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Staged heating, extruding and form-controlling method of powder superalloy component

A high-temperature alloy, stage heating technology, applied in the improvement of powder superalloy component preparation process, stage heating extrusion shape control field, can solve the problems of long preparation cycle, low material utilization rate, complex process, etc., to reduce blank processing waste Quantity, improve material utilization, reduce the effect of manufacturing costs

Active Publication Date: 2017-05-10
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, high-alloyed powder superalloys are generally sensitive to temperature, have a narrow processing window, and are hard-to-deform alloys, which lead to certain difficulties in process execution and microstructure control.
[0003] Foreign powder superalloys are mainly used to prepare high-performance engine turbine discs and other hot-end components, and are mainly prepared by powder hot isostatic pressing + extrusion + isothermal forging. The process is characterized by complex processes, long preparation cycles, and high costs. Moreover, the component blank needs to be machined multiple times between different processes to meet the requirements of the process for the shape and surface state of the component blank, resulting in low material utilization

Method used

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  • Staged heating, extruding and form-controlling method of powder superalloy component
  • Staged heating, extruding and form-controlling method of powder superalloy component
  • Staged heating, extruding and form-controlling method of powder superalloy component

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Experimental program
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Effect test

Embodiment 1

[0044]The step-by-step heating extrusion shape control method for powder superalloy components is characterized in that the steps of the method are:

[0045] Step 1. Powder preparation

[0046] Calculate and weigh 7kg of atomized superalloy powder according to the size of the component, and the weighed weight is calculated according to the following formula:

[0047] m 装载 = m 计算 / 0.8 Formula 1

[0048] In the formula: m 装载 is the weight of the atomized superalloy powder loaded into the mold, m 计算 is the atomized superalloy powder weight calculated according to the volume of the component;

[0049] Step 2. Extrusion mold preparation

[0050] A steel material with a breaking strength exceeding 2000 MPa is used to prepare an extrusion die. The die consists of an upper ring die 1 and a lower ring die 2 to form an extrusion die cavity, wherein the lower ring die 2 is fixed on the lower workbench of the press, and the upper ring die 2 is fixed on the lower workbench of the pre...

Embodiment 2

[0068] The step-by-step heating extrusion shape control method for powder superalloy components is characterized in that the steps of the method are:

[0069] Step 1. Powder preparation

[0070] Calculate and weigh 5kg of atomized superalloy powder according to the size of the component, and the weighed weight is calculated according to the following formula:

[0071] m 装载 = m 计算 / 0.8 Formula 1

[0072] In the formula: m 装载 is the weight of the atomized superalloy powder loaded into the mold, m 计算 is the atomized superalloy powder weight calculated according to the volume of the component;

[0073] Step 2. Extrusion mold preparation

[0074] A steel material with a breaking strength exceeding 2000 MPa is used to prepare an extrusion die. The die consists of an upper ring die 1 and a lower ring die 2 to form an extrusion die cavity, wherein the lower ring die 2 is fixed on the lower workbench of the press, and the upper ring die 2 is fixed on the lower workbench of the pr...

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Abstract

The invention provides a staged heating, extruding and form-controlling method of a powder superalloy component. Through use of good liquidity of powder materials and by the aid of the deformation temperature and pressure which are changed in stages, the powder materials reach preliminary densification under the low temperature and pressure, and powder particles are retained and have surface activity and liquidity to a certain degree; then the deformation temperature and pressure are increased, and the plastic deformation parameters such as the motion direction of a mold and the deformation speed are combined, so that superalloy powder flows and forms a certain shape; during the process, pores among the powder particles are completely eliminated, and full densification is reached; and meanwhile, through circulatory alternation action of forward extrusion and backward extrusion, certain strain conditions are exerted on the powder particles, coarse particles are changed into fine crystal particles, component formation is finished, and a full compact powder component is prepared, so that solidification-structure-formation integration of the powder component is achieved. A powder superalloy forging stock with the compact structure and even and fine crystal particles can be obtained.

Description

technical field [0001] The invention relates to a step-by-step heating extrusion shape control method for powder superalloy components, which belongs to the technical field of thermal processing and relates to the improvement of the preparation process of powder superalloy components. Background technique [0002] Powder superalloy is a plate material developed to solve the solidification segregation and deformation difficulties caused by the high alloying of cast and forged alloy superalloys. Highly alloyed powder superalloys have the advantages of high temperature resistance, high strength and toughness, and low crack growth rate. They are the preferred materials for manufacturing high-performance, high-reliability, and long-life advanced aeroengine turbine disks and other high-temperature resistant components. However, high-alloyed powder superalloys are generally extremely sensitive to temperature, have a narrow processing window, and are hard-to-deform alloys, which lea...

Claims

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Application Information

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IPC IPC(8): B22F3/20
CPCB22F3/20B22F2003/208
Inventor 方爽王淑云姜涛兰博
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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