CN107299210A - 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
- Publication number
- CN107299210A CN107299210A CN201710458949.XA CN201710458949A CN107299210A CN 107299210 A CN107299210 A CN 107299210A CN 201710458949 A CN201710458949 A CN 201710458949A CN 107299210 A CN107299210 A CN 107299210A
- Authority
- CN
- China
- Prior art keywords
- heat treatment
- repaired
- aero
- blisk
- treatment method
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
-
- 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
Abstract
The present invention relates to the heat treatment method after the reparation of the blade of the compressor blisk of aero-engine, the heat treatment method is：Under vacuum conditions, part will be repaired and is warming up to 750~770 DEG C, be incubated 1.9~2.1h, be cooled to afterwards with 45~55 DEG C/h speed after 610~630 DEG C, 3.9~4.1h of insulation, be air-cooled to room temperature.The temperature rise being incubated for the first time in the present invention, soaking time shortens twice, and the part after processing will not produce overaging phenomenon, and the production cycle shortens；The hardness that area is repaired after Overheating Treatment reaches more than the 90% of matrix hardness, and the room temperature strength for repairing area reaches more than the 90% of the requirement of bulk technology condition, and elevated temperature strength reaches more than the 98% 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 can significantly improve the advantage of the mechanical property of laser gain material restoring area again.
Description
Technical field
The present invention relates to aircraft engine maintenance technical field, 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 its material is GH4169G high temperature alloys, by one
Need to repair the blade injury position of blisk after section time use, generally use and matrix material chemical composition phase
Same GH4169G powder is repaired as raw material are repaired using laser gain material technology.Because laser gain material region is rapid cooling
Microscopic structure, cause to repair area's low intensity because hardening constituent is not separated out, it is difficult to meet use requirement, it is necessary to carry out at corresponding heat
Reason.At present, 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 alloys blisk is not applied to.If the GH4169G alloys blisk of reparation is entered using solid solution+double aging system
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 produce " overaging " phenomenon, mechanical property reduction.Such as
What, which formulates a rational heat treating regime, causes 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.
The content of the invention
It is an object of the invention to overcome the deficiencies of the prior art and provide a kind of blade of GH4169G alloys blisk
Heat treatment method after laser gain material reparation, the present invention is solved 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, be incubated 1.9~2.1h, afterwards
It is cooled to 45~55 DEG C/h speed after 610~630 DEG C, 3.9~4.1h of insulation, 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 >=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, 2.0h is incubated.
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, 4.0h is incubated.
Heat treatment method after the blade reparation of the compressor blisk of above-mentioned aero-engine, described blisk
It is made up of GH4169G alloy materials.
Heat treatment method after the blade reparation of the compressor blisk of above-mentioned aero-engine, described 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
Part after heat treatment method processing will not produce overaging phenomenon, and the production cycle shortens；Area is repaired after Overheating Treatment
Hardness reaches more than the 90% of boat material handbook hardness requirement, and the room temperature strength for repairing area reaches the room temperature strength requirement of boat material handbook
More than 90%, elevated temperature strength reaches more than the 98% of boat material handbook elevated temperature strength requirement；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
Do not decline, while the advantage of the mechanical property of laser gain material restoring area can be significantly improved again.
Brief description of the drawings
Fig. 1 is the ESEM shape appearance figure after matrix is heat-treated；
Fig. 2 repairs the ESEM shape appearance figure after area's heat treatment to increase material.
Embodiment
Technical scheme 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
The compressor of certain type aero-engine uses Blisk, and its material is GH4169G high temperature alloys, is generally adopted
, as raw material are repaired, repaired with matrix material chemical composition identical GH4169G powder using laser gain material technology.
After having repaired, handled using the heat treating regime of the present invention.It is being not less than 10~2Under conditions of Pa vacuums, zero will be repaired
Part is put into vacuum drying oven, and 620 DEG C, insulation are cooled to 50 DEG C/h speed after being warming up to 760 DEG C, insulation 2.0h with 12 DEG C/min
Air cooling is to room temperature after 4.0h.Carried out using with stove sample (including base material without reparation, half-and-half increase the plate tensile sample that material is repaired)
Performance test.Hardness test shows that matrix is 47.7~45.6HRC, and it is 43.5~44.2HRC to increase material restoring area.At matrix heat
ESEM shape appearance figure after reason is as shown in Figure 1；The ESEM shape appearance figure increased after material reparation area's heat treatment is as shown in Figure 2.
Mechanical experimental results are as shown in table 1, table 2, table 3 and table 4.Mechanical property shows, mechanical property after heat treatment
Significantly improve, and damage is not caused to substrate performance and tissue.Result of the test shows that the performance test results meet and used
It is required that.
Performance comparison before and after the heat treatment of the matrix of table 1
The matrix of table 2 repairs area's hardness performance with increasing material
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 the mechanical experimental results after area is heat-treated with matrix
Embodiment 2
The compressor of certain type aero-engine uses Blisk, and its material is GH4169G high temperature alloys, is generally adopted
, as raw material are repaired, repaired with matrix material chemical composition identical GH4169G powder using laser gain material technology.
