Application of two-component chromium-aluminium coating on gas turbine cooled blade inner cavities and device to this end. RU patent 2520237.
 Materials resistant to wetting, and products made from them / 2502826Product resistant to wetting includes a coating having the value of open porosity of surface of up to approximately 5 vol. %. Coating includes material containing primary oxide and secondary oxide, where primary oxide contains cation chosen from a group consisting of cerium, praseodymium, terbium and hafnium, and secondary oxide contains cation chosen from the group consisting of rare-earth elements of yttrium and scandium. |
 Wetting resistant materials and articles made therewith / 2495954In one embodiment, such material contains a primary oxide which contains primary oxide cations, said primary oxide cations including cerium and hafnium, and a secondary oxide containing a secondary oxide cation selected from a group consisting of rare-earth elements yttrium and scandium. In another embodiment, the material contains a primary oxide containing a primary oxide cation selected from a group consisting of cerium and hafnium, and a secondary oxide containing two secondary oxide cations, where the first secondary oxide cation includes praseodymium or ytterbium and the second secondary oxide cation includes a cation selected from a group consisting of rare-earth elements yttrium and scandium. The material in the entire article has overall porosity of less than about 5 vol. %. |
 Article with nano-layer coating / 2487781Invention relates to coated cutting plate for removal of material with chip forming (versions), to method of application of coating system and to coated article. Cutting plate comprises backing 22 and coating. One system of wear-proof coating 40 has bottom layer 42 and top layer 46 including aluminium, chromium and nitrogen. Coating system 40 comprises also coating system composed of intermediate nano-layers 44 reiterating many times and including titanium, aluminium, chromium and nitrogen. Said coating system 44 comprises multiple combinations of alternating layers 50, 52, 54, 56, 58, 60, 62.Every combination of alternating layers 50, 52, 54, 56, 58, 60, 62 has basic layer 64 including titanium, aluminium and nitrogen and nano-layer with multiple sets of alternating nano-layers 68, 70, 72, 74, 76, 78. Every set of alternating nano-layers 68, 70, 72, 74, 76, 78 has one nano-layer with aluminium, titanium and nitrogen and one more nano-layer 84 containing aluminium, chromium, titanium and nitrogen. Thickness of basic layer G is larger that that of nano-layer region F. |
 Vacuum treatment plant and method of vacuum treatment / 2472869Treatment is carried out in a vacuum chamber (1), in which a device is installed for generation of an electric low-voltage arc discharge (15) (LVAD), a carrier (7) of an item for reception and displacement of items (2) and at least one input (8) for an inertial and/or a reaction gas. The LVAD comprises a cathode (10) and an anode (13) electrically connected with a cathode via an arc generator. The item carrier (7) is electrically connected with a voltage shift generator (16). At least some surface of the anode (13) includes graphite lining. |
 Sheets of thermoplastic with surface coating reinforced by fibers / 2471889Composite sheet material comprises porous medium layer formed by reinforcing fibers in amount of 20 wt % to 80 wt % of total weight of said medium layer bonded together by thermosetting polymer. Note here that said material contains fireproof agent in amount of 2 wt % to 13 wt % including, at least one of N, P, As, Sb, Bi, S, Se, Te, Po, F, Cl, Br, I and At. Method of making said sheet comprises forming said medium porous layer and laminating at least one coating of its surface. Note also that said coating has oxygen index exceeding 22. |
 Multilayer protective coating for substrate arranged in or outside transport facility, substrate with said coating and method of forming said coating on substrate / 2471888Proposed coating comprises binding layer made on substrate first surface adhered thereto and has surface facing the substrate and that not facing said substrate. It comprises also resistive layer to resist impact forces and corrosion caused by carrion medium nearby substrate which is formed on binding layer surface not facing the substrate that has binding surface and that not binding. It has also sealing layer formed on resistive layer not binding surface. |
 Electric steel plate with non-oriented grain, and its manufacturing method / 2471013Electric steel plate consists of basic material made from steel and film from Fe-Ni alloy, which is created at least on one surface of basic material. Film from Fe-Ni alloy contains the following, wt %: 10%-40% Fe and 60%-90% Ni and has thickness of 0.1 mcm or more. |
| Cutting tool / 2466828 Cutting tool comprises sintered body from cemented carbide, cubic boron nitride, cermet or ceramics, with Re-radius cutting edge, lateral and front surfaces, and single- or multilayer PVD-coating covering, at least, part of sintered body surface and bearing, at least, one oxide layer applied by cathodic arc deposition to cover, at least, sintered body surface part. Note here that edge Re-radius is smaller than 40 mcm, preferably, smaller than or equal to 30 mcm. |
 Hard metal tip / 2465098Invention relates to cutting tool and method of its production. Cutting tool is provided with wear-resistant coating on bearing plate. The latter includes particles on metal carbide and binder including ruthenium. Said wear-resistant coating comprises hafnium carbonitride. Wear-resistant coating containing hafnium carbonitride may have thickness varying from 1 mcm to 10 mcm. In compliance with another version, cutting tool comprises bearing plate made from hard alloy with binder including, at least, one of the following substances: iron, nickel and cobalt. |
