Steam turbines high-temperature stud pins refrigeration method and device for its actualization

FIELD: electricity-producing industry.

SUBSTANCE: invention relates to the method and device for the case high-temperature stud pins refrigeration and the flanged joints of the steam turbines of the thermal power stations (TPS, CHP), more specifically for the high-temperature stud pin of the flange connectors of the high-pressure cylinder (HPC) seal, and can be used in the stud pins refrigerating systems of the turbines of a ST-type. The assigned technical problem in the steam turbines high-temperature stud pins refrigeration method, which includes the cooling steam supply along the cooling line from the flowing channel on one side and the cooling steam removal along the outlet line on the other side is achieved by means of the fact that the steam extraction is carried out from the medium or low-pressure stage of the steam turbine with subsequent direction of the extracted steam for the steam turbines high-temperature stud pins refrigeration. Upon that, the extracted steam flow velocity control is effected on account of the isolation valve adjustment on the extraction steam line from the low or medium pressure stage of the steam turbine, and the extracted steam temperature control is effected on account of the steam extraction from the low or medium pressure stage of the steam turbine. Further, the extracted steam is transferred through the cylindrical connecting leg into the cylindrical metal tube of a minor diameter and then after the distribution in a volume the extracted steam runs into the cooling cylindrical conduit, where the extracted steam is supplied through the perforation hole in the cylindrical metal tube of a minor diameter into the cooling cylindrical conduit, where it removes a part of the heat from the internal surface of the external cylindrical tube of a greater diameter and the steam heats up as consequence of the heat loss. At this time, the extracted steam cools down the external cylindrical metal tube walls of a greater diameter, and further, the steam is forced out into the outlet cylindrical connecting leg and further either goes back into the steam turbine plant cycle or to the atmosphere. The cooling cylindrical conduit is formed by two cylindrical metal tubes with bases that have the common normal axis. Along with this, the cylindrical metal tube of a minor diameter has the perforation hole and is linked to the cylindrical connecting leg, and the external cylindrical metal tube of a greater diameter is linked to the outlet cylindrical connecting leg.

EFFECT: reduction in expenditure, thermal efficiency increase.

4 cl, 3 dwg

 



 

Same patents:

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

FIELD: machine building.

SUBSTANCE: rotor system of magnetoelectric machine contains a casing of the turbine block, shaft installed turbine, the shaft installed in bearings, a generator casing, a rotor. The rotor contains uniformly installed permanent magnets, magnetised in radial direction with alternating polarity. Turbine and rotor are installed on same hollow shaft, with possibility of coolant pumping through its cavity by the pump installed at the turbine side. At end of the hollow shaft a spiral channels are made. The hollow shaft with rotor creates a cylinder with permanent cross-section, on its external surface a bandage shell is installed out of high strength non-magnetic material. The bearings can be made in form of the contact-free gas supports, electromagnetic bearings or hybrid magnetic bearings.

EFFECT: minimised heating of the permanent magnets, and heat transfer between the turbine shaft and generator shaft, increased rigidity and mechanical strength of the system due to the generator shaft and turbine shaft making as single hollow shaft with possibility of the coolant pumping through its cavity, and spiral grooves making at the rotor end.

4 cl, 3 dwg

FIELD: machine building.

SUBSTANCE: unit with the fluid medium flow, in particular, a gas turbine with axially passing heated gas flow, is designed with rows of rotor vanes from the rotor side and rows of the guide vanes from the housing side located respectively axially between consecutive rows of the rotor vanes and also with the rotor shaft surrounded with heat-shielding elements and elements of the basis of the rotor vanes. In the area of the first radial plane of the rotor shaft, inside heat-shielding elements and elements of the base the first cooling air chambers are located which are interconnected to each other and with the cooling air source. In the area of the external second radial plane of the rotor shaft, inside the base plates, between the rotor vanes and their base elements the additional cooling air chambers are located which can be blown by heated gas. Additional cooling air chambers can be blown only from their end faces located upstream the heated air flow.

EFFECT: invention is aimed at optimisation of the cooling air flow and at increase of efficiency by elimination of uncontrollable intake of the cooling air into the heated gas flow.

7 cl, 4 dwg

Axial gas turbine // 2547541

FIELD: machine building.

