Gas turbine engine blade assembly and gas turbine stator with said assembly |
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IPC classes for russian patent Gas turbine engine blade assembly and gas turbine stator with said assembly (RU 2448258):
  
 Sleeve of hinge for blade with adjustable setting angle of turbomachine, turbomachine ring containing such sleeves, as well as compressor of turbomachine and turbomachine containing such ring / 2443870
Sleeve of blade hinge with adjustable setting angle, which is installed into the cavity in turbomachine ring, includes tubular housing around longitudinal axis and devices preventing the rotation in the ring cavity. Tubular housing of sleeve has the first conical annular projection located on one of its ends and the other conical annular projection located on the opposite end. Conical surfaces formed with the first and the second annular projections face each other. Devices preventing the sleeve rotation in the ring cavity include the plate having at least one surface for establishment of flat contact with the corresponding surface of the plate for prevention of rotation of the neighbouring sleeve. One more invention of the group refers to turbomachine ring containing multiple cavities to arrange the hinge and multiple sleeves made as described above. Other inventions of the group refer to turbomachine compressor and turbomachine, each of which includes at least one of the above said rings.
 Stator blade of gas turbine engine with adjustable setting angle, and gas turbine engine / 2436967
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.
 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.
 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: turbine blade assembly comprises cases of low- and high-pressure sides with front edge, rear edge and convex or concave surface there between to form radial outer and inner edges as well as radial inner and outer deck. Every case has inner and outer flanges extending from outer and inner edges, respectively. Radial inner deck comprises multiple lengthwise grooves to receive radial inner flanges of cases of low- and high-pressure sides. Radial outer deck comprises multiple lengthwise grooves to receive radial outer flanges of cases of low- and high-pressure sides. Another invention relates to gas turbine stator comprising blade assembly and radial inner and outer decks. Blade assembly comprises blade, radial inner and outer face plugs and clamping element arranged there between. Blade extends radially between said plugs and comprises cases of low- and high-pressure sides. Clamping element supports cases of low- and high-pressure sides in definite relative orientation and relative to inner and outer face plugs. Radial inner deck comprises lengthwise groove to accommodate radial inner face plug while radial outer deck comprises lengthwise groove to receive radial outer plug. EFFECT: simplified production of blades from ceramic composite materials. 3 cl, 4 dwg
The present invention relates generally to gas turbine engines and more specifically, to an Assembly of turbine blades of the specified motor and the stator. At least some known gas turbine engines burn the fuel-air mixture in the Assembly of the combustion chamber and produce a flow of the working gas, which is supplied to the turbine Assembly through the hot gas path. Compressed air is supplied to the Assembly of the combustion chamber through the compressor Assembly. Assembly of the combustion chambers typically include a fuel Assembly of blades that contribute to the delivery of fuel and air in the combustion zone of the Assembly of the combustion chamber. The turbine Assembly converts thermal energy of the flow of working gas into mechanical energy that rotates the shaft of the turbine Assembly. The product of the turbine Assembly can be used in a power machine such as a generator or pump. Known Assembly of a turbine blade for a gas turbine engine containing casing low pressure side having a front edge, a back edge and a convex surface between them, and the casing of the high pressure side having a front edge, a back edge and a concave surface between them, while the front edge of the casing side low pressure and front edge of the housing side high pressure supported relatively close to on the uh-huh (see U.S. patent 5584652, 1996). Known gas turbine stator containing the Assembly of the blade containing the blade and the cap, the blade passes radially from the stub casing and contains the high pressure side and a separate casing side low pressure (see U.S. patent 5584652,1996). Known assemblies of blades include a lot of parts made of different materials, which are difficult to produce. One such material is laminated ceramic matrix composite. Typically the laminated ceramic matrix composite has a different thickness of the lamination. A suitable thickness of the laminate ensures efficient operation of the fuel Assembly of the scapula. In addition, the laminated ceramic matrix composite has a limited ability to achieve a relatively small bend radius without cracking. Moreover, joining the inclined part of the aerodynamic surface of the blade to the blade platform is a complex procedure. Ceramic matrix composite vane can also be difficult to verify after installation of the scapula. Many famous Assembly of turbine blades include a variety of parts made in connection with the platform of the gas turbine engine. Blade of laminated ceramic matrix composite which may be difficult for the structural attachment to the platform of the gas turbine engine, if you are using a non-integral platforms. The interlaminar stresses in tension in the edges exist when moving blades in the platform, if you are a single platform. Moreover, the laminated ceramic matrix composite makes difficult the control of the resonant frequencies. It is important