Stator blade of gas turbine engine with adjustable setting angle, and gas turbine engine |
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IPC classes for russian patent Stator blade of gas turbine engine with adjustable setting angle, and gas turbine engine (RU 2436967):
 
 Permutation travel meter for the device for hydraulic control system / 2433313
Axial fan is supplied by a hydraulic control system of impellers. The control system substantially consists of a control cylinder and a piston rod with a piston in which one portion is axially movable, and the other one is axially fixed. The axially movable portion is coupled with a control disk whereon impeller shafts are fastened respectively through rotated control levers. A piston rod elongation projecting from the control cylinder is surrounded with an oil adapter used for oil feed to the control cylinder. For permutable travel measurement, the control system is coupled with a magnetostrictive path meter comprising a sensor housing with a waveguide, a sensor head and a ring magnet; the sensor housing and the sensor head of the magnetostrictive path meter are coupled with the oil adapter, and the magnet is attached to a portion of the control system axially movable with respect to the oil adapter.
 Propeller of reversible axial fan / 2427727
Propeller of reversible axial fan consists of hub, of bearing disks, of ferrule and of leaf blades. Also, the leaf blades are arranged in pairs on the ferrule at alternate step; they are set off one relative to another and interconnected with bridges. In a case of the propeller there is installed webbing connecting the hub, the bearing disks and the ferrule. Thickness hb of blade, hf of ferrule, hd of the bearing disks and hh of a hub wall is chosen from condition hb<hf<hd<hh.
 Ring of drive of stator rotary blades of gas-turbine engine compressor / 2411400
Method is implemented in the ring of drive of stator rotary blades of gas-turbine engine with radial holes made in it, in which there installed are collar bushings contacting with the surface of the drive ring, which are connected to rotary blades by means of levers one end of each of which is installed in open rectangular slot made on surface of the drive ring and rigidly attached to the pin contacting with inner surface of bushing, and the other one is rigidly attached to rotary blade; at that, it is equipped with locking members to restrict radial movement of bushings, collars arranged opposite them; at that, slots are made on inner surface of drive ring; levers are installed on the side of the latter; at that, drive ring is equipped with shields; levers are arranged in slots in the gap between inner surface of ring and shields, bushing collars and locking members are arranged on the side of external ring surface.
 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.
 Axial-flow compressor rotating cascade / 2395012
Axial-flow compressor rotating cascade comprises casing accommodating top and bottom journals of vanes. Note here that outer sleeve of top journal is press-fitted into casing, while inner sleeve with curvilinear end sections of outer contact surface is located in cavity of outer sleeve made from zirconium dioxide.
 Device for changing setting angles of rotating blades of fan / 2390659
Device for changing setting angles of rotating fan blades includes electric motor, mechanism for turning fan blades and locking device of support of blades. At that, blade turning mechanism is made in the form of cylindrical stator being in magnetic contact with rotor.
 Axial fan impeller / 2381387
Invention can be used in development of axial fan impellers. Proposed impeller comprises hub 1 furnished with ring 2 and bores accommodating rotary pairs of blades 3. The latter have rotary axle 8 and cup 4 articulated with toothed rack 6 of the device designed to make said axle and cup rotate. Every cup is fixed, via bearing units 7, on axle 8 rigidly fixed on hub 1. Note here that every pair of blades 3 is articulated, via cup 4, with rotation drive of blades 3.
 Multi-stage compressor for turbomachine / 2375607
Invention relates to multi-stage compressor for turbomachine, in particular for aircraft turboprop or turbojet engines. Proposed compressor comprises housing with dual wall, inner wall being made up of shrouds enveloping appropriate circular rows of stator rotating vanes and circular rows of straightening vanes. Note here that aforesaid shrouds are attached to housing outer wall by independent attachments.
 Axial fan impeller with blade rotary mechanism / 2343321
Invention refers to fan engineering and can be used in axial fan impellers with blade rotary mechanisms, and is meant for improving accuracy and reliability of specified angles of setting and rotating of impeller blades, including start and finite angles. The above effect is reached by the fact that blade roots are provided with gear wheels that are conjugated with gear racks fixed on axial cross beams arranged by means of sliding guides in load-carrying plates so that they can move axially, and conjugated by means of lengthwise-adjustable ball rods connected with adjusting plate with the help of ball insets and compensating flat springs. Impeller casing is equipped with threaded cross beams with safety nuts.
