Blade of turbomachine, in particular for made as a whole monowheel

FIELD: energy.

SUBSTANCE: invention relates to power engineering. Blade of a turbomachine containing a blade airfoil elongating in the axial direction between the front edge and the rear edge, and in the radial direction - between the root and the apex. Front edge of the blade airfoil has a sweep angle, which is positive and continuously increasing from the root to the first radial height of the blade airfoil located between 20% and 40% of total radial height of the blade airfoil measured from the root to the apex and continuously decreasing from the said first radial height of the blade airfoil to the apex. Invention also discloses a turbomachine and a turbomachine monowheel made as a whole.

EFFECT: invention enables optimum control over secondary air flows and also enables to consider penetration into the jet, which is called directed downward.

10 cl, 3 dwg

 



 

Same patents:

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: metallurgy.

SUBSTANCE: weld joint is heated by sending an electric current via a weld joint up to 10 kA as current leads are fixed at different sides relative to the weld seam on the process lap of a blade and a blisk. In the process of thermal treatment they measure the temperature of the weld joint surface and adjust it by the variation of the current value within 540-620C. The maximum permissible heating temperature is set with the condition of saving the fine-grained structure of the weld joint. The minimum permissible temperature is set with the condition of removal of residual welding stresses in a weld joint. Thermal treatment is carried out with AC current with thyristor regulation of its value.

EFFECT: invention makes it possible to increase the efficiency of removal of residual stresses of joints due to the reduced distortion of the blisk profile, and also to increase the efficiency of thermal treatment due to direct heating of the entire cross section of the weld joint by electric current of a high value.

3 cl, 1 dwg

FIELD: engines and pumps.

SUBSTANCE: in making vaned disc with multiple vanes jointed said disc radially, vane with ledge to joint it to said disc is formed and said ledge is jointed to disc kedge by linear friction welding. Prior to linear friction welding, said vane is clamped in tooling, brought in contact with said disc and loaded with axial welding force. Then without reducing applied welding force, the vane is fixed in tooling by full clamping force to make linear friction welding by friction of vane and disc. Vane fixture is retained during the entire welding process.

EFFECT: higher quality of welding.

2 dwg

FIELD: engines and pumps.

SUBSTANCE: individual cooled blades from monocrystalline alloy is attached to a disc part from granulated alloy into a solid part by hot isostatic pressing (HIP) in the zone where long-term strengths of those alloys are similar at one and the same temperature in a continuous operating mode. Shaped part, path flange and some part of the root with a cooling air supply branch pipe via a shaped channel to any of the blades are located outside the HIP influence zone; blade roots are aligned with the disc, and mainly end-to-end. Zone of similar long-term strength of both alloys is pre-determined as per long-term strength curves of alloys. Cooled blade includes the air cooling system comprising the air supply device to the blade in the form of an inlet branch pipe or holes in the root, air distribution channels to the shaped part and in the blade shaped part itself, which are located above a certain zone equal approximately to long-term strength of alloys of blades and disc part.

EFFECT: increasing strength, service life and reducing the weight of the turbine impeller for full-size high-temperature gas turbine engines, including high-temperature gas turbine engines with long service life, which are used in aviation, space and ground facilities, and in industrial power engineering.

6 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: in compliance with proposed method, separate blades made from one metal alloy are jointed to disc section made from another metal alloy. Said separate blades are jointed by isostatic pressing to disc section in zone of approximately equal hardness of said alloys. Said zone is predefined by, for example, creep rupture strength Larsson-Muller curves. Profile section, web and part of root above said zone of every blade is located outside the area of isostatic pressing while other part of the root and disc section are encapsulated and located in said isostatic pressing zone. Blade roots are preferably butt-jointed to the disc. Another invention of this set relates to integral bladed disc wherein separate blades made from one metal alloy, including monocrystalline one, are jointed to disc section made from another metal alloy in compliance with above described method.

EFFECT: higher durability, longer life, decreased weight.

5 cl, 13 dwg

FIELD: process engineering.

