Turbine adjustable nozzle assembly |
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IPC classes for russian patent Turbine adjustable nozzle assembly (RU 2294439):
    
 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
 Supporting and locking means for the nozzles high pressure stage in gas turbines / 2223406
The invention relates to a supporting and locking means for the nozzles high pressure stage in a gas turbine
 System steam supply to the turbine cylinder / 2217598
The invention relates to power engineering and can be used to create a new steam turbine or their modernization
 Shut-off valve air cooling of turbine blades / 2037050
The invention relates to turbidostat, in particular to the shut-off valves air cooling of turbine blades
 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.
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.
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.
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.
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.
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.
 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.
 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.
 Nozzle guide assembly of radial-flow turbine / 2306425
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.
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FIELD: mechanical engineering; turbine building. SUBSTANCE: 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. EFFECT: increased economy of turbine in wide range of operating conditions owing to provision of optimum values of angles of vane setting of adjustable nozzle assembly. 2 cl, 2 dwg
The invention relates to mechanical engineering, in particular to the turbines, and can be used in the transport of gas turbine engines and turbochargers for internal combustion engines. Known adjustable guide apparatus are measured [1], which contains the outer and inner shells with shaped slots in which are installed with the possibility of moving the plate-like vanes associated with the actuator. The actuator is made in the form of a clip mounted on the splines on the shaft with the possibility of axial movement, pivotally connected with the yoke levers with weights, bearing and its associated sleeve, spring-loaded relative to the inner shell, and vanes mounted on the outer surface of the sleeve. When starting the turbomachine with increasing rotation speed of the goods under the action of centrifugal force through leverage slip yoke on the shaft splines. The yoke transmits the force through the bearing sleeve, and leaf blades are moved in the slots and take due to the configuration of the latter form. The stiffness of the springs restricts the movement of the blades. With further increase of frequency of rotation of the shaft in the corresponding movement of the blades angle of swirl flow at the entrance to the impeller increases. By reducing the rotation speed of the centrifugal force, is operating on the goods, decreases, the sleeve and the housing under the action of the springs are removed from the wheel, the blades are moved in the slots, and the twist angle of the flow at the entrance to the wheel is reduced. The disadvantage of this technical solution is the complexity of the device for controlling the flow direction at the entrance to the turbine wheel. Known adjustable turbomachine [2], comprising a housing with two symmetrical annular chambers, which are movable in the axial direction radial to allow the device is made in the form of separate sections with different characteristics, separated by radial partitions and placed in the annular chambers. To improve the efficiency variable measured at different loads when changing the operation mode is moved in the axial direction radial to allow the apparatus and before the impeller set section, the blades of which have a profile and constructive angles optimal for this operation. The disadvantage of this technical solution is the complexity of the device to change the angle of the blades by moving sections of a multiple nozzle apparatus are measured. Known adjustable to allow the apparatus radial-axial turbines [3], which are located between the blades of rotary axes and the rotary ring, and to allow up the Arat is equipped with an adjustable bushings with gear and coaxial with them located intermediate gear; a driving ring mounted on the two gear rims, respectively, cooperating with a toothed wheel rotatable bushings and through the intermediate gear with the gear wheels of the rotary axes of the nozzle blades of the device. During nominal operation mode of the scapula with rotary axes are in position and have the specified angles that provides the desired fluid flow. To obtain a new mode of operation of the turbine by changing the gas flow from the actuator drive force is transmitted to the rotary ring, causing it to turn. Through pairs of corresponding toothed gearing is provided by the rotation axes of the blades and in the new position established new geometrical parameters of the nozzle apparatus. The disadvantage of this technical solution adopted for the prototype, is the complexity of the operation of the device for regulating nozzle of the turbine apparatus. The purpose of the invention is to improve efficiency of the turbine in a wide range of operating conditions by ensuring optimal values of the angles of the blades of an adjustable nozzle of the device. This goal is achieved in an adjustable nozzle turbine apparatus, which is contains the vanes, posted on composite rotary axes, sections of which are made of materials having shape memory effect. New adjustable nozzle turbine apparatus is performing a compound of the rotary axes of the sections made from materials having shape memory effect, such as alloys based on iron and Nickel [4]. Figure 1 presents allow the turbine apparatus, a longitudinal section; figure 2 is a view As in figure 1 after turning the composite axis when changing the mode of operation of the turbine. The composite rotation axis and, consequently, the nozzle vanes occurs when changing the operation mode of the engine in the martensitic transformation in sections composite rotary axes when the temperature of the working environment, washer during operation of the turbine nozzle vanes of the apparatus and their composite rotary axis. Adjustable to allow the turbine apparatus (figure 1) contains located between buildings 3 and 4 blades 1 of a rotor of the turbine and nozzle blades 2 with composite rotary axes 9, one end of the fixed in the housing 4, and the other end connected to the blades 2, and the composite rotary axis consists of several sections 5, 6, 7, 8, which for smoother regulation of the angles of the blades may be selected large. Adjustable to allow the device operates in the following manner and on the ohms. With increasing turbine load increases, the temperature of washing nozzle vanes 2 and the compound swivel axis 9, is made in the form of sections 5, 6, 7, 8 from materials having shape memory effect, in which the martensitic transformation occurs in each section separately at different successively increasing temperature. The composite rotation axes 9 and, consequently, the nozzle vanes 2 occurs when changing the mode of operation of the turbine in the martensitic transformation of a material having shape memory effect, in the sections of the rotary axes when the temperature of the working environment. Figure 2 shows the initial position to allow the blade 2 and its position at various angles of rotation of the compound swivel axis 9. With a moderate increase in temperature with increasing load of the turbine is turning section 5 composite rotary axis and the blade 2 is in clause 10, and upon further heating of the blades 2 and sections swivel axis 9 in the martensitic transformation in section 6 derives its rotation and jet blade 2 takes position 11. Subsequent heating of the working environment by increasing the load of the turbine is consistent with the rotation of the sections 7 and 8, resulting in a jet blade 2 is rotated at a greater angle. When the load of the turbine shovels and nozzle apparatus are rotated in the opposite direction due to the decrease in temperature of the working environment and reverse martensitic transformation in the materials sections of the composite rotary axes. Thus, the use of the proposed adjustable nozzle of the apparatus, thus improving efficiency of the turbine by providing optimal values of the angles of the blades in a wide range of operating load modes. Sources of information 1. AS the USSR № 1645570 A1, publ. 30.04.91, bull. No. 16. 2. AS the USSR № 1219831 And, publ. 23.03.86, bull. No. 11. 3. AS the USSR № 1544990 A1, publ. 23.02.90, bull. No. 7. 4. Application of shape memory effect in modern engineering./ Astinov, Apheresis, PIV), mechanical engineering, 1981, - 80 C. 1. Adjustable to allow the turbine apparatus containing located between the shoulder blades with a swivel axis, wherein the swivel axis made of composite materials having a shape memory effect. 2. Adjustable to allow the turbine apparatus according to claim 1, characterized in that as materials having shape memory effect, used alloys based on iron and Nickel, in which the martensitic transformation occurs at different temperatures.
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