CN104741612A - Powder high temperature alloy bar extrusion method - Google Patents
Powder high temperature alloy bar extrusion method Download PDFInfo
- Publication number
- CN104741612A CN104741612A CN201410686420.XA CN201410686420A CN104741612A CN 104741612 A CN104741612 A CN 104741612A CN 201410686420 A CN201410686420 A CN 201410686420A CN 104741612 A CN104741612 A CN 104741612A
- Authority
- CN
- China
- Prior art keywords
- extrusion
- high temperature
- powder metallurgy
- temperature alloy
- billet
- 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.)
- Pending
Links
- 238000001125 extrusion Methods 0.000 title claims abstract description 61
- 239000000843 powder Substances 0.000 title claims abstract description 17
- 229910045601 alloy Inorganic materials 0.000 title abstract description 14
- 239000000956 alloy Substances 0.000 title abstract description 14
- 238000000034 method Methods 0.000 claims abstract description 25
- 239000011521 glass Substances 0.000 claims abstract description 8
- 238000010438 heat treatment Methods 0.000 claims abstract description 8
- 239000010935 stainless steel Substances 0.000 claims abstract description 6
- 229910001220 stainless steel Inorganic materials 0.000 claims abstract description 6
- 238000005507 spraying Methods 0.000 claims abstract description 5
- 239000000314 lubricant Substances 0.000 claims abstract description 4
- 229910000601 superalloy Inorganic materials 0.000 claims description 37
- 238000004663 powder metallurgy Methods 0.000 claims description 35
- 238000003825 pressing Methods 0.000 claims description 7
- 239000007921 spray Substances 0.000 claims description 5
- 239000000428 dust Substances 0.000 claims description 4
- 230000015572 biosynthetic process Effects 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 2
- 238000000576 coating method Methods 0.000 claims description 2
- 230000003647 oxidation Effects 0.000 claims description 2
- 238000007254 oxidation reaction Methods 0.000 claims description 2
- 238000001035 drying Methods 0.000 claims 1
- 230000003064 anti-oxidating effect Effects 0.000 abstract 1
- 230000001050 lubricating effect Effects 0.000 abstract 1
- 239000000463 material Substances 0.000 description 10
- 238000005516 engineering process Methods 0.000 description 3
- 238000005336 cracking Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005275 alloying Methods 0.000 description 1
- 238000000137 annealing Methods 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000007705 chemical test Methods 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 239000008187 granular material Substances 0.000 description 1
- 238000001192 hot extrusion Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000010813 municipal solid waste Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 238000010301 surface-oxidation reaction Methods 0.000 description 1
Landscapes
- Powder Metallurgy (AREA)
Abstract
The invention relates to a powder high temperature alloy bar, in particular to a powder high temperature alloy bar extrusion method, and belongs to the field of plastic working. According to the method, high temperature alloy powder is injected into a stainless steel shell to form a powder high temperature alloy ingot, an upper end cover is arranged at the upper end of the powder high temperature alloy ingot, a base is arranged at the bottom of the powder high temperature alloy ingot, and the parts are welded to integrally form an extrusion billet; after being pre-heated, the extrusion billet is coated with anti-oxidation lubricants and aired, then the extrusion billet is put into a heating furnace to be heated, the extrusion billet is taken out of the furnace after being heated and then is subjected to online spraying and lubricating, a glass mat is arranged at the upper end of the extrusion billet, then the extrusion billet is transferred to an extrusion station to be extruded, and the powder high temperature alloy bar is straightened in the extrusion process. When the powder high temperature alloy ingot is extruded, matched extrusion die angles and matched extrusion temperature and speed are adopted, the powder high temperature alloy bar which is qualified is extruded under the condition that extrusion force is lowered to the largest extent, it is guaranteed that the outer surface of the extrusion billet is made of stainless steel, on one hand, the surface of the extrusion billet is prevented from being oxidized, and on the other hand, consistency of internal temperature and external temperature of the powder high temperature alloy ingot is guaranteed, and surface cracks are prevented in the forming process.
Description
technical field:
The present invention relates to a kind of powder metallurgy superalloy rod, particularly relate to a kind of powder metallurgy superalloy rod pressing method, belong to plastic working field.
background technology:
The turbine disk is the core heat end pieces of most critical in aero-engine, and advanced aero engine is to the serviceability temperature of the turbine disk, and the long-life, high reliability is had higher requirement.Along with the raising of turbine disk material alloying level, traditional casting forging material can not satisfy the demands, and the turbine disk adopting powder metallurgy process to produce progressively grows up just under this technical need promotes.Domestic powder metallurgy superalloy material system and America and Europe close, big-block engine powder disk preparation technology is also close with America and Europe, but owing to there is no aximal deformation value extrusion blooming technology, the defect problems such as powder disk structure property homogeneity question, primary granule border and field trash are made to be difficult to be effectively controlled, have impact on the performance and used life of turbine diskware, finally have impact on the quality of aero-engine and the performance of aircraft.U.S. Wyman-Gordon and French Aubert & Dural is only had to grasp the heavy extrusion technique of aerial high-temperature alloy bar material in the world.
