Device for attachment of guide vanes of turbine, turbine and aircraft engine with such equipment |
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IPC classes for russian patent Device for attachment of guide vanes of turbine, turbine and aircraft engine with such equipment (RU 2436965):
     
 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.
 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.
 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.
 Nozzle box assembly for high-temperature cylinder of steam turbine / 2307254
Proposed nozzle box assembly of high-temperature cylinder of steam turbine includes supply section, transient section and section delivering steam to nozzle segments. Nozzle box assembly is made up of sections welded together, supply section is made of pipe, transient section is made in form of cone changing from pipe into oval, and steam dispensing section is made of two rings, outer and inner ones, with blanks on end faces. Proposed invention provides minimum labor input and metal usage in manufacture, reduced to minimum time taken for heating nozzle box assembly owing to use of more thin walls of welded structure and, consequently, reduced time of starting of high-temperature steam turbine.
 Cooled turbine guide blade and turbine having said blades / 2308601
Guide blade of gas turbine engine comprises front and rear edges, pocket, wing back, as well as opened perforated insert, inlet orifice to supply cooling air inside insert and outlet orifice to remove cooling air portion from blade. The insert defines annular cavity arranged between outer side wall thereof and inner blade wall. Blade has bridges located in cavity part between the insert and inner surface of rear edge to increase blade rigidity. One insert end is fixed to blade. Another one is installed so that the insert end may slide along inner edge of blade under the action of mutual thermal insert expansion relatively inner blade wall. Orifices are created in opened insert so that the orifices are located only in two insert areas. Orifices of the first group are opposite to inner surface of front edge. Orifices of the second group are opposite to inner surface of rear edge to prevent air jet impingement upon bridges.
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FIELD: engines and pumps. SUBSTANCE: 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. EFFECT: inventions allows simplifying and reducing the weight of the attachment device of turbine guide vanes. 21 cl, 7 dwg
The present invention relates to turbine turbojet engines. More specifically, it relates to fastening the guide nozzle apparatus of the turbine turbojet engine. According to the invention a device for fastening the guide nozzle of the device on the fixed elements of the turbine itself. It is also concerned with the turbine containing a device for fastening. It finally relates to a turbojet engine equipped with at least one such device for fastening and/or a turbine. The turbine may be the high-pressure turbine. Turbine turbojet engine includes a stationary element (stator) and moving parts (rotor). Movable elements are wheels carrying the blades are inserted between the bars of stationary vanes, also known as guiding nozzle device of the turbine. The complex guide nozzle unit/wheel forms a stage of the turbine. To facilitate installation of the turbine nozzle guides the vehicles sometimes are made by combining at least two sectors guide nozzle apparatus. Each sector guide nozzle unit contains a certain amount of fixed blades, distributed between the outer ring, called the outer platform and the inner ring, called HV the internal platform. Usually, the internal platform passes radially inward coupling flange serving for fastening the guide nozzle unit or sector on fasteners. To simplify the following description, the term "guide nozzle apparatus" is used to describe a nozzle apparatus, and for its sector. A well-known concept of the fastening device shown in Fig.7, which is a part of the turbojet engine and includes a shaft 102, a camera 104 combustion and stage high-pressure turbine, a wheel which is formed by a disk 106 and movable blades 108 and the guide nozzle apparatus which includes a stationary blade 110, the inner platform 112 and the connecting flange 114. In a known device (7) connection of the guide nozzle apparatus is used as a fastening element for crankcase 122 injectors 116. This fastening element stabilized by fixation on a stationary part of the structure, which is a continuation 124 of the support plate 118 of similar material. The connection formed by locking the connecting flange 114 relative to the crankcase and/or the continuation of the caliper through a bolted connection between the specified continuation 124 of the support plate and the crankcase 122. In the known device (EP 789133) blocking connect is a high flange 114 is made blocking means, which contain the first blocking rod placed in the radial direction and supported on the annular ledge of the specified continuation with the first blocking rod is designed to compress the connecting flange to the crankcase in the axial direction. In this device, disabling devices also contain a second blocking rod passing