FIELD: machine building.
SUBSTANCE: procedure consists in generation of metal sub-layer of heat resistant alloy, transition metal ceramic layer and external ceramic layer of ZrO2, stabilised with Y2O3 on protected surface of blade. First there is applied a metal sub-layer. A layer of high-temperature solder is applied on the sub-layer, and the ceramic layer is applied on the layer of solder. Further, there is carried out diffusion annealing at temperature facilitating production of liquid phase of sub-layer metal. There is formed transition metal-ceramic layer due to wetting ceramic layer with metal of a lower high temperature solder at depth equal to thickness of the transition layer.
EFFECT: increased operational hardness of cohesion at boundary of transition layer-external ceramic layer at simultaneous raise of durability and cyclic strength of parts with protective coating.
26 cl, 3 tbl
Title | Year | Author | Number |
---|---|---|---|
THERMAL PROTECTIVE COATING OBTAINING METHOD | 2010 |
|
RU2479669C2 |
METHOD OF PRODUCING CERAMIC REFRACTORY COAT | 2010 |
|
RU2441099C2 |
HEAT PROTECTING COVER FOR TURBINE BLADES AND PROCEDURE FOR ITS FABRICATION | 2009 |
|
RU2423550C1 |
PROCEDURE FOR APPLICATION OF HEAT PROTECTING COATING | 2009 |
|
RU2423551C2 |
METHOD OF PRODUCING REFRACTORY COAT | 2009 |
|
RU2441103C2 |
METHOD FOR PRODUCTION OF REINFORCED HEAT-SHIELDING COATING | 2009 |
|
RU2447195C2 |
PROCEDURE FOR FORMING HEAT SHIELDING COATING ON TURBINE BLADE OF HEAT RESISTANT NICKEL ALOYS | 2009 |
|
RU2426817C2 |
METHOD OF HARDENING TURBO MACHINE NOZZLE VANE UNIT MADE FROM NICKEL AND COBALT ALLOYS | 2010 |
|
RU2445199C2 |
METHOD OF APPLYING HEAT COATING OF NICKEL OR COBALT ALLOY ON GAS TURBINE PARTS | 2011 |
|
RU2496911C2 |
FORMATION METHOD OF THERMAL PROTECTIVE COATING ON PARTS OF GAS TURBINES FROM NICKEL AND COBALT ALLOYS | 2011 |
|
RU2479666C1 |
Authors
Dates
2011-08-20—Published
2009-11-30—Filed