Method and apparatus for fabrication and repair of thermal barriers
A thermal barrier tile ( 34 ) with a braze layer ( 46 ) co-sintered to a ceramic layer ( 48 ) is brazed to a substrate ( 26 ) of a component for fabrication or repair of a thermal barrier coating ( 28 ) for example on a gas turbine ring segment ( 22, 24 ). The tile may be fabricated by disposing a first layer of a metal brazing material in a die case ( 40 ); disposing a second layer of a ceramic powder on the metal brazing material; and co-sintering the two layers with spark plasma sintering to form the co-sintered ceramic/metal tile. A material property of an existing thermal barrier coating to be repaired may be determined ( 90 ), and the co-sintering may be controlled ( 93 ) responsive to the property to produce tiles compatible with the existing thermal barrier coating in a material property such as thermal conductivity.
1. A method for fabricating a thermal barrier of a gas turbine component, comprising:
determining at least one material property of an existing thermal barrier coating on the component, the material property selected from the group consisting of modulus of elasticity, thermal conductivity, and coefficient of thermal expansion, wherein a value of said at least one material property is determined as a function of operating temperature and operating duration of the existing thermal barrier coating; and
disposing a first layer of a metal brazing material in a die case;
disposing a second layer of a ceramic material on the metal brazing material; and
co-sintering the first and second layers in the die case with spark plasma sintering to form a co-sintered ceramic/metal tile comprising a metal brazing layer, a ceramic thermal barrier layer, and a co-sintered interface there between; and
controlling the co-sintering to make the ceramic/metal tile to match the value of said at least one material property within 10% over an expected range of operating temperatures and time.
2. The method of claim 1 , further comprising forming a predetermined porosity in the ceramic layer by preparing a preform of the ceramic material prior to the disposing of the second layer of the ceramic material on the metal brazing material, wherein the ceramic preform comprises inclusions that produce the porosity after the co-sintering.
3. The method of claim 1 , further comprising forming the co-sintered interface with an interlocking structural pattern.
4. The method of claim 3 , further comprising molding the brazing material into a patterned preform with the interlocking structural pattern thereon before the disposing of the second layer thereon.
5. The method of claim 1 , further comprising making the metal brazing material of Cr 15-25 wt %, Ti 15-25 wt %, and the balance Ni.
6. The method of claim 1 , further comprising making the metal brazing material of Cr 12-16 wt %; Ti 13-16 wt %; Al 0-2.5 wt %; Co 2-4 wt %; W 3-5 wt %; Mo 0-2 wt %; Ta 0-2 wt %; and the balance Ni.