disks internal 10 and external 11. The free ends of two shoulders of the levers 9 are inserted in radial slots in the disks 10 and 11. Between the disks 10 and 11 are mounted rollers 12, the axes of which are connected by leads 13 with the axes of the nearest the pins 8. Drive shaft 14 is connected with the driving lever 15, which is connected to the disks 10 and 11 and a driving device (not shown). To reduce the friction torque on the axle 8 has a bearing 16. Stenka configured to clamp to the blades 7, for example, the spring 17. The boss 18 is a sliding bearing. Regulation of the NSA, as follows. Rotational motion through the drive shaft 14 and the drive lever 15 is transmitted to the disks 10 and 11, which leads to their rotation around the axis 5, and the disks rotate in opposite directions. The rotation of the disks 10 and 11 results in synchronous rotation of the blades 7 through two shoulders roar 9 and pin 8. The bearings 16 and 18 reduce the friction torque in synchronous rotation of the blades 7. 1. Guide to allow the apparatus radial turbine, containing the nozzle vanes are evenly positioned around the axis of the impeller of the turbine and set the pins in the turbine housing with the possibility of an adjustable rotation in the channel formed by the walls of the casing, a driving device, adjusting device in the form of an annular synchronizer turn, interconnected with deployme blades through fixed on their pivots leashes, the free ends of which are located in radial slots of the synchronizer, wherein each of the said leads are made in the form of two shoulders of the lever, and the synchronizer rotation is made in the form of two concentric disks, internal and external, linked with the possibility of mutual reversal, each of which is radial slots addressed to him on the free end of the levers. 2. To allow the apparatus according to claim 1, characterized in that between the facing to each other surfaces of the disks synchronizer placed at least three elements in the form of rolling elements such as rollers or balls. 3. To allow the apparatus according to claim 1, wherein forming the channel wall of the housing at the location to allow the blades are made with the possibility of axial displacement, for example spring-loaded in the direction of the scapula. 4. To allow the apparatus according to claim 3, characterized in that the jet blade interconnected with a movable wall of the housing through the bearings. 5. To allow the apparatus according to claim 1, characterized in that the jet blade interconnected with the housing-side pin bearing.
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