Rotary machine (versions) and method of composite working wheel fastening on metal shaft of rotary machine

FIELD: machine engineering.

SUBSTANCE: rotary machine comprises a stator and a rotor rotatable with relative to the stator and having a metal shaft, a composite working wheel and at least a first metal ring fastening the composite working wheel on said metal shaft. The composite working wheel comprises a composite portion and a metal fixing portion connected to each other, and having a bushing and a radially extending portion that extends radially outward from the bushing. The metal ring has a first engaging surface with a metal fixing portion of the composite working wheel and a second engaging surface with a metal shaft, thereby force applied by the metal ring to the metal fixing portion of the composite working wheel allows to prevent movement between the composite working wheel and the metal shaft. According to another version, the metal ring is mounted on metal fixing portion of the composite working wheel and the metal shaft by a hot fit. When the composite working wheel is secured on the metal shaft of the rotary machine, the composite working wheel is mounted on the metal shaft, and the first metal ring is heated. The metal ring is then mounted on the metal shaft in order to cool and shrink the metal ring for engaging the metal fixing portion of the composite working wheel and the metal shaft.

EFFECT: group of inventions allows to secure the working wheel including the composite portion to the metal shaft and protect such working wheel from heat radiation of metal fixing ring.

7 cl, 12 dwg

 



 

Same patents:

Turbine airfoil // 2554737

FIELD: transport.

SUBSTANCE: turbine airfoil comprises aerodynamic body, heat protection system existing in coated surface zone and uncoated surface zone with no heat protective coat. Uncoated surface zone extends on airfoil outer surface lower pressure side from trailing edge to leading edge up to interface between surface coated zone and surface uncoated zone. Said interface is located at lower pressure side between leading edge and trailing edge while airfoil body comprises step in outer surface extending along said interface. Another invention of the set relates to turbine guide or working vane with abode described turbine airfoil.

EFFECT: better aerodynamics, longer life.

24 cl, 3 dwg

FIELD: process engineering.

SUBSTANCE: for production of said blade, 3D single-piece fibrous workpiece is woven. Fibrous workpiece is shaped to get single-piece fibrous preform with first, second and third parts. First part makes the blade root and butt preform while second part makes the preform of blade inner flange and/or blade outer flange edges. Third part makes the preform of blade inner flange fixture and/or blade outer flange streamlined ledges. Then, fibrous preform is compacted to get the blade of composite with fibrous structure composed by preform and compacted by die. Another invention relates to turbo machine blade from composite including fibrous structure produced by 3D weaving of threads and compacted by die. Said structure has first part making the integral combination with second and third parts. First part makes blade root and butt, second part makes the blade inner flange and/or blade outer flange ledges while third part makes the fixture of inner flange and/or streamlined ledges of the blade outer flange. Parts of fibrous structure corresponding to the first, second and third parts of the blade interweaving threads of fibrous structure first part penetrating into fibrous structure second part. One mote invention of the set relates to turbo machine equipped with aforesaid blade or including blades made as described above.

EFFECT: higher reliability of turbo machine blades.

17 cl, 22 dwg, 1 tbl

FIELD: process engineering.

SUBSTANCE: invention relates to production of metal reinforcing part (30) of turbomachine leading or trailing edge (10). Proposed process comprises fabrication of several elements (30a, 30b, 30s, 30d) with V-like cross-section. Said elements form different sectors of reinforcing part (30) distributed between its root (32) and top (34). Said sectors are places on appliance (40) that reproduces the shape of said edge. Said sectors are connected to make a complete profile of reinforcing part (30) with recombination of different sectors. To make said reinforcing part (30), appliance (40) is used composed of interconnected detachable sectors that make the surface reproducing the shape of leading of trailing edge of turbomachine blade.

EFFECT: perfected method.

13 cl, 6 dwg

FIELD: metallurgy.

