Active turbine nozzle assembly |
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IPC classes for russian patent Active turbine nozzle assembly (RU 2433280):
 
 Control system of stages of rotating blades of stator of compressor of gas turbine engine / 2422644
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.
 Adjustment device of alignment of synchronising control ring of rotating blades of gas-turbine engine, and gas-turbine engine / 2420663
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.
 Antiwear device for guide roller of blade with variable setting angle in compressor of gas-turbine engine, compressor of gas-turbine engine and gas-turbine engine / 2420662
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.
 Procedure for fabrication of blade of guiding mechanism of steam turbine / 2418175
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.
 Stator blade with alternate angle of assembly, gas turbine motor with such blade and procedure for repair of such blade / 2416725
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.
 Row of blades of straightening device driven with rotary ring of automatic centring, compressor equipped with said row of blades and gas-turbine motor containing this compressor / 2416724
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.
 Bush for blade hinge with adjustable mounting angle for turbomachine, ring of turbomachine with such bush, and also compressor of turbomachine and turbomachine with such ring / 2405941
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.
 Turbojet engine crankcase sheathing and turbojet engine / 2398114
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.
 Line of flow-straightening grid vanes driven by rotary ring driven by electrical actuators, compressor incorporating said line of vanes and turbojet engine comprising such compressor / 2397331
Line of vanes with variable pitch comprises vanes arranged in casing and driven by their control system. Said control system comprises driving ring secured on said casing and articulated by levers with aforesaid vanes to set them moving simultaneously. Driving ring is simply revolved around turbojet engine axis. Control system comprises two coaxial parts, namely: inner part rigidly coupled with casing and outer part incorporating said driving ring coupled with aforesaid levers and directed to revolve about said inner part. At least one electrically driven unit is arranged between said inner and outer parts. Another invention of the set relates to compressor furnished with said row of vanes of straightening grid. One more invention relates to turbojet engine comprises aforesaid compressor.
 Device to vary turbine nozzle guide vanes critical section, turbine nozzle guide vanes / 2396437
Proposed device comprises circular element. Nozzle guide vanes are arranged radially between circular outer and inner sites, spaced apart to constrict gaseous combustion product passage in turbine. Vanes are spaced apart to constrict critical section to make it minimum section. Circular element features coefficient of expansion less than that of guide vanes sites. Circular element is secured on outer site to stay in two positions: first position corresponding to site no-expansion state wherein it provides for continuous gas-air flow profile, and second position corresponding to site expansion state wherein it extends into gas-air flow to reduced its section. Another invention of the set relates to turbine nozzle guide vanes comprising above described device.
 Water-steam screw expander / 2432465
Water steam screw expander consists of case of high pressure with inlet branch and of case of low pressure with outlet branch. Driving and driven screws of parallel installed rotors arranged in a steam working cavity of the low pressure case. The rotors are additionally interconnected with engaged synchronising gears. A replaceable spacer is set between the said cases. In the spacer there is made a window connecting the steam working cavity with the inlet branch and there is at least one chamber open from the side of steam working cavity. With outlet steam lines the chamber is connected to consumers of steam of intermediate pressure. The second chamber is preferably made in the spacer, while the said window is positioned between the chambers. Windows for withdrawal of steam of intermediate pressure can be additionally made in a side wall of the low pressure case. The expander can be used not only for its intended purpose under a standard mode, but it can withdraw steam of intermediate pressure to a consumer.
 Joint of metal part with part of ceramic material by soldering / 2432345
Joint comprises a metal part of titanium, aluminium and vanadium or inconel alloy, a part of ceramic material and at least one intermediate element of connection, which is attached by soldering to each of the specified parts. The intermediate element (10') of connection consists of a deformable layer, having at least two flat zones (11, 12), soldered accordingly to each of the specified parts, besides, these two flat zones (11, 12) are connected to each other by a deformable zone (13'), having at least two free waves (19, 20), oriented alternately to the specified metal part and to the specified part from the ceramic material. The part of ceramic material may be formed from a dense silicon carbide or of a composite with ceramic matrix reinforced with carbon fibres.