 Ceramic powder, ceramic layer and multilayer system with pyrochlore phase and oxides / 2464175Invention relates to ceramic powder, as well as a ceramic layer and a multilayer material obtained from said powder, and can be used to produce heat-insulating materials. The powder contains pyrochlore phase of general formula AxByOz c x, y = 2, z = 7, where A= Gd or Sm, or Nd, or La, or Y, B= Hf or Zr, or Ti, or Sn, C= Hf or Zr, or Ti, or Sn, and a secondary oxide CrOs with r, s>0 with content of 0.5-10 wt %. The disclosed ceramic layer (13) is obtained from said ceramic powder, wherein the multilayer material has a base (4) and said ceramic layer (13). |
 Method and device for deposition reactors (versions) / 2503744Feed line serves to feed initial product steam from initial product source into reaction chamber. Device to withdraw heat from reaction chamber heater serves to prevent initial product steam condensation in liquid or solid phase between initial product source and reaction chamber. |
 Unit and method for obtaining polycrystalline silicon / 2495164Method is implemented in a reactor containing a bottom plate forming a lower part of the reactor and a bell-shaped vacuum cap attached to the bottom plate so that it can be removed, in which on the bottom plate there located is a variety of gas inlet holes for supply of raw gas in upward direction to the reactor, and gas outlet holes for discharge of waste gas after the reaction, and in which the variety of gas inlet holes is located concentrically along the whole surface area enveloping the upper surface of the bottom plate, in which many silicon target rods are installed; at that, silicon target rods are heated and polycrystalline silicon is deposited from raw gas on surfaces of silicon target rods. Supply of raw gas from gas inlet holes is stopped near the reactor centre during the specified period of time while raw gas is being supplied form other gas inlet holes at early stage of the reaction, and a way for descending gas flow is provided after it collides with vacuum cap ceiling. |
 Method of producing polycrystalline silicon / 2475570Method involves heating multiple silicon nucleating rods placed in a reaction furnace, followed by deposition of polycrystalline silicon on the surface of the nucleating rods using a feed gas released from gas vents lying in the inner bottom part of the reaction furnace. The method includes a deposit stabilisation step, wherein the rate of release of feed gas from the gas vents is gradually increased at the first step for depositing polycrystalline silicon, wherein 5-15% of the gas vents are closed; a shaping step, wherein the first rate of release is increased, with the rate of increase higher than the rate of increase at the stabilisation step, and the rate of release is then gradually increased at a rate lower than the rate of increase; wherein the time required for the shaping step is 20-35% of the total duration of deposition of polycrystalline silicon and 30-55% of the gas vents are closed; and a growth step, wherein after the shaping step, the rate of release of feed gas is reduced by reducing the number of closed gas vents compared to the shaping step. |
 Reservoir of source for vpe-reactor / 2439215Invention refers to the design of source of the device for applying the coating by means of vapour-phase epitaxy method (VPE). Source includes reservoir 2 containing liquid or solid initial material 1 and having in the upward direction a hole, supply line 3 for reactive gas 4 that reacts with initial material 1 for formation of process gas 5 containing initial material, cover 6 located immediately on initial material 1; at that, cover 6 forms between itself and surface 7 of initial material 1 the volume 8 for reactive gas 4 passage parallel to surface 7, to which supply line 3 is connected, and floats on initial material 1 by means of floats 9 protruding from below cover 6; at that, floats 9 are formed with hollow bodies of cylindrical shape, which are opened in upward direction. |
 Resistant coating and its manufacturing method / 2405858Body made from steel, hard metals, cermets or ceramics and covered with hard material with single-layered or multi-layered systems of layers contains at least one solid layer Ti1-xAIxN, which has been obtained by chemical deposition from gaseous phase. Solid layer represents either single-phase layer of cubic NaCl-structure and stoichiometric coefficient x > 0.75 to x = 0.93, and constant grid afcc between 0.412 nm and 0.405 nm, or multi-phase layer the basic phase of which consists of Ti1-xAIxN with cubic NaCl-structure, with stoichiometric coefficient x > 0.75 to x = 0.93, and constant grid afcc between 0.412 nm and 0.405 nm. In addition to the basic phase the layer also contains the other phases from Ti1-xAIxN with wurtzite structure, and/or from TiNx with NaCI-structure; at that, chlorine content of solid layer of Ti1-xAIxN lies within the range of 0.05 to 0.9 atomic %. Bodies made from steel, hard metals, cermets or ceramics are coated with single-level or multi-level system of layers, which contains at least one solid layer of Ti1-xAIxN. To the bodies there applied is coating in rector at temperatures of 700°C to 900°C by means of chemical deposition, as precursors there used are titanium halides, aluminium halides, and reactive nitrogen-containing compounds which are mixed at increased temperatures. |