SUBSTANCE: invention may be used in fabricating integral vaned disk for, for example, gas turbine rotor. Vanes 1 are arranged to make a rim in mould that features rotational symmetry. Disintegrating or decomposing material preheated to temperature exceeding its fusion temperature is poured on said rim. Moulded rim 10 is withdrawn from said mould after curing of said material. Friction welding is used to joint moulded rim 10 to disk 4 Disintegrating or decomposing material is removed.

EFFECT: simultaneous jointing of multiple vanes to disk by friction welding.

14 cl, 5 dwg

Steam turbine // 2432466

FIELD: machine building.

SUBSTANCE: steam turbine consists of: stator unit and rotor unit. The stator unit includes nozzles directing flow of steam. The rotor unit includes blades receiving flow of steam. The rotor unit consists of: a section of retention, the first end of a shaft on the first end of the retention section and the second end of the shaft on the second end of the retention section opposite to the first end of the retention section. The retention section has a packaged rotor section including one or more rotor plates each made of an integral metal work piece. The blades are connected with the rotor plate forming a monolith connection. The rotor unit also contains a forged rotor section located near the retention section and including: a forged rotor part and rotor steps having blades with lugs in form of dove tail arranged in slots on external surface of the forged rotor part.

EFFECT: simplified manufacture, eliminating fabrication and assembly of separate steps of blades and separate rotor plates since forged rotor section is located near retention section.

5 cl, 13 dwg

FIELD: machine building.

SUBSTANCE: stator unit consists of stator plates forming main case of stator of flat shape. The main case of the stator includes the first and second axial end surface opposite to the first one, aerodynamic base surface of the stator along internal by radius end of the main case of the stator, nozzles directing flow of vapour and passing along radius inside from aerodynamic base surface of the stator and packing of the stator plates installed to prevent effect of vapour on end surfaces of the stator plates. The rotor unit consists of stator plates forming main case of stator of flat shape. The main case of the rotor includes the first and the second end surface opposite to the first one, aerodynamic base surface of the stator on an external by radius end of the main case of the stator, blades receiving flow of vapour and passing along radius outside from aerodynamic base surface of the stator and packing of the rotor plates installed to prevent effect of vapour on axial end surfaces of the stator plates.

EFFECT: reduced cost and time for manufacture of steam turbine and its units due to implementation of plates and elimination of steam leaks between them.

10 cl, 13 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed method of restoring bladed disk with at least one damaged zone comprises preparing said zone, building up metal on appropriate machine tool and finishing restored zone. In preparing, damaged zone is subjected to machining to produce preset profile restored zone. Then meat is built up on test piece, called initial test piece, with said preset profile using laser built-up tool with preset operating parametres. After build-up, test piece quality is checked and, if it complies with acceptance criterion, metal build-up is performed in zone to be restored using the same laser tool without changing its operating parametres. Other inventions of the set relate to test pieces intended for above described method and made from titanium alloy. In compliance with one version, shape of said test pieces imitates the tip of aerodynamic profile, while, in compliance with another version, it imitates the angle of front or rear edge of aerodynamic profile tip subjected to machining to preset model.

EFFECT: longer life and higher reliability of turbo machine restored disk.

17 cl, 9 dwg

FIELD: engines and pumps.

SUBSTANCE: method of assembling integral bladed disks of, particularly, turbojet engine compressor disks comprises mounting vibration damper both on the blades and between them, and welding the disks together. Proposed vibration damping device is be mounted on disk blades to dampen blades vibration by welding the disks together. It comprises appliances to close the blades and gaps there between, and locking appliances to hold and clamp the former ones arranged on the blades. Blades closing appliances are made from elastically deformed material.

EFFECT: reduced vibrations, ruling out resonance vibrations in friction welding.

17 cl, 5 dwg

FIELD: machine building.

