Device for fixation of stationary blade in circular carter of turbo-machine, turbo-reactive engine containing such device and procedure for blade assembly |
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IPC classes for russian patent Device for fixation of stationary blade in circular carter of turbo-machine, turbo-reactive engine containing such device and procedure for blade assembly (RU 2435037):
   
 Diffusion cell of turbojet engine and turbojet engine / 2365762
Diffusion cell of turbojet engine is located between compressor and combustion chamber, is implemented independent from compressor and fixed to outer shell of combustion chamber by means of only one suspension member. Suspension member passes between outer shell and external longitudinal wall of diffusion cell and is formed by the first and the second walls in the form of truncated cone. The first wall in the form of truncated cone passes from outer longitudinal wall of diffusion cell in the direction of combustion chamber. The second wall in the form of truncated cone is affixed to the first wall in the form of truncated cone and passes to compressor between the first wall in the form of truncated cone and outer shell of combustion chamber. The other invention of group relates to turbojet engine, which contains compressor, combustion chamber, specified higher the diffusion cell and cross wall, installed between compressor's stator and outer shell for formation of annular space. Cross wall projects downwards the flow around entrance length of diffusion cell, and specified two walls in the form of truncated cone of suspension member is surrounded projecting downwards by flow part of cross wall.
 Air supercharger for flying vehicles with soft gas-filled wings / 2305652
Proposed device has cylindrical load-bearing body with air intake wells located inside it, bars for securing the body to paramotor and adapter pipe unions of air ducts which are connected with elastic gas lines. Provision is made for air-locking gills.
 Device for control of rotatable blade in compressor / 2304234
Device comprises tie (20), connecting means (8) which define the pivot joint between first end (20a) of the tie and control ring, and units (12) for locking second end (20b) of the tie on pin (30 ) of the blade to be controlled. The clamping members (40) act in the direction transverse to the longitudinal mid plane of the tie for locking the second end of the tie on pin (30) of the blade to provided joint rotation.
 Turbocompressor recirculating device / 2296247
Proposed recirculating device for turbocompressor has ring chamber arranged in zone of free ends of blade rim and radially adjoining main through channel, and great number of guide elements arranged in ring chamber and distributed over its circumference. Possibility is provided for passing of flow in circumferential direction in front and/or rear parts of ring chamber, and guide elements are connected with at least one wall of ring chamber and, as to the rest, they cantilever of freely project into ring chamber. Heads of guide elements pointed to main through channel lie on and/or near line limiting its contour and are axially overlapped with free ends of blade or adjoin, in axial direction, zone in which free ends of blades are located.
 Compressor guide-vane assembly and device to control vane in this assembly / 2295655
Invention relates to device to control vane with adjustable angle and to guide-vane assembly of turbomachine compressor. Proposed device has tie-rod 30, connectors 24 forming hinge between first end 32 of tie-rod and control ring and locks of second end 34 of tie-rod on vane trunnion 12 of vane to be controlled, and radial cavity 16 made in vane trunnion and designed to take in second end of tie-rod. Said cavity has at least one flat side wall 16 a tilted relative to longitudinal middle plane P of cavity and engaging with corresponding tilted side wall 34a of second end of tie-rod, and tightening cover 44 fitted on second end of tie-rod which is exposed to action of locks. Said tightening cover has inner surface 48a forming flat contact with outer surface 36 of second end of tie-rod to hold second end of tie-rod on vane trunnion without clearance owing to contact between said tilted side walls.
 Guide apparatus of axial-flow hydraulic pump and method of manufacture of such apparatus / 2267655
Guide apparatus consists of external and internal shells whose surfaces are directed towards flow passage; they are used as boundaries of flow passage and are made in form of cone-shaped bodies of revolution. Shells are interconnected by means of blades of guide apparatus; they have hydrodynamic form. External and internal shells and blades of guide apparatus are made from sheet material and are connected by welding; streamlined surface of guide apparatus blade is formed by surfaces which are equidistant relative to middle surface which is linear surface in shape obtained during motion of section of straight line whose ends move over sections of smooth curves lying on inner surface of external shell and on outer surface of internal shell. External and internal shells and guide apparatus blades are manufactured as separate parts from sheet material. They are cut from developed views on sheet. Then leading and trailing edges of blades are thinned by chamfering; then blanks are bent in multi-purpose die for obtaining three-dimensional hydrodynamic shape of blade; then, parts are assembled by means of welding.