 Reactor / 2405063Reactor includes vacuum chamber (1) having the first end wall (2) with mounting manhole, the second end wall (3) with rear flange, side walls/housing (4), which connect the first and the second end walls (2, 3), and at least one fitting (5) of material of source for source material supply to vacuum chamber (1) of reactor. At least one of fittings (5) of source material is located in side wall/housing (4) of vacuum chamber (1) of reactor. |
| Method of making silicon dioxide film / 2398913 Method of making silicon dioxide film involves feeding tetramethoxysilane and oxygen in a stream of inert gas into a reaction zone in volume ratio of tetramethoxysilane to oxygen equal to 1:5-10, decomposition of tetramethoxysilane vapour in the presence of oxygen and deposition of a silicon dioxide film on plates at temperature of 380-500°C at atmospheric pressure for 10-30 minutes. The film is deposited on quartz or silicon plates. |
 Source for vapour-phase deposition, mount for this source and method of mounting and dismantling said source / 2398048Invention relates to liquid or solid material source for vapour-phase deposition, and mount for this source to be arranged in reactor. Proposed source can be placed in at least partially, in fitting communicated with vapour-phase deposition reactor reaction chamber. Source consists of rod 5 with first and second ends 11 and 9, respectively, chamber 1 for solid or liquid material arranged on second end 9 or nearby it and having at least one partially open wall and isolating appliances representing casing to be fitted on the wall of chamber 1 to separate it from ambient atmosphere. Aforesaid casing and chamber can slide relative to each other to open and/or close chamber 1 after mounting proposed source in reactor fitting. |
 Cvd-reactor and method of synthesis of hetero-epitaxial films of silicon carbide on silicon / 2394117Invention relates to production of hetero-epitaxial structures of silicon carbide on silicon that can be used as substrates in making solid-state components to be operated at high radiation and temperature. Reactor for synthesis of hetero-epitaxial silicon carbide films on silicon substrate via gas plating comprises quartz tube with container 5 accommodating substrate 1, heaters 6 with resistance or induction heating and appliances to feed film components and hydrogen into synthesis zone. Note here that hydrogen feed appliance includes active hydrogen and represents tube 9 arranged in top and bottom walls of container 5 and having holes directed along normal line to substrate 1. Note also that film component feed device is arranged in evaporator 10 with gas control ring with holes through which said components are fed into synthesis zone parallel with substrate. Mind that said feed appliances are isolated. Peculiarity of said reactor consists in that heaters and substrates are arranged parallel each other to make sandwich. Proposed design allows efficient use of radiation from every heater. Silicon carbide film synthesis is performed at pressure varying from 5·102 to 5·10-2 Pa on the surface of at least two silicon substrates at 800 to 1380°C, and hydrogen temperature exceeding that of substrate and film components by at least 100°C. |
 Method of making thin films of chemical compounds and installation for realising said method / 2388770Invention relates to methods and devices for making thin films of coordination compounds. The method involves conversion of initial compounds to a gas phase in spatially isolated areas, their separate transportation to a gas phase reaction zone through a carrier gas and deposition of a thin film. One of the initial compounds is fed into the reaction zone filled with a second initial compound in a direction perpendicular the direction of the substrate, and the initial compounds are mixed in the immediate proximity of the substrate. The installation for realising the method has three zones joined together and separately temperature-controlled - (1) and (2) for converting the initial compounds to gas phase and (3) for carrying out the gas phase reaction. Also the device has a substrate holder (4) placed in zone (3), outlets (6) and (7) for carrier gas into zones (1) and (2) respectively and an outlet (8) for the carrier gas from the installation, placed in zone (3) behind the substrate holder (4). Zones (1) and (3) are joined with possibility of moving carrier gas from zone (1) to zone (3) through outlet (5) whose cross sectional area is less than that of zone (3) and whose end lies closer to the substrate holder (4) than the connection point of zones (2) and (3). |
 Device for application of metallic coatings on internal surfaces of friction type bearings by cvd-method of organometallic compounds / 2456373Device comprises a reactor with a heater and the ability to feed reaction gaseous medium inside it and removal of reaction products. The reactor is made up of two identical lids interconnected with the possibility of changing the distance between them and with its subsequent fixation and facing each other, having a common axis of symmetry and made with a hole along the axis of symmetry for the supply of reaction gaseous medium inside the reactor in one of them and a hole along the axis of symmetry for withdrawal of reaction products into the other one and made with a possibility of installing a graphite separation ring on the internal surface of each of them. There is a friction bearing installed on each splitter ring that can be alternated and that form a sealed area of metallisation by their inner cylindrical surfaces. Axis of symmetry of each friction bearing and each graphite splitter ring coincide and are located on the axis of symmetry of the lids. |
FIELD: process engineering.