SUBSTANCE: axial gas turbine contains a rotor with alternating rows of air-cooled rotor blades and rotor heat shields, and the stator with alternating rows of air-cooled guide vanes and the stator heat shields installed in the holder of the guide vanes. The stator coaxially encloses the rotor outside with formation of the path of hot gases flow between them so that the rows of rotor blades and stator heat shields and rows of the guide vanes and rotor heat shields are located opposite to each other respectively. The row of the guide vanes and the next row of rotor blades downstream form a turbine stage. Rotor blades of the turbine stage are designed with external platforms on their ends. The turbine stage contains the devices guiding the cooling air already used for cooling of the profile part of the turbine stage guide vanes, into the first cavity located between external platforms of the rotor blades and stator heat shields located opposite for protection of stator heat shields against hot gases and for cooling of external platforms of the rotor blades. Each of the guide vanes contains an external platform. Devices for guiding of the cooling air include the second cavity for intake of the cooling air which leaves the profile part of the guide vane. Besides, the devices for guiding of the cooling air include devices of supply of received cooling air in the radial direction into the named first cavity.

EFFECT: invention is aimed at improvement of cooling efficiency and minimising of cooling air consumption.

7 cl, 6 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to gas turbines. This structural element is provided with at least one coolant guide channel terminating at unstructured surface. Surface located nearby channel mouth has at least one groove-like recess separated from said mouth by web for efficient decrease in concentration of strain caused by the channel as compared with strain in the case of groove-like recess absence. Said web features minimum wall thickness while channel has minimum mouth diameter. Wall minimum depth-to-diameter ratio varies from 0.05 to 3, preferably, from 0.05 to 2.

EFFECT: longer life of structural element.

12 cl, 4 dwg

Axial gas turbine // 2547351

FIELD: machine building.

SUBSTANCE: axial gas turbine contains a rotor with alternating rows of air-cooled rotor blades and rotor heat shields, and the stator with alternating rows of air-cooled guide vanes and air-cooled heat shields of the stator installed in the holder of the guide vanes. The stator coaxially encloses the rotor outside with formation of the path of hot gases flow between them so that the rows of rotor blades and heat shields of the stator and rows of the guide vanes and rotor heat shields are located with reference to each other in a specific manner respectively. The rows of the guide vanes and the next row of rotor blades downstream form a turbine stage. The turbine stage is fitted with devices for recycling of the cooling air already used for cooling, in particular, of profile parts of the guiding turbine stage blades, for the purpose of cooling of the stator heat shields of the named turbine stage downstream the named guide vanes.

EFFECT: invention is aimed at improvement of cooling efficiency and minimising of cooling air consumption.

9 cl, 5 dwg

Axial gas turbine // 2543101

FIELD: machine building.

SUBSTANCE: gas turbine comprises a rotor with alternating rows of air cooled working blades and rotor heat shields and a stator with alternating rows of air cooled guide blades and stator heat shields which are installed in the guide blade holder. The stator encloses the rotor from outside so that a hot gas path is formed between them and the working blade rows and heat shields of the rotor and guide blade rows and heat shields of the stator are set opposite each other respectively. A row of guide blade and the next row of working blades in the flow downstream direction form a turbine stage. Each working blade of a turbine stage is fitted by a tip at its end. Each guide blade of a turbine stage is fitted by an external platform of the guide blade. The external platforms of guide blades in the turbine stage and the adjacent heat shields of the stator are matched to each other due to the fact that every external guide blade platform is fitted by a projection on its back wall in the downstream direction. The projection passes downstream to the front edge of the working blade tip and into the respective recess made in the adjacent heat shield of the stator. The stator heat shields in the turbine stage are cooled by the introduction of cooling air into the cavity located at the back of each stator heat shield. The cooling air enters the hot gas path through the holes in the side surface of the stator heat shield passing upstream and downstream. The cavity for the cooling air to enter through the hole is located at the back of the external platform of every guide blade in the turbine stage. The cooling air jets are delivered to the working blade tips from the cavity by means of the holes passing through the said projection downstream. It is provided for the grooves passing in downstream direction through the projections to direct the cooling air flow exactly into the gap between the adjacent circumferential heat shields of the stator.

EFFECT: invention is aimed at cooling efficiency increase, decrease of cooling air mass flow rate.

3 cl, 7 dwg

FIELD: machine building.

SUBSTANCE: working blade of a gas turbine comprises a profile part passing in the longitudinal direction and a blade root to fix the working blade on the gas turbine rotor shaft. The profile part of the working blade is provided with internal cooling channels. The cooling channels, preferably, pass in the longitudinal direction and can be supplied with cooling air by cooling air supplying units located inside the blade root. The working blade root is fitted with a channel passing in the transverse direction through the said working blade root and communicated with the cooling channels. An insert is introduced into the blade channel to set the final configuration and characteristics of connections between the blade channel and cooling channels. The blade channel is a cylindrical channel. The insert is of tubular form so it is wholly located inside the cylindrical channel. The insert wall is fitted by at least one nozzle through which one of the cooling channels is connected to the working blade channel and which defines the mass flow rate of cooling air supplied to one cooling channel.

