FIELD: machine building.
SUBSTANCE: procedure consists in forming metal under-layer in protected surface of blade, in forming transition metal-ceramic layer and external ceramic layer. Transition metal-ceramic layer along its thickness is formed with step-by step change of ratio of metal content to ceramics from 1 % to 20 % of weight per step and with reduction of metal amount by thickness of the transition layer from 100 % to 0 % at thickness of the transition layer from 8 mcm to 100 mcm. Transition metal-ceramic layer is formed with gas-thermal sputtering or it is formed by vacuum ion-plasma methods or magnetron methods or electron-ray evaporation and condensation in vacuum.
EFFECT: high operational characteristics of cover.
37 cl, 3 tbl, 1 ex
| Title | Year | Author | Number |
|---|---|---|---|
| HEAT RESISTANT COATING AND PROCEDURE FOR ITS FABRICATION | 2009 |
|
RU2426819C1 |
| METHOD OF PRODUCING CERAMIC REFRACTORY COAT | 2010 |
|
RU2441099C2 |
| METHOD OF HARDENING TURBO MACHINE NOZZLE VANE UNIT MADE FROM NICKEL AND COBALT ALLOYS | 2010 |
|
RU2445199C2 |
| PROCEDURE FOR APPLICATION OF HEAT PROTECTING COATING | 2009 |
|
RU2423551C2 |
| PROCEDURE FOR FORMING HEAT SHIELDING COATING ON TURBINE BLADE OF HEAT RESISTANT NICKEL ALOYS | 2009 |
|
RU2426817C2 |
| METHOD OF PRODUCING REFRACTORY COAT | 2009 |
|
RU2441103C2 |
| METHOD FOR PRODUCTION OF REINFORCED HEAT-SHIELDING COATING | 2009 |
|
RU2447195C2 |
| THERMAL PROTECTIVE COATING OBTAINING METHOD | 2010 |
|
RU2479669C2 |
| FORMATION METHOD OF THERMAL PROTECTIVE COATING ON PARTS OF GAS TURBINES FROM NICKEL AND COBALT ALLOYS | 2011 |
|
RU2479666C1 |
| METHOD OF PRODUCING HEAT-RESISTING COAT ON GAS TURBINE VANES | 2010 |
|
RU2441100C2 |