SUBSTANCE: invention relates to machine building and may be used in aircraft and power engineering. Plies of chromium and aluminium are deposited and subjected to high temperature annealing in vacuum at 1050±5°C, residual pressure of 1.3(10-1-10-3) Pa for 2-5 hours. Chromium ply deposition from gas phase is executed at thermal decomposition of Cr(CO)6, while that of aluminium ply is performed at thermal decomposition of Al(CH3)3. Note here that at chromium decomposition Cr(CO)6 is heated to 110-120°C to set 400-450°C in deposition area while chromium ply is formed during at least 2-3 hours. At aluminium deposition Al(CH3)3 is heated to 100-110°C to set 300-350°C in deposition zone while aluminium ply is formed at least 5-6 hours. Proposed device comprises reaction chamber arranged inside vacuum chamber and separated by heat-insulating dense-vacuum web to preliminary zone and deposition zone that feature different temperature fields. Heated containers to accommodate coating material sources are arranged outside vacuum chamber and connected via heated transfer systems and heated valves with inlet into reaction chamber preliminary zone. Temperature field is created by heating system with the help of temperature field formation shields arranged in reaction chamber deposition zone.
EFFECT: higher quality of coating for operation at higher temperatures.
2 cl, 1 dwg, 1 tbl
The invention relates to the mechanical engineering, in particular to methods for deposition of functional coatings of chromium and aluminum by vapour deposition, and can be used in the aviation and energy turbines for protection of gas turbine blades from high-temperature gas corrosion of internal cavities of the cooled blades of the turbines.
The modern level of operating temperatures and capacity gas-turbine engines (GTE) is largely determined by the use of a cooled turbine blades with a complex configuration of the internal cavity with a cooled channels that connect to Vozduhoflotsky channels of gas path of the engine with a system of punched holes.
When such a very complex structure of blades protection of internal and external Traktovaya surfaces from high-temperature gas corrosion is a complicated task.
It is known that in the modern advanced engines of the fifth generation turbine blades must work within the specified resource at gas temperature before the turbine 1850-1900°K and more than that, of course, is impossible without reliable they are sewn from gas corrosion [Y. Elisha. Promising technologies of production of GTE blades. The engine, 2001, №5(17), p.4]. Practice has shown that the most effective way to ensure high durability of gas turbine blades used for construction materials is the use of protective coatings.
A method of obtaining protective coatings on the gas turbine blades, including sequential deposition in vacuum on the external surface of the pen blades of the first layer, the subsequent deposition of the second layer on the basis of aluminium and vacuum annealing [see the description of the patent RF №2171315, M.K. C23C 14/06, publ. 27.07.2001,]. The first layer is a condensed floor of Nickel alloy, which precipitated by a layer of carbide metal, selected from the group of titanium, chromium, niobium, tantalum, molybdenum, tungsten, vanadium or hafnium, received the vacuum-arc method.
The application of the above inventions, according to the authors, will allow to receive a new class of coatings can significantly (up to two times) to increase the service life of the turbine blades.
However, this method is applicable only for coating on the external surface of the turbine blades and cannot be used for application of metal coatings on surfaces of the inner channels of the blades.