 Procedure for operation of steam-turbine plant and device for steam generation / 2431749
Procedure for operation of steam-turbine plant consists of at least one steam generator heated with solid granulated fuel, for example, brown coal. Also, fuel is preliminary subjected to drying with indirect heating in a dryer with a fluidisated layer. The dryer with a fluidisated layer at least partially is heated with steam from a steam-water circuit of the steam generator. Temperature control in the dryer is performed in two stages depending on contents of moisture in fuel. Initially, temperature of the dryer with a fluidisated layer is controlled by means of pressure of steam for heating; after this regulation there is controlled temperature of superheat of steam for heating depending on steam pressure. The device for steam generation consists of at least one steam turbine with the generator connected after the steam generator. The dryer consists of at least one heat exchanger whereto there is supplied steam for heating and which is connected to the steam water circuit of the steam generator. At least one additional turbine is arranged before the heat exchanger for control of dryer temperature.
 Steam turbine plant for low-potential steam sources / 2422643
Steam turbine plant for low-potential steam sources consists of separator-expansion tank 1 with steam space 2 and water space 3 and steam turbine with nozzle box 5 with working nozzles 4, housing with exhaust branch pipe 6, outboard rotor with speed stages 7, bearings 9 and detachable connection, for example flange 8 attached to nozzle box 5.
 Generating method of mechanical energy, and radial jet rotary engine with rotors of opposite rotation for its implementation / 2420661
Method and device for generation of mechanical energy by using rotors of opposite rotation with nozzles includes supply of working medium to laval nozzle in the rotor of the first stage, acceleration of working medium in nozzles to supersonic speed so that reactive force and torque moment acting on rotor and transmitted to the shaft is created, and supply of accelerated working medium to closed space after rotor of the first stage so that compression shock of working medium occurs in that closed space between rotors of the first and the second stages. Then, working medium is supplied to convergent nozzles of rotor of the second stage and accelerated in nozzles so that reactive force and torque moment acting on rotor of the second stage and transmitted to the shaft is created. At least some part of each rotor is made in the form of a ring. One of those rings encloses another one. Inlets and outlets of nozzles lie on cylindrical surfaces of rings and central lines of nozzles lie in the plane perpendicular to rotor rotation axis. Acceleration of working medium in nozzles of each rotor is performed with rotation of flow in each nozzle to the opposite side relative to direction of flow at the inlet to that nozzle. Acceleration of working medium in nozzles of rotor of the second stage is performed with rotation of flow to opposite side in relation to direction of flow turn in nozzles of rotor of the first stage. Device can bring generator shaft into rotation.
 Axial three-dimesional machine, gas-turbine engine and aircraft gas-turbine engine (versions) / 2418955
Axial three-dimensional machine includes input located at one axis with output and at a distance upstream, core unit that includes internal main part located inside external main part. Internal and external main parts extend from input to output. Note that internal and external main parts have shifted inner and outer axes correspondingly. At least one of internal and external parts can be rotated about one of inner and outer axes correspondingly. Internal and external main parts have intercrossing inner and outer screw-type blades. The axes of screw-type surfaces are inner and outer axes correspondingly. Inner and outer screw-type blades are located radially on inner and outer sides correspondingly. Inner screw-type blades are located radially from inner hub of internal main part towards outer side. Core unit has first, second and third sections that are located sequentially downstream between input and output. Inner and outer screw-type blades have first, second and third pitch angles in first, second and third sections correspondingly. First pitch angles are smaller than second pitch angles, and third pitch angles are smaller than second pitch angles. Combustion section goes downwards along axis through at least some part of second section.
 Unit functioning as heat-and mass exchanger, turbine and pump - htp / 2417328
Unit functioning as heat and mass exchanger, turbine and pump consists of case, of ferrule (section of pipe) or of two ferrules of different diametre successively interconnected and equipped with front and back end covers, of washer (circular partition) with central orifice for water inlet installed at distance from front cover, and of tangential or radial branches for water supply connected to case between front cover and washer. The unit also consists of a steam line connected with an internal part of the case via an intermediate steam chamber around the case and via tangential nozzles passing through the wall of the case. The unit includes an outlet pipeline of hot water connected to the case tangentially. Disks are successively put on at a distance from each other and fixed on the shaft inside the case along its axis. A working wheel of the pump (centrifugal or axial) is arranged and fixed between the washer and disks on the shaft; or an elongated end of the shaft projects beyond the front end cover and is connected to the shaft of the centrifugal pump, while the pump proper is installed into an inset of the pipeline supplying water to the unit.
 Soldered joint between titanium-based metal part and part of ceramic material based on silicon carbide (sic) and/or carbon / 2416587
This compound may be used in aviation, in particular, in turbomachine, to connect parts included into the composition of a nozzle, a combustion chamber and an afterburner. The joint comprises a multi-layer structure, which includes the following components joined to each other by means of soldering: a titanium-based metal part (10), the first substrate (11), capable of deformation for adjustment to the difference in expansion of the metal part (10) and a part of ceramic material (20) based on silicon carbide and/or carbon, the second rigid substrate (12) of aluminium (AIN) or tungsten (W) nitride with an expansion ratio that is close to the expansion ratio of the specified part from the ceramic material (20), and the part of the ceramic material (20).
