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High-temperature alloy casting resistant to high-temperature hot corrosion

A technology of superalloys and castings, which is applied in the directions of casting molds, casting mold components, casting molding equipment, etc., can solve the problems of low temperature bearing capacity, difficult turbine blades, and difficulties with large-sized blades, and achieves heat-resistant corrosion performance and microstructure stability. The effect of improved performance, good casting process performance and excellent hot corrosion performance

Active Publication Date: 2016-02-24
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing gas turbine blade materials usually have good structural stability and thermal corrosion resistance, but mainly have the following disadvantages: 1. Generally, the material has a low temperature bearing capacity, which cannot meet the temperature bearing capacity of higher-level gas turbine blade materials Requirements; 2. In terms of element matching in alloy design, the casting process performance is usually not taken into account. It is difficult to cast turbine blades with complex hollow structures, and it is also difficult to cast large-size blades that are prone to casting defects, thus increasing mass production. difficulty

Method used

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  • High-temperature alloy casting resistant to high-temperature hot corrosion
  • High-temperature alloy casting resistant to high-temperature hot corrosion
  • High-temperature alloy casting resistant to high-temperature hot corrosion

Examples

Experimental program
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Effect test

Embodiment 1-10

[0018] Embodiment 1-10 alloy composition

[0019] The chemical composition and mass percentage of the alloy are: Al3.8~6.0%; Ti0.5~3.5%; Cr10.0~12.0%; Ta5.0~7.0%; Co8.0~10.0%; W4.0~ 7.0%; Mo1.0~3.0%; Hf0~3.0%; Re0~4; C0.02~0.15%; B0.002~0.02%, the balance is nickel; Al, Ti, Hf and C+B in the alloy The chemical composition is controlled in the following ratio, 1.0≤(Al / Ti)≤11, Hf0~3.0%; among them, when 1.0≤(Al / Ti)≤1.6, Hf0~0.5%, 0.022≤C+B≤0.09 ;When 1.60.09; when 2.50.09 . Table 1 lists embodiment 1-10 composition and proportioning (by weight percentage).

Embodiment 1

[0021] The composition of the high temperature and corrosion resistant superalloy involved in this embodiment is calculated by weight percentage, as shown in Example 1 in Table 1, and the composition in Example 1 in Table 1 is used to cast a large-size directional solidification with a length of more than 200 mm. Single crystal gas turbine blades.

[0022] In this embodiment, the double vacuum induction method is used for smelting. According to the required target components, the ingredients are proportioned according to the proportion, and put into the vacuum induction melting furnace for melting, and the master alloy ingot is cast. This process needs to go through melting-refining-cooling-alloying -Pouring is done in five steps. In the melting step, nickel, cobalt, molybdenum, tungsten, tantalum, chromium, carbon, and rhenium are directly loaded into the crucible, and refined for 40 minutes after refining. For titanium, stir after 3 minutes of smelting, then add boron and h...

Embodiment 2

[0024] The composition of the high-temperature and hot-corrosion-resistant superalloy involved in this example is calculated by weight percentage, as shown in Example 2 in Table 1. The composition in Example 2 in Table 1 is used to cast a directionally solidified columnar crystal test rod.

[0025] In this embodiment, the double vacuum induction method is used for smelting. According to the required target components, the ingredients are proportioned according to the proportion, and put into the vacuum induction melting furnace for melting, and the master alloy ingot is cast. This process needs to go through melting-refining-cooling-alloying -Pouring is done in five steps. In the melting step, nickel, cobalt, molybdenum, tungsten, tantalum, chromium, carbon, and rhenium are directly loaded into the crucible, and refined for 40 minutes after refining. For titanium, stir after smelting for 10 minutes, then add boron and hafnium and stir after smelting for 10 minutes to promote t...

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Abstract

The invention belongs to the field of metal materials and relates to a high-temperature alloy casting which is resistant to high-temperature hot corrosion and is used for a part at the hot end of a gas turbine. Alloy comprises, by mass, 3.8%-6.0% of Al, 0.5%-3.5% of Ti, 10.0%-12.0% of Cr, 5.0%-7.0% of Ta, 8.0-10.0% of Co, 4.0%-7.0% of W, 1.0%-3.0% of Mo, 0-3.0% of Hf, 0-4% of Re, 0.02%-0.15% of C, 0.002-0.02% of B and the balance nickel. According to the high-temperature alloy casting resistant to high-temperature hot corrosion, the Al / Ti value, the content of Hf and the ratio of the content of Hf to the content of C and B are adjusted, so that the casting performance of the alloy is improved, and the high-temperature burning hot corrosion performance of the alloy is improved. Thus, the gas turbine high-temperature alloy more suitable for hollow blade casting is obtained.

Description

technical field [0001] The invention belongs to the field of metal materials, and relates to a high-temperature heat-corrosion-resistant superalloy casting, in particular to a high-temperature heat-corrosion-resistant high-temperature alloy used for hot-end components of a gas turbine. Background technique [0002] With the objective requirements of sustainable world economy, energy conservation and environmental protection, and low-carbon development, heavy-duty gas turbines and their combined devices with advantages such as high efficiency, water saving, and low carbon emissions have become the mainstream of new power generation equipment in the world. With the increase of the air inlet temperature of the ground gas turbine, a severe test is put forward for the material of the turbine blade. On the one hand, the material is required to have good mechanical properties and stability; on the other hand, the service environment of the blade material is complex, the fuel contai...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C22C19/05C22F1/10B22C9/04B22D27/04
Inventor 李青肖程波陈晶阳宋尽霞杨海青
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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