CN102912100A - Micro deformation processing technique of OCr17Ni4Cu4Nb material thin-wall gear parts - Google Patents
Micro deformation processing technique of OCr17Ni4Cu4Nb material thin-wall gear parts Download PDFInfo
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- CN102912100A CN102912100A CN2012102312988A CN201210231298A CN102912100A CN 102912100 A CN102912100 A CN 102912100A CN 2012102312988 A CN2012102312988 A CN 2012102312988A CN 201210231298 A CN201210231298 A CN 201210231298A CN 102912100 A CN102912100 A CN 102912100A
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Abstract
The invention discloses a micro deformation processing technique of OCr17Ni4Cu4Nb material thin-wall gear parts. The technique comprises the following working procedures of material preparation-rough turning-solid melting-vehicle working-pincer working-aging-inserting-pincer working-aging-inserting-pincer working-vehicle working-aging hardening-checking-storing. A subzero treatment working procedure is added after the solid melting working procedure. The processing technique of OCr17Ni4Cu4Nb material thin-wall gear parts is summarized, parts processed by the processing technique is small in part deformation, not easy to oxidize, high in hardness and good in corrosion resistance. The hardness of the parts processed by the existing technique is HRC28-33, and the hardness of the parts processed by the processing technique can improve to (HRC38-42). The micro deformation processing technique can be used for processing the OCr17Ni4Cu4Nb material thin-wall gear parts, can also be used for processing other OCr17Ni4Cu4Nb material thin-wall parts, and can be applicable to processing requirements for high-reliability, high-hardness and high-corrosion resistance parts in aviation and aerospace.
Description
Technical field
The present invention relates to a kind of little deformation processing technique of OCr17Ni4Cu4Nb material thin wall gear part, belong to the heat treatment step technical field in the complete processing, particularly complete processing of OCr17Ni4Cu4Nb material.
Background technology
Along with the Aeronautics and Astronautics industrial expansion, the demand of high reliability, high rigidity, corrosion resistant precision gear is increased year by year.Therefore, the control of the stability of material, heat treated distortion also there is strict demand.When the thin-wall gear part of a kind of OCr17Ni4Cu4Nb material of processing, adopt following technology: get the raw materials ready → rough turn → solid solution → car → pincers → timeliness → insert → pincers → timeliness → insert → pincers → car → age hardening → check → warehouse-in at present.By existing complete processing, part is in that to finish the age hardening after strain larger, often can scrap because of the distortion of part outer and the distortion of length of common normal, and tooling cost and material cost are higher.
Summary of the invention
The object of the invention is to, a kind of little deformation processing technique of OCr17Ni4Cu4Nb material thin wall gear part is provided.Can solve the large problem of thin-walled parts heat treatment process distortion, to overcome the deficiencies in the prior art.
Technical scheme of the present invention:
Little deformation processing technique of OCr17Ni4Cu4Nb material thin wall gear part, this technique comprises following operation: get the raw materials ready → rough turn → solid solution → car → pincers → timeliness → insert → pincers → timeliness → insert → pincers → car → age hardening → check → warehouse-in; This technical scheme is to increase the sub-zero treatment operation after the solid solution operation one.
In the aforementioned complete processing, described rough turn operation is that 1.5～2.5mm process redundancy is reserved in later precision work.
In the aforementioned complete processing, described rough turn operation is that 2mm process redundancy is reserved in later precision work.
In the aforementioned complete processing, described solid solution operation is part to be put into process furnace be warming up to 250 ± 100 ℃ of insulations 40 minutes, then is heated to 1050 ± 10 ℃, and soaking time was come out of the stove after 1 hour, oil cooling to 100 ℃ or room temperature.
In the aforementioned complete processing, described part is put into solid solution furnace before at first preheating of part, drying and processing, and preheating temperature is not less than 100 ℃.
In the aforementioned complete processing, described sub-zero treatment operation is that the part after the solid solution operation is processed is put into cooling apparatus and fallen 2 ℃ rate of cooling with per minute and be cooled to-100 ℃, be incubated and after 1 hour part taken out from cooling apparatus, after naturally cooling to room temperature, put into again process furnace and heat to 150 ± 10 ℃, be incubated and take out naturally cooling after 3 hours.