SUBSTANCE: protective coating for protection of a structural component of a gas or a steam turbine against corrosion and/or oxidation, namely at high temperatures, which is made in the form of a single metal layer from an alloy containing the following, wt %: cobalt 24-26, chrome 12-14, aluminium 10-12, and 0.2-0.5 of at least one element of the group including scandium and rare-earth elements, and nickel is the rest. The coating has no tantalum, rhenium and silicone.

EFFECT: coating is characterised by high properties of resistance to high-temperature corrosion and oxidation.

4 cl, 5 dwg

FIELD: metallurgy.

SUBSTANCE: invention relates to metallurgy, and namely to nickel-based alloys to manufacture mechanical components of the turbomachines. Nickel-based super alloy for the mechanical component of the turbomachines contains, wt %: chrome - from 3 to 7, tungsten - from 3 to 15, tantalum - from 4 to 6, aluminium - from 4 to 8, carbon below 0.8, nickel and admixtures - rest. Mechanical components made from the specified alloy can operate under high temperatures.

EFFECT: alloy is characterised by high mechanical, chemical and thermal strength.

10 cl, 8 dwg

FIELD: process engineering.

SUBSTANCE: invention can be used for production of turbine moist-steam stage blades. Wear-resistant stellite strap is welded n steel blade leading edge. Note here that refractory solder powder mixed with antioxidant flux is filled in between cleaned contact surfaces of said parts, joint is heated to solder fusion point and strap is pressed to the blade unless solder is solidified after termination of heating. Portion of solder is pre-applied in thin ply on both surface by arc doping using the solder bar as doping electrode. Depth of said solder makes 40-190 mcm. Arc doping is executed at single pulse power of 0.3-0.7 J and specific doping interval of 0.5-1.0 min/cm2. Solder pre-application is performed preferably in vacuum or inert gas.

EFFECT: longer life of blades subjected to impact-drop effects.

2 cl

FIELD: engines and pumps.

SUBSTANCE: outlet straightener vane for the turbojet engine contains extended single-block front and back sections, and also external layer, joined together by hot pressing. The extended single-block front section is cut out from the pultruded profile, containing resin-impregnated fibres, and forms a front edge of the vane. The extended single-block back section is cut out from the pultruded profile, containing resin-impregnated fibres, and forms a back edge of the vane. The external layer is made on the basis of resin-impregnated fibres and located between the front and back edges with forming of lateral sides of the vane. The external layer overlaps the zones of the front and back edges. Another invention of the group relates to the turbojet engine containing multiple vanes, mentioned above, each of which is fixed on the housing.

EFFECT: group of the inventions allows to simplify manufacture and installation of the vane of the turbojet engine.

15 cl, 4 dwg

FIELD: process engineering.

SUBSTANCE: nozzle element is made of composite including fibrous reinforcement compacted by ceramic matrix. It comprises sections of inner and outer bases and at least one blade attached thereto. Base sections extend at every zone of their attachment to the blade. Fibrous reinforcement comprises fibrous structure woven by 3D or multiple ply weaving that features continuity in the entire volume of nozzle element and over the entire periphery of one or every blade. Solid fibrous blank is woven that contains in lengthwise direction, at least the following elements: one pattern including first segment that makes the blade preform blank, second segment extending the first one at its one lengthwise end to make two wings facing each other. Third element extends the first one at its opposite end to make two wings facing each other. This blank is turned to make wings of the second and third segments extend perpendicular to first segment. Blank shape is developed to make fibrous preform of nozzle element. Note here that blade part making the preform is produced by shaping the first segment. Parts that make the preforms of base sections are produced from wings. Then, preforms are compacted by matrix to make a solid nozzle element with fibrous reinforcement. Fibrous reinforcement comprises fibrous structure that features continuity in the entire volume of nozzle element and over the entire periphery of one or every blade. Other inventions of the set relate to turbine nozzle made as described above and to gas turbine with such nozzle.