 Stator of gas-turbine axial-flow compressor / 2247872
Invention relates to stator of gas-turbine axial-flow compressor containing rigid outer ring equipment 2, rings 4a, 4b, 4c axially adjoining each other and arranged inside relative to said equipment 2 and carrying rims of fixed guide vanes 5. Said rings are formed by ring sectors 7 secured on equipment 2 whose inner wall limits aerodynamic channel passing compressed gaseous medium in outer direction differing in that ring sectors 7 are essentially soldered sectors formed by filler of cellular structure 8 enclosed between inner sheet 10 limiting said aerodynamic channel and outer sheet 9 and that tie with equipment 2 is provided only by means of outer sheet 9.
 Pressure diffuser axial compressor / 2235921
The invention relates to mechanical engineering and can be used in axial compressors of gas turbine plants with internal combustion chamber arranged vertically with respect to the axis of the machine
 Stage turbomachine / 2148732
The invention relates to aircraft engine industry and can be used in the compressors of gas turbine engines
 A device for the release of gases from the measured / 2144986
The invention relates to the field of turbine construction and is intended for use in industrial installations
 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.
 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.
 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.
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FIELD: machine building. SUBSTANCE: 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. EFFECT: simplified installation of stationary blade in circular carter of fan of turbo-reactive engine. 10 cl, 5 dwg
The present invention relates to the field of turbomachines, in particular turbojet engines. Turbofan engine to ensure the safety of transport aircraft contains the fan is usually installed at the entrance and creates an annular air stream containing the Central primary ring part of powering the motor that spins the fan, and the outer secondary annular part, which is released into the atmosphere, creating a large part of tractive effort. The fan is a Carter fan, limiting outside secondary circuit. Carter primary circuit separates the primary flow from the secondary flow at the level of the separation of the sock. The present invention relates to the mounting and installation of fixed blade profiles or blades directing vanes installed at the outlet of the fan. Installation of blades directing vanes in a turbine engine is a fairly common technology for engines of medium size type CFM. This mounting technology is traditionally called mounting type slot/support". It is used for mounting blades of a straightening apparatus, for example, in the secondary circuit between the case fan and crankcase primary circuit for rectification of the secondary flow along the axis number is I, shown in figure 1. Within this application the stationary blade includes a cylinder formed by the platform with two edges, one of which forms a cutting edge, and the other rear edge, and a pen and a leg. Carter fan includes a circumferential annular groove made in its inner wall and containing the front Board and the rear Board, the head of the scapula is fixed by injecting site in the annular groove. The platform is held in the annular groove by means of two fastening screws, which are screwed up in the space, respectively, on each side of the sides of the pen, as shown in figure 1. At the other end of the pen leg of the scapula is held by introducing into the hole made in the casing of the primary path. For engines of medium size radial engine size is sufficient so that the technician can manipulate the blades between the sump of the primary circuit and Carter fan, that is, rotate them and move forward movement without fear of collision with the case or with other previously installed blade. Blades are available back, i.e. at the exit of the blades in the secondary circuit, which facilitates the operation, maintenance and replacement of worn blades. When compared with the engine of medium size at a given number of blades, the linear density of the blades on p is referee Carter fan above the motor of small size, although the angular density remains the same. This creates several problems arising in the place of fixed blades. Pad, peripheral size which is chosen large to install the mounting screws are located close to each other on the periphery of the crankcase. In this case, the introduction of the blades in the engine difficult, in particular, during installation of the vanes in the annular groove Carter fan, because moving in the transverse direction is limited. The screws securing the venues that are located respectively on each side of the sides of the pen is inserted between two adjacent feathers, making it difficult to access them when using davinciaudio tools. An example of this type of