FIELD: machine building.
SUBSTANCE: refractory sub layer is applied on gas turbine engine vanes, then reinforced ceramic layer is formed. Note here that said reinforced ceramic layer is formed step-by-step in the following order. Discrete layer of ceramic material in the form of insular areas on sublayer surface leaving exposed 4-98% of its total surface, at least on solid metal layer from refractory material with thickness varying from 1 mcm to 12 mcm, and outer solid ceramic layer. Discrete layer is formed from round, oval or cellular insular sites with sizes varying from 0.02 mm to 5 mm. Material of said discrete ceramic layer and outer ceramic layer may be ZrO2-Y2O3 taking in the following amount: Y2O3 - 5-9 wt % , ZrO2 making the rest.
EFFECT: better operating properties, reduced labor input, higher cyclic durability and strength.
24 cl, 3 tbl
Title | Year | Author | Number |
---|---|---|---|
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 APPLYING HEAT COATING OF NICKEL OR COBALT ALLOY ON GAS TURBINE PARTS | 2011 |
|
RU2496911C2 |
PROCEDURE FOR FORMING HEAT SHIELDING COATING ON TURBINE BLADE OF HEAT RESISTANT NICKEL ALOYS | 2009 |
|
RU2426817C2 |
HEAT RESISTANT COATING AND PROCEDURE FOR ITS FABRICATION | 2009 |
|
RU2426819C1 |
METHOD OF PRODUCING REFRACTORY COAT | 2009 |
|
RU2441103C2 |
PROCEDURE FOR APPLICATION OF HEAT PROTECTING COATING | 2009 |
|
RU2423551C2 |
METHOD OF PRODUCING HEAT-RESISTING COAT ON GAS TURBINE VANES | 2010 |
|
RU2441100C2 |
HEAT PROTECTING COVER FOR TURBINE BLADES AND PROCEDURE FOR ITS FABRICATION | 2009 |
|
RU2423550C1 |
Authors
Dates
2012-01-27—Published
2010-04-13—Filed