to minimize interlayer voltage by maintaining in-plane load, where possible. A BRIEF summary of the INVENTION According to the invention the generated Assembly turbine blade for a gas turbine engine containing casing low pressure side having a front edge, a back edge and a convex surface between them, the housing of the high pressure side having a front edge, a back edge and a concave surface between them, each of the convex and concave surfaces forms a radial outer edge and a radial inner edge, the radial outer end cap for connection with the radial outer edges of the casing side of the low pressure casing of the high pressure side, the radial inner end cap for connection with the radial inner edges of the casing side of the low pressure and the shroud side high pressure and clamping element located between the outer end cap and the inner end cap and designed to be supported by the I casing of the high pressure side and the shroud side of the low pressure, essentially, a fixed orientation relative to each other and relative to the outer end cap and the inner end cap, and the front edge of the casing side low pressure and front edge of the housing side high pressure supported relatively close to each other. At least one of the casing side of the low pressure casing of the high pressure side may be made of a ceramic matrix composite. The radial inner end cap may be designed for connection with a longitudinally oriented slot of a stator of the turbine, and a radial outer end cap is designed for connection with other longitudinally oriented slot of a stator of the turbine. The front and rear edges of the casing side of the low pressure casing of the high pressure side may contain a corresponding mating surface for the formation of a winding path between them, including at least one of the following items: overlap, a protrusion, a groove, a V-shape and the sealing element. The Assembly may further comprise a radial outer platform containing longitudinally oriented groove for receiving the radial outer end cap, and a radial inner platform containing longitudinally oriented groove for receiving radiation is Inoi inner end caps, with the front and rear edges of the casing side of the low pressure casing of the high pressure side contain the corresponding mating surface for the formation of a winding path between them, including at least one of the elements overlap, the protrusion and groove, V-shape and the sealing element. In another embodiment, the Assembly of the turbine blade for a gas turbine engine includes a casing low pressure side having a front edge, a back edge and a convex surface between them, forming a radial outer edge and a radial inner edge and including a radial outer flange extending from the radial outer edge, and a radial internal flange extending from the radial inner edge, the casing of the high pressure side having a front edge, a back edge and a concave surface between them, forming a radial outer edge and a radial inner edge and including a radial outer flange extending from the radial outer edge, and radial internal flange extending from the radial inner edge of the radial inner platform containing multiple longitudinally oriented grooves for receiving radial internal flange of the casing of the low side pressure and the shroud side high pressure, and radiation is inuu external platform, containing numerous longitudinally oriented grooves for receiving the radial external flange of the casing of the low side pressure and the shroud side pressure. According to the invention results from the gas-turbine stator containing the Assembly of the blade containing the blade, the radial outer end cap, radial inner end cap, the clamping element located between the radial outer end cap and the radial inner end of the plug, while the blade is held radially between the said plug and casing contains the high pressure side and a separate casing side low pressure, the clamping element is designed to maintain the casing of the high pressure side and the shroud side of the low pressure in essentially fixed orientation relative to each other and relative to the outer end cap and the inner end cap, and a platform for the Assembly of the blade. The casing of the high pressure side may contain a front edge, a back edge and a concave surface between them, cover the side of low pressure may include a front edge, a rear edge and a convex surface between them, while the front edge of the casing side low pressure and front edge of the housing side high pressure supported relatively close to each other, is, at least one of the casing side of the low pressure casing of the high pressure side is made of a ceramic matrix composite. Hereinafter the invention is described in more detail with reference to the accompanying drawings, which depict the following: figure 1 - schematic view of a typical gas turbine engine; figure 2 - cross section of a typical gas turbine Assembly with a three-stage nozzle that can be used with gas turbine engine of figure 1; figure 3 - schematic view of Assembly of a ceramic matrix composite turbine blades, which can be used with gas turbine engine of figure 1; 4 is a schematic view of an alternative implementation of an Assembly of ceramic matrix composite turbine blades, which can be used with gas turbine engine of figure 1. Figure 1 shows a typical gas turbine engine 100 includes a compressor 102 and chamber 104 combustion. The camera 104 of the combustion zone includes 105 combustion and Assembly 106 of the fuel injectors. The engine 100 also includes a turbine 108 and the total for the compressor and turbine shaft 110 (sometimes referred to as the rotor 110). In one embodiment, the implementation of the engine 100 is engine MS7001FB, sometimes specified as the engine 9FB, manufactured by General Electric company, Greenville,South Carolina. The present