CN107299210B - Heat treatment method after the blade reparation of the compressor blisk of aero-engine - Google Patents
Heat treatment method after the blade reparation of the compressor blisk of aero-engine Download PDFInfo
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- CN107299210B CN107299210B CN201710458949.XA CN201710458949A CN107299210B CN 107299210 B CN107299210 B CN 107299210B CN 201710458949 A CN201710458949 A CN 201710458949A CN 107299210 B CN107299210 B CN 107299210B
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/0068—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for particular articles not mentioned below
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- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
- C21D1/74—Methods of treatment in inert gas, controlled atmosphere, vacuum or pulverulent material
- C21D1/773—Methods of treatment in inert gas, controlled atmosphere, vacuum or pulverulent material under reduced pressure or vacuum
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- Crystallography & Structural Chemistry (AREA)
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- Organic Chemistry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Heat treatment method after being repaired the present invention relates to the blade of the compressor blisk of aero-engine, the heat treatment method are：Under vacuum conditions, part will be repaired and is warming up to 750~770 DEG C, kept the temperature 1.9~2.1h, be cooled to 610~630 DEG C later with 45~55 DEG C/h speed, after keeping the temperature 3.9~4.1h, be air-cooled to room temperature.The temperature kept the temperature for the first time in the present invention increases, and soaking time shortens twice, and treated, and part not will produce overaging phenomenon, and the production cycle shortens；The hardness that area is repaired after Overheating Treatment reaches 90% of matrix hardness or more, and the room temperature intensity for repairing area reaches 90% or more of the requirement of bulk technology condition, and elevated temperature strength reaches 98% or more of bulk technology condition requirement；Plate tensile sample high cycle fatigue test >=107Cycle is not broken.There is the present invention alloy substrate mechanical property not decline, while the advantages of can significantly improve the mechanical property of laser gain material restoring area again.
Description
Technical field
The present invention relates to aircraft engine maintenance technical fields, and in particular to the compressor blisk of aero-engine
Heat treatment method after blade reparation.
Background technology
The compressor of certain type aero-engine uses Blisk, and material is GH4169G high temperature alloys, by one
It needs to repair the blade injury position of blisk after section time use, generally use and basis material chemical composition phase
Same GH4169G powder is repaired as raw material are repaired using laser gain material technology.Since laser gain material region is rapid cooling
Microscopic structure, because hardening constituent be not precipitated cause to repair area's intensity it is low, it is difficult to meet requirement, it is necessary to carry out at corresponding heat
Reason.Currently, the heat treatment of GH4146G alloy materials mainly have solid solution+double aging (institution of prescription be 720 DEG C × 8h+620 DEG C ×
8h), and directly double aging (institution of prescription be 720 DEG C × 8h+620 DEG C × 8h), these heat treating regimes are for reparation
GH4169G alloy blisks are not applicable.If the GH4169G alloys blisk of reparation using solid solution+double aging system into
The crystal grain that row heat treatment can cause blisk not repair area is grown up, and mechanical property is remarkably decreased；If using direct double aging
System, which carries out heat treatment, can cause the tissue of the non-restoring area of blisk to generate " overaging " phenomenon, and mechanical property reduces.Such as
What, which formulates a rational heat treating regime, makes GH4169G alloy substrate mechanical properties not decline, while can significantly improve again
The mechanical property of laser gain material restoring area is a difficult point.
Invention content
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of blades of GH4169G alloys blisk
Heat treatment method after laser gain material reparation, the present invention solve while GH4169G alloy substrate mechanical properties do not decline again
The problem of improving the mechanical property of laser gain material restoring area.
Heat treatment method after the blade reparation of the compressor blisk of aero-engine of the present invention, the heat treatment side
Method is：Under vacuum conditions, part will be repaired and is warming up to 750~770 DEG C with 10~15 DEG C/min, keep the temperature 1.9~2.1h, later
610~630 DEG C are cooled to 45~55 DEG C/h speed, after keeping the temperature 3.9~4.1h, is air-cooled to room temperature.
Heat treatment method after the blade reparation of the compressor blisk of above-mentioned aero-engine, the vacuum environment
Vacuum degree >=10~2Pa。
Further, the heat treatment method after the blade of the compressor blisk of above-mentioned aero-engine is repaired, true
Under Altitude, part will be repaired and be warming up to 760 DEG C with 12 DEG C/min, keep the temperature 2.0h.
