Part made of ceramic material with base and wall

FIELD: machine engineering.

SUBSTANCE: ceramic material part comprises a part forming a base and a part forming a wall. The base is made of ceramic material of low porosity, and the wall contains a low-porosity shell and a core inside the shell. The porosity of the core is greater than the porosity of the base increasing with distance from the base. The base and the wall are obtained by ceramic powder sintering. The wall is formed in a powder-containing vessel by selectively sintering the powder by successive layers by a laser beam or an electron beam.

EFFECT: reduced level of stresses in the part base.

11 cl, 5 dwg

 



 

Same patents:

FIELD: machine building.

SUBSTANCE: method of cooling of structural elements of engine turbine containing at output structure with positive recuperation coefficient Cp for set of operation modes meaning presence of cooling intended for at least pair of structural elements, one of them is a front stator of the guide vanes, and another the stator adjoining the support of the sealing ring of the rear regulated blades means extraction of the surrounding air flow by suction at level of at least one cooled structural element. Suction is accompanied by passage, that results in creation of the forced convection linked with this structural element, and then by rear air re-supply in the output pipe. Cooling is performed by sequential method by means of successive circulation of the same air flow in two structural elements. Cooling is also performed by parallel method by means of independent circulations if air flows in each of the structural elements or by mixed method by means of successive circulation of the same flow in two structural elements and by independent circulation of the second flow in the second structural element by ambient air extraction at level of the front stator of the guide vanes for successive and mixed cooling, and each structural elements for parallel and mixed cooling.

EFFECT: invention reduces operation expenses, and increases cooling efficiency.

10 cl, 7 dwg

FIELD: machine building.

SUBSTANCE: blade comprises inner cavities for cooling gas circulation. The cavities are separated by partitions passing in the radial direction. One of the partitions, the closest one to the rear blade edge, is declined from the radial direction in the direction towards the rear edge starting from at least 70% of the blade height if considered from the blade platform to the outer edge radius. One of the cavities, limited by the said partition, the closest one to the rear blade edge, in the direction of the rear blade edge comprises a row of drilled channels leading to the lateral side of the blade. The drilled channels open into the said cavity through holes set along the line parallel to the said partition.

EFFECT: invention is aimed at higher efficiency of cooling in the upper blade part in the corner between the rear edge and the outer edge.

2 cl, 4 dwg

Cooled turbine // 2546371

FIELD: machine building.

SUBSTANCE: cooled turbine of aircraft gas turbine engine contains an impeller with working vanes, installed on it, two cooling loops, series connected with air channels in the impeller, with independent ring diffusion channels, nozzle vanes and a heat exchanger. Ring diffusion channels are formed on the impellor surface and connected with nozzle vortex devices and transit air ducts upstream. Every nozzle blade is composed of a structural element confined by top and bottom shrouds and space between them, confined by blade root convex and concave walls in the form of leading edge and distribution chamber arranged along blade root axis. Leading edge distribution manifold inlet is communicated with combustion chamber air chamber while its outlet communicates via perforations with turbine flow section. Heat exchanger inlet communicates with air chamber of combustion chamber and its outlet communicates with air manifold and distribution chamber. The cooled turbine incorporates distribution manifold for cooling air, cooling deflector and two transit deflectors arranged in said distribution chamber in its axis with clearance between each other and relative to blade root concave and convex wall to make cooling channels along said walls. Cooling deflector has perforated bores on its two opposite walls and arranged in distribution chamber at distribution manifold wall and gas its perforated wall directed to nozzle blades root concave and convex walls. Blade top and bottom shrouds have air ducts their inlets being communicated with turbine flow section. The distribution manifold for cooling air is connected with an air source, with the air duct inlet of the top shroud and the inlet of the cooling baffle plate. The air duct inlet in the bottom shroud is connected with the outlet of the cooling baffle plate. Air manifold is connected with inlet of transit deflectors, and distribution chamber communicates with the turbine flow section.

EFFECT: invention allows to improve efficiency of the turbine cooling, and also to increase its profitability.

7 cl, 5 dwg

FIELD: machine building.

SUBSTANCE: cooled perforated turbine blade comprises a perforated shell with cooling holes of small diameter. Oval separating cavities are provided in the perforated shell of the blade at the holes, the oval width is equal to the hole diameter and the oval height is slightly greater than the hole diameter, the cavities are arranged so that the oval height is oriented in the radial direction.

EFFECT: invention improves the turbine blade cooling efficiency.

3 dwg

FIELD: machine building.

SUBSTANCE: working vane or the deflector vane with at least one internal radial channel for circulation of the cooling agent limited by a high pressure wall on a high pressure surface and a low pressure wall on a low pressure surface that are connected in a radially oriented forward edge upstream and in a back edge downstream, contains at least one outlet hole located at least in one of the following places - in a wall on the increased pressure side or in a wall on the decreased pressure side for the cooling agent discharge from the internal radial channel into ambient air. Along the back edge at least one output hole communicated with a high pressure surface of the back edge is located. On the high pressure surface of the working vane / deflector vane the back edge contains a ledge facing towards a low pressure surface. At least one output hole on the back edge is partially communicated with ambient air in the zone o the named ledge. The outlet hole on the back edge is designed so that the cooling agent is brought to it along the channel only partially opened in the radially located surface of the ledge front edge. The channel passes at least partially along the length of the ledge bottom surface with formation of a hole with cut.

