FIELD: machine building.
SUBSTANCE: method includes application of a sublayer from a heat-resistant alloy and formation of a reinforced ceramic layer on the sublayer. The reinforced ceramic layer is formed in stages. At first the discrete ceramic layer is applied in the form of isle sections on the sublayer surface, leaving open from 4% to 98% of the total sublayer surface. Then at least one discrete metal layer is applied onto the discrete ceramic layer and open sections of the sublayer in the form of strips or a grid with the area from 4% to 98% from the total surface of the formed coating and thickness from 0.8 mcm to 5 mcm. Afterwards the outer solid ceramic layer is applied.
EFFECT: higher operational properties of coatings, reduced labour intensiveness of the method, increased endurance and cyclic strength of parts with the coating.
24 cl, 3 tbl
Title | Year | Author | Number |
---|---|---|---|
METHOD OF PRODUCING CERAMIC REFRACTORY COAT | 2010 |
|
RU2441099C2 |
PROCEDURE FOR FORMING HEAT SHIELDING COATING ON TURBINE BLADE OF HEAT RESISTANT NICKEL ALOYS | 2009 |
|
RU2426817C2 |
PROCEDURE FOR APPLICATION OF HEAT PROTECTING COATING | 2009 |
|
RU2423551C2 |
HEAT RESISTANT COATING AND PROCEDURE FOR ITS FABRICATION | 2009 |
|
RU2426819C1 |
HEAT PROTECTING COVER FOR TURBINE BLADES AND PROCEDURE FOR ITS FABRICATION | 2009 |
|
RU2423550C1 |
THERMAL PROTECTIVE COATING OBTAINING METHOD | 2010 |
|
RU2479669C2 |
METHOD OF PRODUCING REFRACTORY COAT | 2009 |
|
RU2441103C2 |
FORMATION METHOD OF THERMAL PROTECTIVE COATING ON PARTS OF GAS TURBINES FROM NICKEL AND COBALT ALLOYS | 2011 |
|
RU2479666C1 |
METHOD OF APPLYING HEAT COATING OF NICKEL OR COBALT ALLOY ON GAS TURBINE PARTS | 2011 |
|
RU2496911C2 |
METHOD OF HARDENING TURBO MACHINE NOZZLE VANE UNIT MADE FROM NICKEL AND COBALT ALLOYS | 2010 |
|
RU2445199C2 |
Authors
Dates
2012-04-10—Published
2009-07-06—Filed