Further, the heat treatment method after the blade of the compressor blisk of above-mentioned aero-engine is repaired, true
Under Altitude, part will be repaired and be cooled to 620 DEG C with 50 DEG C/h speed, keep the temperature 4.0h.
Heat treatment method after the blade reparation of the compressor blisk of above-mentioned aero-engine, the blisk
It is made of GH4169G alloy materials.
Heat treatment method after the blade reparation of the compressor blisk of above-mentioned aero-engine, the blisk
Blade repaired using laser gain material mode.
The beneficial effects of the invention are as follows：After being repaired using the blade of the compressor blisk of aero-engine of the present invention
Treated that part not will produce overaging phenomenon for heat treatment method, and the production cycle shortens；Area is repaired after Overheating Treatment
Hardness reaches 90% or more of boat material handbook hardness requirement, and the room temperature intensity for repairing area reaches what boat material handbook room temperature intensity required
90% or more, elevated temperature strength reaches 98% or more that boat material handbook elevated temperature strength requires；Test (the test of plate tensile sample high cycle fatigue
Condition：670~690 DEG C, 570~590MPa, R=-1) >=107Cycle is not broken.The present invention has alloy substrate mechanical property
The advantages of not declining, while the mechanical property of laser gain material restoring area can be significantly improved again.
Description of the drawings
Fig. 1 is the scanning electron microscope shape appearance figure after matrix heat treatment；
Fig. 2 is to increase material to repair the scanning electron microscope shape appearance figure after area's heat treatment.
Specific implementation mode
Technical scheme of the present invention is described in further detail with reference to specific embodiment, but protection scope of the present invention is not
It is confined to as described below.
Embodiment 1
It is GH4169G high temperature alloys that the compressor of certain type aero-engine, which uses Blisk, material, is usually adopted
It uses GH4169G powder identical with basis material chemical composition as raw material are repaired, is repaired using laser gain material technology.
After having repaired, heat treating regime using the present invention is handled.Not less than 10~2Under conditions of Pa vacuum degrees, zero will be repaired
Part is put into vacuum drying oven, and 760 DEG C are warming up to 12 DEG C/min, is kept the temperature and is cooled to 620 DEG C with 50 DEG C/h speed after 2.0h, heat preservation
It is air-cooled after 4.0h to arrive room temperature.It is carried out using with stove sample (including base material that do not repair, half-and-half increase the plate tensile sample of material reparation)
Performance test.Hardness test shows that matrix is 47.7~45.6HRC, and increasing material restoring area is 43.5~44.2HRC.At matrix heat
Scanning electron microscope shape appearance figure after reason is as shown in Figure 1；It is as shown in Figure 2 to increase the scanning electron microscope shape appearance figure that material is repaired after area's heat treatment.
Mechanical experimental results are as shown in table 1, table 2, table 3 and table 4.Mechanical property shows mechanical property after heat treatment
It significantly improves, and substrate performance and tissue is not caused to damage.Test result shows that the performance test results meet and uses
It is required that.
The front and back performance comparison of 1 matrix of table heat treatment
2 matrix of table repairs area's hardness performance with material is increased
Table 3 repairs the nonheat-treated mechanical experimental results in area
| Test temperature | Sample classification | σb/MPa |
| Room temperature | Half-and-half increase the plate tensile sample of material | 1020,1010 |
| 680℃ | Half-and-half increase the plate tensile sample of material | 795,780 |
Table 4 repairs area and the mechanical experimental results after matrix heat treatment
Embodiment 2
It is GH4169G high temperature alloys that the compressor of certain type aero-engine, which uses Blisk, material, is usually adopted
It uses GH4169G powder identical with basis material chemical composition as raw material are repaired, is repaired using laser gain material technology.
After having repaired, heat treating regime using the present invention is handled.Not less than 10~2Under conditions of Pa vacuum degrees, zero will be repaired
Part is put into vacuum drying oven, and 750 DEG C are warming up to 10 DEG C/min, is kept the temperature and is cooled to 610 DEG C with 55 DEG C/h speed after 2.1h, heat preservation
It is air-cooled after 4.1h to arrive room temperature.It is carried out using with stove sample (including base material that do not repair, half-and-half increase the plate tensile sample of material reparation)
Performance test.Hardness test shows that matrix is 47.4~45.6HRC, and increasing material restoring area is 43.5~44.1HRC.