 Device to vary blades angle in two-stage fixed bladding of turbojet engine / 2338932
Propose mechanism allows separate adjustment of the blades in two adjacent turbojet engine stages controlled by common drive. For this, mechanisms' synchronisation lever 9 comes into an inclined position defined by the link made up of pin 22 and groove 23 coupling the aforesaid lever with the said case. Note that another link made up of pin 26 and groove 27 couples the said lever 9 and one of the aforesaid mechanisms.
 Device for attachment of guide vanes of turbine, turbine and aircraft engine with such equipment / 2436965
Device for attachment of guide vanes of turbine, which is fixed on support that in its turn is installed on stabilising part, contains slot connection devices for connection to slot of the support edge with stabilising edge of stabilising part, retention part for retention in slot of support edge and stabilising edge and retention devices for prevention of relative rotation of support edge and stabilising edge. Retention devices include at least one groove having semispherical shape in its section and made on plane of support edge, and at least one groove having semispherical shape in its section and made on plane of stabilising edge. Grooves are arranged one opposite another and form retention hole at installation of both edges into the slot. The other invention of the group refers to turbine containing the above device for attachment of guide vanes. One more invention refers to aircraft engine containing the above turbine and/or the above device for attachment of guide vanes.
 Guide unit for air flow at inlet of combustion chamber of gas turbine engine / 2435104
Straightening unit includes two coaxial shells between which the blades passing mainly in radial direction are arranged. Diffuser includes two coaxial walls representing rotation bodies and connected to each other by means of radial partitions. One of the shells of straightening unit is made in the form of single part with one wall of diffuser, which represents rotation body. The other shell of straightening unit is connected to and fixed on the other diffuser wall representing rotation body. Blades of strengthening unit are rigidly connected through one end to one shell of straightening unit and are located at some distance with a small gap from the other shell on the other end.
 Device for fixation of stationary blade in circular carter of turbo-machine, turbo-reactive engine containing such device and procedure for blade assembly / 2435037
Here is disclosed device for fixation of stationary blade in circular carter of fan of turbo-machine, wherein blade consists of head formed with platform with front and back ends, blade body and blade root. The circular carter has a circular slot made in its internal wall and front and back boards. The back board of the circular slot is made in form of a groove with and axial orifice directed forward, while a back end of the platform is inserted into the said back board. The blade has a section of the platform between the blade root and the front end containing a through hole wherein there is installed a fastener holding the platform in the circular slot. Another invention of the group refers to two-circuit turbo-reactive engine with a front fan containing a set of stationary blades forming a straightener blade at output of a rotor of the fan wherein the blades are maintained inside the carter by means of the above said device. One more invention of the group refers to the procedure of assembly of the stationary blade of the above said turbo-reactive engine consisting in installation of the blade root in the orifice of the carter of the primary circuit, in inclining the blade for insertion of the back end of the platform into the back groove of the circular slot and in turning the blade around the groove inserting the front end of the platform into a circular slot. Further, the platform is secured on the carter by means of fasteners.
 Active turbine nozzle assembly / 2433280
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.
 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.
 Journal bearing for rotary blade of stator with changeable angle of setting, blade of guiding mechanism of impeller machine containing above said bearing (versions), impeller machine (versions) / 2434142
Impeller machine consists of rotary blade with changeable tilt angle, of pin installed in orifice made in carter of impeller machine and journal for securing rod of control of blade setting. The pin is installed by means of two bearings, one of which is located on a side of a platform, while another bearing on an end of the rotary pin is positioned from the side of the control rod. The journal bearing at the end of the pin has an internal bush stationary connected with the said axis and an external bush equipped with a flange and stationary connected with the said orifice. Elastomer material is inserted between the internal bush and external bush; this material facilitates turn of the blade around its axis and at least partial damping bending force of the rotating pin perpendicular to axis. The internal bush contains two cylinder elements continuing one another and divided with a circular layer of elastomer.
