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Preparation process of high-temperature alloy multigang hollow turbine blade

A high-temperature alloy and turbine blade technology, which is applied in the field of precision casting, can solve the problems of difficulty in preparing wax patterns, low success rate of wax patterns, and fractures, and achieve the effects of avoiding incomplete strict consistency, improving success rate, and simplifying the manufacturing process

Inactive Publication Date: 2011-03-30
SHENYANG POLYTECHNIC UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The hollow structure is formed by ceramic cores. In the wax mold preparation process of multi-connected turbine blades, due to the incomplete and strict consistency of the dimensions of multiple ceramic cores, there is certain mutual interference between the dimensional accuracy. During the wax mold molding process , due to the very small size difference, it can lead to the eccentricity or fracture of the ceramic core, so that the success rate of the wax mold is very low, and it is even difficult to prepare a suitable wax mold to make the turbine blade.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] The ceramic core adopts a silica-based ceramic core, and the wax mold of each unit airfoil (with ceramic core) is formed by injection molding. The injection temperature is 65°C, the pressure is 0.5MPa, the injection time is 20 seconds, and the pressure holding time 10 seconds; put the wax molds of each blade unit blade body (with ceramic core) into the multi-unit wax mold mold for integral molding to make a multi-unit wax mold mold; paint the multi-unit wax mold mold to make a shell The surface coating is made of corundum powder (320 mesh) and silica sol, and the mass ratio of corundum powder to silica sol is 3.5:1; the first layer of sanding material is 80 mesh corundum sand, and the second layer is 60 mesh corundum sand , the third layer is 32-mesh corundum sand, the fourth-seventh layer is 24-mesh corundum sand, and the final sealant layer is made of surface coating; the wax mold is removed by steam method, the steam temperature is 150 ° C, and the time is 30 minutes;...

Embodiment 2

[0024] The ceramic core adopts a silica-based ceramic core, and the wax mold of each unit airfoil (with ceramic core) is formed by injection molding. The injection temperature is 65°C, the pressure is 0.5MPa, the injection time is 10 seconds, and the pressure holding time 30 seconds; put the wax molds of each blade unit blade body (with ceramic core) into the multi-unit wax mold mold for integral molding to make a multi-unit wax mold mold; paint the multi-unit wax mold mold to make a shell , the surface coating uses corundum powder (320 mesh) and silica sol solution, the mass ratio of corundum powder to silica sol solution is 3.3:1; the first layer of sanding material is 80 mesh corundum sand, and the second layer is 60 mesh corundum sand. The third layer is 32-mesh corundum sand, the fourth-seventh layer is 24-mesh corundum sand, and the final sealant layer is made of surface coating; the wax mold is removed by steam method, the steam temperature is 120°C, and the time is 30 m...

Embodiment 3

[0026] The ceramic core adopts aluminum oxide-based ceramic core, and the wax molds of each unit blade (with ceramic core) are formed by injection molding. The injection temperature is 68°C, the pressure is 0.4MPa, and the injection time is 20 seconds. The time is 20 seconds; put the wax molds of each blade unit blade body (with ceramic core) into the multi-unit wax mold mold for integral molding to make a multi-unit wax mold mold; paint the multi-unit wax mold mold Shell and surface coatings are made of corundum powder (320 mesh) and silica sol solution, the mass ratio of corundum powder to silica sol solution is 3.0-3.5:1; the first layer of sanding material is 80 mesh corundum sand; the second layer is 60 mesh mesh corundum sand, the third layer is 32 mesh corundum sand, the fourth-seventh layer is 24 mesh corundum sand, and the final sealant layer is made of surface coating; the wax mold is removed by steam method, the steam temperature is 150 ℃, and the time is 20 minutes...

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PUM

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Abstract

The invention relates to a preparation process of a high-temperature alloy multigang hollow turbine blade. The process comprises the following steps of: (1) partitioning the multigang blade into a plurality of blade units and manufacturing a blade body wax mold for each unit blade, wherein a blade body is provided with a ceramic mold core, the unit blade body wax mold with the ceramic mold core is molded in an injection molding way, injection temperature is between 63 and 68 DEG C, the pressure is between 0.3 and 0.5 MPa, the injection time is between 10 and 30 seconds and the pressure is preserved for 10 to 30 seconds; (2) putting each unit blade body wax mold with the ceramic mold core into a multigang mold and injecting wax for primary molding so as to obtain a multigang hollow blade wax mold; and (3) coating, dewaxing, sintering, pouring, clearing and stripping the multigang hollow blade wax mold so as to obtain a high-temperature alloy multigang hollow turbine blade casting.

Description

Technical field [0001] The invention is a precision casting field, especially a high -temperature alloy turbine blade casting process. Background technique [0002] With the continuous improvement of the forward import temperature of aviation engines and gas turbine turbine, the turbine blades of key thermal components have also changed dramatically.At present, the forward import temperature of the military aviation engine turbine is close to 2200K, and the front import temperature of the turbine of the gas turbine is also increasing.The ability of turbine blades to rely on the material itself to resist high temperature is far from meeting actual needs, and the large amount of composite cooling methods can make turbine blades be able to withstand higher temperatures, but this also makes the internal cooling channels of the leaves extremely complicated and prepared to prepare.The difficulty of the blades, coupled with the double -connected or multi -linked heart turbine blades des...

Claims

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Application Information

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IPC IPC(8): B22C9/04B22C9/24
Inventor 毛萍莉姜卫国刘鸣刘正王国欣董媛
Owner SHENYANG POLYTECHNIC UNIV
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