device mounting blades is the device according to patent FR 2859509. The present invention is to eliminate the above disadvantages and to develop the device mounting and installation method of stationary blades in the annular sump, providing a quick and easy mounting of the blades in the sump. In this regard, the applicant proposes a device for fastening the stationary vanes of a turbomachine in the annular sump of the turbomachine, the blade includes a cylinder formed by the platform with two edges, one of which forms a cutting edge, and the other rear edge, with the o-ring crankcase contains the circumferential annular groove, made in the inside wall and containing the front Board and the rear Board, and the blade is held by introducing a site in the ring groove of the front edge of the front Board and the rear edge to the rear side of the annular groove, while the rear side of annular groove made in the form of a groove with an axial aperture, directed forward, while the rear edge of the pad is inserted in said rear wall and install the retaining means designed to hold the platform in the annular groove at the entrance, characterized in that the blade contains a plot of ground between the pen and the front edge containing a through hole made with possibility of installation mentioned fastening means. Preferably, the front Board annular groove does not require the use of separate fastening means, which facilitates insertion and fastening of the blades in the crankcase. The fastening tool set only on the inlet vanes, which allows mounting of the blades from the front side of the engine and not on each side of the feathers. In this case, the fastening means easily accessible for the mounting of tools that allows you to quickly produce the attachment site in the annular groove. Preferably, the fastening tool was made in the form of one or two screws. Preferably, the screw or two screws were stable the s near the front edge of the platform for securing it in the annular groove. The availability of the screws in the front makes it easy to use davinciaudio tools. Preferably, between the rear edge of the platform and the bottom of the said groove was made layer of elastomeric material. Preferably, the elastomeric material is allowed to absorb the displacement of the blades from input to output while straightening the blade coming from the fan air flow. The object of the present invention is also turbofan engine with the front fan, which contains a set of fixed blades, forming a straightening device for straightening the flow at the exit of the fan rotor, and blades which are held inside the crankcase of the fan, using the device in accordance with the present invention. Preferably, the blades were located between the case fan and the case of the primary circuit, while the legs of the blades is inserted with a clearance into the holes made in said crankcase primary circuit, and in this gap install the seal. Preferably, the gasket was installed in the gap to prevent the penetration of air flow into the crankcase of the primary path. Preferably, the blades and the crankcase of the primary beam were made from metal or comp the attributes of the material. The object of the present invention is also a method of mounting the blades set, according to which the blade is inserted the pin into the said hole, the blade tips so to insert the rear end of the platform in the rear groove of the circumferential annular groove, the blade rotates around the grooves, drawing it forth unto the going down of the front edge of the platform in the annular groove and a platform attached to the crankcase by means of fixing means. Preferably, the method of mounting it possible to set the blade between the case fan and crankcase primary flow while limiting lateral movement of the blades relative to the axis of the engine and facilitating radial movement. Preferably around the pen near the legs of the previously installed gasket. Preferably, the blade is not bent during installation to install the gaskets, and put together with a gasket, pre-attached to the pen. Preferably, between the rear edge of the platform and the bottom of the grooves was performed layer of elastomeric material. Preferably, the layer of elastomeric material applied before the introduction of the scapula to amortize its offset. The present invention will be better understood from the following description given with reference to alagaesia drawings. Figure 1 depicts a view in section of a turbojet engine with blades directing vanes at the outlet of the fan is fixed with the fastening device of the prior art. Figure 2 is a view in isometric of blades fixed in the circular crankcase in accordance with the present invention. Figure 3 is a view in ISO mounting pad blades in the casing of the fan in accordance with the present invention. 4 is a view in section of the mounting of the blades in the casing of the fan in accordance with the present invention. 