simultaneously through the crankcase and connecting flange for locking the connecting flange in the radial and circumferential directions. In another known device (US 5143512) each connecting unit includes a groove for locking the crankcase, and this groove opens radially outward and positioned to ensure that it included the connecting flange, and its blocking radially outward. In accordance with this concept device for the connection also includes a locking rod positioned in the axial direction radially and intended for blocking the connecting flange in the radial and circumferential directions, simultaneously passing through the connecting flange and the casing and axially abutting against the continued support. And in that and other existing concepts, devices for connecting the crankcase of the injectors and the continued support of the grated material bonded together by bolted connection is to be neglected. The technical task of the present invention is to simplify the connection and, in particular, the exception bolted connection by creating a device for fastening the guide nozzle apparatus of the turbine, while the guide nozzle device attached to the caliper, which, in turn, is mounted on a stabilizing details. The invention relates to a device for fastening, which contains means to connect the groove in the edge of the caliper parts of the caliper and stabilizing stabilizing edge details, and retainer to keep United in the groove edge of the caliper and a stabilizing edge, when this arrangement is characterized in that it contains means of restraint to resist relative rotation of the edge of the caliper and roll edge. The latter contain at least one hollow groove with a semicircular cross section on the cut edge of the caliper and at least one groove of semicircular cross section on the cutoff roll edge, thus, when both of the groove when the work stacked on top of one another, they together form the hole. The means of connection in the groove contain, in addition, means to connect the edges of the caliper, as well as the template and tools for more sizing roll edge. These connectors contain, in addition to t the th, at least one locking pin for insertion in said hole when the two edges are connected in a groove. Retainer has a ring shape and in cross section almost has the shape of a "J". It contains a Central frame, which at one end continues radial part of the ongoing terminal part, parallel to the Central frame, the Central frame, the radial portion and the terminal portion to form a retaining groove, and the Central frame at the other end continues flange, the plane of which is perpendicular to the frame and rises above the radial part and the end part. The arrangement also includes a mechanism for locking the edges of the support plate and retainer. The specified locking mechanism includes teeth on the end of the caliper and additional teeth on the retainer. The teeth on the end of the caliper are located on the flange end of the caliper. Additional teeth retainer located on the end part of the retainer. Device for fastening also includes locking means to prevent rotation of the retainer relative to the edge of the caliper. Means locking is performed in the form of a protuberance on the retainer. They also contain a hole for locking the end of the caliper and the hole for the locking retainer,with the two holes for the locking performed almost the same diameter, as the locking rod designed for passage in both holes for locking. The hole for the locking retainer is in one of the additional teeth retainer and the hole for locking the end of the caliper is on one of the teeth on the end of the caliper. Device for fastening contains, in addition, means for locking the guide nozzle of the apparatus relative to the end of the caliper, while the guide nozzle apparatus includes a stationary blade, distributed through a certain angle between the two almost circular concentric platforms through equal angular intervals. Disabling devices contain: the mounting flange of the guide nozzle apparatus, which passes over the platform of the smallest radius of curvature relative to the blades, holes intersecting the mounting flange and posted on its circumference groove to lock the edge of the caliper, which opens radially outward holes passing through the wall of the groove to block, and a locking pin passing simultaneously through the holes of the mounting flange and the holes in the walls of the locking groove. Preferably the locking rod is made with the shoulder. The locking rod when the work is held between the edge of the caliper and arivudai detail. In accordance with a variant of the invention the part of the caliper is formed by a crankcase injectors, and a stabilizing part is formed by a continuation of the caliper from the abrasion of the material. In accordance with the second aspect of the invention relates to a turbine containing at least one device for fastening the guide nozzle of the device. In accordance with a third aspect of the invention relates to the engine of the plane containing the turbine and/or at least one device for fastening. The technical effect of the claimed invention is that it decreases the overall weight of the aircraft engine, as the