Mechanical experimental results are as shown in table 4, table 5, table 6 and table 7.Mechanical property shows mechanical property after heat treatment
It significantly improves, and substrate performance and tissue is not caused to damage.Test result shows that the performance test results meet and uses
It is required that.
The front and back performance comparison of 4 matrix of table heat treatment
5 matrix of table repairs area's hardness performance with material is increased
Table 6 repairs the nonheat-treated mechanical experimental results in area
| Test temperature | Sample classification | σb/MPa |
| Room temperature | Half-and-half increase the plate tensile sample of material | 1022,1013 |
| 680℃ | Half-and-half increase the plate tensile sample of material | 796,782 |
Table 7 repairs area and the mechanical experimental results after matrix heat treatment
Embodiment 3
It is GH4169G high temperature alloys that the compressor of certain type aero-engine, which uses Blisk, material, is usually adopted
It uses GH4169G powder identical with basis material chemical composition as raw material are repaired, is repaired using laser gain material technology.
After having repaired, heat treating regime using the present invention is handled.Not less than 10~2Under conditions of Pa vacuum degrees, zero will be repaired
Part is put into vacuum drying oven, and 770 DEG C are warming up to 15 DEG C/min, is kept the temperature and is cooled to 630 DEG C with 45 DEG C/h speed after 1.9h, heat preservation
It is air-cooled after 3.9h to arrive room temperature.It is carried out using with stove sample (including base material that do not repair, half-and-half increase the plate tensile sample of material reparation)
Performance test.Hardness test shows that matrix is 47.8~45.7HRC, and increasing material restoring area is 43.4~44.2HRC.
Mechanical experimental results are as shown in table 8, table 9, table 10 and table 11.Mechanical property shows mechanical property after heat treatment
It can significantly improve, and substrate performance and tissue not caused to damage.Test result shows that the performance test results satisfaction makes
With requiring.
The front and back performance comparison of 8 matrix of table heat treatment
9 matrix of table repairs area's hardness performance with material is increased
Table 10 repairs the nonheat-treated mechanical experimental results in area
| Test temperature | Sample classification | σb/MPa |
| Room temperature | Half-and-half increase the plate tensile sample of material | 1018,1012 |
| 680℃ | Half-and-half increase the plate tensile sample of material | 788,783 |
Table 11 repairs area and the mechanical experimental results after matrix heat treatment
The above is only a preferred embodiment of the present invention, it should be understood that the present invention is not limited to described herein
Form is not to be taken as excluding other embodiments, and can be used for other combinations, modifications, and environments, and can be at this
In the text contemplated scope, modifications can be made through the above teachings or related fields of technology or knowledge.And those skilled in the art institute into
Capable modifications and changes do not depart from the spirit and scope of the present invention, then all should be in the protection domain of appended claims of the present invention
It is interior.
Claims (4)
1. the heat treatment method after the blade reparation of the compressor blisk of aero-engine, which is characterized in that at the heat
Reason method is：Under vacuum conditions, part will be repaired and is warming up to 750~770 DEG C with 10~15 DEG C/min, keep the temperature 1.9~2.1h,
610~630 DEG C are cooled to 45~55 DEG C/h speed later, after keeping the temperature 3.9~4.1h, is air-cooled to room temperature；
The blisk is made of GH4169G alloy materials；
The blade of the blisk is repaired using laser gain material mode.
2. the heat treatment method after the blade reparation of the compressor blisk of aero-engine according to claim 1,
It is characterized in that, vacuum degree >=10 of the vacuum environment~2Pa。
3. the heat treatment method after the blade reparation of the compressor blisk of aero-engine according to claim 1,
It is characterized in that, under vacuum conditions, part will be repaired and be warming up to 760 DEG C with 12 DEG C/min, keep the temperature 2.0h.
4. the heat treatment method after the blade reparation of the compressor blisk of aero-engine according to claim 1,
It is characterized in that, under vacuum conditions, part will be repaired and be cooled to 620 DEG C with 50 DEG C/h speed, keep the temperature 4.0h.
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| CN109317918A (en) * | 2018-11-01 | 2019-02-12 | 中国人民解放军第五七九工厂 | A kind of aero-engine high-pressure compressor rotor sector clearance control method |
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Address after: No. 10 high tech Zone Gaopeng road in Chengdu city of Sichuan Province in 610041 Patentee after: State-run West Sichuan machine factory Address before: No.10 Gaopeng Avenue, high tech Zone, Chengdu, Sichuan 610000 Patentee before: PLA NO.5719 FACTORY |