Material for thermal barrier coating

A technology of thermal insulation coating and coating film, which is applied in the direction of coating, metal material coating process, air transportation, etc., and can solve problems such as residual tensile stress
CN100376505CInactive Publication Date: 2008-03-26MITSUBISHI HEAVY IND LTD
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
MITSUBISHI HEAVY IND LTD
Publication Date
2008-03-26
Estimated Expiration
Not applicable · inactive patent

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Abstract

The invention provides a novel thermal barrier coating material free from problems of the phase transition having a melting point higher than the temperature region for use, and having a thermal conductivity less than that of zirconia and a thermal expansion coefficient greater than that of zirconia. The thermal barrier coating material comprises a composition having an orthorhombic or monoclinic structure (for example, a tabular perovskite structure represented by the empirical formula: A2B2O7) derived from a perovskite structure or a tetragonal layer structure having a c axis / a axis ratio of 3 or more (for example, a K2NiF4 structure, a Sr3Ti2O7 structure and a Sr4Ti3O10 structure), a composition represented by the empirical formula: LaTaO4, or a composition having an olivine type structure represented by the empirical formula: M2SiO4 or (MM')2SiO4, wherein M and M' are divalent metal elements.
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Description

Technical field

[0001] The present invention relates to a heat-insulating coating material applicable to mechanical parts used in high-temperature environments such as rotor blades, stator blades, combustors, and jet engines of gas turbines for power generation. Background technique

[0002] In order to improve the efficiency of gas turbines and jet engines, methods of increasing the temperature of their combustion gases are adopted. Therefore, in order to protect metal parts at high temperatures (for example, the blade surface temperature of a 1500°C gas turbine is about 1400°C), the surface of the part is covered with a thermal barrier coating (TBC). As the material of the thermal barrier coating, a low thermal conductivity ceramic represented by rare earth stabilized zirconia is used (for example, refer to JP-A 8-074505 and JP-A 10-183013). The above-mentioned thermal barrier coating is implemented by forming a metal bonding layer by reduced pressure plasma spraying or the lik...

Claims

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