5 is a schematic view of a leg of blades inserted into the hole of the primary sump, as shown in figure 2. As shown in figure 2, the stationary blade 10 or blade profile 10 of a straightening apparatus in this case is installed in the channel of the secondary circuit bypass turbofan engine at the output of the fan between the crankcase 20 of the fan and crankcase 30 of the primary circuit. The blade 10 includes a head 12 formed by the platform 14, with two edges - front edge 141 and the rear edge 142, pen 11 and the leg 13. In this case, the blades 10 and the crankcase 30 of the primary circuit are made of metal, but can also be run from a composite material. The blade 10 is placed in the circuit in the radial direction, while the leg 13 is directed towards the axis of the engine, so Pero contains front edge 151 and the rear edge 152, this space 14 is essentially perpendicular to Peru 11. In this case, the platform 14 is in the form parallelepipedal block, the thickness of which decreases from the leading edge 141 to the rear edge 142, while the front edge 141 terminates at its front end by a ledge 1411 performed on the side of the pad in contact with the crankcase 20, and the ledge 1411 facilitates insertion site 14 in the sump 20. The rear edge contains a plot 1421 rounded. The platform 14 includes two through holes 17, 18, performed at the level of the land area between the front edge 141 and the stylus 11. Each of the holes 17, 18 are made with the possibility of going into it fixing means 40. The crankcase 20 of the fan has a circumferential annular groove 23 made in its inner wall, in which the insert pad 14. The annular groove 23 includes a front Board 21 and rear wall 22. The tailgate 22 is in the form of grooves of circular cross section with an axial mouth pointing towards the entrance. The blade 10 is held by introducing its platform 14 in the annular groove 23 of the front edge 141 to the front Board 21 and the rear edge 142 to the rear side 22 of the annular groove 23. The rounded section 1421 of the rear edge 142 communicates with the groove 22. Between the front side 141 and the front edge 21 perform a gap to facilitate the introduction of the platform 14 in calcev the second groove 23. Between the rear edge 142 of the pad 14 and the bottom of the said groove 22 perform the layer of elastomeric material. The elastomer 60 allows you to limit the displacement of the blade 10, when it is acted by forces from the flow of air from the fan. The layer 60 of elastomeric material includes a locking tongue 61, protruding in the radial direction and communicating with the recess 25, is made in the inner wall of the annular groove 23 near the groove 22, and the tongue 61 holds the elastomeric layer 60 at the bottom of the groove 22. The pad 14 is held in the annular groove 23 by means of screws 40 passing through holes 17, 18, as shown in figure 3. As shown in figure 4, in this case the two screws 40 set at the level of the front edge 141 for mounting heads 12 of the blade 10. At the other end of the blade 10 to the leg 13 is inserted with a gap in the through hole 31 made in the crankcase 30 of the primary circuit, as shown in figure 5. At the level of the legs 13 on the feather 11 wearing a sealing gasket 50 for sealing attachment of the blades 10 in the casing 30 relative to the air. The installation of fixed blades 10 can also be accomplished from the entrance. First back in the groove 22 installing elastomeric gasket 60 and separat it with radially protruding tongue 61 in the recess 25 of the annular groove 23. When the elastomer 60 prig is anxious to the bottom of the groove 22. Then through the leg 13 of the blade 10 on the feather 11 wearing a ring sealing gasket 50, which moves above its end position, so as not to cover the end of the leg 13 of the blade 10. After that, with the gasket 50, the raised pen 11, the blade 10 in an inclined position and with the leg 13 directed towards the exit, is inserted into the through hole 31 of the crankcase 30 of the primary circuit. The leg is moved from input to output on its end position in said crankcase 30 to maintain clearance for straightening vanes 10. Then the head 12 of the blade 10 raise in the rear direction, the leg 13 is directed into the hole 31, and the rounded section 1421 of the rear edge is inserted into the groove 22 of annular groove 22, the groove 22 is pre-covered with an elastomeric layer 60. After that, the blade 10 rotates around the groove 22 by moving the blade 10 forward until the front edge 141 of the platform 14 will not come into contact with the bottom of the annular groove 23, and the gap left between the front side 21 and the front edge 141, facilitates the introduction of the platform 14 in the annular groove 23. Thereafter, an annular gasket 50 is moved by sliding along the pen 11, and the spacer 50 fills the