FIELD: machine building.
SUBSTANCE: procedure consists in forming under-layer by successive application of heat resistant, transition and external ceramic layers with following diffusion annealing. Also, composition of the transition layer consists of material mixture of the ceramic layer and constituents of the heat resistant alloy, at first annealing and formation of a liquid fusible phase facilitating wetting ceramic constituent of the transitional layer, and further forming a refractory heat resistant chemical compound. Transition and heat-protection layers are applied by the gas-thermal method. As applied material for the transitional layer there is used a powder mixture consisting of: material of the ceramic layer from 1 to 99 %; constituents of a heat resistant alloy - the rest, while for heat protection layer - ZrO2-Y2O3. Before application of the heat resistant layer surface of a blade is ion-plasma treated with ions of Nb, Pt, Yb, Y, La, Hf Cr, Si or their combination. Ion implantation is carried out at ion power from 0.2 keV to 30 keV and dose of implantation of ions from 1010 to 5·1020 ion/cm2.
EFFECT: upgraded properties of coating.
22 cl, 3 tbl
Title | Year | Author | Number |
---|---|---|---|
HEAT RESISTANT COATING AND PROCEDURE FOR ITS FABRICATION | 2009 |
|
RU2426819C1 |
METHOD FOR PRODUCTION OF REINFORCED HEAT-SHIELDING COATING | 2009 |
|
RU2447195C2 |
HEAT PROTECTING COVER FOR TURBINE BLADES AND PROCEDURE FOR ITS FABRICATION | 2009 |
|
RU2423550C1 |
PROCEDURE FOR FORMING HEAT SHIELDING COATING ON TURBINE BLADE OF HEAT RESISTANT NICKEL ALOYS | 2009 |
|
RU2426817C2 |
METHOD OF PRODUCING REFRACTORY COAT | 2009 |
|
RU2441103C2 |
METHOD OF RECONDITIONING TURBO MACHINE NOZZLE VANES ASSEMBLY MADE FROM NICKEL AND COBALT ALLOYS | 2009 |
|
RU2426632C1 |
THERMAL PROTECTIVE COATING OBTAINING METHOD | 2010 |
|
RU2479669C2 |
METHOD OF PRODUCING CERAMIC REFRACTORY COAT | 2010 |
|
RU2441099C2 |
METHOD OF HARDENING TURBO MACHINE NOZZLE VANE UNIT MADE FROM NICKEL AND COBALT ALLOYS | 2010 |
|
RU2445199C2 |
METHOD OF PRODUCING REFRACTORY COAT OF GAS TURBINE VANES | 2010 |
|
RU2441101C2 |
Authors
Dates
2011-07-10—Published
2009-09-23—Filed