Last stage of steam turbine

FIELD: machine engineering.

SUBSTANCE: blades are made with a selection of moisture and steam inlet channels, communicating with through slots selection of moisture and steam inlet. The blades are divided into two groups: one group of blades disposed at the bottom of the diaphragm and the most remote from the connector, included in the nozzle array sector with a central angle of 120º-180º, and another group of the remaining blades. The annular chamber in every part of the rim of the diaphragm seals the inlet chamber is divided into steam and water sampling chamber. By the steam inlet chamber, the steam-receiving box is connected with steam supply pipes, which are installed in the throttle pressure regulators, and the moisture sampling chamber communicates with the holes in the rim, in which the throttling members are mounted. In the body of the diaphragm, the wet-receiving slots are made.

EFFECT: proposed design of the blades of both groups and the presence of various elements dripping can improve efficiency, which increases the efficiency of the stage and the overall efficiency of the steam turbine, reducing the risk of increased wet-steam erosion of rotor blades.

3 cl, 5 dwg

 



 

Same patents:

FIELD: power engineering.

SUBSTANCE: support stand (430) for a steam turbine diaphragm comprises the main vertical part (435) with a bulge (447), which passes from the specified part (435) substantially perpendicular to it. The bulge comprises the first bulge, stretching from the upper end of the main vertical part (435), and the second bulge stretching from the area near the lower end of the main vertical part (435). The first bulge is at a certain distance from the second bulge. The first and second bulges are designed for coupling with an appropriate slot (450), made in the turbine diaphragm. In the bulges there is a hole (455), which passes via them vertically and is designed to place a fastening element (460), stretching via the first and second bulges (447) to ensure vertical attachment of the main vertical part (435) and specified bulges (447) to the turbine diaphragm.

EFFECT: reduced duration and cost of maintenance cycle, since it provides for possibility of access for extraction of a lower half (410) of the diaphragm for maintenance without rotor removal.

9 cl, 7 dwg

FIELD: machine building.

SUBSTANCE: high temperature gas turbine comprises a labyrinth seal as per honeycomb block on the inner shoulder made with a baffle plate and with an internal air cavity of the nozzle blade being cooled. The air cavity at the nozzle blade outlet is connected to the perforation which leads to internal cavities of honeycomb block cells via a dosing hole in the baffle plate and via a distributing channel and axial channel system which are set in the inner shoulder circumferentially. The axial channels are additionally connected by perforation to the outer surface of the inner shoulder of the nozzle blade.

EFFECT: invention improves reliability and cost efficiency of a high temperature gas turbine due to the prevention of overheating and destruction of the honeycomb block of a labyrinth seal, and reduction of the radial clearance in the seal.

2 cl, 3 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: housing of a jet-turbine engine has the possibility of installing into it of a variety of blades and includes attachment devices of the end of each blade, which are located on the housing side opposite to blades. Attachment devices include a ring-shaped element passing around the housing, and the housing includes holes through which ends of blades pass for their interaction with attachment devices. The housing is made of long fibres connected with thermoplastic resin. The ring-shaped element is obtained by pultrusion and soaked with thermoplastic resin welded with thermoplastic resin of the housing; besides, the whole assembly is connected by means of hot pressing. The other invention of the group relates to a jet-turbine engine containing the above housing and many blades, each of which has an end connected to the housing.

EFFECT: group of inventions allows simplifying production and assembly of a jet-turbine engine housing.

5 cl, 4 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: gas turbine connected with secondary combustion chamber contains a set of guide vanes of LP turbine installed downstream of the specified combustion chamber. Radially the external border of the secondary combustion chamber is made by the external wall segment secured on the supporting component radially installed outside. The hot gases flow is limited radially from outside, inside the guide vanes by the external platform secured on the support of the guide vane. Between the wall segment and the external platform there is radially continuing cavity with width from 1 to 25 mm in axial direction in the inlet area. The cavity inlet area has step element reducing the cavity width by 10% per step, and continuing in the cavity at right angle to the direction of the hot gas flow. Relatively to the step element the cavity width radially outside again increases to width of the inlet area by means of the step continuing in the cavity at right angle to the direction of the hot gas flow.