Also known method of formation of metal coatings on surfaces of the inner channels of the turbine blades, provided that the blade of the turbine has an external surface and at least one internal channel including placing of the turbine blades inside the camera chemical vapour deposition (CVD), the connection of gas collector-reagent not less than one inlet nozzle inner channel, the coating on the surface of not less than one internal channel for technology CVD, with the use of the reactant gases, covering metal, for the formation of the metal film on a surface of not less than one internal channel, and pumping out the residual of the reactant gases, covering metal, not less than one internal channel through a single outlet, passing through external the surface of one internal channel [see Description to the U.S. patent №7838070, MCL B05D 7/22, publ. 23.11.10 g]. The method is characterized by the fact that the gas-reagents covering metal, contain not less than one aluminum gas-reagent, chrome gas-reagent and cobalt gas-chemical which includes subsequent vacuum heat treatment of metal coating, which is carried at a temperature within 1800 F-2000 F, and within 2-10 hours, then (pre) put a mask layer on the outer surface of the turbine blades to protect against metal precipitation, which are removed from the outer surface of the turbine blades by a crumb of such sediments with outer surface of the turbine blades, as well as by liquid honing the outer surface of the turbine blades. Metal reagent includes organo-metallic material from a number of triethylamine, triisobutylaluminum, trimethylaluminum, dimethylamine hydride, dimethylethylamine and trimethylamine. The method is realized in the temperature range from 200 F to 1000 F or in the temperature range from 200 F to 800°F.
The above solution allows you to put two-chrome - aluminum coating on the surfaces of internal channels of lopatok.
However, the above method does not provide the required quality of coverage in connection with unstable adhesion of the coating material shoulder, which reduces the reliability of details in the course of their operation, and by reducing requirements to the parameters of the engine operation reduces their capacity.
Closest to the claimed technical solution on purpose, technical nature and the achieved result when you use is getcirclesize method of applying functional two-chrome-aluminum coating on the inner cavity cooled blades of gas turbines for protection against high temperature gas corrosion, including successive deposition of layers of chrome and aluminium with subsequent high-temperature annealing in vacuum for the final formation of the coating structure [Boguslayev A.V., Murashko V.V. Getcirclesize coverage of blades of the turbine gas turbine engines. Journal of propulsion, №4/2006, p.73-75], which after the preliminary abrasive preparation of surfaces of the blades moving atoms of chromium and aluminium from the mixture on the surface of blades performed with the use of halogen-free at temperatures of 1,000 OC±10 C, and the establishment of optimal structure of the coating is carried out in a vacuum furnaces at temperature 1050°±10 C and a residual pressure of 1,3 (10 -1 ...10 -3 ) PA.
The result of this treatment, get coverage, microstructure which consists of two zones: single-phase external and internal (diffusion) multiphase. The Al content in the external coverage area is 18...22% and Cr 4...4,5%. Diffusion zone contains 12...14% Al and 6...7,5% Cr, as well as increased content in comparison with the basic material V, Nb, W, which creates an additional "barrenest" elements and prevent the depletion of the main material of blades during operation.
However, the drawback of such coverings is, first of all, the likelihood of exfoliation of the deposited layers, as well as high cost, complexity and lack of opportunities to control the technological process of coating.
Although at this time the circulation method of application gazoturbinnyh coatings (STP) system Ni-AL-Cr is the only one used in serial production on the territory of Ukraine and Russia, such coverage is not always provide the necessary durability blades of the turbines during their operation, especially for turbine blades modern promising aircraft engines with significantly improved characteristics.
A device for coating on parts of gas turbine containing reaction chamber, in which parts are coated and source of metal that is also located in the reaction chamber [see the description of the patent application, US no US 2010/0098971, Coating for the parts of a gas turbine, the method and the device for coating, M. class. B32B 15/01, publ. 22.04.2010,] and the components that are coated and sources of metal located in the camera against each other on parallel levels so that the distance between the parts that cover, and the sources of the metal is within 10-150 mm, This distance may be within 20-150 mm. Several parts, which cover, respectively, are located between the two corresponding levels of sources located one above the other, and ten levels of sources can be located in the reaction chamber. Reaction chamber has axisymmetric configuration with diameter from 200 mm to 1500 mm and a height of more than 1500 mm, the Volume density of the source in relation to the volume of the reaction chamber is from 2% to 5%. In the unit, at least one of halogen compound may be directed to the source through the feed line.
The above device, according to the applicants, efficiently and economically in the coating.