fastening guide nozzle apparatus no longer has bolted joints. Hence reducing the cost of operation of the engine of the aircraft, expressed in fuel economy at different stages of flight. Another advantage of the invention is that reduced installation time due to the absence of bolted connections. Hence the decrease in the cost of service. The invention is further explained in the description of the preferred variants of the embodiment with reference to the accompanying drawings, in which: figure 1 is a schematic axial section turbojet engine turbine, provided with locking device, with whom according to the invention; figure 2 is an axial section of the device mounting according to the invention; figure 3 - General view of the edge of the caliper, and means of connection in the groove and locking means according to the invention; 4 is a General view of the connection groove edge of the caliper with a stabilizing edge, and means to hold according to the invention; 5 is a General view of the retainer, means for wedging and locking means according to the invention; 6 - slot connection edge of the caliper with a stabilizing edge (radial section), and their bond with retainer according to the invention; 7 is an axial section of part of a turbojet engine with a device for fastening according to the prior art. 1 schematically shows a turbojet engine 1, containing the turbine 2 high-pressure turbine 3 low pressure, the combustion chamber 4, a compressor 5 high-pressure, fan 6. Turbine 2 high-pressure fitted with guide vanes nozzle device 8. Figure 2 shows the device 20 mounting the guide nozzle apparatus 8 of the turbine, comprising a fixed blade 10, arranged between the outer platform (not shown) and the inner platform 12. The connecting flange 14 extends from the inner platform 12 is perpendicular to the stationary blades 10 otnositelnosti 12. Similar known devices mounting the guide nozzle apparatus 8 of the turbine is attached to a retainer mounted on the stabilizing parts. According to the described variant embodiment of the invention represented in the drawings, the crankcase 22 of the injector forms a retainer, and a stabilizing part is a continuation 30 of the support plate 18 from abrasion material. The device 20 of the mounting according to the invention contains a retainer 60, which serves for fixing the stabilizing part 30 and part 22 of the support plate and which is used to fasten the guide nozzle apparatus 8 parts 22 of the caliper. Similarly, well-known device for fastening the locking guide nozzle unit 8 relative to the part 22 of the carriage is effected by means of a connecting flange 14, which is secured in the locking groove 16 of the edge 26 of the crankcase 22 of the injectors with locking rod 28. In this case, the dimensions of the locking grooves 16 correspond to the dimensions of the connecting flange 14, with the mounting flange 14 has a connecting hole (not shown), and the wall of the locking grooves 16 have corresponding holes in the walls 160 (figure 4). The locking rod 28 passes through a hole in the connecting flange and the holes in the walls. The locking pin 28 to perform the EN with the shoulder so that he rests in one of the walls of the locking groove 16 in the bottom wall (figure 2). The connecting flange 14, the locking groove 16, the locking pin 28 and the corresponding holes form a means of locking the fastening device 20 according to the invention. In addition to the tools 14, 16, 28 locking the mounting device according to the invention contains means 44 connection-groove edge 26 of the crankcase 22 of the injectors with the edge 30 of the extension 24 of the support plate 18 from abrasion material, means 46, 48, 50, 52 retention to prevent relative rotation of the crankcase 22 and the extension 24, the retainer 60 to hold the crankcase 22 and the extension 24, the means 34, 72 locking (figure 5) retainer 60 on the crankcase 22 and the means 76, 78, 80, 82 locking to prevent rotation of the retainer 60 relative to the crankcase 22. All these tools are described below. To facilitate the description of the edge 26 of the crankcase 22 will be called "edge 26 of the caliper, and the edge 30 of the extension 24 will be called "stabilizing edge 30". As shown in figure 3, the edge 26 of the caliper is a detail of rotation about the axial direction, which includes a housing 36 of the edge from which radially outward are two walls bounding the above-described locking groove 16. The housing 36 of the edge is in the axial direction nearly rectangular cross-section. The housing 36 kPa which has an internal plane 38, located next to the rear surface 40, radially directed, on the other hand the locking grooves 16 and the upper surface 39. The rear wall of the groove 16 includes a flange 32 (6), which carries on the back wall towards the rear wall 40 of the housing 36 edges. This flange 32 is directed radially and in parallel in the direction opposite to the direction of the entrance to the groove. Between the flange 32 and the back plane 40 is formed in the rear groove 42. On the free end of the flange 32 is made of the teeth 34, which are placed along the periphery of the flange 32. These teeth radially directed inward. On the connection of the