Therefore, exploitation aero-engine turbine disk powder metallurgy superalloy hot extrusion process method, realizes the extruded of powder metallurgy superalloy ingot, meets the needs of civil aircraft to long-life, the high reliability turbine disk, is a realistic problem being badly in need of solving.
summary of the invention:
The object of the present invention is to provide a kind of powder metallurgy superalloy rod pressing method can avoiding cracking in powder metallurgy superalloy ingot forming process.
Technical solution:
Powder metallurgy superalloy rod pressing method, it is characterized in that, method step is as follows:
1) superalloy powder is injected in Stainless Steel Shell form powder metallurgy superalloy ingot, be provided with upper end cover in powder metallurgy superalloy ingot upper end, bottom powder metallurgy superalloy ingot, be provided with base, integrally welded formation extrusion billet;
2) to coating LMP glass dust lubricant after extrusion billet preheating;
3) extrusion billet after preheating is put into heating furnace, heating-up temperature (1050 DEG C-1080 DEG C), time: 9-11 hour;
4) after heating, extrusion billet is transported in the process of extrusion position, on-line spray process is carried out on extrusion billet surface, placing glass pad on extrusion billet after spray coating, proceed to extrusion position to extrude, be squeezed into powder metallurgy superalloy rod, extruding modular angle 55 °-65 °, extrusion speed 20mm/s-30 mm/s;
5) at extrusion die upper end configuration guide pipe or fairlead, powder metallurgy superalloy rod is placed in guide pipe or fairlead, carries out alignment, ensure that powder metallurgy superalloy rod does not bend in extrusion process.
Further: extrusion billet preheat temperature 700 °-900 °, preheating 8-15 minute.
Further: step 4) adopts glass dust to carry out on-line spray process.
The present invention is when compaction of powders high temperature alloy, adopt the extruding modular angle of coupling, extrusion temperature and extrusion speed, make to squeeze out up-to-standard extruded bars under the condition reducing extruding force to greatest extent, and the outer surface ensureing extrusion billet is all stainless steel, prevent extrusion billet surface oxidation on the one hand, ensure that powder metallurgy superalloy ingot internal and external temperature is consistent on the other hand, prevent from cracking in forming process.
accompanying drawing illustrates:
Fig. 1 is extrusion billet installation diagram of the present invention;
Fig. 2 is that the present invention extrudes rear bar Physico-chemical tests sampling schematic diagram;
Fig. 3 is that the present invention extrudes rear bar circle centre position direction of extrusion grain structure figure;
Fig. 4 is that the present invention extrudes rear bar 1/2 radius direction of extrusion grain structure figure;
Fig. 5 is that the present invention extrudes rear bar edge direction of extrusion grain structure figure.
detailed description of the invention:
Embodiment 1
Produce the FGH96 powder metallurgy superalloy material bar of φ 280 х 7200mm
1) superalloy powder is injected in Stainless Steel Shell form powder metallurgy superalloy ingot 1, be provided with upper end cover 2 in powder metallurgy superalloy ingot upper end, bottom powder metallurgy superalloy ingot, be provided with base 3, integrally welded formation extrusion billet; Avoid face crack in forming process to produce, improve stock utilization about 30%;
2) to extrusion billet preheating, preheat temperature 800 ± 10 DEG C, preheating is after 10 minutes, coats oxidation lubricant that Beijing Research Inst. of Aeronautic Material provides and dries;
3) extrusion billet after preheating is put into heating furnace, heating-up temperature 1070 DEG C, the time: 10 hours;
4) after heating, extrusion billet is transported in the process of extrusion position, on-line spray process is carried out on extrusion billet surface, spraying raw material is the glass dust of Beijing Aviation investigation of materials development, extrusion billet is after spray coating placed the glass isolator that Bei Chong group manufactures, proceed to extrusion position to extrude, be squeezed into powder metallurgy superalloy rod, extruding modular angle 60 °, extrusion speed 25mm/s; In extrusion process, material is through three-dimensional compressive stress effect, optimizes material structure performance, by more than the material grains degree to 10 after distortion grade, sees Fig. 3-5;
5) at extrusion die upper end configuration guide pipe or fairlead, powder metallurgy superalloy rod is placed in guide pipe or fairlead, carries out alignment, ensure that powder metallurgy superalloy rod does not bend in extrusion process;
6) cut to high temperature alloy rod after extruding the end, take out, air cooling;
7) annealing in process is carried out;
8) cut two, be finally met the powder metallurgy superalloy rod of the φ 280 х 7200mm of quality criteria requirements.