Closest to the claimed technical solution on purpose, technical nature and the achieved result when you use is a device for coating, consisting of a reaction chamber, made with the possibility of vacuum, which sets out the means for placement of the processed parts, means for placement of the sources of the coating material [see Boguslayev A.V., Murashko CENTURIES, Getcirclesize coverage of blades of the turbine gas turbine engines, Technology of production and repair, journal of propulsion, №4/2006, p.73-74]. The device is made with the possibility of creating the necessary temperature field contains an internal protective shield tool for leveling the temperature field in the reaction chamber and the means of ensuring the circulation of the gas components inside of the protective screen.
The above device provides the possibility of obtaining coatings on the blades of gas turbines at temperatures from 900 to 1,000 degrees Celsius and is together with the described above, as noted above, the only currently used in conditions of serial production in Ukraine and Russia.
This goal is achieved by the fact that in the known method of drawing two-chrome-aluminum coating on the inner cavity cooled blades of gas turbines, including successive deposition of layers of chrome and aluminium with subsequent high-temperature annealing in vacuum, according to the invention, the deposition from the gas phase layers of chrome performs during thermal decomposition of hexacarbonyl chromium Cr(CO) 6 and aluminum during thermal decomposition of trimethylaluminum Al(CH 3 ) 3 , sedimentation layers of chromium and aluminum do when the pressure in the vacuum chamber 1,0-1,2 .10 -2 mm Hg, when precipitation of chromium hexacarbonyl chromium Cr(CO) 6 heated to a temperature of 110-120 degrees C and in the zone of sedimentation set temperature 400-450 C, chromium form for at least 2-3 hours, in the deposition of aluminium trimethylaluminum Al(CH 3 ) 3 heated to a temperature of 100-110 degrees C and in the zone of sedimentation set temperature 300-350 C, aluminium layer is formed for at least 5-6 hours.
This goal is achieved also by the fact that the known device for drawing two-chrome-aluminum coating on the inner cavity cooled blades of gas turbine containing heated container for placing sources coating material hexacarbonyl chromium Cr(CO) 6 and trimethylaluminum Al(CH 3 ) 3 and tools to create the necessary temperature field, according to the invention, reaction chamber, installed inside the vacuum chamber, separated by insulating vacuum-tight bulkhead in pre-area and zone of sedimentation with different temperature field, and mentioned the partition is done as a means to install it machined blades so that the locking part of the scapula is advanced, and the working part of the scapula in the zone of sedimentation, the installation additionally contains a heated containers for placing sources coating material hexacarbonyl chromium Cr(CO) 6 and trimethylaluminum Al(CH 3 ) 3 , established outside of the vacuum chamber and United with warmed transport systems and warmed valves with entrance to the preliminary zone reaction chamber, which has a lower temperature than the zone of sedimentation, as a means to create the temperature field is used in heating system and forming temperature field screens placed in the zone of the deposition of the reaction chamber.
As can be seen from the statement of the essence of the proposed technical solutions, they differ from the prototype and, therefore, are new.
Decisions also have an inventive step. The basis of the proposed technical solution the task of improving the method of application functional two-chromium-aluminium coatings on surfaces of the inner channels of gas turbine blades, which, following the implementation of the deposition from the gas phase layer of chromium during thermal decomposition of hexacarbonyl chromium Cr(CO) 6 and aluminum during thermal decomposition of trimethylaluminum Al(CH 3 ) 3 ., run deposition layers of chrome and aluminium pressure in the vacuum chamber 1,0-1,2 .10 -2 mm Hg, heating during the precipitation of chromium hexacarbonyl chromium Cr(CO) 6 up to a temperature of 110-120°C, establishing in the area of deposition temperature 400-450 C, forming a layer of chromium for at least 2-3 hours of heating in the deposition of aluminium trimethylaluminum Al(CH 3 ) 3 to temperature 100-110 C, establishing in the area of deposition temperature 300-350 C, formation of a layer of aluminium for at least 5-6 hours, provided new technical result.
The basis of the proposed technical solution is also tasked improve device for applying coatings on parts of gas turbines, which, due to the installation of the reaction chamber inside the vacuum chamber, separated by insulating vacuum-tight bulkhead in pre-area and zone of sedimentation with different temperature field, the execution of the said partition as a means to install it machined blades so that the locking part of the scapula is advanced, and the working part of the scapula in the zone of sedimentation, the installation additionally contains a heated containers for placing the sources of the coating material hexacarbonyl chromium Cr(CO) 6 and trimethylaluminum Al(CH 3 ) 3 , established outside of the vacuum chamber and United with warmed transport systems and warmed valves with entrance to the preliminary zone reaction chamber, which has a lower temperature than the zone of sedimentation, use as a means to create the temperature field of the heating system and forming temperature field screens placed in the zone of sedimentation reaction chamber, is provided new technical result.