In the aforementioned complete processing, described timeliness operation adopts oil oven to carry out timeliness, and oil temperature is put into part after rising to 200 ± 10 ℃, is incubated and comes out of the stove air cooling to envrionment temperature after 4 hours.
In the aforementioned complete processing, described age hardening operation is the part that machining is finished to be put into 420 ± 5 ℃ heat treatment furnace, and soaking time was taken out the part air cooling to envrionment temperature more than or equal to 1.5 hours after soaking time finishes.
In the aforementioned complete processing, the part that described machining is finished is put into before 420 ± 5 ℃ the heat treatment furnace, uses first greasy dirt and the foreign matter on No. 120 industrial naptha cleaning components surfaces.
In the aforementioned complete processing, the temperature control process of described solid solution operation, sub-zero treatment operation, timeliness operation and age hardening operation adopts thermocouple measuring temperature, adopts self-registering instrument writing time, and temperature uniformity requires to be ± 5 ℃.
Compared with prior art, the present invention has summed up the complete processing of a cover OCr17Ni4Cu4Nb material thin wall gear part, and the part deformation that this complete processing processes is little, is difficult for oxidation, hardness height, anticorrosive good.The part hardness of now technology processing is between HRC28～33, and the part hardness of the present invention's processing can be increased to (HRC38～42).The present invention not only can be used for processing OCr17Ni4Cu4Nb material thin wall gear part, also can be used for processing other OCr17Ni4Cu4Nb material thin wall part, applicable to the processing request of Aeronautics and Astronautics high reliability, high rigidity, high corrosion resistance part.
Description of drawings
Fig. 1 is an instance graph of institute of the present invention processing parts.
Embodiment
The present invention is described in further detail below in conjunction with drawings and Examples, but not as any limitation of the invention.
Embodiment.Little deformation processing technique of OCr17Ni4Cu4Nb material thin wall gear part (as shown in Figure 1) comprises following operation: get the raw materials ready → rough turn → solid solution → car → pincers → timeliness → insert → pincers → timeliness → insert → pincers → car → age hardening → check → warehouse-in; The present invention increases the sub-zero treatment operation one after the solid solution operation.The sub-zero treatment operation is that the part after the solid solution operation is processed is put into cooling apparatus and fallen 2 ℃ rate of cooling with per minute and be cooled to-100 ℃, be incubated and after 1 hour part taken out from cooling apparatus, after naturally cooling to room temperature, put into again process furnace and heat to 150 ± 10 ℃, be incubated and take out naturally cooling after 3 hours.
Add man-hour by above-mentioned manufacturing procedure, rough turn operation is that 2mm process redundancy is reserved in later precision work.The solid solution operation is part to be put into process furnace be warming up to 250 ± 100 ℃ of insulations 40 minutes, then is heated to 1050 ± 10 ℃, and soaking time was come out of the stove after 1 hour, oil cooling to 100 ℃ or room temperature; To at first preheating of part, drying and processing, preheating temperature is not less than 100 ℃ before part is put into solid solution furnace.The timeliness operation adopts oil oven to carry out timeliness, and oil temperature is put into part after rising to 200 ± 10 ℃, is incubated and comes out of the stove air cooling to envrionment temperature after 4 hours.The age hardening operation is the part that machining is finished to be put into 420 ± 5 ℃ heat treatment furnace, and soaking time was taken out the part air cooling to envrionment temperature more than or equal to 1.5 hours after soaking time finishes; The part that machining is finished is put into before 420 ± 5 ℃ the heat treatment furnace, uses first greasy dirt and the foreign matter on No. 120 industrial naptha cleaning components surfaces.The temperature control process of aforementioned solid solution operation, sub-zero treatment operation, timeliness operation and age hardening operation adopts thermocouple measuring temperature, adopts self-registering instrument writing time, and temperature uniformity requires to be ± 5 ℃.
