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Method of preparing target material for high-purity aero-engine blade bonding coating

A technology of aero-engine and bonding coating, which is applied in coating, vacuum evaporation plating, metal material coating process, etc., and can solve the problems of unfavorable target performance, improvement, and low target purity.

Inactive Publication Date: 2019-03-29
SUZHOU INST OF BEIHANG UNIV +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the purity of the target prepared by the existing preparation process is low, which is not conducive to the improvement of the performance of the target

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] Example 1: A method for preparing a high-purity aero-engine blade bond coating target

[0030] Include the following steps in order:

[0031] 1) Raw material pretreatment: After polishing the surface scale of Ni block, Co block, Cr block, Al block and Y block, use acetone to clean ultrasonically at a frequency of 20-30KHz twice, each time for 5 min, and clean Finally, put it in an oven and dry it at 373K for 10-30 minutes to obtain the pretreated target raw material;

[0032]2) Crucible and ingot mold pretreatment: Put the vacuum induction smelted graphite ingot mold and the graphite ingot mold molded in the molding sand box into the resistance furnace when the temperature is raised to 1173K, and keep it warm for 2 to 4 hours;

[0033] 3) Crucible and ingot mold installation: install the crucible and the fully preheated ingot mold in the vacuum induction melting furnace, clean the crucible and ingot mold, and install a ceramic filter on the sprue cup;

[0034] 4) Batc...

Embodiment 2

[0045] Example 2: A method for preparing a high-purity aeroengine blade bond coating target

[0046] Include the following steps in order:

[0047] 1) Raw material pretreatment: After polishing the surface scale of Ni block, Co block, Cr block, Al block and Y block, use acetone to clean ultrasonically at a frequency of 20-30KHz twice, each time for 5 min, and clean Finally, put it in an oven and dry it at 373K for 10-30 minutes to obtain the pretreated target raw material;

[0048] 2) Crucible and ingot mold pretreatment: Put the vacuum induction smelted graphite ingot mold and the graphite ingot mold molded in the molding sand box into the resistance furnace when the temperature is raised to 1173K, and keep it warm for 2 to 4 hours;

[0049] 3) Crucible and ingot mold installation: install the crucible and the fully preheated ingot mold in the vacuum induction melting furnace, clean the crucible and ingot mold, and install a ceramic filter on the sprue cup;

[0050] 4) Batc...

Embodiment 3

[0061] Example 3: A method for preparing a high-purity aeroengine blade bond coating target

[0062] Include the following steps in order:

[0063] 1) Raw material pretreatment: After polishing the surface scale of Ni block, Co block, Cr block, Al block and Y block, use acetone to clean ultrasonically at a frequency of 20-30KHz twice, each time for 5 min, and clean Finally, put it in an oven and dry it at 373K for 10-30 minutes to obtain the pretreated target raw material;

[0064] 2) Crucible and ingot mold pretreatment: Put the vacuum induction smelted graphite ingot mold and the graphite ingot mold molded in the molding sand box into the resistance furnace when the temperature is raised to 1173K, and keep it warm for 2 to 4 hours;

[0065] 3) Crucible and ingot mold installation: install the crucible and the fully preheated ingot mold in the vacuum induction melting furnace, clean the crucible and ingot mold, and install a ceramic filter on the sprue cup;

[0066] 4) Batc...

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PUM

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Abstract

The invention discloses a method of preparing a target material for high-purity aero-engine blade bonding coating. The method is characterized by sequential comprising the following steps the raw materials are pretreated; a crucible and an ingot mold are pretreated, a graphite ingot mold which is subjected to vacuum induction melting and a graphite ingot mold which is modeled by a molding sand box are put in a resistance furnace , when the temperature is heated to 1170-1175 K, and the temperature is kept for 2-4 hours; and the crucible and the fully preheated ingot mold are installed in a vacuum induction smelting furnace; burdening and charging are carried out; vacuumizing is carried out; melting is carried out until all metal blocks are molten; an aluminum block is added; slagging off is carried out; argon gas is introduced; a yttrium block is added; refining is carried out; and casting and forming is carried out, and finally the material is taken to obtain the target material. According to the method, procedures of the selecting of raw materials of the production process, the removing of oxide skin, controlling and optimizing of the components, cleaning of the crucible and theingot mold, smelting of protection atmosphere and the like are controlled strictly, and the introduction of impurity elements can be avoided in each procedure, so that the high-purity MCrAlY target material is obtained.

Description

technical field [0001] The invention relates to the field of aviation material preparation, in particular to a method for preparing a high-purity aeroengine blade bonding coating target. Background technique [0002] As the thrust-to-weight ratio of aeroengines continues to increase, the turbine inlet temperature also continues to increase. The turbine inlet temperature of an aero-engine with a thrust-to-weight ratio of 10 has reached 1600-1700°C, while the design inlet temperature of an aero-engine with a thrust-to-weight ratio of 12-15 will reach 1700-1800°C. Similarly, the development of advanced gas turbines has also increased the initial temperature of the gas, and the turbine blades are exposed to temperatures as high as 1100 °C, which has exceeded the limit service temperature of nickel-based superalloys (1075 °C). The preparation of thermal barrier coating on the surface of the blade can greatly reduce the temperature of the blade by about 90-150°C, improve its work...

Claims

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Application Information

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IPC IPC(8): C22C30/00C22C1/02C23C14/34
CPCC22C1/023C22C19/058C22C30/00C23C14/3414
Inventor 张花蕊张虎
Owner SUZHOU INST OF BEIHANG UNIV
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