EFFECT: higher mechanical properties.

15 cl, 30 dwg

FIELD: machine building.

SUBSTANCE: fan rotor blade comprises an airfoil and a tang made from composite material, and a metal shell. The blade tang is made at the base end of the blade airfoil and can be coupled with the groove of a fan disk. The metal shell is attached to the leading edge of the blade airfoil and passes in the direction of the span to protect its leading edge. The metal shell comprises a base part and a pair of connecting flanges extending from its back edges. The metal shell is divided into a base shell segment on the side of the base end of the blade airfoil and an upper shell segment on the side of the upper end of the blade airfoil smoothly extending from the base segment. The length of the upper segment does not exceed the length of the base shell segment in the span direction. The length k of the base part of the shell in the supposed point of the impact amounts to 10% ≤ k ≤ 60% of the chord, and the supposed impact point is located at the distance of 80% of the span from the base shell end. The length m of the shell along the end face edge of the fan rotor blade amounts to m ≥ 40% of the chord. Another invention of the group relates to a fan comprising a disk with a variety of connection grooves on its external periphery and set inside the engine case as well as a variety of the above fan rotor blades coupled with the variety of the connection grooves.

EFFECT: group of inventions allows for the protection of a blade made from composite material against being damaged by a foreign item without significant increase of its weight and deterioration of aerodynamic characteristics.

6 cl, 6 dwg

FIELD: metallurgy.

SUBSTANCE: metal coating of nickel-based alloy for gas turbine parts contains γ and γ' phase and, optionally, β phase. Note here that said alloy contains the following substances, in wt %: tantalum - 0.1-7.0, cobalt - at least 1, chromium - 12-22, preferably, 15-19, aluminium - 5-15, preferably, 8-12. Note also that this alloy does not, preferably, contain silicon (Si) and/or hafnium (Hf) and/or zirconium.

EFFECT: high thermomechanical properties, resistance to oxidation, longer life.

12 cl, 5 dwg

FIELD: chemistry.

SUBSTANCE: invention relates to a multilayered thermal barrier coating on components of a hot path of energy gas turbine installations of high power. The multi-layered thermal barrier includes a basic metal sublayer, made from a nickel-based alloy, an upper ceramic thermal barrier layer and an additional metal thermal barrier sublayer between the basic sublayer and the ceramic layer. The basic metal sublayer contains 18…25% of cobalt, 14…20% of chrome, 11…14% aluminium and 0.1…0.7 yttrium. The upper ceramic thermal barrier layer is made from a material based on zirconium dioxide ZrO2, partially stabilised 6…8% by yttrium oxide weight. The additional metal thermal barrier layer is made from a nickel-based alloy, containing 18…25% of cobalt, 14…20% of chrome, 10…13% of aluminium and 0.1…0.7 of yttrium.

EFFECT: protection against an impact of high temperatures, erosion and corrosion by the formation of long-lasting thermal barrier coatings.

1 ex

FIELD: process engineering.

SUBSTANCE: invention relates to repair of gas turbine blades with at least one worn-out root with one lateral surface that features insufficient size. Note here that application of material on at least one surface is performed so that root features overdimension. Then, the root is machined to remove material from at least one side surface to rated size. Adhesive material is used for recovery of rated size of the root. Note here that adhesive material application is performed for recovery of turbine blade heat-isolation coating system comprising adhesive layer and heat-isolation layer.

EFFECT: efficient recovery with lower costs and material input.

12 cl, 6 dwg

FIELD: metallurgy.