Ultimate principle of the present invention: part shown in Figure 1 aviation duplicate gear for becoming with OCr17Ni4Cu4Nb materials processing.The material of this duplicate gear belongs to age hardening type stainless steel, and its typical heat treatment process mode is: solid solution+age hardening, the present invention has increased the sub-zero treatment operation in solid solution between the age hardening two procedures.Effectively controlled the dimensional stability of part after heat treatment deformation and the thermal treatment.
Solution treatment: will cool off with suitable speed of cooling behind the steel austenitizing, make the workpiece thermal treatment process that whole or certain weave construction changes in cross section.
Sub-zero treatment: sub-zero treatment is the temperature reduction with martensitic transformation destination node in the OCr17Ni4Cu4Nb material, a kind of method that can continue in the OCr17Ni4Cu4Nb material changed towards the martensite direction, effectively reduced the content of residual austenite, made part size in subsequent heat treatment more stable.
Ageing treatment: will be heated to through the part after the solution treatment the following proper temperature of stagnation point and keep certain hour, subsequently with satisfactory method cooling, to obtain the thermal treatment process of needed tissue and performance.
After the solution treatment, part hardness is increased to (HRC38～42) through hardness after the age hardening between HRC28～33.Because its matrix is martensitic stucture after the solution treatment, sub-zero treatment reduces the residual austenite of part.In the ag(e)ing process, carbide precipitate particle on the martensitic matrix makes matrix hardness be able to height (carbide hardness high), because the content of residual austenite is few, part size after age hardening is more stable, be out of shape little, thereby realize little distortion.
Claims (10)
1. little deformation processing technique of an OCr17Ni4Cu4Nb material thin wall gear part, this technique comprises following operation: get the raw materials ready → rough turn → solid solution → car → pincers → timeliness → insert → pincers → timeliness → insert → pincers → car → age hardening → check → warehouse-in; It is characterized in that: after the solid solution operation, increase the sub-zero treatment operation one.
2. described complete processing according to claim 1, it is characterized in that: described rough turn operation is that 1.5～2.5mm process redundancy is reserved in later precision work.
3. described complete processing according to claim 2, it is characterized in that: described rough turn operation is that 2mm process redundancy is reserved in later precision work.
4. described complete processing according to claim 1, it is characterized in that: described solid solution operation is part to be put into process furnace be warming up to 250 ± 100 ℃ of insulations 40 minutes, then be heated to 1050 ± 10 ℃, soaking time was come out of the stove after 1 hour, oil cooling to 100 ℃ or room temperature.
5. described complete processing according to claim 4 is characterized in that: described part is put into before the solid solution furnace at first preheating of part, drying and processing, and preheating temperature is not less than 100 ℃.
6. described complete processing according to claim 4, it is characterized in that: described sub-zero treatment operation is that the part after the solid solution operation is processed is put into cooling apparatus and fallen 2 ℃ rate of cooling with per minute and be cooled to-100 ℃, be incubated and after 1 hour part taken out from cooling apparatus, after naturally cooling to room temperature, put into again process furnace and heat to 150 ± 10 ℃, be incubated and take out naturally cooling after 3 hours.
7. described complete processing according to claim 1, it is characterized in that: described timeliness operation adopts oil oven to carry out timeliness, and oil temperature is put into part after rising to 200 ± 10 ℃, is incubated and comes out of the stove air cooling to envrionment temperature after 4 hours.
8. described complete processing according to claim 1, it is characterized in that: described age hardening operation is the part that machining is finished to be put into 420 ± 5 ℃ heat treatment furnace, soaking time was taken out the part air cooling to envrionment temperature more than or equal to 1.5 hours after soaking time finishes.
9. described complete processing according to claim 8 is characterized in that: the part that described machining is finished is put into before 420 ± 5 ℃ the heat treatment furnace, uses first greasy dirt and the foreign matter on No. 120 industrial naptha cleaning components surfaces.
10. the described complete processing of arbitrary claim according to claim 1～8, it is characterized in that: the temperature control process of described solid solution operation, sub-zero treatment operation, timeliness operation and age hardening operation adopts thermocouple measuring temperature, adopt self-registering instrument writing time, temperature uniformity requires to be ± 5 ℃.