After having repaired, handled using the heat treating regime of the present invention.It is being not less than 10~2Under conditions of Pa vacuums, zero will be repaired
Part is put into vacuum drying oven, and 610 DEG C, insulation are cooled to 55 DEG C/h speed after being warming up to 750 DEG C, insulation 2.1h with 10 DEG C/min
Air cooling is to room temperature after 4.1h.Carried out using with stove sample (including base material without reparation, half-and-half increase the plate tensile sample that material is repaired)
Performance test.Hardness test shows that matrix is 47.4~45.6HRC, and it is 43.5~44.1HRC to increase material restoring area.
Mechanical experimental results are as shown in table 4, table 5, table 6 and table 7.Mechanical property shows, mechanical property after heat treatment
Significantly improve, and damage is not caused to substrate performance and tissue.Result of the test shows that the performance test results meet and used
It is required that.
Performance comparison before and after the heat treatment of the matrix of table 4
The matrix of table 5 repairs area's hardness performance with increasing material
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 the mechanical experimental results after area is heat-treated with matrix
Embodiment 3
The compressor of certain type aero-engine uses Blisk, and its material is GH4169G high temperature alloys, is generally adopted
, as raw material are repaired, repaired with matrix material chemical composition identical GH4169G powder using laser gain material technology.
After having repaired, handled using the heat treating regime of the present invention.It is being not less than 10~2Under conditions of Pa vacuums, zero will be repaired
Part is put into vacuum drying oven, and 630 DEG C, insulation are cooled to 45 DEG C/h speed after being warming up to 770 DEG C, insulation 1.9h with 15 DEG C/min
Air cooling is to room temperature after 3.9h.Carried out using with stove sample (including base material without reparation, half-and-half increase the plate tensile sample that material is repaired)
Performance test.Hardness test shows that matrix is 47.8~45.7HRC, and it is 43.4~44.2HRC to increase material restoring area.
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 damage not caused to substrate performance and tissue.Result of the test shows that the performance test results, which are met, to be made
With requiring.
Performance comparison before and after the heat treatment of the matrix of table 8
The matrix of table 9 repairs area's hardness performance with increasing material
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 the mechanical experimental results after area is heat-treated with matrix
Described above is only the 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 the exclusion to other embodiment, and available for various other combinations, modification and environment, and can be at this
In the text contemplated scope, it is modified by the technology or knowledge of above-mentioned teaching or association area.And those skilled in the art are entered
Capable change and change does not depart from the spirit and scope of the present invention, then all should appended claims of the present invention protection domain
It is interior.
Claims (6)
1. the heat treatment method after the blade reparation of the compressor blisk of aero-engine, it is characterised 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, be incubated 1.9~2.1h,
It is cooled to afterwards with 45~55 DEG C/h speed after 610~630 DEG C, 3.9~4.1h of insulation, is air-cooled to room temperature.
2. the heat treatment method after the blade reparation of the compressor blisk of aero-engine according to claim 1,
Characterized in that, vacuum >=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,
Characterized in that, under vacuum conditions, part will be repaired and be warming up to 760 DEG C with 12 DEG C/min, 2.0h is incubated.
4. the heat treatment method after the blade reparation of the compressor blisk of aero-engine according to claim 1,
Characterized in that, under vacuum conditions, part will be repaired and be cooled to 620 DEG C with 50 DEG C/h speed, 4.0h is incubated.
5. the heat after the blade reparation of the compressor blisk of the aero-engine according to any one of Claims 1 to 4
Processing method, it is characterised in that described blisk is made up of GH4169G alloy materials.
