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Heat treatment method for recovering performance of K465 alloy turbine blade

A heat treatment method and technology of turbine blades, applied in the field of metallurgy, can solve problems such as no precedent for K465 alloy turbine blade performance recovery, and achieve strong operability and easy operation

Active Publication Date: 2014-03-19
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

So far, there is no domestic precedent for K465 alloy turbine blade performance recovery

Method used

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  • Heat treatment method for recovering performance of K465 alloy turbine blade
  • Heat treatment method for recovering performance of K465 alloy turbine blade
  • Heat treatment method for recovering performance of K465 alloy turbine blade

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0029] A K465 alloy turbine blade recovery performance heat treatment method is carried out according to the following steps:

[0030] (1) Blade loading: Put the K465 alloy turbine blades that have served for one life into the vacuum furnace perpendicular to the surface of the fixture; figure 1 or figure 2 shown;

[0031] (2) Heat preservation after heating up with the furnace: under the protection of inert gas, the vacuum furnace is powered from room temperature, heated and heated up with the furnace, kept at 950 ° C ~ 960 ° C for 40 minutes, kept at 1190 ° C ~ 1200 ° C for 2.5 hours, and heated from room temperature To 1230°C, the entire heating time should be controlled within 6.0h; keep warm at 1230°C for 4h;

[0032] (3) Cool down with the furnace: Cool from 1230°C to 1000°C at a cooling rate of 40±25°C / min, and cool with inert gas partial pressure; at 1000°C, fill inert gas and cool to 300°C, the cooling rate is equivalent For air cooling, the air cooling pressure is...

Embodiment 2

[0040] Example 2 is basically the same as Example 1, the difference is: (2) heat preservation after heating up with the furnace: under vacuum, the vacuum furnace is powered from room temperature, heated and heated up with the furnace, and kept at 950 ° C ~ 960 ° C for 45 minutes. Keep warm at 1190°C~1200°C for 2 hours, heat from room temperature to 1230°C, the whole heating time should be controlled within 5.5h; keep warm at 1230°C for 4.5h,

[0041] After K465 alloy undergoes recovery heat treatment at 1230℃ for 4.5h, its microstructure is Figure 4 (b) transforms into Figure 4 (e), its mechanical properties are shown in Table 3; the morphology of intragranular γ′ is restored from polygonal or flower basket to cubic, and its morphology is more square than that before heat treatment. It can be seen from Table 3 that its mechanical properties meet the requirements of technical conditions.

[0042] Table 3 Mechanical properties after heat treatment

[0043]

[0044]Aft...

Embodiment 3

[0046] Example 3 is basically the same as Example 1, the difference is: (2) heat preservation after heating up with the furnace: under vacuum, the vacuum furnace is powered from room temperature, heated and heated up with the furnace, and kept at 950 ° C ~ 960 ° C for 43 minutes. Insulate at 1190°C~1200°C for 2.2 hours, heat from room temperature to 1230°C, the entire heating time should be controlled within 5.7 hours; keep at 1230°C for (4~4.5) hours.

[0047] After testing, after heat treatment for recovery performance, the morphology of intragranular γ′ recovers from polygonal or flower basket shape to cubic shape, which is more square than before heat treatment for recovery performance. Its mechanical properties meet the requirements of technical conditions.

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Abstract

The invention discloses a heat treatment method for recovering the performance of a K465 alloy turbine blade and belongs to the technical field of metallurgy. The heat treatment method comprises the following steps of 1, blade feeding, 2, furnace heating and then heat preservation: in vacuum or inert gas protective atmosphere, carrying out heat preservation at a temperature of 950-960 DEG C for 40-45min, carrying out heat preservation at a temperature of 1190-1200 DEG C for 2-2.5h and carrying out heat preservation at a temperature of 1230 DEG C for 4-4.5h, and 3, furnace cooling: (1), carrying out cooling from a temperature of 1230 DEG C to a temperature of 1000 DEG C at a cooling rate of 40+ / -25 DEG C / min by inert gas-based differential pressure cooling, and (2), feeding inert gas at a temperature of 1000 DEG C, carrying out cooling to a temperature of 300 DEG C, and opening a furnace door at a temperature below 300 DEG C and carrying out cooling. The heat treatment method can obviously recover the performance (such as creep deformation) of the K465 alloy turbine blade after a service cycle. Through the heat treatment method, transgranular gamma' polygonal or flower basket-shaped morphology is transformed into the cubical morphology so that morphology squaring is promoted.

Description

technical field [0001] The invention belongs to the technical field of metallurgy, and in particular relates to a heat treatment method for K465 alloy turbine blades to restore performance. Background technique [0002] K465 alloy has high thermal strength, good oxidation resistance and corrosion resistance, and is widely used in the manufacture of aero-engine turbine blades, and the blades can be used for a long time below 1000 ° C, taking a leading position in the world. The alloy is a precipitation-strengthened casting superalloy, and its intragranular γ′ strengthening phase content is about 63% (volume percentage). The service life of the blade is determined by the morphology of the intragranular γ′ strengthening phase. After the blade has been in service for a life span (500h~600h), the morphology of the γ′ phase changes from the original square shape to polygonal or flower basket shape. So far, there is no precedent for K465 alloy turbine blade performance recovery ...

Claims

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Application Information

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IPC IPC(8): C22F1/10C21D9/00
Inventor 彭志江张明俊邹建波韩欢乐献刚
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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