 Cylinder of medium pressure in steam turbine / 2414602
Cylinder of medium pressure in steam turbine consists of case with chamber, of steam inlet connected to cavity of lower pressure via separator, of guiding mechanism of first step with working blades arranged behind it with inter-rim gap, of ferrule of stator with radial packing positioned over band of working blades secured to guiding mechanism of first step. The ferrule forms a circular cavity with case of cylinder, while with diaphragm of second step it forms an open inter-step gap communicated with circular cavity. Separate circular chambers positioned opposite the inter-rim gap of the first step are made in the ferule, opposite to an inlet edge of the working blades band of this step and over pins of the working blades between the steps of radial packing. The separate circular chambers are communicated with the circular cavity of the case by means of drain channels beneath the ferrule. Outlet sections of the drain channels are arranged in the ferrule with set-off in a sequence corresponding to the position of the circular chambers in the ferrule. To external surface of the ferrule at a back end wall there is attached a circular screen separating a part of the circular cavity of the case with the outlet sections of the drain channels from the part of the circular cavity with an open gap between the first and the second step. Additional circular chambers located opposite to packing collars of the band of the first step blades can be made in the ferrule.
 Rotor-vortex hydraulic motor / 2399770
Motor consists of rotor-vortex turbines installed in case 1, of stators 2 in turbine case1 with blades 3 and of rotors 5 mounted on hollow shaft 4. Each turbine has two blocks 6, 7 parallel coupled with a cavity of shaft 4. Blocks 6, 7 contain equal number of pairs stator 2-rotor 5 arranged in groups including at least three pairs divided in axial direction with stops 8. Between the groups there are positioned centralisers 9 of shaft 4 in case 1 consisting of supports 10 and bearing sleeves 11. Rotors 5, stops 8 and sleeves 11 are fixed on shaft 4 with nut 12. Blind channel 13 and orifices 19 for supply of fluid into groups are made in shaft 4. Groups of rotors 5 are centred relative to groups of stators 2 by means of radial supports consisting of bushings 14, 15. Stop sleeve 17 installed in case 1 and forming cavity 16 envelops each group of stators 2. Cavities 16 are intercommunicated. Groups of stators are fixed relative to sleeve 17 by means of lugs 18. Packing unit 21 is made as labyrinth. Case 1 is equipped with subs 22, 23, while shaft 4 is equipped with half-coupling 24.
 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: machine building. SUBSTANCE: 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. EFFECT: simplified design and production procedure. 3 dwg
The invention relates to the design of nozzle devices active low-flow turbines with partial supply of gas and can be used in power engineering. In partial low-flow turbines are widely used nozzle apparatus with conical axisymmetric nozzles (see, for example, Emine O., Zaritsky S. p. "Air and gas turbines with single nozzles", Moscow, Mashinostroenie, 1975, p.16, 19). Such nozzle apparatus is simple in terms of technology and have minimal gas loss in the axisymmetric nozzle and acceptable aerodynamic characteristics for specific applications. The expansion of the scope counteract two properties of axisymmetric nozzles: - output section such nozzles on a plane oblique slice has the form of an ellipse and ill accords with rectangular input section of the channels of the impeller of the turbine; - the height of the blades limits the degree of expansion of the nozzle and forces the use of a complex in design Mnogomernye nozzle apparatus. Also known nozzle apparatus with nozzles of rectangular cross-section, output section which are in better agreement with rectangular input sections of the working arrays turbine wheel and is capable of implementing a high degree of expansion gas is on stream. In particular, it is known to allow the device containing the nozzle of rectangular cross-section including upper and output sections, in which the output section of the nozzle at a slanted cut has a mean radius equal to the average radius of the working grating wheel, the projection of the longitudinal axis of symmetry of the accelerating section on the plane of the nozzle apparatus is placed at a tangent to the circle formed by the average radius of the turbine stage (see RF patent №2232902 priority from 05.07.2002,, IPC (7) F01D 9/02 - the prototype of the invention). In comparison with axisymmetric nozzles of the nozzle of rectangular cross-section less technologically advanced and have high gas losses. The problem to which the invention is directed, is to minimize the disadvantages of the nozzle apparatus. The technical result is achieved when the solution of the problem, expressed in the creation of a nozzle apparatus having only useful properties known constructive solutions. The problem is solved in that the nozzle device of the axial turbine containing a nozzle, having an accelerating section