gap between the blade 10 and the hole 31. The spacer 50 made in this case, the elastomeric material during injection can be compressed, and the ZAT is decompressed after as it turns out between the blade 10 and the hole 30, making the mounting of the blades 10 in the housing 20 is sealed with respect to the air. Finally, the platform 14 is stationary connected to the crankcase 20 by screwing screws 40 at the level of the front edge 141 of the platform 14 to its mounting in the annular groove 23. Screwing perform using davinciaudio instruments, as the front edge 141 is easily accessible from the front side of the engine. In another embodiment, prior to slipping the gasket 50 in the lower sealed position, you can also partially tighten the screws 40 into the space 14 so as to maintain clearance during installation of the gasket 50. After you install the gasket 50 in place of the mounting platform 14 in the annular groove 23 complete, providing, thus, protecting the whole site. During operation, the air coming from the fan, SpryAssets along the axis of the turbojet engine as the seal 50 prevents air to enter the crankcase 30 of the primary circuit, and the elastomeric layer 60 absorbs the displacement of the blade 10. When damage to the blades 10 can be easily replaced by operations of the installation in the reverse order, and the elastomer 60 in case of wear can be easily changed. Describe the methods of mounting and Dismounting the blade 10 can also be applied to engines with high linear density lo is atok on the circumference of the crankcase 20. These methods are particularly preferred for engines of small size, blades 10 which are located very close to each other. 1. The mounting device is stationary blades (10) are measured in the annular casing (20) fan of the turbomachine, the blade (10) comprises a head (12)formed by the space (14) with two edges (141, 142), one of which forms a cutting edge (141), and the other forms the rear edge (142), pen (11) and the foot (13), while the o-ring crankcase (20) includes a circumferential annular groove (23)made in its inner wall and containing the front side (21) and the rear side (22), the blade (10) is held by introducing a platform (14) in the annular groove (23) of the front edge (141) to the front Board (21) and the rear edge (142) to the rear side (22) of the annular groove (23), while the rear side (22) of the annular groove (23) made in the form of grooves (22) with the axial mouth, directed forward, while the rear edge (142) ground (14) is inserted in the above-mentioned rear wall (22) and install the retaining means (40)designed to hold the pad (14) in the annular groove (23) on the input, characterized in that the blade (10) contains a plot of the area (14) between the pen (11) and the front edge (141)containing a through hole (17), made with the possibility of installation mentioned fastening means (40). 2. The device according to claim 1, in which the fastening means is the tsya screw (40). 3. The device according to claim 1, in which the fastening means comprises two screws (40). 4. Device according to one of claims 1 to 3 containing layer (60) made of elastomeric material between the rear edge (142) ground (14) and the bottom of the said groove (22). 5. Turbofan engine with a front fan, containing a set of stationary blades (10), forming a straightening device for straightening the flow at the exit of the fan rotor in which the blades (10) are held inside the casing (20) fan, using the device according to one of the preceding paragraphs. 6. Turbojet engine according to claim 5, in which the blades (10) are located between the crankcase (20) fan housing (30) of the primary loop, with the legs (13) of the blades (10) is inserted with a clearance into the holes (31), is performed in the above-mentioned casing (30) of the primary circuit, and in this gap install gasket (50). 7. Turbojet engine according to one of the subparagraph 5 or 6, in which the blades (10) and the casing (30) of the primary beam are made of metal or composite material. 8. The method of mounting the stationary vanes turbojet engine according to one of pp.5-7, according to which the blade (10) insert the leg (13) in said hole (31), the blade (10) incline thus, to insert the rear edge (142) ground (14) in the rear groove (22) of the district of annular groove (23), l is petcu (10) turn around grooves (22), bringing the blade (10) forward unto the going down of the front edge (141) site (14) in the annular groove (23), and pad (14) is fixed to the casing (20) by means of fixing means (40). 9. The method according to claim 8, in which around the pen (11) near the legs (13) pre-install gasket (50). 10. The method according to one of p or 9, in which between the rear edge (142) ground (14) and the bottom of the groove (22) through the layer (60) of elastomeric material.
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