invention is not limited to any one particular engine and may be implemented in connection with other engines, including, for example, MS7001FA (7FA) and MS9001FA (9FA) model motors company General Electric. In the action of the air flows through the compressor 102 and compressed air are fed into the chamber 104 of the combustion. Specifically, compressed air is supplied to the Assembly 106 of the fuel injectors, which is part of the camera 104 combustion. Assembly 106 is in communication with the area 105 of combustion. Assembly 106 of the fuel injectors also communicated with a fuel source (not shown in Fig.1) and the channels of fuel and air in the area 105 of combustion. The camera 104 combustion ignites and burns the fuel. The camera 104 combustion associated with the turbine 108, for which thermal energy of the gas stream is converted into mechanical energy of rotation. Turbine 108 is connected with a possibility of rotation and drives the rotor 110. The compressor 102 is also connected for rotation with the shaft 110. In a typical embodiment uses multiple cameras 104 of the combustion chamber Assembly 106 of the fuel injectors. In the following description, unless otherwise specified, will be considered only one of each component. Shown in figure 2, the turbine Assembly 108 with a three-stage nozzle can be used with gas turbine engine 100 of figure 1. The turbine Assembly 108 includes Assembly 112 of the blade. The Assembly 112 is opacki held in the turbine Assembly 108 radial external platform 114 and the radial inner platform 116. Shown in figure 3 Assembly 112 of the turbine blades can be used with gas turbine engine 100 of figure 1. The Assembly 112 of the turbine blades includes a housing 118 of the low pressure and the casing 120 of the high-pressure side. In a typical embodiment, the casing 118 of the low pressure and the casing 120 of the high-pressure side is made of a ceramic matrix composite. Ceramic matrix composite promotes the densification of the scapula. The casing 118 of the low pressure includes a front edge 122 and the rear edge 123. The casing 120 of the high-pressure side includes a front edge 124 and the rear edge 125. The casing 118 of the low pressure includes a convex surface, and the casing 120 of the high-pressure side includes a concave surface. Concave and convex surface - ergonomic contours that guide or reorienting the flow of gaseous products of combustion through the blade. The leading edge 122 and the front edge 124 installed in relatively close proximity. The leading edge 122 and the front edge 124 can be positioned close to or depart at a very small distance between them. The leading edge 122 and the front edge 124 contain mating surface formed for forming a tortuous path. This trajectory can be formed, is using, for example, but not limited to, the overlapping ledge and groove, V-shape or sealing element. The rear edge 123 and the rear edge 125 is also set relatively close to each other. The rear edge 123 and the rear edge 125 may be positioned close to or depart at a very small distance between them. The rear edge 123 and the rear edge 125 contain mating surface, formed by a winding path. This trajectory can be formed using, for example, but not limited to, the overlapping ledge and groove, V-shape or sealing element. The casing 118 of the low pressure includes a radial outer edge 126 and a radial inner edge 127. The casing 120 of the high-pressure side includes a radial outer edge 128 and the radial inner edge 129. The casing 120 of the high-pressure side is in contact with the contour of the recess 130 in the outer end cap 132 and the inner end cap 134, as well as the casing 118 of the low pressure comes in contact with the contour of the recess 130 in the outer end cap 132 and the inner end cap 134. The radial outer edge 126 is aligned with the recess 130 in the outer end cap 132. The radial outer edge 128 is aligned with the recess 130 in the outer end cap 132. Radial internal chrome is and 127 aligned with the recess 130 in the inner end cap 134. The radial inner edge 129 is aligned with the recess 130 in the inner end cap 134. The clamping element 136 has a radially between the outer end cap 132 and the inner end cap 134. The clamping element 136 helps to hold the casing 120 of the high-pressure side and the casing 118 of the low pressure firmly in a fixed position relative to each other. In addition the clamping element 136 carries the structural load on the Assembly 112 of the blade to facilitate the involvement of the casing 120 of the high-pressure side and the casing 118 of the low pressure, providing aerodynamic contours. In a typical embodiment, the radial outer end cap 132 includes a mounting part 133. Fastener 133 are connected by a threaded clamping element 136. The connection of the outer end caps 132 and inner end caps 134 with a clamping element 136 holds the casing 118 of the low pressure casing 120 of the high-pressure side, the clamping element 136, the outer end cap 132 and the inner end cap 134 in a fixed orientation relative to each other. In an alternative embodiment, the clamping element 136 includes an offset element, for example element memorizing shapes, metal spar and/or spring. The clamping element 136 can IP alsowhat cooling air to help reduce heating of the clamping element 136 and/or blades. The clamping element 136 may include one or more jumpers 137, passing in the longitudinal direction from the clamping element 136. Jumper 137 and its specified position helps reduce vibration of the blades, with regard to specific critical forms a resonant mode. The Assembly 112 of the turbine blades includes a radial outer platform 114 and the radial inner platform 116. Radial internal platform 116 has a lot of longitudinally oriented grooves 139 located on the same circle around the platform 116. The radial outer