Preparation method of combined type shell with heat insulating materials implanted therein

A thermal insulation material and composite technology, which is applied in casting molding equipment, casting molds, cores, etc., can solve problems such as uneven grain formation, and achieve the effect of solving uneven growth and saving production costs

Active Publication Date: 2015-02-04
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] The purpose of the present invention is to solve the problems existing in the above-mentioned prior art, and to provide a method for preparing a composite shell with an internally embedded thermal ins

Method used

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  • Preparation method of combined type shell with heat insulating materials implanted therein
  • Preparation method of combined type shell with heat insulating materials implanted therein
  • Preparation method of combined type shell with heat insulating materials implanted therein

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Experimental program
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Effect test

preparation example Construction

[0043] 2) Preparation of surface layer slurry

[0044] Mix silica sol, 325-mesh zircon powder, 270-320-mesh cobalt aluminate, penetrant "T" and analytically pure n-octanol, stir evenly and park for 12 hours to obtain the surface layer slurry; among them, The mass ratio of silica sol to zircon powder is 1:(5~5.5), the mass ratio of silica sol to penetrant "T" is 200:1, and the mass ratio of silica sol to analytically pure n-octanol is 100:1 ; Wherein, the prepared surface layer slurry has a specific gravity of 2.75 to 2.95 and a viscosity of 40S to 50S. Silica sol was purchased from Shangyu Yuda Chemical Co., Ltd., zircon powder was purchased from Australia Pan Asia Industrial Co., Ltd., cobalt aluminate was purchased from Prince Minerals, penetrant "T" was purchased from Shenyang Auxiliary Factory, and analytically pure n-octanol Purchased from Xi'an Chemical Preparation Factory.

[0045] 3) Preparation of remaining coating slurry

[0046] Take the ethyl silicate hydrolyzat...

Embodiment 1

[0055] 1. Combined with the structure of the parts, formulate a reasonable wax model combination plan, and complete the module combination work according to the requirements of the combination plan, such as figure 1 shown; figure 1 It is the structure diagram of the blade, the upper edge plate 1 and the lower edge plate 2 are respectively located on both sides of the airfoil 3, the thickness of the intake edge 4 is 11.4mm, and the thickness of the exhaust edge 5 is 1.2mm.

[0056] 2. Configure the surface layer slurry, add grain inoculants and refiners (cobalt aluminate with a particle size of about 270 mesh to 320 mesh), and stir evenly according to the specific process requirements, and prepare for coating and hanging modules;

[0057] 3. Coat the surface layer slurry and hanging sand on the module, and carry out self-drying to complete the surface layer coating and hanging work;

[0058] 4. Complete 2-5 layers of coating and hanging work respectively, and ensure that the 5...

Embodiment 2

[0065] 1. Combined with the structure of the parts, formulate a reasonable wax model combination plan, and complete the module combination work according to the requirements of the combination plan, such as image 3 ; image 3 For the schematic diagram of implanting thermal insulation cotton into the shell after coating and hanging 5 layers, a layer of thermal insulation cotton 12 is pasted on the exhaust side 5 .

[0066] 2. Configure the surface layer slurry, add grain inoculants and refiners (cobalt aluminate with a particle size of about 270 mesh to 320 mesh), and stir evenly according to the specific process requirements, and prepare for coating and hanging modules;

[0067] 3. Coat the surface layer slurry and hanging sand on the module, and carry out self-drying to complete the surface layer coating and hanging work;

[0068] 4. Complete 2-6 layers of coating and hanging work respectively, and ensure that the 6th layer is dry;

[0069] 5. According to the length of th...

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Abstract

The invention discloses a preparation method of a combined type shell in which heat insulating materials are implanted and mainly relates to a control method of the grain size of a precision-casting turbine blade which has the defects of large and wide margin plate, long blade, wide chord and large blade profile thickness difference. According to the preparation method, ceramic heat-preservation cotton is implanted in the shell, so that the defects in the prior art are effectively made up, the problem of extremely poor grain size of the exhaust side of the precision-casting turbine blade with the large and wide margin plate, the long blade, the wide chord and the large blade profile thickness difference is solved (primarily, the problem of columnar grains perpendicular to the exhaust side is solved), and uniform equiaxed grains are obtained. By adopting the preparation method, the problem of non-uniformity in growth of grains in a thin-wall area of a similar casting is completely solved, the qualified rate of the casting is increased from 30% before improvement to 70%, and the production cost is reduced.

Description

technical field [0001] The invention relates to a preparation method of a composite type shell embedded with thermal insulation material. Background technique [0002] The equiaxed crystal blades made by the precision casting process are prone to defects such as coarse grains on the surface, insufficient pouring, cold shut, and trachoma during the pouring process. Among them, the columnar grains produced in equiaxed crystal blades exceed the standard requirements, which will reduce the fatigue resistance of the blade itself. Therefore, in the production process of precision casting blades, on the basis of the normal shell preparation process, the control of grains is general. There are several methods: [0003] 1. Thermal control method [0004] This method mainly adjusts the temperature gradient during solidification of the alloy, the supercooling degree of the alloy, and the non-uniform nucleation number of refined grains in the shell surface refiner by strictly controll...

Claims

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Application Information

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IPC IPC(8): B22C9/04B22C3/00B22C9/12B22D15/00
CPCB22C3/00B22C9/043B22C9/22
Inventor 闵蓉赵儒梁常涛岐海潮李长青刘晓飞骞磊赵虹
Owner AECC AVIATION POWER CO LTD
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