inner plane 38 and the rear surface 40 of the housing 36 of the edge has a groove edge of the support formed by the tool 44 uncoupling with the first face 442, almost parallel to the back plane 40, and a second face 444, perpendicular to the specified first face 442. The second face 444 executed grooves 46, oriented in the axial direction and having a semicircular profile. Figure 4 shows the connection into the groove edges 26 of the caliper and a stabilizing edge 30. To this end, the stabilizing edge 30 is made in form and dimensions corresponding to the groove edge 26 of the caliper. In particular, the stabilizing edge 30 includes a first plane and the second plane, intended for contact respectively with the specified first face of the 442 and the second edge 444 edge 26 of the caliper. Grooves 48 are made in the second plane is oriented in the axial direction and have a semicircular profile. When assembling the edge 26 of the caliper and a stabilizing edge 30 are connected to one another in the groove, forming a nest. This connection in the groove made by the first connection face 442 and a second face 444, respectively, the edges 26 of the caliper with the first plane and the second plane stabilizing edge 30, respectively. The connection into the groove is designed in such a way that the grooves 46 of the second face 444 edge 26 of the support plate are aligned with the grooves 48 of the second plane stabilizing edge 30 forming a complex holding holes 50. The locking rods 52 are inserted in these holes to prevent axial rotation of the edge 26 of the caliper and a stabilizing edge 30 of one relative to another. The means of connection in the groove of the fastening device 20 contain the specified notch 44 in the edge 26 of the caliper, as well as forms and the corresponding dimensions of the stabilizing edge 30. Means of restraint device 20 mounting contain the above-mentioned grooves 46 in the edge 26 of the support grooves 48 in the stabilizing region 30 and the retaining hole 50, and a locking rod 52. The connection into the groove between the edge 26 of the caliper and restraint 30 is carried out by means of fasteners 60 (figure 5). Retainer 60 is made in the form of a body of rotation wok is ug axial direction. It contains a Central rectilinear frame 62. The latter continued with one side of the radial part 64, which becomes the target portion 66 returning to the main frame 62 and parallel to it. The Central frame 62, the radial portion 64 and the terminal portion 66 form a retaining groove 68, and the Central frame 62 on the other hand continued orthogonal rectilinear projection 70, which hangs over the radial part 64 and the terminal part 66. In the axial section retainer 60 has a cross section in the shape of a "J" and the vertical bar corresponds to the Central frame 62 and the horizontal bar corresponds to the protrusion 70. The Central frame 62 forms an elastically deformable zone retainer 60, which allows the operator to set it in place, as will be described below. On the free end of the terminal portion 66 is made of the teeth 72, which follow one another along the entire periphery of the terminal portion 66. The shape and size of teeth 72 complement the form and dimensions of the teeth 34 of the flange 32 of the edge 26 of the caliper. Retainer 60 also includes a flange 74 for gripping, which runs from the Central frame 62 on the side opposite the retaining groove 68 relative to the Central frame 62, and slightly offset relative to the protrusion 70. The knob 74 for gripping contains two pic is edutella hosted zone that are displaced around the circumference of one relative to another and to facilitate manual handling of this knob 74 for gripping, and the deformation of the Central frame 62 by the operator. 6 illustrates in radial section view of the Assembly of the two edges 26, 30 using the retainer 60. Retainer 60 is fixed to the edge 26 of the caliper, which is shown only partially. The post operation is carried out as follows. The operator takes the retainer 60 for the knob 74 for gripping. He enters the free end of the terminal portion 66 of the retainer 60 in the rear groove 42 of the housing 36 of the edge 26, inserting the teeth 72 of the retainer 60 between the teeth 34 of the flange 32. Simultaneously, the flange 32 of the edge 26 of the support plate is inserted in the holding groove 68 of the retainer 60. This introduction is facilitated by the presence of the elastic zone in the retainer 60. The operator then releases the knob 74 for gripping. The Central frame 62 of the retainer 60 is superimposed, so that the flange 32 of the retainer 26 and the ledge 70 of the retainer 60 is placed on the upper part 39 of the edge 26 of the caliper. The operator then rotates the retainer 60 in relation to the edge 26 of the caliper. The teeth 34 of the flange 32 are in the depression between the respective teeth 72 of the retainer 60 and prevent separation of the edges 26 of the caliper and hold ivalsa part 60. Thus, it is a snap fit type bayonet connection. In the snap roll edge 30 is axially pressed against the first face 442 of the edge 26 of the caliper terminal part 66 of the retainer 60. Means latching device mount 20 contain the teeth 34 