Precision casting process of high-temperature alloy turbine

A technology of precision casting and superalloy, which is applied in the direction of manufacturing tools, casting molding equipment, metal processing equipment, etc., can solve problems such as shrinkage porosity, achieve the effects of reducing shrinkage porosity, facilitating rapid cooling, and solving the problems of oxidation and shrinkage porosity

Inactive Publication Date: 2019-08-30
鹰普航空科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The parts produced by the existing technology are prone to shrinkage in the inner cavity of the part

Method used

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  • Precision casting process of high-temperature alloy turbine
  • Precision casting process of high-temperature alloy turbine
  • Precision casting process of high-temperature alloy turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0033] A precision casting process for a superalloy turbine, comprising the following steps:

[0034] (1) Part mold design and manufacture: The part wax mold adopts the bottom injection design to ensure the overall filling of the wax mold. The mold material is forged aluminum 6061. The overall mold is a box structure, which is composed of 40 live blocks. Figure 1~3 mold shown;

[0035] (2) Ceramic core preparation: Due to the complex structure of the inner cavity of the part, the inner cavity of the part is filled with a ceramic core. The ceramic core is aluminum-based ceramics, and the surface is coated with cobalt aluminate to reduce shrinkage porosity on the surface of the part. The mass fraction of alumina 99.5%, cobalt aluminate 0.5%, prepared Figure 10~12 mold shown;

[0036] (3) Preparation of shell slurry: the surface layer slurry is mixed with quick-drying silica sol, zircon powder, and cobalt aluminate powder at a weight ratio of 2:10:1, and stirred for 24 hours ...

Embodiment 2

[0042] A precision casting process for a superalloy turbine, comprising the following steps:

[0043] (1) Part mold design and manufacture: The part wax mold adopts the bottom injection design to ensure the overall filling of the wax mold. The mold material is forged aluminum 6061. The overall mold is a box structure, which is composed of 40 movable blocks;

[0044] (2) Ceramic core preparation: Due to the complex structure of the inner cavity of the part, the inner cavity of the part is filled with a ceramic core. The ceramic core is aluminum-based ceramics, and the surface is coated with cobalt aluminate to reduce shrinkage porosity on the surface of the part. The mass fraction of alumina is 99%, cobalt aluminate 1%, and the mold is prepared;

[0045] (3) Preparation of shell slurry: the surface layer slurry is mixed with quick-drying silica sol, zircon powder, and cobalt aluminate powder at a weight ratio of 2.5:10.5:0.8, and stirred for 24 hours until the slurry is evenly ...

Embodiment 3

[0051] A precision casting process for a superalloy turbine, comprising the following steps:

[0052] (1) Part mold design and manufacture: The part wax mold adopts the bottom injection design to ensure the overall filling of the wax mold. The mold material is forged aluminum 6061. The overall mold is a box structure, which is composed of 40 movable blocks;

[0053] (2) Ceramic core preparation: Due to the complex structure of the inner cavity of the part, the inner cavity of the part is filled with a ceramic core. The ceramic core is aluminum-based ceramics, and the surface is coated with cobalt aluminate to reduce shrinkage porosity on the surface of the part. The mass fraction of alumina is 99%, cobalt aluminate 1%, and the mold is prepared;

[0054] (3) Preparation of shell slurry: the surface layer slurry is mixed with quick-drying silica sol, zircon powder, and cobalt aluminate powder at a weight ratio of 2.5:10:1, and stirred for 24 hours until the slurry is evenly mixe...

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Abstract

The invention belongs to the technical field of aviation precision casting, and particularly relates to a precision casting process of a high-temperature alloy turbine. The precision casting process of the high-temperature alloy turbine comprises the following steps of designing and manufacturing a part mold, preparing a ceramic core, preparation of a shell slurry, preparation of a part shell, dewaxing of a shell, pre-roasting of the shell and casting of the part, wherein the part mold is designed to ensure the integral punching of a wax mold by adopting a bottom injection type design. An inner cavity of the part is filled with the ceramic core, the ceramic core is an aluminum-based ceramic coated with cobalt aluminate on the surface, the surface of the inner cavity of the part can be effectively reduced by coating the surface of the ceramic core with cobalt aluminate, so that the problems of oxidation and shrinkage in the inner cavity of a traditional casting process casting are successfully solved, and meanwhile, the high porosity can ensure that the ceramic core can be removed by a high-pressure water gun after being poured.

Description

technical field [0001] The invention belongs to the technical field of aviation precision casting, and in particular relates to a precision casting process of a superalloy turbine. Background technique [0002] With the gradual development of the civil aviation industry, the aero-engine, as the most critical component of a civil aircraft, has higher and higher requirements. Nickel-based superalloys are the main materials of aero-engines. Due to the complex and harsh service environment, superalloy parts generally have relatively complex inner cavity structures. Parts produced by the prior art are prone to shrinkage in the inner cavity of the part. Contents of the invention [0003] The technical problem to be solved by the present invention is to provide a high-temperature alloy turbine precision casting process for the above-mentioned deficiencies in the prior art. The ceramic core used in the preparation process of the present invention is a composite material of alumi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22C9/28B22C7/02B22C9/04B22C9/10B22C3/00B22C9/12B22D27/15
CPCB22C3/00B22C7/02B22C9/04B22C9/10B22C9/12B22C9/28B22D27/15
Inventor 安庆贺庄绪雷
Owner 鹰普航空科技有限公司
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