New technical result is manifested in higher adhesion layer of chromium, which consistently precipitated a layer of aluminum. No unwanted absorbed atoms and molecules, such as from air allows you to besiege the aluminum layer to perfectly cleaned surfaces, and such surfaces can form a new strong interatomic bonds. This excludes further peeling of the coating on the whole in the further processing of turbine blades in a vacuum.
As noted above, it is known use of the method of chemical vapour deposition (analogue getcirclesize way) [see description to the U.S. patent №7838070, M. class. B05D 7/22, publ. 23.11.10 g], including the use of the reactant gases from a number aluminum gas-reagent, chrome gas-reagent, and cobalt gas-reagent. The method involves the use of organo-metallic materials from a number of triethylamine, triisobutylaluminum, trimethylaluminum, dimethylamine hydride, dimethylethylamine Alan and trimethylamine Alan. The method involves coating to the surface using the method of chemical vapour deposition in the temperature range from 93 deg C to 537 C. Method involves vacuum heat treatment of metal coating at temperature in the range 1000 C to 1100 C and within 2-10 hours.
However, the proposed method and the device is fundamentally different from the known to the creation and use of high-purity surface that is deposited complex covering layers that provide the adhesion and diffusion processes in the conditions maximally effective manifestation of these properties. In addition, in comparison with the reference method serves to use compounds that are netoksicski and less corrosive, which greatly facilitates the process of work with them. This corrosion load on the equipment is significantly reduced, significantly reduced the requirements to construction materials equipment. The process of deposition of coatings is carried out at much lower temperatures, is well controlled and provides a high repeatability of technological processes. The proposed method and apparatus allow purposeful change of coating properties with reference to the processed material and the conditions of processing that ensures better quality coverings. Due to the construction technology of the device of coatings of chromium and aluminum are applied in the same vacuum chamber in a single technological cycle, which significantly reduces the processing time and significantly increases economic indicators of quality. The presence of vacuum and thermally separated the two chambers in technological device makes it possible to separately apply coating on internal and external surfaces of the blades, which is important for the subsequent application of high-quality heat-protecting coatings.
The solution is industrially applicable, as implemented in the process of formation of two-chromium-aluminium coatings on surfaces of the inner channels cooled workers turbine blades.
In Fig. shows the scheme of the device for realization of the proposed method.
The method of drawing two-chrome-aluminum coating on the inner cavity cooled blades of gas turbines. The blades of gas-turbine engine is placed in the reaction chamber. Download containers hexacarbonyl chromium Cr(CO) 6 and trimethylaluminum Al(CH 3 ) 3 , decrease in the reaction chamber pressure up to P 1 =1,0...1,2·10 -4 mm Hg After lowering the pressure in the device to the specified values begin to gradually raise the temperature in the three areas of the device. In the warm-up set when the precipitation of chromium in the reaction chamber in the area of deposition temperature of 400 to 450 degrees C and in other areas and systems establish a temperature not lower than 110-120 C. Within 2-3 hours in the device maintain the preset temperature, and on the inner surfaces of the blade is formed a layer of chromium Cr thickness of 5-7 microns. After completion of chromium deposition again to set the device up to a pressure of P=1,1 1,0....10 -4 mm Hg, in the zone of sedimentation set temperature 300-350°C, and in other areas of the device set the temperature 100-110 C. for 5-6 hours on the inner surfaces of the blades on a layer of chromium is formed a layer of aluminum with thickness of 20-25 mm. After the completion of the formation of a layer of aluminium again in a vacuum chamber is reduced to P=1,1 1,0....10 -4 mm Hg
Terminates the process of formation of chromium-aluminium coating annealing vanes of gas turbine engine at temperature 1050±5 C, residual pressure of 1.3(10 -1 ...10 -3 ) PA within 2-5 hours.