Adopt the present invention also to produce the powder metallurgy superalloy bar of external diameter 210-300 mm, solve a difficult problem for such difficult deformable metal crimp.
Claims (3)
1. powder metallurgy superalloy rod pressing method, it is characterized in that, method step is as follows:
1) superalloy powder is injected in Stainless Steel Shell form powder metallurgy superalloy ingot, be provided with upper end cover in powder metallurgy superalloy ingot upper end, bottom powder metallurgy superalloy ingot, be provided with base, integrally welded formation extrusion billet;
2) to coating oxidation lubricant after extrusion billet preheating and drying;
3) extrusion billet after preheating is put into heating furnace heating, heating-up temperature: 1050 DEG C-1080 DEG C, time: 9-11 hour;
4) extrusion billet after heating is transported in the process of extrusion position, on-line spray process is carried out on extrusion billet surface, extrusion billet upper ends glass isolator after spraying, then proceed to extrusion position to extrude, be squeezed into powder metallurgy superalloy rod, extruding modular angle 55 °-65 °, extrusion speed 20mm/s-30 mm/s;
5) at extrusion die upper end configuration guide pipe or fairlead, the powder metallurgy superalloy rod after extruding is placed in guide pipe or fairlead, carries out alignment, ensure that powder metallurgy superalloy rod does not bend in extrusion process.
2. powder metallurgy superalloy rod pressing method according to claim 1, is characterized in that, extrusion billet preheat temperature 700 DEG C-900 DEG C, preheating 8-15 minute.
3. powder metallurgy superalloy rod pressing method according to claim 1, it is characterized in that, step 4) adopts glass dust to carry out on-line spray process.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410686420.XA CN104741612A (en) | 2014-11-26 | 2014-11-26 | Powder high temperature alloy bar extrusion method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410686420.XA CN104741612A (en) | 2014-11-26 | 2014-11-26 | Powder high temperature alloy bar extrusion method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104741612A true CN104741612A (en) | 2015-07-01 |
Family
ID=53582183
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410686420.XA Pending CN104741612A (en) | 2014-11-26 | 2014-11-26 | Powder high temperature alloy bar extrusion method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104741612A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107511483A (en) * | 2017-10-11 | 2017-12-26 | 南通聚星铸锻有限公司 | A kind of powder metallurgy superalloy rod pressing method |
| CN112045188A (en) * | 2020-09-04 | 2020-12-08 | 中国航发北京航空材料研究院 | Horizontal extrusion mold core for powder high-temperature alloy and preparation method thereof |
| CN117380956A (en) * | 2023-12-08 | 2024-01-12 | 北京钢研高纳科技股份有限公司 | Low-cost high-homogeneity large-specification powder high-temperature alloy bar and hot extrusion method thereof |
| RU2829983C1 (en) * | 2023-12-08 | 2024-11-11 | Гаона Аеро Материал Ко.Лтд. | Rod from powdered superalloy, characterized by low cost, high homogeneity and large dimensions, and method of manufacturing such rod |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1405749A (en) * | 1971-06-22 | 1975-09-10 | Davy Int Ltd | Extrusion of powder billets |
| DE2838850A1 (en) * | 1978-09-06 | 1980-03-27 | Graenges Nyby Ab | METHOD FOR TREATING EXTRUDED PIPES MADE OF STAINLESS STEEL |
| US4373012A (en) * | 1978-10-26 | 1983-02-08 | Granges Nyby Ab | Casings and pressed parts utilized for the extrusion of articles, particularly pipes, and manufacturing process of such casings and pressed parts |
| JPH0277536A (en) * | 1988-06-08 | 1990-03-16 | Sanyo Special Steel Co Ltd | Production of high-carbon cobalt-base alloy member |
| JPH02270903A (en) * | 1989-04-13 | 1990-11-06 | Ube Ind Ltd | Method for manufacturing aluminum alloy parts |
| CN1507962A (en) * | 2002-12-18 | 2004-06-30 | 中国科学院金属研究所 | A kind of processing method of superalloy tube billet |
| CN1824402A (en) * | 2006-03-23 | 2006-08-30 | 沈阳理工大学 | Alloy pipe hot extrusion method and extrusion die |
-
2014
- 2014-11-26 CN CN201410686420.XA patent/CN104741612A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1405749A (en) * | 1971-06-22 | 1975-09-10 | Davy Int Ltd | Extrusion of powder billets |
| DE2838850A1 (en) * | 1978-09-06 | 1980-03-27 | Graenges Nyby Ab | METHOD FOR TREATING EXTRUDED PIPES MADE OF STAINLESS STEEL |