EFFECT: invention is aimed at the optimization of cooling air distribution and supply, without simple design of a working blade being traded.

9 cl, 8 dwg

Axial gas turbine // 2539404

FIELD: machine building.

SUBSTANCE: axial gas turbine comprises a rotor and a stator. The stator is a case embracing the rotor from outside to form a hot gas path in-between through which the hot gas produced in the combustion chamber flows. The rotor comprises a shaft with axial grooves, in particular, of fir-tree type, to fix a great number of working blades in them in the form of sequential rows of working blades. Heat shields of the rotor are installed between the adjacent working blade rows and thus the inner border of the hot gas path is formed. The rotor shaft can transport the cooling air mainstream flow in the axial direction along the heat shields of the rotor and lower parts of the working blades. The rotor shaft provides the working blades with cooling air coming to the inner cavity of the working blades. The axial gas turbine is provided with leakproof channels for cooling air which pass in axial direction via the rotor shaft separately from the cooling air mainstream flow and supply the working blades with cooling air.

EFFECT: reduced cooling air leakages and increased efficiency of turbine operation.

13 cl, 9 dwg

FIELD: engines and pumps.

SUBSTANCE: invention relates to gas turbine rotors, particularly, to aircraft and surface gas turbine rotors. A turbine rotor comprises a labyrinth with an inner radial rib arranged at a gas downstream side of a disc rim and a flange fitted at the front side of the said disc. The said flange and disc rim make a circular air chamber connected at the outlet with a gas chamber and, at the inlet, via channels in a blade-to-disc joint, with the labyrinth inner chamber. The labyrinth is mounted at the disc as a radial flange connected to the radial rib by an elastic element. The labyrinth inner chamber is connected to a lock joint via the labyrinth radial flange groove exposed toward the disc. The air chamber on the disc front side is connected to the gas chamber via chamfers in a clock joint between the blade and disc. The ratio of the labyrinth circular rear rib axial length to the inner radial rib to the axial length of the labyrinth front circular front rib axial length relative to the inner radial rib makes 2…5. The ratio of the axial length of the labyrinth front circular rib radial length relative to the inner radial rib to the elastic element surface radius makes 1.5…3.

EFFECT: invention provides higher reliability and efficiency of the low-pressure rotor.

1 dwg

FIELD: machine building.

SUBSTANCE: high-temperature turbine rotor comprises disks of the first and second stages between which an intermediate disk with radial protrusions is mounted. The intermediate disk is fixed by radial protrusions in the circumferential direction in relation to the axial protrusions set on the first stage disk body. The axial protrusions on the first stage disk body are made so that to form an U-shaped protrusion in the cross-section. The circumferential rib of the intermediate disk placed on the inner side of the first stage disk rim is provided with grooves. The said grooves serve to connect the air cavities of increased pressure to the annular air cavity of decreased pressure which is limited by the circumferential rib of the intermediate disk, radial protrusions of the intermediate disk, the U-shaped protrusion and the first stage disk body. The relation of the U-shaped protrusion in the axial direction to the depth of the U-shaped protrusion groove accounts for 1.1-2.

EFFECT: invention allows for higher reliability and reduced weight of a high-temperature turbine rotor.

3 dwg

FIELD: machine building.

SUBSTANCE: outlet branch pipe (110) of a steam turbine (10) comprises lower outlet branch pipe (105), a steam guide (24), a condenser hole (26), a plate (200) of the outlet branch pipe and an inner channel. The lower outlet branch pipe (105) is connected to the steam turbine (10). The steam guide (24) is mounted in the lower outlet branch pipe (105) and is designed to guide a waste steam flow (35) from the blades (14) of the last stage of the steam turbine (10) casing. The condenser hole (26) is set below the lower outlet branch pipe (105) and is designed to receive the waste steam flow (35) from the above branch pipe (105). The branch pipe plate (200) is mounted in the lower outlet branch pipe (105) and is designed to guide a waste steam flow (35) from the axial direction to the radial one to the condenser hole (26). The inner channel (215) is located in the outlet branch pipe plate (200) and is designed to guide a heat carrier flow inside it as well as to cool and condense the waste steam flow (35) near the plate (200).

EFFECT: improved turbine characteristics due to the condensation in the zone with low velocities near the outlet branch pipe plate (200) providing for reduced boundary layer and improved flow passing through the said branch pipe.

9 cl, 4 dwg

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