FIELD: machine building.
SUBSTANCE: on surface of top of turbine blade there are secured particles of silicon carbide (SiC) for forming abrading layer. On SiC-particles there is formed a self-recovering preventing layer out of metal or alloy facilitating formation of carbides, thermodynamically more stable, than SiC. Said metal or alloy is chosen from the group consisting of chromium (Cr), zirconium (Zr), titanium (Ti), tantalum (Ta), niobium (Nb), hafnium (Hf), yttrium (Y), scandium (Sc), thorium (Th), uranium (U), molybdenum (Mo), and also alloys of said elements. SiC-particles are fixed by their intrusion into a metal matrix or by high-temperature soldering with brasing metal or by laser weld.
EFFECT: produced self-recovering abrading layer possesses high resistance against destruction of SiC-particles at good cutting and grinding properties.
20 cl, 4 dwg
Title | Year | Author | Number |
---|---|---|---|
BINDING METAL COATING WITH HIGH GAMMA/GAMMA' TRANSITION TEMPERATURE, AND COMPONENT | 2010 |
|
RU2521925C2 |
LAYERED SYSTEM OF COATING WITH MCRALX LAYER AND CHROME-ENRICHED LAYER AND METHOD OF OBTAINING THEREOF | 2009 |
|
RU2542870C2 |
HONEYCOMB SEAL AND METHOD OF ITS MANUFACTURING | 2009 |
|
RU2515869C2 |
RECONDITIONING OF TURBINE BLADE WITH AT LEAST ONE ROOT | 2011 |
|
RU2527509C2 |
METHOD OF APPLYING PROTECTIVE COATING ON GAS TURBINE BLADES | 1999 |
|
RU2171315C2 |
MATERIAL AND SYSTEM OF LAYERS | 2006 |
|
RU2395624C2 |
TURBINE BLADE AND METHOD FOR ITS MANUFACTURE | 1992 |
|
RU2065505C1 |
MATRIX AND LAMINATED SYSTEM WITH NON-STOICHIOMETRIC PARTICLES | 2007 |
|
RU2412277C2 |
ALLOY, PROTECTIVE LAYER AND STRUCTURAL PART | 2011 |
|
RU2562656C2 |
NICKEL-BASED ALLOY, USE AND METHOD | 2012 |
|
RU2567140C2 |
Authors
Dates
2011-03-20—Published
2006-07-13—Filed