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High temperature thermal insulation material, particularly for gas turbine, and manufacturing method thereof

A high-temperature thermal insulation material and technology for gas turbines, which are used in the fields of high-temperature thermal insulation materials for gas turbine components and materials for thermal barrier coatings, can solve problems such as low thermal conductivity, achieve high firing temperature and improve turbine efficiency.

Active Publication Date: 2019-01-22
ANSALDO ENERGIA IP UK LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0013] However, even though ceramic materials are known to generally have low thermal conductivity, currently available materials still have room for improvement, especially for higher operating temperatures, lower thermal conductivity, longer life expectancy, and increased resistance to mechanical and chemical stress

Method used

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  • High temperature thermal insulation material, particularly for gas turbine, and manufacturing method thereof
  • High temperature thermal insulation material, particularly for gas turbine, and manufacturing method thereof
  • High temperature thermal insulation material, particularly for gas turbine, and manufacturing method thereof

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Embodiment Construction

[0064] As previously stated, the material according to the invention is a composite material comprising a ceramic matrix of fully stabilized zirconia, in particular fully yttria-stabilized zirconia (YSZ), dispersed with agglomerated hafnium dioxide particles, and having Porous structure of fine pores (with predetermined dimensions) obtained by adding at least one porogen.

[0065] Advantageously, the hafnium dioxide particles are agglomerated particles, ie particles gathered together in clusters of particles. The clusters are uniformly dispersed in the ceramic matrix.

[0066] Optionally, the material also includes fine-sized particles of hafnium dioxide (or another similar refractory inorganic powder).

[0067] The ceramic composite material of the invention can be prepared, for example, by a manufacturing process of the general type usually used for the manufacture of ceramic materials, in particular a dry process comprising a pressureless sintering step followed by a uniax...

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Abstract

A high temperature thermal insulation material is provided, particularly for gas turbine components, comprising a porous ceramic matrix of yttrium oxide-stabilized zirconia (YSZ) having a porous microstructure; and hafnium dioxide (HfO2 ) particles incorporated within the porous ceramic matrix in form of aggregated clusters.

Description

[0001] priority claim [0002] This application claims priority to European Patent Application No. 17181554.1 filed on July 14, 2017, the disclosure of which is incorporated by reference. technical field [0003] The invention relates to a high temperature heat insulating material, especially a high temperature heat insulating material for gas turbine components, and a manufacturing method thereof. [0004] In particular, the present invention relates to a material suitable for replacing current thermal barrier coatings (TBC). Background technique [0005] In many technical fields, for example in the field of gas turbines, it is well known that there is a need for effective thermal protection of components / surfaces operating at very high temperatures. [0006] In gas turbines in particular, internal components are exposed to a particularly aggressive environment, subjecting the components to high levels of stress, not only thermal but also corrosive and mechanical. [0007...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/48C04B38/06
CPCC04B35/48C04B38/067C04B2235/3244C04B2235/3225C04B35/486C04B35/488C04B35/4885C04B35/6261C04B35/78C04B38/0074F01D5/284C04B2235/3217C04B2235/3239C04B2235/3246C04B2235/50C04B2235/5436C04B2235/5445C04B2235/604C04B2235/77C04B2235/80C04B2235/96C04B2235/9607C04B2235/9669F01D25/005F05D2300/2118F05D2300/61C04B2111/2084F01D5/282F01D5/288F23R3/007F05D2300/6033F23R2900/00018C04B35/80
Inventor H-P.博斯曼D.雷努施T-T.楚M.米彻勒J.库尔伯勒
Owner ANSALDO ENERGIA IP UK LTD