FIELD: deposition of high-temperature protective coatings. SUBSTANCE: method involves applying heat-resistant underlayer of powders by diffusion onto part surface; plasma spraying of metal layer based on NiCoCrAlSi V and ceramic layer based on zirconium dioxide with additives of aluminum , chromium, yttrium, nickel and silicon oxides. Method allows shaped parts operating under high-temperature conditions of 1200 C ( for instance, tip blades and units of turbine, combustion chambers) to be protected. EFFECT: increased efficiency and wider operational capabilities. 3 tbl
| Title | Year | Author | Number |
|---|---|---|---|
| METHOD OF APPLYING COATS | 2001 |
|
RU2214475C2 |
| METHOD OF DEPOSITION OF THE COATING | 2004 |
|
RU2280095C2 |
| METHOD OF PROTECTION OF GAS TURBINE BLADES FROM HIGH-TEMPERATURE CORROSION | 1992 |
|
RU2033474C1 |
| PROCEDURE OF APPLICATION OF PROTECTIVE COATING ON PARTS OUT OF NICKEL ALLOYS | 2008 |
|
RU2375497C1 |
| METHOD OF PROTECTION OF GAS TURBINE BLADES | 2000 |
|
RU2190691C2 |
| PROCEDURE FOR APPLICATION OF COMBINED HEAT INSULATED COATING ON PARTS OUT OF HEAT RESISTANT ALLOYS | 2009 |
|
RU2402639C1 |
| METHOD FOR APPLYING COMBINED HEAT-RESISTANT COATING TO TURBINE BLADES OF GTE | 2020 |
|
RU2755131C1 |
| MATERIAL OF CERAMIC LAYER OF HEAT PROTECTING COATING | 2013 |
|
RU2556248C1 |
| METHOD OF COMBINATION HEAT-RESISTANT COATING ON TURBINE BLADES OF GAS-TURBINE ENGINE | 2007 |
|
RU2349679C1 |
| APPLICATION METHOD OF COMBINED THERMAL PROTECTIVE COATING TO PART FROM HEAT-RESISTANT ALLOYS | 2011 |
|
RU2469129C1 |