platform 114 has a lot of longitudinally oriented grooves 138 located on the same circle around the platform 114. The groove 138 is configured to receive the radial outer end cap 132. The groove 139 is configured to receive the radial inner end cap 134. Figure 4 shows an alternative implementation of the Assembly 112 of the turbine blades, which can be used with gas turbine engine 100 shown in figure 1. The Assembly 112 of the turbine blades includes a housing 140 of the low side pressure and the shroud 142 the high pressure side. In a typical embodiment, the casing 140 of the low pressure casing 142 of the high-pressure side is made of a ceramic matrix composite. Ceramic matrix composite pic is of bstweet elimination breaks the seal. The casing 140 of the low pressure includes a front edge 160 and the rear edge 162. The casing 142 the high pressure side includes a front edge 164 and the rear edge 166. The casing 140 of the low pressure includes a convex surface, and the casing 142 the high pressure side includes a concave surface. Concave surface and convex surface - ergonomic contours that guide or reorienting the flow through the blade. Front edge 160 and the front edge 164 are located in relatively close proximity. Front edge 160 and the front edge 164 may be positioned close to or depart at a very small distance between them. Front edge 160 and the front edge 164 contain mating surface forming a winding path. This trajectory can be formed using, for example, but not limited to, the overlapping ledge and groove, V-shape or sealing element. The back edge 162 and the rear edge 166 is also installed in relatively close proximity. The back edge 162 and the rear edge 166 may be positioned close to or depart at a very small distance between them. The back edge 162 and the rear edge 166 contain mating surface forming a winding path. Twisted path can be formed using, for example, is not limited to, overlap the protrusion and groove, V-shape or sealing element. The casing 142 the high pressure side includes a radial outer flange 144 extending from the radial outer edge 146 of the concave surface, and the casing 142 of the high-pressure side also includes a radial internal flange 143 extending from the radial inner edge 148 of the concave surface. The casing 140 of the low pressure includes a flange 150 extending from the radial outer edge 147 of the convex surface, and the casing 140 of the low pressure also includes a flange 151 extending from the radial inner edge 14 9 convex surface. The Assembly 112 of the turbine blades includes a housing 142 of the high-pressure side and the casing 140 of the low pressure. Radial internal platform 174 has a lot of longitudinally oriented grooves 170 located on the same circle around the platform 174. The radial outer platform 176 has a lot of longitudinally oriented grooves 172 located on the same circle around the platform 176. The groove 172 is configured to receive external radial flange 150 and a radial external flange 144. The groove 170 is configured to receive radial internal flange 151 and a radial internal flange 143. Although the invention has been described in terms of various individual vari is now implementation specialists in the art will recognize that the invention can be implemented with modification within the essence and scope of the claims. 1. Assembly of the turbine blade for a gas turbine engine containing casing low pressure side having a front edge, a back edge and a convex surface between them, forming a radial outer edge and a radial inner edge and including a radial outer flange extending from the radial outer edge, and a radial internal flange extending from the radial inner edge, the casing of the high pressure side having a front edge, a back edge and a concave surface between them, forming a radial outer edge and a radial inner edge and including a radial outer flange extending from the radial outer edge, and a radial internal flange, passing from the radial inner edge of the radial inner platform containing multiple longitudinally oriented grooves to accommodate radial internal flange of the casing of the low side pressure and the shroud side high pressure, and radial outer platform containing multiple longitudinally oriented grooves to accommodate radial external flange of the casing of the low side pressure and the shroud side high the th pressure. 2. Gas turbine stator containing the Assembly of the blade containing the blade, the radial outer end cap, radial inner end cap, the clamping element located between the radial outer end cap and the radial inner end of the plug, while the blade is held radially between the said plug and casing contains the high pressure side and a separate casing side low pressure, the clamping element is designed to maintain the casing of the high pressure side and the shroud side of the low pressure in essentially fixed orientation relative to each other and relative to the outer end cap and the inner end cap and the platform for the Assembly of blades containing radial internal platform containing longitudinally oriented groove for accommodating the radial inner end caps, and a radial outer platform containing longitudinally oriented groove for accommodating the radial outer end of the stub. 3. Gas turbine stator according to claim 2, in which the casing of the high pressure side includes a front edge, a rear edge and a concave surface between them, cover the side of low pressure contains a front edge, a back edge and a convex surface between them, while the front edge of the casing side Nizkor the pressure and the front edge of the housing side high pressure supported relatively close to each other, and at least one of the casing side of the low pressure casing of the high pressure side is made of a ceramic matrix composite.
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