SUBSTANCE: alloy contains the following, wt %: up to 20 of sum of Co and Fe, between 17 and 21 Cr, between 0.5 and 3 of sum of Mo and W, not more than 2 Mo, between 4.8 and 6 Al, between 1.5 and 5 Ta, between 0.01 and 0.2 of sum of C and B, between 0.01 and 0.2 Zr, between 0.05 and 1.5 Hf, between 0.05 and 1.0 Si, and between 0.01 and 0.5 of sum of at least two elements of actinides and rare-earth metals, such as Sc, Y and lanthanides. Content of each element is not more than 0.3. Alloy is used in high-temperature components representing rotating blades, guide vanes, heat shields, seals or parts of a combustion chamber in gas turbines, as well as process alloy for repair welding and/or cladding of such high-temperature components.

EFFECT: alloy has high properties of stability to oxidation, resistance to high-temperature corrosion, strength and ductility, weldability.

21 cl

FIELD: metallurgy.

SUBSTANCE: method to produce a blank of a blade of gas turbine engines (GTE) with ultra-fine grain structure from titanium alloys includes preliminary heating of the blank to temperature below temperature of polymorphous conversion and treatment by means of multiple intensive plastic deformation with changing of deformation directions in several cycles. Treatment is carried out under isothermic conditions at identical temperature of the blank and the punch. In each cycle deformation is carried out at temperature of alloy annealing according to stages, which include setting of the cylindrical blank in the closed punch, open setting with production of the blank in the form of a disc, flattening to the disc rib in the closed punch for production of the blank with the square section, its setting in the closed punch to the cylindrical blank. Number of treatment cycles is determined based on achievement of the extent of accumulated deformation of at least five. Then closed setting of the blank is carried out at the temperature of 50-100°C below the alloy annealing temperature, squeezing into the cylindrical blank, having two different diameters of cross section for a blade foot and airfoil, and flat stamping of the blade blank.

EFFECT: homogeneous ultra-fine grain structure is produced in a blade blank, providing for high physical and mechanical and operating properties of a blade.

2 dwg

FIELD: process engineering.

SUBSTANCE: invention relates to machine building. Proposed method comprises the following jobs: collecting coordinates of points on parts surface. Note here that combination of points forms a cloud, comparing known profile with said cloud to define part bulged or thinner zones, forming said profile by morphing to allow formed profile to interpolate said cloud. Note here that profile deformation defines the function of morphing and profile and comprises comparison of part every bulged or thinner zone with elementary configurations, each representing grid section simulating the profile and points simulating points of aforesaid cloud. Note here that elementary configuration of deformation are classified in data base. Note also that data base related, for every said deformation elementary configuration, the parameters of morphing function. Machining of damaged part is performed at appropriate machine with parameters defined subject to morphing function.

EFFECT: reconditioning of blade aerofoil using adequate model of part current state.

6 cl, 1 ex, 5 dwg

FIELD: machine building.

SUBSTANCE: methods of designing axial or radial turbine blading whereby turbine cascade blade channel is divided into two sections. Channel meridional outline height is varied or not on entire section of bend in blade channel or its part. Second section of acceleration with additional bend or without it comprises skew edge of blade channel wherein said height is decreased toward channel outlet to verge coupled with mouth cross-section. Behind said verge, height is varied to increase open flow area. Narrow area of every blade channel is formed. At second acceleration section, arranged are multiple possible locations of mouth are including that whereat mouth area center is located on turbine cascade front outlet cross-section. Ring ledges are arranged behind outlet area, on periphery, or nearby barrel, or on periphery and barrel at a time.

EFFECT: higher efficiency, lower hydraulic losses.

8 cl, 14 dwg

FIELD: machine building.

SUBSTANCE: hydraulic control unit for blades (2) of impeller (1) of the axial fan comprises regulating cylinder (6), which has first chamber (11) and second chamber (12) on both sides of internal moving piston (7); each of the chambers is linked with control channels (A, B) through connections (14, 15). Control channels (A, B) are connected to the 4-stroke valves. Both supply channel (P) leading to one of control channels (A) and outlet channel (T) connected to another control channel (B) are split into two parallel branches (P1/A1, P2, A2, T1/B1, T2/B2). There are two auxiliary 4-stroke valves (23), (33), each of which is built into one of parallel branches (P1, A1 or P2, B2) and (T1, B1 or T2, B2). There is seated valve (24), (25), (34), (35) closing with a spring force and installed in each branch (A1, A2) of one control channel (A) and in each branch (B1, B2) of the other control channel (B) between relevant connections (14), (15) and corresponding 4-stroke valves (23), ( 33).