SUBSTANCE: gas turbine comprises an exhaust diffuser installed downstream after the last turbine stage and comprising a jet passing section and a pole. The jet passing section comprises parts of the first and the second walls, and the pole is fitted by a front edge passing between the part of the first wall and the part of the second wall. The pole's front edge comprises the first and the second parts, and the second part of the front edge is located between the first part of the front edge and the part of the second wall. The front edge of the pole is also fitted by the third straight part set between the fisrt and the second parts of the front edge. The first part of the front edge passes at 20-40% of the distance between the first front extreme point in which the front edge touches the part of the first wall, and the second front extreme point in which the front edge touches the part of the second wall. The first part of the front edge is inclined to the section outlet in relation to the direction of the normal line perpendicular to the part of the first wall in the first front extreme point, thus allowing for the reduction of Mach number in the direction perpendicular to the front edge. The second part of the front edge is inclined to the section outlet in relation to the direction of the normal line perpendicular to the part of the second wall in the second front extreme point, in which the front edge touches the part of the second wall.

EFFECT: invention allows for the increased efficiency of a turbine due to the reduction of losses in a diffuser.

21 cl, 16 dwg

FIELD: machine building.

SUBSTANCE: subsonic blade of axial turbine machine intended for radial installation on the specified machine, contains frond edge, rear edge and two aerodynamic surfaces. The aerodynamic surfaces are located at opposite sides and pass through the blade length, at that each connects the front edge with the rear edge. The blade front edge has S-shaped lateral profile. The most front part of the front edge is at height within 3-20% of blade length, and/or the most rear part of the rear edge is at height within range 85-97% of the blade height. The another invention of the group relates to the compressor of the axial turbine machine containing rotor with at least one stage of rotor blades and stator with at least one stage of stator blades, at that blades of at least one stage of rotor and stator are made as specified above. One more invention of the group relates to axial turbine machine containing the above compressor.

EFFECT: group of inventions increases the engine capacity by at least 1% in comparison with the optimised stage having blades with front edges of S-shape profile.

19 cl, 5 dwg

FIELD: machine building.

SUBSTANCE: turbomachine compressor rotor consists of a disk which carries blades. The wall of the disk at its radial outer ring is made from several angular sectors each of which is limited between the first blade back and the pressure side of the second blade following the first blade in the circumferential direction. Each of the sectors comprises a bulge section being convex in the axial and circumferential directions. The tip of the bulge section is set radially outside in respect to the imaginary surface of rotation around a rotor disk axis passing through four points determined by the intersection of the wall respectively with the front edge of each of the first and second blade and the rear edge of each of the blades. The tip is distanced in the circumferential direction from the first blade back by 30-70% of the circumferential distance between the back and the pressure side of the blades measured at the tip level. The wall comprises also a recess section located upstream from the bulge section and being concave in the axial direction and in the circumferential direction and having a base being approximately point-like one. Other inventions of the group refer to the compressor including such a rotor and a turbomachine including such a compressor.

EFFECT: group of inventions allows for increasing the efficiency of turbomachine compressor rotor.

6 cl, 2 dwg

FIELD: machine building.

SUBSTANCE: cooled turbine blade for a turbomachine comprises a blade set on a platform which is located at a stem. The blade is hollow with one or more cavities for cooling air circulation. The cavity set along the rear edge is fed by cooling air from a feeding channel made as an elbow inside the stem and connecting the air inlet in the lower stem part to the cavity of the rear edge. The channel is fitted by a recess provided under the platform and having a bell-like shape, at the axis essentially radial in respect to the inlet hole. The recess tip comprises a dedusting hole crossing the platform and is limited inside the stem by walls closing it and set essentially radially from the platform.

EFFECT: invention is aimed at keeping the blade integrity by removing dust from cooling medium and at optimising the use of dedusting air in blade cooling.

14 cl, 7 dwg

FIELD: machine building.

SUBSTANCE: blade with airfoil comprises an inner platform zone and an outer tip zone in the radial direction, and a front entrance edge and a rear exit edge, between the platform zone and the tip zone, in axial direction. The blade is fitted with a pressure side being concave in the radial direction between the inner platform zone and the outer tip zone, as well as with a back being convex in the radial direction between the inner platform zone and the outer tip zone. The blade width in the axial direction between the entrance edge and the straight exit edge is changed parabolically from the maximal width in the platform and tip zones to the minimal width at the section between the platform zone and the tip zone. The other invention of the group refers to an axial turbomachine comprising the group of the above blades with airfoil.