of the flange 32 of the edge 26 of the caliper, as well as complementary teeth 72 of the retainer 60. The means of attachment 20 also include locking means to prevent rotation retainer 60 in relation to the edge 26 of the caliper, which could lead to undesirable consequences. Mentioned locking means have a slightly convex profile 76 of the Central frame 62, the convexity of which is placed by the holding grooves 68 (figure 5). This is slightly convex profile 76 causes the axial stress in the retainer 60, which causes friction between the retaining part 60 and the rear surface 40 of the edge 26 of the caliper and prevents relative rotation of these two parts (6). Additional locking means shown in figure 3 and 5. They contain a locking hole 78 of the edge 26 of the caliper, made in one of the teeth 34 of the flange 32. They also contain locking hole 80 in the retainer 60, made in one of the complementary teeth 72. They contain, finally, the locking rod 82, intended for introduction is in these two locking holes 78, 80, which have the same diameter. Preferably the locking rod 82 is made with the shoulder (figure 3). During the operation of latching the operator sets the teeth with the locking holes 78, 80 one against the other and stoparic both locked in detail, introducing the locking rod 82 in both stopping placed one opposite the other holes 78, 80. The invention is not limited to the above particular variant embodiment. It also applies to equivalent forms of embodiment, well-known experts in this field. 1. The device for fastening the guide nozzle apparatus of the turbine, while the nozzle unit is fixed to the caliper, which, in turn, is mounted on a stabilizing part containing 2. Device for fastening according to claim 1, characterized in that the said means of retention additionally contain at least one locking rod that is designed for insertion into the retaining hole when both edges in the connection into the groove. 3. Device for fastening according to claim 1, characterized in that the retainer is made of a ring and has a J-shaped cross-section. 4. Device for fastening according to claim 3, wherein the retainer has a Central frame, which continues radial part, which, in turn, continues terminal part, parallel to the Central frame, the Central frame, the radial portion and the terminal portion to form a retaining groove, and the Central frame on the other hand has a perpendicular ledge that hangs over the radial part and the target part. 5. Device for fastening according to claim 4, wherein the retainer further comprises a knob for grasping, which is perpendicular to the Central frame at the side opposite the retaining groove relative to the Central frame. 6. Device for fastening according to claim 1, characterized in that the content is t means locking edge of the support plate and retainer. 7. Device for fastening according to claim 6, characterized in that the locking means include teeth edge of the caliper and the complementary teeth retainer. 8. Device for fastening according to claim 7, characterized in that the teeth edge of the caliper is made in the flange edge of the caliper. 9. Device for fastening according to claim 7, characterized in that the complementary teeth retainer is placed on the terminal part of the retainer. 10. Device for fastening according to claim 1, characterized in that it further comprises locking means to prevent rotation of the retainer relative to the edge of the caliper. 11. Device for fastening of claim 10, wherein the locking means have a convex profile retainer. 12. Device for fastening according to claim 11, characterized in that the locking means also include stopping the hole in the edge of the caliper and the locking hole in the retainer, both locking holes have the same diameter, the same as the blocking rod intended to enter into both locking holes. 13. Device for mounting on item 12, characterized in that the locking hole of the retainer made in one of the complementary teeth retainer, and locking hole edge of the caliper is made in the bottom of the teeth edge of the caliper. 14. Device for fastening according to claim 1, characterized in that it further includes means for locking the guide nozzle apparatus, comprising a fixed blade, distributed evenly between the two annular concentric platforms. 15. Device for fastening at 14, characterized in that the said means blocking contain 16. Device for mounting on 15, characterized in that the blocking rod is made with the shoulder. 17. Device for mounting on 15, characterized in that the blocking rod is introduced into the edge of the support plate and retainer. 18. Device for fastening according to claim 1, characterized in that the part of the caliper is formed by a crankcase of the injectors. 19. Device for fastening according to claim 1, characterized in that the stabilizing part is formed by a support plate of toughened is imago material. 20. Turbine, characterized in that it contains at least one device for fastening the guide nozzle apparatus according to claim 1. 21. The engine of the aircraft, characterized in that it contains a turbine according to clause 16 and/or at least one device according to claim 1.
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