RU2012107601A - METHOD FOR APPLICATION OF TWO-COMPONENT CHROMIUM-ALUMINUM COATINGS ON THE INTERNAL CAVES OF COOLED WORKING BLADES OF GAS TURBINES AND DEVICE FOR IMPLEMENTING THE METHOD - Google Patents
METHOD FOR APPLICATION OF TWO-COMPONENT CHROMIUM-ALUMINUM COATINGS ON THE INTERNAL CAVES OF COOLED WORKING BLADES OF GAS TURBINES AND DEVICE FOR IMPLEMENTING THE METHOD Download PDFInfo
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- RU2012107601A RU2012107601A RU2012107601/02A RU2012107601A RU2012107601A RU 2012107601 A RU2012107601 A RU 2012107601A RU 2012107601/02 A RU2012107601/02 A RU 2012107601/02A RU 2012107601 A RU2012107601 A RU 2012107601A RU 2012107601 A RU2012107601 A RU 2012107601A
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Abstract
1. Способ нанесения двухкомпонентных хром-алюминиевых покрытий на внутренние полости охлаждаемых рабочих лопаток газовых турбин, включающий последовательное осаждение слоев хрома и алюминия с последующим высокотемпературным отжигом в вакууме, отличающийся тем, что осаждение из газовой фазы слоев хрома выполняют при термическом разложении гексакарбонила хрома Cr(СО)и алюминия при термическом разложении триметилалюминия Al(СН), при этом предварительно формируют три температурные зоны вначале для осаждения хрома, а затем для осаждения алюминия.2. Способ по п.1, отличающийся тем, что осаждение слоев хрома и алюминия выполняют при давлении в вакуумной камере 1,0-1,2·10мм рт.ст.3. Способ по п.1, отличающийся тем, что при осаждении хрома гексакарбонил хрома Cr(СО)нагревают до температуры 110-120°С, в промежуточной зоне обеспечивают эту же температуру, а в зоне осаждения устанавливают температуру 400-450°С.4. Способ по п.3, отличающийся тем, что слой хрома формируют в течение не менее 2-3 ч.5. Способ по п.1, отличающийся тем, что при осаждении алюминия триметилалюминия Al(CH)нагревают до температуры 100-110°С, в промежуточной зоне обеспечивают эту же температуру, а в зоне осаждения устанавливают температуру 300-350°С.6. Способ по п.5, отличающийся тем, что слой алюминия формируют в течение не менее 5-6 ч.7. Устройство для нанесения покрытия на детали газовой турбины, содержащее реакционную камеру, в которой установлено средство для размещения обрабатываемых деталей, и средства для создания необходимого температурного поля, отличающееся тем, что реакционная камера, установленная внутри вакуумной камеры, разделена теплоизолирующей вакуумноплотно�1. The method of applying two-component chromium-aluminum coatings on the internal cavity of the cooled working blades of gas turbines, including sequential deposition of chromium and aluminum layers followed by high-temperature annealing in vacuum, characterized in that the deposition of chromium layers from the gas phase is performed by thermal decomposition of chromium hexacarbonyl Cr ( СО) and aluminum during the thermal decomposition of trimethylaluminum Al (СН), in this case three temperature zones are preliminarily formed first for precipitation of chromium and then for precipitation of al Yuminia. 2. The method according to claim 1, characterized in that the deposition of layers of chromium and aluminum is performed at a pressure in the vacuum chamber of 1.0-1.2 · 10 mm RT.article 3. The method according to claim 1, characterized in that during the deposition of chromium, hexacarbonyl chromium Cr (CO) is heated to a temperature of 110-120 ° C, the same temperature is provided in the intermediate zone, and a temperature of 400-450 ° C is set in the precipitation zone. The method according to claim 3, characterized in that the chromium layer is formed for at least 2-3 hours. The method according to claim 1, characterized in that during the precipitation of aluminum trimethylaluminum Al (CH) is heated to a temperature of 100-110 ° C, the same temperature is provided in the intermediate zone, and a temperature of 300-350 ° C is set in the precipitation zone. The method according to claim 5, characterized in that the aluminum layer is formed for at least 5-6 hours. A device for coating parts of a gas turbine containing a reaction chamber, in which means for accommodating the workpieces are installed, and means for creating the necessary temperature field, characterized in that the reaction chamber installed inside the vacuum chamber is separated by a heat-insulating vacuum tight
Claims (7)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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RU2012107601/02A RU2520237C2 (en) | 2012-02-28 | 2012-02-28 | Application of two-component chromium-aluminium coating on gas turbine cooled blade inner cavities and device to this end |
Applications Claiming Priority (1)
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RU2012107601/02A RU2520237C2 (en) | 2012-02-28 | 2012-02-28 | Application of two-component chromium-aluminium coating on gas turbine cooled blade inner cavities and device to this end |
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RU2012107601A true RU2012107601A (en) | 2013-09-10 |
RU2520237C2 RU2520237C2 (en) | 2014-06-20 |
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RU2012107601/02A RU2520237C2 (en) | 2012-02-28 | 2012-02-28 | Application of two-component chromium-aluminium coating on gas turbine cooled blade inner cavities and device to this end |
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Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
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EP0840809B1 (en) * | 1995-07-25 | 1999-04-21 | Siemens Aktiengesellschaft | Product with a metallic base body provided with cooling channels and its manufacture |
US7838070B2 (en) * | 2005-07-28 | 2010-11-23 | General Electric Company | Method of coating gas turbine components |
DE102007008278A1 (en) * | 2007-02-20 | 2008-08-21 | Mtu Aero Engines Gmbh | Gas turbine component coating and method and apparatus for providing a coating |
RU2358034C2 (en) * | 2007-05-25 | 2009-06-10 | Александр Германович Ермилов | Metal coating of upgraded adhesion to material of pad and method of fabrication of this coating |
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Effective date: 20190617 |