Multi-element co-stabilizing zirconia of heat barrier coat material and preparation method

A technology for stabilizing zirconia and thermal barrier coatings, applied in the field of materials, can solve the problems of thermal barrier coating failure, volume increase, coating defects, etc., to achieve the effect of improving scattering, increasing service temperature, and increasing defects

Inactive Publication Date: 2009-04-01
INNER MONGOLIA UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the currently used Y-PSZ-based thermal barrier coating materials have the following disadvantages: 1) When the service temperature is higher than 1100 ° C, the coating is easy to sinter, and the microcracks and micropores in the coating will heal, resulting in the ceramic coating Densification causes the volume change of the coating material, aggravates the stress mismatch between the coating and the substrate, and further leads to the occurrence of

Method used

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  • Multi-element co-stabilizing zirconia of heat barrier coat material and preparation method
  • Multi-element co-stabilizing zirconia of heat barrier coat material and preparation method
  • Multi-element co-stabilizing zirconia of heat barrier coat material and preparation method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0015] Weigh ZrO according to the calculation 2 19.490 grams, Y 2 o 3 3.555 grams, Ta 2 o 5 6.956 g, Nd 2 o 3 1.276 g, put it into a polyurethane ball mill jar, use zirconia balls as the grinding body, add an appropriate amount of ethanol for wet grinding, take it out after 20 hours and put it in an oven at 80°C to dry to constant weight. Then transfer the dry powder to a mortar, add a little binder made of polyvinyl alcohol for granulation, and use a desktop tablet press to mold it. Put the compact obtained above into a molybdenum disilicide furnace and pre-fire it to 1550°C, keep it warm for 5 hours, and take it out after cooling with the furnace. Crush the pre-fired biscuit, continue to use zirconia balls as the grinding body for wet grinding for 24 hours, put it in an oven and bake it at 70°C until it reaches a constant weight, then granulate, mold and degumming, and then send it into a high-temperature furnace for further processing. Sintering, sintering temper...

Embodiment 2

[0017] Weigh 19.490 g of ZrO according to the calculation 2 , 3.555 g Y 2 o 3 , 6.956 g Ta 2 o 5 and 1.323 grams of Sm 2 o 3 , put it into a ball mill jar, use zirconia balls as the grinding rest, add an appropriate amount of ethanol for wet grinding, take it out after 16 hours and put it in an oven at 60°C to dry to constant weight. Then transfer the dry powder to a mortar, add a little binder made of polyvinyl alcohol for granulation, and use a desktop tablet press to mold it. Put the compact obtained above into a molybdenum disilicide furnace and pre-fire it to 1450°C, keep it warm for 10 hours, and take it out after cooling with the furnace. Grind the pre-fired biscuit, continue to use zirconia balls as the grinding body for wet grinding for 16 hours, put it in an oven at 70°C and bake it to constant weight, then granulate, mold and degumming, and then send it into a high-temperature furnace for further processing. Sintering, sintering temperature: 1300°C, time: 20h...

Embodiment 3

[0019] Weigh 19.490 g of ZrO according to the calculation 2 , 3.555 g Y 2 o 3 , 6.956 g Ta 2 o 5 and 1.375 grams of Gd 2 o 3 , put it into a ball mill jar, use zirconia balls as the grinding body, add an appropriate amount of ethanol for wet grinding, take it out after 18 hours and put it in an oven at 90°C to dry to constant weight. Then transfer the dry powder to a mortar, add a little binder made of polyvinyl alcohol for granulation, and use a desktop tablet press to mold it. Put the compact obtained above into a molybdenum disilicide furnace and pre-fire it to 1300°C, keep it warm for 12 hours, and take it out after cooling with the furnace. Crush the pre-fired biscuit, continue to use zirconia balls as the grinding body for wet grinding for 18 hours, put it in an oven and bake it at 70°C until it reaches a constant weight, then granulate, mold and degumming, and then send it into a high-temperature furnace for further processing. Sintering, sintering temperature: 1...

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Abstract

The invention relates to a multivariant co-stable zirconia thermal barrier coating material and a preparation method which belong to the field of materials. The multivariant co-stable zirconia thermal barrier coating material is characterized by consisting of the following materials according to mole fractions: zirconia, yttria, niobium oxide or tantalum oxide and rare earth oxide. The preparation method comprises the following steps: a zirconia ball is ground by wet process, dried and molded; a pre-burnt block is obtained by pre-burning; the pre-burnt block is smashed and further carried out with the wet ball milling to obtain slurry; the slurry is dried, granulated and mould pressed to obtain a green body, the green body is sintered to obtain the multivariant co-stable zirconia thermal barrier coating material; the ceramic material can be used as a target material for preparing a thermal barrier coating by using the EB-PVD method. A third phase of Nb2O5/Ta2O5 is introduced in YSZ to develop the stable existence interval of t-ZrO2 to further obtain non-transition t'-ZrO2, and the rare earth oxide is added to increase the defects to further improve the phonon or photon scattering on the basis, thereby improving the using temperature of the ZrO2 thermal barrier coating and reducing the thermal conductivity of the material.

Description

1. Technical field [0001] The invention relates to a multi-component co-stabilized zirconia thermal barrier coating material and a preparation method, belonging to the field of materials. 2. Background technology [0002] With the development of the aerospace industry, the engine has a high thrust-to-weight ratio and a large driving force. The main measure adopted is to increase the inlet temperature of the turbine. This makes the original high-temperature alloy materials for manufacturing aero-engines unable to meet the requirements. In order to increase the service temperature of the engine, the method commonly used at present is to first coat a layer of transition alloy layer such as NiCrAlY on the surface of the hot end parts such as the turbine working blades, guide vanes, turbine disks, and combustion chambers of aero-engines and various gas turbines. , and then coat it with a layer of 6-8% yttrium oxide (Y 2 o 3 ) partially stabilized zirconia (ZrO 2 ) (Y-PSZ) the...

Claims

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Application Information

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IPC IPC(8): C04B35/66C09D1/00C09D5/18C04B35/48
Inventor 宋希文谢敏李培忠于海涛赵鸣郭巍安胜利
Owner INNER MONGOLIA UNIV OF SCI & TECH
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