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A method for manufacturing complex structural ceramic parts for gas turbine hot end components

A technology of hot-end components and complex structures, which is applied in the field of rapid casting, can solve problems such as high sintering temperature and difficulty, and achieve the effects of improving molding efficiency, fast molding speed, and improved efficiency

Active Publication Date: 2017-01-04
XI AN JIAOTONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The sintering temperature of ceramics is very high, it is difficult to directly sinter with laser

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0045] A method for manufacturing complex structural ceramic parts oriented to gas turbine hot end components, comprising the following steps:

[0046] 1), preparation of ceramic powder

[0047] The ceramic powder matrix material is silicon carbide powder coated with phenolic resin on the surface, the particle size is 2-45 μm, and the mass fraction of the ceramic powder mixture is 75%. Add 1mm short silicon carbide fiber to improve the toughness of the blade, accounting for 15% of the mass fraction of the ceramic powder mixture. In order to ensure the strength of the ceramic blade after laser sintering and during the degreasing process, solid particle polymethyl methacrylate (PMMA) is added as a binder, and the mass fraction of the ceramic powder mixture is 10%. The above weighed powders were put into a ball mill and mixed evenly to obtain a ceramic powder mixture. The speed of the ball mill was 120r / min, and the ball milling time was 1h.

[0048] 2), laser sintering molding ...

Embodiment 2

[0057] A method for manufacturing complex structural ceramic parts oriented to gas turbine hot end components, comprising the following steps:

[0058] 1), preparation of ceramic powder

[0059] The ceramic powder matrix material is silicon carbide powder coated with phenolic resin on the surface, the particle size is 2-45 μm, and the mass fraction of the ceramic powder mixture is 80%. Adding 1 mm short silicon carbide fibers to improve the toughness of the blades accounts for 5% by mass of the ceramic powder mixture. In order to ensure the strength of the ceramic blade after laser sintering and degreasing, solid particle polymethyl methacrylate (PMMA) is added as a binder, and the mass fraction of the ceramic powder mixture is 15%. The above weighed powders were put into a ball mill and mixed evenly to obtain a ceramic powder mixture. The speed of the ball mill was 120r / min, and the ball milling time was 1h.

[0060] 2), laser sintering molding

[0061] The homogeneously m...

Embodiment 3

[0069] A method for manufacturing complex structural ceramic parts oriented to gas turbine hot end components, comprising the following steps:

[0070] 1), preparation of ceramic powder

[0071] The ceramic powder base material is silicon carbide powder coated with phenolic resin on the surface, the particle size is 2-45 μm, and the mass fraction of the ceramic powder mixture is 85%. Adding 1 mm short silicon carbide fibers to improve the toughness of the blades accounts for 5% by mass of the ceramic powder mixture. In order to ensure the strength of the ceramic blade after laser sintering and during the degreasing process, solid particle polymethyl methacrylate (PMMA) is added as a binder, and the mass fraction of the ceramic powder mixture is 10%. The above weighed powders were put into a ball mill and mixed evenly to obtain a ceramic powder mixture. The speed of the ball mill was 120r / min, and the ball milling time was 1h.

[0072] 2), laser sintering molding

[0073] Th...

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PUM

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Abstract

The invention discloses a manufacturing method of a complicated structure ceramic part of a gas turbine-oriented hot-end component. The method comprises the following steps: laminating phenolic resin on ceramic powder surface; adding a binder, and carrying out assisted forming; adding a proper amount of staple fibers to toughen; and stacking and molding the parts by using a material increase manufacturing technology. According to the method disclosed by the invention, siliconing or dipping treatment is carried out on the ceramic part; internal gaps of the part are filled by a chemical gas phase permeability technology; the compactness is improved, and thus, the manufacturing method is suitable for manufacturing of complicated structure part of the gas turbine; the manufacturing efficiency and the success rate can be greatly improved; and the method has high practical value.

Description

[0001] 【Technical field】 [0002] The invention belongs to the field of rapid casting, and in particular relates to a method for manufacturing ceramic parts with complex structures facing the hot end parts of gas turbines. [0003] 【Background technique】 [0004] As the gas turbine cooling system continues to become more complex, its manufacturing and processing difficulties continue to increase, and traditional machining methods have been difficult to meet its processing requirements. The development and research of new and effective manufacturing methods has become the goal pursued by researchers in this field. [0005] At present, investment casting technology is mainly used at home and abroad to prepare complex structural parts of hot end parts of gas turbines: firstly, ceramic cores with complex shapes are prepared by hot pressing and other processes; then metal molds are manufactured, and ceramic cores are assembled in metal molds , fill the gap between the metal mold an...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/185C04B35/10C04B35/622
CPCC04B2235/6026
Inventor 鲁中良白树钊刘涛曹继伟李涤尘
Owner XI AN JIAOTONG UNIV