EFFECT: invention is aimed at improvement of film cooling of the vane back edge.

14 cl, 12 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

FIELD: machine building.

SUBSTANCE: for the purpose of cooling the wall thermally loaded at its front, a coolable element of a gas turbine comprises a variety of pins distributed over the surface of the wall back as well as units to form directed cooling medium jets in the pin zone towards the wall back that are intended for impact cooling. Distribution of pins within the critical zones (Ac) of the element is of higher density than in other element zones. The units to form directed jets towards the wall back comprise an impact cooling plate with distributed impact cooling holes. The density of impact cooling holes is correlated with the density of pins.

EFFECT: invention is aimed at the design of a coolable gas turbine element with its cooling being optimally correlated with the locally changing thermal load without additional consumption of cooling air.

4 cl, 4 dwg

FIELD: machine building.

SUBSTANCE: cooled blade of a gas turbine comprises an airfoil which is set in the flow direction between the leading edge and the rear edge and is limited by respective walls on the suction side and discharge side. The inner space is provided between the walls where the cooling air passes in the flow direction to the rear edge and escapes to outside in the rear edge zone. The wall on the discharge side is ended in the flow direction with the a rim on the discharge side at a distance from the rear edge. The cooling air escapes from the inner space on the discharge side. The inner space at a distance from the rear edge is divided by a variety of ridges oriented in parallel to the flow direction into a variety of cooling channels, which are parallel, providing for pressure differential and fitted by swirlers to enhance cooling effect being additionally installed in them. Immediately before the cooling air escape from the inner space, a portion of flow partitions is provided in the cooling air flow path, the said partitions are distributed across the flow direction and their linear density is less than the linear density of the ridges. A variety of pins in the form of two-dimensional lattice structure is provided between the cooling channels and flow partitions, the pins pass through the inner space across the flow direction between the wall on the suction side and the wall on the discharge side.

EFFECT: invention is aimed at the decrease of aerodynamic losses at the rear edge and lower cooling air consumption.

4 cl, 2 dwg

FIELD: machine building.

SUBSTANCE: cooled blade for a gas turbine includes an aerodynamic section that passes in turbine radial direction or passes in longitudinal direction of the blade between a bandage flange and the peripheral part of the blade, which is provided with a tip. The aerodynamic section is restricted perpendicular in relation to longitudinal direction by means of the front edge and the rear edge and has a working surface and a suction surface with cooled channels passing mainly in radial direction between the bandage flange and the peripheral part of the blade into the inner part of the aerodynamic section. Cooling medium flows through these cooling channels. The first cooling holes for convective cooling are made on the blade working surface. The second cooling holes for film cooling are made on suction surface of blade, in the peripheral part of the blade and functionally connected to cooling channels; with that, they are distributed along the blade width. Cooling medium is taken out to the outside in the area of the tip and/or through the blade tip. The first cooling holes are open to the space enveloping the blade by means of a fan-shaped section of the channel. The first cooling holes that are located outside the rear edge of the blade are open to the space enveloping the blade by means of the fan-shaped section of the channel that has three-dimensional symmetry. The fan-shaped section of the channel with three-dimensional symmetry has the first angle of the hole, which has the range of 10° to 50° and preferably comprising about 24°, and the second angle (φ2) of the hole, which is perpendicular to the above said first angle (2φ1) of the hole. The second angle of the holes has the range of 5° to 25° and is preferably about 12°. The first cooling holes that are located on the rear edge of the blade are open to the space enveloping the blade by means of the fan-shaped section of the channel that has three-dimensional symmetry. The fan-shaped section of the channel with two-dimensional symmetry has the third angle (2φ3) of the hole, which has the range of 10° to 40° and is preferably about 20°.

EFFECT: improvement of cooling in the blade periphery area.

15 cl, 12 dwg

FIELD: machine building.

SUBSTANCE: moving blade of a gas turbine engine turbine comprises an upper end platform with labyrinth seal teeth being set on it. The platform is fitted by a through hole for cooling air and is made as a parallelogram with two sides of the latter being oriented in the rotation direction and the other two being fitted by oppositely directed cuts with contact surfaces and strain compensators embracing them. The platform is equipped by support and control ribs. The support rib is set between the strain compensators with the length of (0.7 - 0.9)H and at the distance of (0.1 - 0.9)L from the cut vertex. The control rib is provided on the side edge of the platform on the side of the convex surface of the profile part between the strain compensator and the labyrinth seal tooth with the height of (0.7 - 0.85)h of the seal tooth height. The height of the strain compensators and the support rib respectively amounts to (1 - 2)d and (1.5 - 3)d, where H stands for the distance between the strain compensators; L - distance from the cut vertex to the rear side of the platform oriented in the rotation direction; h - seal tooth height; d - platform thickness.

EFFECT: longer service life of engine turbine blade at keeping the necessary air consumption via the cooling system for a moving blade and insignificant increase of weight.

3 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

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

Up!