EFFECT: invention allows for the reduction of profile losses at a blade.

15 cl, 5 dwg

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: machine building.

SUBSTANCE: axial-flow compressor blade comprises an entrance edge, an exit edge, a pressure surface and a back with its surface being fitted by spherical vortex generators concave to the inside of the blade. Each vortex generator is equipped by at least two supply channels with outlet holes with the diameter of (0.05 - 0.25)D which are equidistanced from the vortex generator symmetry axis oriented in the direction of the approach flow. Distance from the vortex generator symmetry axis to the outlet hole amounts to (0.1 - 0.4)D. The inlet holes of the supply channels are set on the pressure surface and the outlet ones are set at the distance of (0.025 - 0.7)D from the entrance edge of the vortex generator. The supply channels are made at the angle of 20 - 110 to the blade chord, where D - the diameter of the vortex generator indentation.

EFFECT: increased range of attached flotation over the blades, increased air flow through the compressor and its improved efficiency.

5 cl, 5 dwg

FIELD: machine building.

SUBSTANCE: group of inventions relates to a centrifugal compressor, in particular, to drop catchers to remove liquid from a compressor as well as to the method to improve efficiency of centrifugal compressor performance in gas turbine engines. A device for catching liquid drops set in the compressor impeller comprises the first hole set on the impeller surface and made so that to receiver liquid drops, and a channel set below the said hole and communicating with it by flow. The channel is made so that the liquid drops are led out from the first hole and the compressor impeller. A centrifugal compressor set in a gas turbine engine comprises a centrifugal impeller which includes rotating solid blades each of them having a root part and an end part and providing for air compression in the centrifugal gravitational field, and units for catching the liquid drops. According to the method for improving the efficiency of centrifugal compressor performance by the removal of liquid drops, a liquid drop catching device is installed in the part of the centrifugal impeller effective from the point of view of catching the liquid drops in the place of their collision with the centrifugal impeller; afterwards the liquid drops are caught in the hole of the said device and removed from the centrifugal compressor by being led from the hole to the channel in the said device.

EFFECT: prevention of accumulation of liquid and formation of larger drops or liquid film on the centrifugal compressor impeller thus eliminating the risk of increased erosion impact and reduced compressor efficiency.

20 cl, 8 dwg

FIELD: engines and pumps.

SUBSTANCE: turbine wheel and rotor blade has pressure side surface (19) and rarefaction side surface (21). Rarefaction side is smooth at its larger portion except for some bulges (25). Bulges are distributed nearby and along rear edge (17). Pressure side surface is smooth.

EFFECT: smaller separation zone nearby blade surface charged with disturbances influencing the turbine efficiency.

12 cl, 4 dwg

FIELD: engines and pumps.

SUBSTANCE: turbine wheel comprises turbine blades (20) shaped aerodynamic part (102). Said aerodynamic shape has rated profile corresponding to data cited in the tables 1 through 11 wherein distances X, Y, Z and R are given in inches and the tables 1' through 11' wherein said distances are given in centimetres. Magnitudes if coordinates X and Y are smoothly connected by arc with radius R to make profile cross-section of said shaped part at every distance Z. Profile cross-section at distances Z are smoothly interconnected to produce a complete aerodynamic shape.

EFFECT: higher efficiency and bearing capacity of the blade of aerodynamic part and the blade on the whole.

10 cl, 3 dwg, 22 tbl

FIELD: power engineering.

SUBSTANCE: multi-stage turbine and axial-flow turbine stage comprise working wheels that rotate in the opposite directions, are arranged on individual shafts, and have blade cascades on the intermediate diameter, which terns the fluid flow at the angle ΔβCA = 180° - (β1I + β2EFF), where β1I is the blade cascade inlet angle, β2EFF is the effective angle of the blade cascade output. The blade cascade of the first upstream working wheel turns the fluid not more than by 15°. Between the wheels, power is transmitted via a reduction gear. Between the shafts and the common shaft, power is transmitted through a conical reduction gear.

EFFECT: reduced losses.

4 cl, 12 dwg

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