and the exhaust section, in which the output section of the nozzle in a plane oblique slice has a mean radius equal to the average radius of the working grid turbine wheel, unlike the prototype, the upper section is made of an axisymmetric nozzle and ogologo extending channel, the width is constant and equal to the diameter of the output section of an axisymmetric nozzle, and the height of the channel is made gradually increasing the diameter of the output section of an axisymmetric nozzle up to a maximum value at the exit area nozzle of the apparatus, the axis of the axisymmetric nozzle is at a tangent to the circumference of the middle of the bend radius of the expanding channel, the output section of the axisymmetric nozzle does not exceed the height of the blades of the working turbine lattice and the surface of the expanding channel formed by two coaxial cylindrical surfaces with an average bending radius equal to the average radius of the outlet cross section of the nozzle in the plane of the oblique slice, and two associated with the edges politologie surfaces, the diameter of which is equal to the diameter of the output section axisymmetric nozzle. The claimed performance of the nozzle apparatus impulse turbine implements positive properties of axisymmetric nozzles (simplicity and manufacturability, the minimum gas loss in the nozzle and nozzle of rectangular cross-section (output section is in good agreement with rectangular input section of the working grid turbine wheel, the degree of expansion of the gas flow in the nozzle is not limited to the height of the blade) while minimizing their disadvantages (oval output section on a plane obliquely what about the cutoff and limit the degree of extension height blades (axisymmetric nozzle), less adaptability and increased losses in nozzles of rectangular cross-section). Figure 1 shows the cross-section of the turbine. Figure 2 is given scan along section A-A. Figure 3 shows a section b-B of the nozzle. To allow the device includes a nozzle 1, having an upper section 2 and the outlet pipe 3, in which the output section 4 of the nozzle in a plane oblique slice 5 has an average bending radius Rsrisequal to the average radius Rcfworking grating 6 wheel 7 of the turbine. Upper section 2 of the nozzle is made of an axisymmetric nozzle 8 with a critical section of the dkrand the output section of the d1and curved expanding channel 9, the width of which hcconstant and equal to the diameter of the output section of the d1axisymmetric nozzle 8, and the height of the channel 9 is made gradually increasing the diameter of the output section of the d1axisymmetric nozzle 8 to the maximum value at the output section 3 nozzle system. The axis of the axisymmetric nozzle 8 is executed on 10 tangent to the circumference of the middle of the bend radius RCSRSthe expanding channel 9, the output section of the d1axisymmetric nozzle 8 does not exceed a height of hlblades working grating 6 of the turbine, and the surface of the expanding channel 9 is formed by two coaxial cylindrical surfaces 11 and 12 with an average radius and the bending R CSRSequal to the average radius Rsristhe output section on the plane 5, an oblique slice, and two associated with the edges politologie surfaces 13 and 14, the diameter of which is equal to the diameter of the output section of the d1axisymmetric nozzle 8. During operation of the nozzle unit impulse turbine from a source of high pressure gas into the nozzle 1, which accelerates in the boost phase 2 and through the outlet pipe 3 is supplied to the working grid 6 wheel 7, bringing it into rotation. During the course of the gas flow in the boost phase 2 gas losses are minimal and are determined by the friction losses. Using the stated nozzle apparatus will allow to increase the efficiency of impulse turbine. Allow the unit impulse turbine containing a nozzle, having an accelerating section and an output section in which the output section of the nozzle in a plane oblique slice has an average bending radius, equal to the average radius of the working grid turbine wheel, characterized in that it upper section made of an axisymmetric nozzle and a curved, widening of the channel, the width of which is constant and equal to the diameter of the output section of an axisymmetric nozzle, and the height of the channel is made gradually increasing the diameter of the output section of an axisymmetric nozzle up to a maximum value at the output is a plot of nozzle apparatus, thus the axis of the axisymmetric nozzle is at a tangent to the circumference of the middle of the bend radius of the expanding channel, the output section of the axisymmetric nozzle does not exceed the height of the blades of the working turbine lattice and the surface of the expanding channel formed by two coaxial cylindrical surfaces with an average bending radius equal to the average radius of the outlet cross section of the nozzle in the plane of the oblique slice, and two associated with the edges politologie surfaces, the diameter of which is equal to the diameter of the output section of an axisymmetric nozzle.
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