| US4373012A (en) * | 1978-10-26 | 1983-02-08 | Granges Nyby Ab | Casings and pressed parts utilized for the extrusion of articles, particularly pipes, and manufacturing process of such casings and pressed parts |
| JPH0277536A (en) * | 1988-06-08 | 1990-03-16 | Sanyo Special Steel Co Ltd | Production of high-carbon cobalt-base alloy member |
| JPH02270903A (en) * | 1989-04-13 | 1990-11-06 | Ube Ind Ltd | Method for manufacturing aluminum alloy parts |
| CN1507962A (en) * | 2002-12-18 | 2004-06-30 | 中国科学院金属研究所 | A kind of processing method of superalloy tube billet |
| CN1824402A (en) * | 2006-03-23 | 2006-08-30 | 沈阳理工大学 | Alloy pipe hot extrusion method and extrusion die |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107511483A (en) * | 2017-10-11 | 2017-12-26 | 南通聚星铸锻有限公司 | A kind of powder metallurgy superalloy rod pressing method |
| CN112045188A (en) * | 2020-09-04 | 2020-12-08 | 中国航发北京航空材料研究院 | Horizontal extrusion mold core for powder high-temperature alloy and preparation method thereof |
| CN117380956A (en) * | 2023-12-08 | 2024-01-12 | 北京钢研高纳科技股份有限公司 | Low-cost high-homogeneity large-specification powder high-temperature alloy bar and hot extrusion method thereof |
| CN117380956B (en) * | 2023-12-08 | 2024-03-12 | 北京钢研高纳科技股份有限公司 | Low-cost high-homogeneity large-specification powder high-temperature alloy bar and hot extrusion method thereof |
| WO2024183426A1 (en) * | 2023-12-08 | 2024-09-12 | 北京钢研高纳科技股份有限公司 | Low-cost, high-homogeneity and large-specification powder high-temperature alloy bar, and hot extrusion method therefor |
| RU2829983C1 (en) * | 2023-12-08 | 2024-11-11 | Гаона Аеро Материал Ко.Лтд. | Rod from powdered superalloy, characterized by low cost, high homogeneity and large dimensions, and method of manufacturing such rod |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104060203B (en) | A kind of production technique of alloy extrusion bar | |
| CN104148558B (en) | The production method of T-shaped ring-type forge piece blank reheating in SB564 UNS N06690 alloy large-size | |
| CN111753453B (en) | A high-precision simulation method for forming process of high-strength steel die forgings | |
| CN104759850A (en) | Processing technique of high aluminum alloy cylinder | |
| CN104493167A (en) | Method for forming powder high-temperature alloy annular member | |
| CN104707931A (en) | Manufacturing method for large high-temperature alloy disk-type die forging parts | |
| CN107675112A (en) | A kind of jacket deformation method of ultra-high-strength aluminum alloy | |
| CN105921672A (en) | Isothermal forging method of straight bevel gear | |
| CN104826969A (en) | Method for forging 500-Kg-level GH3230 high-temperature alloy | |
| CN104741612A (en) | Powder high temperature alloy bar extrusion method | |
| CN110252899A (en) | A rapid heating cold die hot plate forming method for titanium alloy thin-walled components | |
| CN104841830A (en) | Method for manufacturing TC4-DT titanium alloy large-size forged blanks | |
| CN101259584A (en) | Method for preparing high-density molybdenum tube | |
| CN105731792B (en) | A kind of lubricant for abros hot extrusion and preparation method thereof | |
| CN102717078A (en) | Process of tungsten alloy rotary swaging rod with high density and high performance | |
| CN106734795A (en) | A kind of preparation method of niobium GH4169 alloy bar materials high | |
| CN103934397A (en) | Engine turbine disc optimizing manufacturing process and device based on heat-resisting alloy | |
| CN104624914A (en) | Semisolid process for manufacturing engine aluminum alloy cam shaft through radial forging strain provocation method | |
| CN1683097A (en) | Blooming method of thermal insulation forging for GH742 alloy large steel ingot | |
| CN108620452A (en) | A kind of hot straightening method of titanium alloy abnormal shape tubular casting | |
| CN103352912B (en) | V-six engine crankshaft forging and forging method thereof | |
| LI et al. | Integrated simulation of the forging process for GH4738 alloy turbine disk and its application | |
| CN105499449B (en) | The method for eliminating casting and rolling composite forming large ring metallurgical imperfection | |
| CN104646945B (en) | Special high-strength aluminum alloy part forming method | |
| CN105728537A (en) | Hot-spinning cogging method based on nonuniform heating of aluminum alloy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150701 |
|
| WD01 | Invention patent application deemed withdrawn after publication |