EFFECT: invention reduces ingress of the hot gas in the cavity between the wall segment and external platform of the guide vanes.

16 cl, 9 dwg

FIELD: engines and pumps.

SUBSTANCE: nozzle assembly of gas turbine contains external and internal housings, between which stator vanes are located. The nozzle assembly vanes are electrically isolated from each other and fitted with electric contacts. The electric contacts of vanes are connected through electric cables to unlike poles of DC power supply so that the vanes connected to unlike poles of DC power supply alternate between each other uniformly along the whole circle.

EFFECT: invention allows to use the structure elements of the gas turbine for temperature measurement.

4 dwg

FIELD: engines and pumps.

SUBSTANCE: transition duct for connection of a combustion chamber and a turbine part of a gas turbine engine comprises a shell including the first and second surfaces. The first and second surfaces of the shell are connected by piercing, and the shell of the transition duct is made at least from one sheet stamped into a shape that creates a transition duct with a double shell. The other invention of the group relates to a gas turbine engine comprising the above transition duct. When the above transition duct is manufactured, the shell is produced, which comprises the first and second surfaces, and connection is made by piercing to connect the specified surfaces.

EFFECT: group of inventions makes it possible to simplify manufacturing of a transition duct.

12 cl, 10 dwg

FIELD: machine building.

SUBSTANCE: turbine outlet device comprises hollow aerodynamic profiled supports located after the runner of the last turbine stage as well as aerodynamic profiled contours. The contours are formed by the front and rear blades set between the supports with displacement in respect to each other. The mean lines of input zones of the contours and input zones of the profiled supports are turned to the turbine longitudinal axis by 20-40° in the direction of the rotation of the last turbine stage runner. The mean lines of the output zones of the contours are directed along the turbine longitudinal axis. The blades are set with displacement in respect to each other at the distance equal to 0.03-0.15 of the length of the front blade chord. Along the contour chord the blades are set in the position of matching the front of the exit edge of the front blade and the front of the leading edge of the rear blade or are displaced in respect to the latter. The number of the contours set between the supports is determined by the dependence protected by the present invention.

EFFECT: invention allows for increasing the efficiency of the last turbine stage and reduction of swirling of the output flow.

3 dwg

FIELD: engines and pumps.

SUBSTANCE: device for repair of the flange including some ledges uniformly located in circle comprises hollow bent reinforcement part shaped to flange and flange reconditioning part. Reinforcement part can be secured at the flange sound ledges and has two perpendicular mirror planes. Flange reconditioning part is arranged at reinforcement part with the help of fasteners located in one of mirror planes of said reinforcement part. The other invention of the set relates to aircraft engine module including crankcase flange repaired with help of aforesaid device. One more invention relates to aircraft engine including aforesaid module. In flange repair, sound damaged ledge is cut to select the free ledge at the flange adjoining the cut-off ledge for reinforcement and reconditioning parts to be located thereat. Then, reinforcement and reconditioning parts are assembled for them to be secured at the flange via bores of the flange safe ledges and reinforcement part bores.

EFFECT: simplified repair of crankcase damaged flange.

13 cl, 4 dwg

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

Steam turbine // 2508452

FIELD: machine building.

SUBSTANCE: steam turbine comprises working blades and diaphragm outer ring arranged on outer side of said blades. Every working blade comprises end flange, moisture catch grooves, drop removal bore and drain guide flute. End flange is arranged at working blade end to get in contact with end flanges of adjacent working blades. Moisture catch grooves are made at blade back in lengthwise direction. Moisture removal bore communicate end flange outer surface on diaphragm outer ring side and end flange inner surface on working blade inner side. Drain guide flute communicate moisture catch groove ends on end flange side surface with moisture catch bore. Drain guide flute bottom has inclination to blade rear and in steam turbine radial direction. Diaphragm outer ring has drain pocket facing the moisture removal bore.

EFFECT: higher removal of moisture from working blade.

9 cl, 15 dwg

Up!