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Technological process for forming turbine vane by splashing of magnesium ore

A technology of turbine blade and process method, applied in the direction of turbines, mechanical equipment, etc., can solve the problems of complex molds and processes of bismuth ore powder and metal powder, and achieve the effect of low cost of raw materials, reduction of manufacturing cost, and guarantee of finished product performance.

Inactive Publication Date: 2006-10-04
周彦学
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In view of the above existing problems, the present invention provides a process method for forming turbine blades by flying brucite powder and metal powder. It is an injection molding process for magnesium products, using magnesium ore as raw material to manufacture turbine blades that can replace superalloys by flying injection molding

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0022] Embodiment 1, the present invention comprises following process steps:

[0023] 1. Mixing: Use 200 mesh, about 1 μm magnesium ore ultrafine powder, add binder, choose BFZ cobalt powder as binder, add BFZ cobalt powder in a weight ratio of 4%, and fully stir through the mixer;

[0024] 2. Granulation: make particles with a diameter of 1.5 μm;

[0025] 3. Making the turbo automatic opening mold: including the following steps:

[0026] a. Design the turbine blade mold, which is equipped with a handle for easy opening;

[0027] c. Select 3Cr258 as the material required for the turbine blade mold;

[0028] b. Process and manufacture the turbine blade mold;

[0029] 4. Injection molding: After being heated to 150°C and hot-melted, it is injected into the turbine blade mold for molding;

[0030] 5. Debonding: After molding, oxidize and debond for 3 hours in a sintering furnace at a temperature of about 500°C;

[0031] 6. Sintering: After heating, that is, sintering at 600...

Embodiment 2

[0032] Embodiment 2, the present invention comprises following processing steps:

[0033] 1. Mixing: use 5000 mesh, about 1μm high temperature resistant metal powder (such as K13), add binder, choose BFZ cobalt powder as binder, add BFZ cobalt powder in a weight ratio of 4%, and fully stir;

[0034] 2. Granulation: make particles with a diameter of 2.5 μm;

[0035] 3. making the turbine automatically open the mold with embodiment 1;

[0036] 4. Injection molding: After being heated to 170°C and hot-melted, it is injected into the turbine blade mold for molding;

[0037] 5. Debonding: chemical debonding is carried out after molding, and soaked in a chemical solution composed of 70% epoxy resin, 15% sodium hydroxide and 15% water for about 2 hours;

[0038] 6. Sintering: sintering at 700°C after heating, sintering the metal powder at 1300°C for 4 hours to make the lattice network, and finally the turbine blade is finished after inspection.

Embodiment 3

[0039] Embodiment 3, process step of the present invention is as follows:

[0040] 1. Mixing: use 2500 mesh, about 1 μm magnesium ore ultrafine powder, add binder, choose BFZ cobalt powder as binder, add BFZ cobalt powder in a weight ratio of 4%, and fully stir through the mixer;

[0041] 2. Granulation: make particles with a diameter of 2 μm;

[0042] 3. making the turbine automatically open the mold with embodiment 1;

[0043] 4. Injection molding: After being heated to 160°C and hot-melted, it is injected into the turbine blade mold for molding;

[0044] 5. Debonding: with embodiment 1;

[0045] 6. Sintering: Sintering by heating to a high temperature of 650°C to make the lattice network, and finally passing the inspection is the finished turbine blade.

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Abstract

The invention discloses a magnesium powdered ore fly-shoot forming turbine blades technique, which comprises the following steps: using 200-5000 order about 1 mum magnesium powdered ore colloidal powder; adding in adhensive; mixing through mixing-material device; forming 1.5-2.5 mum diameter; preparing turbine automatic open die; injecting hot melt at 150-170 deg.c in turbine blades die to form; carrying out oxidation abhesion and chemical abhesion after forming; sintering at 600-700deg.c to make it crystal lattice network; forming turbine blades completed product. The invention improves operating efficiency, which reduces the cost.

Description

technical field [0001] The invention relates to a process method for forming turbine blades by flying magnesium ore powder, in particular to a process method for forming integral turbine blades by flying magnesium ore powder, magnesium oxide alloy powder, metal powder, and superfine magnesium carbonate powder , belongs to the technical field of powder metallurgy replacing traditional precision casting. Background technique [0002] Traditional high-temperature-resistant materials generally use high-temperature alloy materials, and various parts made of high-temperature alloy materials, especially the turbine and compressor wheels, have always been completed by precision casting technology, requiring dozens of processes and time. The efficiency is not high, and the general efficiency is between 70% and 80%, which makes the production enterprises overwhelmed. The turbine blades that can replace superalloys made by flying injection molding have not been reported yet. Contents...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B22F5/04
Inventor 周彦学
Owner 周彦学
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