6. the heat after the blade reparation of the compressor blisk of the aero-engine according to any one of Claims 1 to 4
Processing method, it is characterised in that the blade of described blisk is repaired using laser gain material mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710458949.XA CN107299210B (en) | 2017-06-16 | 2017-06-16 | Heat treatment method after the blade reparation of the compressor blisk of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710458949.XA CN107299210B (en) | 2017-06-16 | 2017-06-16 | Heat treatment method after the blade reparation of the compressor blisk of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107299210A true CN107299210A (en) | 2017-10-27 |
| CN107299210B CN107299210B (en) | 2018-10-30 |
Family
ID=60135436
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710458949.XA Active CN107299210B (en) | 2017-06-16 | 2017-06-16 | Heat treatment method after the blade reparation of the compressor blisk of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107299210B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2586887A1 (en) * | 2011-10-31 | 2013-05-01 | Alstom Technology Ltd | Method for manufacturing components or coupons made of a high temperature superalloy |
| CN105014073A (en) * | 2015-08-18 | 2015-11-04 | 上海航天精密机械研究所 | TC4 titanium alloy laser selective melting material additive manufacturing and heat treatment method |
| CN105543747A (en) * | 2015-12-21 | 2016-05-04 | 西北工业大学 | Preparation method of material increase manufactured nickel-based high-temperature alloy reserved with Laves phase |
| CN106119749A (en) * | 2016-06-28 | 2016-11-16 | 深圳市晶莱新材料科技有限公司 | A kind of 3D prints Ti 6Al 4V structural member Technology for Heating Processing |
| CN106180719A (en) * | 2016-09-27 | 2016-12-07 | 飞而康快速制造科技有限责任公司 | Selective laser fusing increases IN718 component, system, heat treatment method and the device that material manufactures |
-
2017
- 2017-06-16 CN CN201710458949.XA patent/CN107299210B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2586887A1 (en) * | 2011-10-31 | 2013-05-01 | Alstom Technology Ltd | Method for manufacturing components or coupons made of a high temperature superalloy |
| CN103088275B (en) * | 2011-10-31 | 2017-03-01 | 通用电器技术有限公司 | Superalloy components or the production method of accessory |
| CN105014073A (en) * | 2015-08-18 | 2015-11-04 | 上海航天精密机械研究所 | TC4 titanium alloy laser selective melting material additive manufacturing and heat treatment method |
| CN105543747A (en) * | 2015-12-21 | 2016-05-04 | 西北工业大学 | Preparation method of material increase manufactured nickel-based high-temperature alloy reserved with Laves phase |
| CN106119749A (en) * | 2016-06-28 | 2016-11-16 | 深圳市晶莱新材料科技有限公司 | A kind of 3D prints Ti 6Al 4V structural member Technology for Heating Processing |
| CN106180719A (en) * | 2016-09-27 | 2016-12-07 | 飞而康快速制造科技有限责任公司 | Selective laser fusing increases IN718 component, system, heat treatment method and the device that material manufactures |
Non-Patent Citations (3)
| Title |
|---|
| 卞宏友等: ""热处理对激光沉积修复GH4169合金高温性能的影响"", 《中国激光》 * |
| 孙骁: ""选区激光成形用IN718合金粉末特性及成形组织结构的研究"", 《中国优秀硕士学位论文全文数据库工程科技Ⅰ辑》 * |
| 葛锋等: ""热处理对Inconel718合金组织与性能影响的研究进展"", 《热加工工艺》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107299210B (en) | 2018-10-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108559934B (en) | Cryogenic treatment process for TC6 titanium alloy forging | |
| CN106929656B (en) | A kind of hardening and tempering method of 34CrNiMo6 large forgings | |
| KR20090130663A (en) | Method of heat treatment of ni based superalloy for wave type grain-boundary and ni based superalloy the same | |
| CN110358991B (en) | Processing method for enhancing thermal fatigue property of forged Ni-Cr-Co base alloy | |
| CN108977629B (en) | Annealing method of variable-thickness automobile skylight cross beam | |
| CN116411231A (en) | Grain refinement method for free forging nickel-based superalloy | |
| CN107299210B (en) | Heat treatment method after the blade reparation of the compressor blisk of aero-engine | |
| CN104099455B (en) | The high tough non-isothermal annealing treatment method of PH Stainless Steel | |
| CN103695798A (en) | Heat-resisting steel material used as ultra supercritical steam turbine rotor and preparation method thereof | |
| CN106947930A (en) | A kind of repair process method of titanium alloy plate deformation damage | |
| CN104372276B (en) | The method improving GH4698 alloy high-temp performance | |
| CN107447086B (en) | A kind of vacuum heat treatment process of FV520B-S steel | |
| CN108385045A (en) | The heat treatment method of δ phases is uniformly precipitated in a kind of control IN718 alloys | |
| CN105369022B (en) | A kind of method that 2Cr12NiMo1W1V forging carries out crystal grain refinement in process of production | |
| CN108754101B (en) | Cryogenic treatment process for AerMet100 steel | |
| CN112680630A (en) | Vacuum heat treatment method for ultra-high-toughness, medium-strength and high-plasticity TC32 titanium alloy part | |
| CN109355464B (en) | Heat treatment process for eliminating R26 high-temperature alloy bolt banded structure | |
| CN102127627B (en) | Method for obtaining high hardness and low deformation crack inclination of carbon tool steel | |
| CN105274373A (en) | Powder metallurgy preparation technology of gamma'' phase reinforced high temperature alloy | |
| CN105543748A (en) | Heat treatment method for Nimonic101 nickel-based alloy | |
| CN102876854A (en) | Tempering treatment technical method for 1Cr12 martensite stainless steel pressure spring forge piece | |
| CN105274297B (en) | Domestic GMH20 mould steel vacuum heat treatment process | |
| CN106868279A (en) | A kind of elimination 20CrMnTiH residual forging heats isothermal normalizing produces the Technology for Heating Processing of acicular ferrite | |
| CN109023185B (en) | Method for refining surface grain of GH80A high-temperature alloy part | |
| CN112280960A (en) | Heat treatment process for improving grain size of B50A789G blade steel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
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 |
|
| CP03 | Change of name, title or address |