EFFECT: control of the blades that ensures that even in case of power failure it is possible to keep the blades in their last position before the incident until another control unit takes over control of the blades position after switching over of the mains supply.

11 cl, 4 dwg

FIELD: metallurgy.

SUBSTANCE: nickel-based superalloy is proposed with a strengthening gamma-line-phase, containing the following components: up to 20 wt% Co, from 12 to 14 wt % Cr, from 1 to 2 wt % Mo, from 1.4 to 2.8 wt % W, from 5.1 to 5.9 wt % Al, from 1.1 to 1.6 wt % Ti, from 3 to 7 wt % Ta, from 0.01 to 0.3 wt % C+Zr+B, from 0.05 to 1 wt % Hf, from 0.05 to 1 wt % Si, and from 0.01 to 0.2 wt % of rare earth elements. Also alloy application as a hot machine component is proposed.

EFFECT: alloy is characterised with high resistance to high-temperature corrosion, oxidation, high compatibility with coatings, phase stability, high resistance to creepage and low density.

12 cl, 1 dwg

FIELD: machine building.

SUBSTANCE: impeller of centrifugal compressor includes the main and cover discs and blades located between them and forming interblade channels; at that, in the middle part of the blade, near each of the blades there made is a slot; one end of each slot is located near the corresponding disc; the other end of each slot is located closer to impeller outlet, and each slot makes an angle of 12-18 degrees with the corresponding disc.

EFFECT: reducing hydraulic losses in impeller and increasing the efficiency of centrifugal compressor.

2 dwg

FIELD: machine building.

SUBSTANCE: procedure for preparation of rotating element for longer service life of bearing consists in: application of metal material on surface of rotating element orthogonally to lengthwise axis of rotating element, also, contents of chromium in material is less, than contents of chromium in rotating element. Further, the procedure consists in treatment of surface of metal material orthogonal to axis of the rotating element. The rotating element increasing service life of the bearing consists of: the rotating element; surface of metal material orthogonal to lengthwise axis of the rotating element with contents of chromium, less than the rotating element; a boundary layer between surface of metal material and the rotating element orthogonal to lengthwise axis of the rotating element; also, surface of metal material corresponds to supporting surface taking axial load; surface of metal material has contents of chromium below 2.2 percents.

EFFECT: increased service life of bearing; finished supporting surface eliminates problems of fluffiness.

10 cl, 4 dwg

Gas turbine engine // 2553889

FIELD: engines and pumps.

SUBSTANCE: gas-turbine engine (1) comprises a fan (2) disk (13) and a tapered shaft (8) of a low pressure compressor (3) fixed by radial flanges (9) and (16) on a radial flange (11) of a common shaft (12) of the fan with fit bolts (19). The tapered shaft (8) of the low pressure compressor is mounted by the flange (9) on the external surface of the (12) fan (11) shaft (10) flange. The fan disk (13) is placed by the flange (16) on the internal surface (17) of the (12) fan (11) shaft (17) flange. The ratio of the thickness h of the radial flange of the fan disk in the location of the fit bolts to the thickness H of the radial flange of the fan shaft is within 0.8…1.2. The ratio of the thickness h1 of the radial flange of the tapered shaft of the low pressure compressor in the location of the fit bolts to the thickness H of the radial flange of the fan shaft is within 0.4…0.8.

EFFECT: due to avoidance of collapse of the fit bolts, avoidance of imbalance of the fan rotors and the low pressure compressor rotors during the gas-turbine engine operation its reliability is improved.

2 dwg

Up!