Device for applying metal coatings contains the reaction chamber 1, installed in the vacuum chamber 2. Reaction chamber 1 is divided into two zones 3 and 4 sealed insulating wall 5, made with the possibility for installation of gas turbine blades. Lock part blades 6, containing the inlet 7, is in advanced reaction chamber 3, and working part 8 blades, on the inner perforated the cavity which is applied a covering, installed in the area of deposition of the reaction chamber 4. Preliminary zone 3 reaction chamber through the heat transport system 9, 10 and valve 11, 12 connected with heated containers 13 and 14, which have ORGANOMETALLIC reagents. Vacuum chamber 2 zone 3 are connected to the bypass line 15 16 valve. In the area of deposition of the reaction chamber 4 is installed heating system 17 and forming a temperature field screens 18.
The device works as follows. When establishing the appropriate pressure and temperature fields in zones 3, 4 reaction chamber 1 and the corresponding heat transport systems 9, 10 and containers 13, 14 in the last evaporation or hexacarbonyl chromium Cr(CO) 6 or trimethylaluminum Al(CH 3 ) 3 and their transport from areas with less a heat 3, 9, 10, 13, 14, in zone 4 of the reaction chamber 1 with a higher temperature. At temperatures 400-450°C, 300-350°C decomposition respectively hexacarbonyl chromium Cr(CO) 6 and trimethylaluminum Al(CH 3 ) 3 , with the formation of layers of chrome and aluminium.
The table below shows the results of implementation of the method in the above device.
Connection
T 1 - t-RA heating, C
T 1 - t-RA decay, C
t-time, hour
d is the thickness, microns
∑Delta that microns
QualityExample 1
Cr(CO) 6
100 400 2 5 25Adhesion layer Cr with good
Al(CH 3 ) 3
100 300 5 20Adhesion layers Al with a layer of Cr good
Example 2
Cr(CO) 6
100 450 2 5 25Grip Cr layer with base good
Al(CH 3 ) 3
100 350 5 20Adhesion layers Al with a layer of Cr good
Example 3
Cr(CO) 6
110 400 3 7 32Adhesion layer Cr with good
Al(CH 3 ) 3
110 300 6 25Adhesion layers Al with a layer of Cr good
Example 4
Cr(CO) 6
110 450 3 7 32Adhesion layer Cr with good
Al(CH 3 ) 3
110 350 6 25Adhesion layers Al with a layer of Cr good
As can be seen from the description of the method and the device for its implementation, the proposed technical solutions allows to improve quality by improving the characteristics of coverings in terms of strength and cohesion with the material turbine blades at high parameters of operation of gas turbine engine. In addition, the proposed device allows a greater degree of control over the processes taking place in the reaction chamber, which reduces overall costs of its operation.
1. The method of drawing two-chrome-aluminum coating on the inner cavity cooled blades of gas turbines, including successive deposition of layers of chrome and aluminium with subsequent high-temperature annealing in vacuum, characterized in that the deposition from the gas phase layers of chrome performs during thermal decomposition of hexacarbonyl chromium Cr(CO) 6 and aluminum during thermal decomposition of trimethylaluminum Al(CH 3 ) 3 , sedimentation layers of chromium and aluminum do when the pressure in the vacuum chamber 1,0-1,2·10 -2 mm RT. century, when the precipitation of chromium hexacarbonyl chromium Cr(CO) 6 heated to a temperature of 110-120 C, in the zone of sedimentation set temperature 400-450 C, the chromium form for at least 2-3 hours, in the deposition of aluminium trimethylaluminum Al(CH 3 ) 3 heated to a temperature of 100-110 C, in the zone of sedimentation set temperature 300-350 C, aluminium layer is formed for at least 5-6 hours, and high-temperature annealing spend at temperature 1050±5 C, residual pressure of 1.3(10 -1 -10 -3 ) PA within 2-5 hours.
2. The device for drawing two-chrome-aluminum coating on the inner cavity cooled blades of gas turbine containing the reaction chamber where the installation media for the machined blades and tools to create the necessary temperature field, wherein the reaction chamber, installed inside the vacuum chamber, separated by insulating vacuum-tight bulkhead in pre-area and zone of sedimentation with different the temperature field, and mentioned the partition is done as a means to install it machined blades so that the locking part of the scapula is advanced, and the working part of the scapula in the zone of sedimentation, the installation additionally contains a heated containers for placing sources coating material hexacarbonyl chromium Cr(CO) 6 and trimethylaluminum Al(CH 3 ) 3 , established outside of the vacuum chamber and United with warmed transport systems and warmed valves with entrance to the preliminary zone reaction chamber with lower temperature than the zone of sedimentation, as a means to create the temperature field is used in heating system and forming temperature field screens placed in the zone of the deposition of the reaction chamber.