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FIELD: engines and pumps. SUBSTANCE: stator blade of gas turbine engine with adjustable setting angle includes blade continued on one side with turning support by means of which it is installed with possibility of being rotated in the hole of case of gas turbine engine, and platform. Platform is provided between blade and turning support perpendicular to the direction formed with blade and turning support. The platform plane lying opposite to the blade includes the first and the second zones; at that, the first zone is subject to intense friction with wall of case due to transverse forces applied to the blade, and thickness of platform in the second zone has been decreased in comparison to thickness of platform in the first zone. The other invention of the group refers to gas turbine engine containing at least one above described stator blade. EFFECT: inventions allow reducing the weight of gas turbine engine without reducing its reliability. 8 cl, 3 dwg
The present invention relates to the field of gas turbine engines of the type axial compressors of gas turbine engines, in particular the stator blades of the engine with a variable angle. Consider the system in the form of output vanes with a variable angle contains mutually moving one relative to another part. Figures 1 and 2 schematically presents the output guide vane 1 with a variable angle, placed in the casing 3 of the engine. The stator vane includes a vane 12, the plate or platform 13 and the rotary support 14 on the end. Rotary support 14 is placed in the bore or a radial hole made in the wall of the casing 3, at different bearings. The blade is fixed only to this end. The other end of the scapula is held floating annular element 16, in which it is installed to rotate the second rotary support 17. The ring is provided with sealing means from the adjacent part of the rotor 18. Rotary support 14 rotates in a corresponding hole of the crankcase bearings, for example on the lower bearing 4. The platform 13 is placed in the cavity formed by rostenkowski wall of the crankcase. The wall of the crankcase is in radial contact with the platform 13 either directly or through a bushing or washer. The upper part of the swivel TNA is s 14 is held in the upper bearing 5. The opposite portion of the platform 13 relative to the bearing 4 forms the base of the blades and purged with gas from the compressor. This part of the plate is formed in such a way as to ensure the continuity of the thread formed by the crankcase. The nut holding the blade in the seat, and a lever controlled by the relevant authorities, controls the rotation of the blades on the axis XX support for mounting the blades in the desired position relative to the gas stream. Mutual movements are the result of slip in the contact surfaces. In the case of an axial compressor with turbo engine with a gas turbine or axial compressor with air or another gas, such as blast or natural gas, the blade 12 along the entire length is subjected to aerodynamic forces and pressure gas streams. Component of these forces, oriented perpendicular to the chord in the direction from the inner part of the blade surface to the outside, passes through the axis of the swivel bearing is the most important factor. Noted however, that in the event of a serious variance component can move away from this axis. The blade is exposed axial efforts static pressure directed upwards, due to the pressure difference between the upper and lower parts. The resultant force indicated what relay F in the drawings. Hence the use of time, which accompanies the regulated rotation axis XX on the peak value, which can reach and exceed 40 degrees and create a zone of intense friction. This friction leads to the use of the platform and/or sleeves. The first zone 20 intense friction localized on part of the surface of the platform. She shaded in figure 2. During normal operation of the machine due to variable loads on the blade 12, the platform comes into contact with the first zone 20 against the surface of the placement in the wall of the crankcase, while on the side diametrically opposite the rotary support, the support efforts are zero or negligible. In Aeronautics excluded any weight load, and regardless of its resolve to reduce the mass, which does not perform any function, whether it's mechanical or aerodynamic. As the closest analogue of the applicant used the patent EP 546935, in which is disclosed a blade of a gas turbine engine with a variable angle. The applicant has the task to find solutions to ease the car without compromising its reliability and quality. Any massive shell improves the efficiency of the vehicle and reduces the cost of operation. To solve this problem, the applicant came to the present invention, concerning a hundred who priori blades with a variable angle. According to the invention the stator vane of a turbomachine with a variable angle containing the blade extended from one side of the swivel bearing, whereby it is mounted for rotation in the bore of the crankcase gas turbine engine, and a platform disposed between the blade and swivel bearing perpendicular to the direction formed by the blade and swivel bearing, characterized in that the surface of the platform, opposite the blades, contains first and second areas, the first area are subject to intense friction with the wall of the crankcase due to transverse forces applied to the blades, and the second zone during normal operation are subject to less friction than the first, moreover, the thickness of the platform in the second area is reduced compared to the thickness of the plate in the first area. Known blades with a variable angle, in particular the blades of axial compressors have a platform of the same thickness, if not to take into account the curvature and/or the nonlinearity of the gas flow. Thanks to the invention it is possible to reduce the weight of