Novel heat barrier coating material

Abstract

The invention relates to a series of ceramic materials used as high temperature thermal barrier coating materials and their use, wherein the chemical constitution of the ceramic material being A2ZrxCe(1-x)2O7, wherein 0<=x<=0.9, an is one or combination of two of Nd, Sm, Eu, Gd and Tb. The ceramic material has high coefficient of thermal expansion, thus can be designed into thermal barrier coating material, whose application temperature interval is between room temperature to 1400 deg. C.

Description

technical field [0001] The invention belongs to high-temperature thermal barrier coating technology and related coating materials. Background technique [0002] With the development of aviation, aerospace and civil technology, the temperature requirements of the hot end parts of the vortex engine are getting higher and higher, and the superalloy single crystal has reached the limit state of the material. In this case, from the material point of view, another feasible technology to reduce the operating temperature of engine blades - thermal barrier coating technology has been widely used. [0003] A comparative study by NASA showed that ZrO 2 The overall performance is superior. At 1000°C, ZrO 2 The coefficient of thermal expansion is 11×10 -6 K -1 , which is closest to the thermal expansion coefficient of the base alloy, while the thermal conductivity is only 2.1-2.2Wm -1 K -1 . But pure ZrO 2 In the usual temperature range, a martensitic phase transformation from t...

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Problems solved by technology

But La 2 Zr 2 o 7 The thermal expansion coefficient is smaller than that of YSZ, and the thermal expansion coefficient of the base alloy is more different. The internal stress of the coating caused by the mismatch of high temperature thermal expansion will be more serious, and the coating cycle life will be short.

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