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zrb with core-shell structure 2 ‑sic/si composite powder and preparation method thereof

A technology of composite powder and core-shell structure, which is applied in the coating and other directions, can solve the problems that the coating is difficult to meet the high-temperature thermal protection performance requirements, the two phases in the coating cannot be uniformly dispersed, and the SiC composition is insufficient, etc., to achieve large-scale production. Industrialized production, promoting the improvement of coating performance, and the effect of low equipment requirements

Active Publication Date: 2017-02-22
BEIJING GENERAL RES INST OF MINING & METALLURGY +1
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, in the ZrB prepared by ordinary spray-drying agglomeration granulation technology 2 - SiC group aggregate composite powder, or mechanically mixed powder for plasma spraying ZrB 2 -SiC-based coatings, due to the high-temperature, easy-to-decompose and volatile properties of SiC, will cause a large amount of burning loss, resulting in insufficient SiC components in the coating, the two phases in the coating cannot be uniformly dispersed, and the coating is difficult to meet the high-temperature thermal protection performance requirements And other issues

Method used

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  • zrb with core-shell structure <sub>2</sub> ‑sic/si composite powder and preparation method thereof
  • zrb with core-shell structure <sub>2</sub> ‑sic/si composite powder and preparation method thereof
  • zrb with core-shell structure <sub>2</sub> ‑sic/si composite powder and preparation method thereof

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preparation example Construction

[0042] The present invention provides a kind of above-mentioned ZrB with core-shell structure 2 -The preparation method of SiC / Si composite powder, specifically comprises the following steps:

[0043] 1): The particle size refinement of each original powder:

[0044] After the powder is refined, the primary primary particle size of each primary powder is less than 5 μm;

[0045] 2): Powder spray drying agglomeration granulation:

[0046] The refined powder is weighed according to the mass percentage of the nucleus, and used as spray granulation;

[0047] The refined powder is mixed with an organic binder to form a slurry for ball milling, and then the slurry after ball milling is spray-dried and agglomerated in a spray drying tower. 60-100ml / min; the inlet temperature is between 250-350°C, the outlet temperature is between 100-220°C, and after spray drying, solid aggregate particles containing organic binders are obtained, namely ZrB 2 - SiC composite powder;

[0048] 3):...

Embodiment 1

[0067] In the core-shell structure composite powder prepared in this example: the shell is completely ZrB 2 , accounting for 15wt% of the total powder weight, ZrB in the inner core 2 and SiC composition percentages were 60wt% and 25wt%.

[0068] The core-shell structure ZrB in the present embodiment 2 Pack ZrB 2 -SiC homogeneously dispersed composite powder is prepared by the following method, including the following steps:

[0069] 1) The particle size refinement of each original powder:

[0070] Using ball milling process, in the ball mill, add ZrB respectively 2 , SiC, ZrO 2 Grinding balls and water, set the mass ratio of grinding balls: powder: ball milling medium water at 7.5:1:2.5, the ball milling speed is set to 300r / min, the ball milling time is 6h, and the ball milling is dried at 120°C for 10h in vacuum.

[0071] After ball milling and drying, ZrB 2 and the particle size distribution diagrams of SiC, respectively, as figure 2 and image 3 shown.

[0072] ...

Embodiment 2

[0082] The core-shell structure composite powder prepared in this example: the shell is completely ZrB 2, accounting for 15wt% of the total composition of the powder, ZrB in the core 2 and Si composition percentages were 77.3wt% and 7.7wt%.

[0083] The core-shell structure ZrB in the present embodiment 2 Pack ZrB 2 -Si homogeneously dispersed composite powder is prepared by the following method, including the following steps:

[0084] 1) The particle size refinement of each original powder:

[0085] Original ZrB 2 , Si, etc. are respectively added to the jet milling classifier and processed by jet milling method, the crushing pressure is: 0.8Mpa, and the airflow speed can reach supersonic speed 400m / s at this time.

[0086] 2) Spray drying and agglomeration granulation of powder:

[0087] Weigh the refined powder according to the required mass percentage of the nucleus. Spray granulation virgin powder ZrB 2 , Si and organic binder solution are mixed to form a slurry f...

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Abstract

The invention discloses a core-shell-structure ZrB2-SiC / Si composite powder and a preparation method thereof. The composite powder comprises an inner core and an outer shell coated outside the inner core, wherein the inner core is ZrB2 and SiC or the inner core is ZrB2 and Si, and the outer shell is a ZrB2 layer. The invention also discloses a preparation method of the core-shell-structure ZrB2-SiC / Si composite powder, which comprises the following steps: 1) refinement of the particle sizes of original powders; 2) spray drying and aggregation granulation of powder; 3) coating of powder; and 4) high-temperature sintering. The high-melting-point ZrB2 is adopted to protect the inner SiC, thereby effectively preventing the SiC from decomposition and burning loss in the plasma spraying process and implementing consistence of the coating composition and powder composition. The ZrB2 and SiC microzones in the powder are uniformly dispersed, and the coating prepared by plasma spraying can implement multiphase microzone uniform distribution and promote the enhancement of the coating performance.

Description

technical field [0001] The invention relates to the field of ultra-high temperature oxidation resistant materials, in particular to a ZrB with core-shell structure 2 -SiC / Si composite powder and its preparation method. Background technique [0002] When high-temperature structural materials such as refractory metals and alloys, ceramic matrix composites, and fiber-reinforced composites are used in high-temperature oxidizing environments, their surfaces must be protected with an anti-oxidation thermal protective coating. Non-oxides such as borides, silicides, and carbides have the characteristics of high melting point, low density, and good phase stability. They have been widely used in nose cones and wing leading edges of re-entry vehicles, space propulsion system materials, space shuttles, etc. High-temperature heat insulation protection for the hottest parts such as thermal protection systems and space aircraft thermal structural materials. [0003] At present, in the pr...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B22F1/02C04B35/58C04B35/628B22F9/08
Inventor 于月光张鑫吴琼彭浩然冀晓鹃张春鸣王彦军
Owner BEIJING GENERAL RES INST OF MINING & METALLURGY
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