this part of the blade without compromising its functionality by providing continuity and reduce losses along the swivel bearings. Preferably, the portion of the second zone having a smaller thickness, was located in an arc of from 60 to 120 degrees around the axis of the rotary support./p> It is preferable that the first area was situated on the side of the back, and the second side trough blades. It is preferable that the second zone of reduced thickness was limited to the border with the formation of the chamber decompression between the peripheral platform and the rotary support. This border has a large thickness, and the upper facet of this border is a continuation of the upper surface of the platform than the first area, forming a decompression chamber between the periphery of the platform and swivel bearing, which improves the seal. In addition, this border allows you to create contact in case of inverting head, in particular when there is the phenomenon of surging of the compressor. Furthermore, this arrangement facilitates Assembly of the machine, preventing the swinging parts. A simple and economical means of manufacture of the blades with the thus obtained second area is the production platform. Preferably, the second zone of lesser thickness was formed cavity during processing platform. It is preferable that the bottom of the cavity, depending on the instrument could be made flat or curved. It is preferable that the cavity was made in the form of an elongated circular arc. Another object of the invention is (the country : Russia the first motor, containing the above-mentioned stator blade with a variable angle. Other characteristics and advantages of the invention ensue from the description, representing one of the variants of the invention, given with reference to figures, in which: figure 1 depicts a view in section, performed on the engine axis, the stator vanes with a variable angle that is installed in the crankcase of the compressor; figure 2 is a top view of the same blade; figure 3 - General view of part of the blade according to the invention. Figure 3 depicts a single blade of the stator of the rotary support 14. The platform 13 is depicted in isometric. In accordance with the embodiment of the invention in the second zone 22 of the surface of the platform, facing the crankcase 3, the cavity 22A, and the area 22 is not exposed to the resulting impact force F on the blade 12. The cavity 22A is made in a known manner. The bottom of the cavity may be flat or curved, when the processing tool is made spherical shape. There may be other embodiments of the bottom cavity. In addition, instead of tooling can be used for casting or forging or powder metallurgy. The cavity is placed in an arc, such as arc of a circle from 60 to 120 degrees corresponding to the zone of intense friction. The cavity reduces weight love the key, but does not impair its mechanical characteristics. The resulting thickness of the platform sufficient to ensure the mechanical strength of the plate. On the edge of the platform passes the border 23. It performs a dual function. The first is the formation of a chamber decompression, reducing air loss between the flow of the gas turbine engine and the rotary support 14 through the hole in the crankcase, which houses the rotary support 14. The second feature is the formation of the bearing surface in the case of inverting the resulting force when anomalies in the operation of the turbomachine, such as the surging of the compressor. In addition, facilitated the operation of the installation. Width of the border may be different. For example, in the area of the great effort it can be more. Preferably its upper surface is in the plane of the platform from the side of the sump. Reducing the thickness of the top surface of the platform is known from the prior art. However, in the framework of the invention is to reduce the thickness obtained by forming a cavity in the platform, hosted by the flow of gas or purified platform on this site. 1. The stator vane of a gas turbine engine with a variable angle containing the blade (12), extended from one side of the swivel bearing (14), by which it is mounted rotatably in the bore of the crankcase (3)gas turbine engine, and the platform (13) between the blade and swivel bearing, perpendicular to the direction formed by the blade and swivel bearing, characterized in that the plane of the platform, opposite the blades, contains the first (20) and second (22) zone, the first zone (20) subject to intense friction with the wall of the crankcase (3) due to transverse forces applied to the blades (12), and the thickness of the platform in the second zone (22) is reduced compared to the thickness of the platform in the first area (20). 2. The stator vane according to claim 1, characterized in that the part of the second zone (22)having a smaller thickness, is made in the form of an arc extending from 60 to 120° around the rotary support (14). 3. The stator vane according to claim 1, characterized in that the first zone situated on the side of the back, and the second zone from the trough of the blade. 4. The stator vane according to one of claims 1, 2 or 3, characterized in that the second zone of lesser thickness is limited by the curb (23) forming a chamber decompression between the periphery of the platform (13) and the swivel bearing (14). 5. The stator vane according to claim 1, characterized in that the second zone (22) the smaller the thickness of the formed cavity during processing platform (13). 6. The stator vane according to claim 5, characterized in that the bottom of the cavity is planar or curved. 7. The stator vane according to claim 1, characterized in that the cavity is made in the form of an elongated arc OCD is gnosti. 8. Gas turbine engine containing at least one stator blade tiltable installation according to one of claims 1 to 7.
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