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A method for manufacturing a low-deformation toughened silicon-based ceramic core

A technology of ceramic core and manufacturing method, which is applied in the field of precision casting to achieve the effects of reducing sintering deformation, lowering sintering temperature and high toughness

Active Publication Date: 2017-12-12
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aiming at the problems existing in the prior art, the present invention provides a method for making a low-deformation toughened silicon-based ceramic core. Cracks and deformation caused by it can improve the qualified rate of ceramic core preparation and meet the preparation requirements of ceramic core with increasingly complex structure

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  • A method for manufacturing a low-deformation toughened silicon-based ceramic core

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Experimental program
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Effect test

Embodiment 1

[0018] The manufacturing method of the low-deformation toughened silicon-based ceramic core of the present embodiment is carried out according to the following steps:

[0019] (1) Weigh the powder according to the weight ratio of magnesia fiber to zirconia 1:40, put the powder into a ball mill and mix it for 0.5h, then put it into a roaster for roasting, the roasting conditions are as follows figure 1 As shown, the temperature is raised to 800°C at a heating rate of 160°C / h, kept at 800°C for 1 hour, then raised to 1300°C at a heating rate of 125°C / h, kept at 1300°C for 2 hours, and then discharged with the furnace to cool to room temperature , put into the grinder after discharging, add the grinding body in a weight ratio of 1:1, after grinding for 1.5h, pass through a 200 mesh sieve, and the powder obtained is used as a prefabricated mineralizer for subsequent use;

[0020] (2) According to weight percentage, 22% of 270-360-mesh quartz glass powder, 55% of 600-800-mesh quart...

Embodiment 2

[0023] The manufacturing method of the low-deformation toughened silicon-based ceramic core of the present embodiment is carried out according to the following steps:

[0024] (1) Weigh the powder according to the weight ratio of magnesia fiber to zirconia 1:45, put the powder into the ball mill and mix it for 0.5h, then put it into the roaster for roasting, as figure 1 As shown, the calcination condition is to heat up to 800°C at a heating rate of 160°C / h, hold at 800°C for 1 hour, then raise the temperature to 1300°C at a heating rate of 125°C / h, hold at 1300°C for 2 hours, and then cool to room temperature with the furnace Discharging, after discharging, put it into the grinder, add grinding body at a weight ratio of 1:1, after grinding for 3 hours, pass through a 200-mesh sieve, and the obtained powder is used as a prefabricated mineralizer for subsequent use;

[0025] (2) According to weight percentage, 33% of 270-mesh-360-mesh quartz glass powder, 50% of 600-mesh-800-mes...

Embodiment 3

[0028] The manufacturing method of the low-deformation toughened silicon-based ceramic core of the present embodiment is carried out according to the following steps:

[0029] (1) Weigh the powder according to the weight ratio of magnesia fiber to zirconia 1:42, put the powder into a ball mill and mix it for 0.5h, then put it into a roaster for roasting, as figure 1 As shown, the calcination condition is to heat up to 800°C at a heating rate of 160°C / h, hold at 800°C for 1 hour, then raise the temperature to 1300°C at a heating rate of 125°C / h, hold at 1300°C for 2 hours, and then cool to room temperature with the furnace Discharging, after discharging, put it into the grinding machine, add grinding body at a weight ratio of 1:1, after grinding for 2 hours, pass through a 200-mesh sieve, and the obtained powder is used as a prefabricated mineralizer for subsequent use;

[0030] (2) According to weight percentage, 45% of 270-360-mesh quartz glass powder, 40% of 600-800-mesh qua...

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Abstract

The invention belongs to the technical field of precision casting, and particularly relates to a making method of a low-deformation toughened silica-based ceramic core. Zirconium oxide is doped with different-valence metallic oxide magnesium oxide to serve as a stabilizer, ZrO2 can be maintained in a tetragonal phase or a cubic phase at room temperature, magnesium oxide is further added to a core sizing formula, a fibrous structure of the magnesium oxide can increase the toughness of a wet core when a core wet billet is pressed, drawing deformation and cracks of the core wet billet can be reduced, and the fracture rate during core trimming can be decreased. The making method of the low-deformation toughened silica-based ceramic core is not only suitable for preparing ceramic cores of large parts which are complex in shape and thin in wall, but also suitable for producing ceramic cores for equiaxial and directed hollow turbine blades. The core wet billet prepared through the making method is good in toughness, high in drawing yield, small in deformation and small in sintering deformation of the core.

Description

technical field [0001] The invention belongs to the technical field of precision casting, and in particular relates to a method for manufacturing a low-deformation toughened silicon-based ceramic core. Background technique [0002] With the continuous upgrading of the thrust-to-weight ratio of aero-engines, the temperature at the front inlet of the turbine continues to increase, and the requirements for the written capacity of the blades are also getting higher and higher. The blade has developed from real to hollow, from polycrystalline to single crystal, and the shape of the inner cavity of the blade has become increasingly complex. The ceramic core is the key component that forms the inner cavity of the blade, and its manufacturing technology has become the key technology of hollow smelting and manufacturing. The increasingly complex structure of the inner cavity of the blade makes the ceramic core easy to break and cause stress concentration during wet mold removal duri...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/14C04B35/63B28B3/00
CPCB28B3/00C04B35/14C04B35/63C04B2235/3246C04B2235/522C04B2235/602C04B2235/9607
Inventor 张玲黄静杜洪强张世东冯文刚
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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