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Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns

A columnar structure and thermal barrier technology, applied in the field of turbines and turbine components, can solve the problem that the barrier is not high enough, and achieve the effect of great flexibility

Inactive Publication Date: 2013-03-13
SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] However all these barriers are not sufficiently high performing and it is necessary to further improve their performance in both domains

Method used

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  • Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns
  • Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns
  • Thermal barrier for turbine blades, having a columnar structure with spaced-apart columns

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Embodiment Construction

[0033] refer to figure 1 , seen in cross-section is the composition of the thermal barrier deposited on the surface of the turbine blade based on the thermal flow indicated by the arrow pointing towards the left of the figure. The metal that makes up the blade (typically a superalloy based on nickel or cobalt) forms the substrate 1 on which is deposited a sublayer made of aluminum 2 sandwiched between the substrate 1 and the ceramic layer 3 . The role of the aluminum sublayer is to hold the ceramic layer and to provide a certain elasticity to the assembly so that it can absorb the difference in expansion, indicated by the two arrows in opposite directions, between the high expansion substrate 1 and the low expansion ceramic between 3.

[0034] The ceramic 3 represented here belongs to the columnar structure, which allows lateral displacement due to the cracks that appear between the columns, and which gives it a good service life. The aluminum is then brought into contact w...

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Abstract

Process for depositing a ceramic layer on a metal substrate (1) for producing a thermal barrier, the process including a step of depositing said ceramic in a columnar structure, characterized in that said deposition is carried out through a grid pierced with holes, which is positioned parallel to the surface of the substrate (1) so as to produce ceramic columns (5) separated from one another by a space. Preferably, the process further includes a subsequent step of depositing an isotropic ceramic layer (7) in said spaces.

Description

technical field [0001] The field of the invention is that of turbomachines, and more particularly of components for these turbomachines that are subjected to high temperatures. Background technique [0002] Turbines used for propulsion, as in the field of aviation, include an atmospheric intake that communicates with one or more compressors, usually including a fan rotating about the same axis. This primary stream of air supplies a combustion chamber positioned annularly around this shaft before being compressed and mixed with fuel to provide hot gases downstream to one or more turbines by which the hot gases expand , the turbine rotor drives the compressor rotor. The engine runs at the temperature of the engine gases at the turbine inlet, which is sought to be as high as possible, since this temperature regulates the performance of the turbine. For this purpose, the material of the hot part is chosen to withstand these operating conditions and provide cooling means for th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C14/04C23C14/58F01D5/28C23C18/12C23C30/00
CPCC23C14/30F05B2230/90C23C18/06Y02T50/67C23C14/042F05C2203/08C23C14/58C23C18/1245C23C18/1208F01D5/288F05D2230/90C23C18/1254F01D5/284C23C4/02F05D2300/21C23C30/00C23C18/1225C23C18/1216Y10T428/24174Y02T50/60
Inventor 贾斯廷·曼纽伊莎拉·哈玛迪朱丽特·于戈安德鲁·休伯特·路易斯·马利法布里斯·克里博斯
Owner SN DETUDE & DE CONSTR DE MOTEURS DAVIATION S N E C M A