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104148896A (en) * | 2014-08-04 | 2014-11-19 | 贵州航宇科技发展股份有限公司 | Manufacturing method of GH4169 high-temperature alloy semi-ring |
| CN104439988A (en) * | 2013-09-17 | 2015-03-25 | 贵州群建精密机械有限公司 | Machining technology for gear made of 9Cr18 material |
| CN104451425A (en) * | 2014-11-14 | 2015-03-25 | 无锡信大气象传感网科技有限公司 | Elastomeric material for weighing sensor and heat treatment method thereof |
| CN104451423A (en) * | 2014-11-14 | 2015-03-25 | 无锡信大气象传感网科技有限公司 | Stainless steel elastomer material of weighing sensor and heat treatment method of stainless steel elastomer material |
| CN104694709A (en) * | 2015-03-09 | 2015-06-10 | 中船重工西安东仪科工集团有限公司 | Heat treatment technique for improving hardness of 05Cr17Ni4Cu4Nb steel part |
| CN106514165A (en) * | 2016-12-15 | 2017-03-22 | 贵州群建精密机械有限公司 | Glow-ion nitriding treatment method for gear made of 05Cr17Ni4Cu4Nb material |
| CN110724797A (en) * | 2019-10-23 | 2020-01-24 | 成都飞机工业（集团）有限责任公司 | Method for processing aviation PH13-8Mo part |
| CN112091629A (en) * | 2020-09-15 | 2020-12-18 | 中国航发贵州黎阳航空动力有限公司 | Machining method of thin-wall gear ring with key groove |
| CN112522499A (en) * | 2020-11-11 | 2021-03-19 | 中国航发中传机械有限公司 | Heat treatment method of oblique-amplitude plate cylindrical gear for aviation |
| CN113789431A (en) * | 2021-08-31 | 2021-12-14 | 贵州群建精密机械有限公司 | Manufacturing method of harmonic flexible gear |
| CN115029524A (en) * | 2022-04-29 | 2022-09-09 | 沈阳鼓风机集团往复机有限公司 | Cryogenic treatment process for S51740 material |
| US20230341038A1 (en) * | 2021-02-26 | 2023-10-26 | Npc Robotics Corporation | Boltless unitary ring gear-flange body |
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2012
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104439988A (en) * | 2013-09-17 | 2015-03-25 | 贵州群建精密机械有限公司 | Machining technology for gear made of 9Cr18 material |
| CN104148896A (en) * | 2014-08-04 | 2014-11-19 | 贵州航宇科技发展股份有限公司 | Manufacturing method of GH4169 high-temperature alloy semi-ring |
| CN104451425A (en) * | 2014-11-14 | 2015-03-25 | 无锡信大气象传感网科技有限公司 | Elastomeric material for weighing sensor and heat treatment method thereof |
| CN104451423A (en) * | 2014-11-14 | 2015-03-25 | 无锡信大气象传感网科技有限公司 | Stainless steel elastomer material of weighing sensor and heat treatment method of stainless steel elastomer material |
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| CN106514165A (en) * | 2016-12-15 | 2017-03-22 | 贵州群建精密机械有限公司 | Glow-ion nitriding treatment method for gear made of 05Cr17Ni4Cu4Nb material |
| CN110724797A (en) * | 2019-10-23 | 2020-01-24 | 成都飞机工业（集团）有限责任公司 | Method for processing aviation PH13-8Mo part |
| CN110724797B (en) * | 2019-10-23 | 2022-05-06 | 成都飞机工业（集团）有限责任公司 | Method for processing aviation PH13-8Mo part |
| CN112091629A (en) * | 2020-09-15 | 2020-12-18 | 中国航发贵州黎阳航空动力有限公司 | Machining method of thin-wall gear ring with key groove |
| CN112522499A (en) * | 2020-11-11 | 2021-03-19 | 中国航发中传机械有限公司 | Heat treatment method of oblique-amplitude plate cylindrical gear for aviation |
| US20230341038A1 (en) * | 2021-02-26 | 2023-10-26 | Npc Robotics Corporation | Boltless unitary ring gear-flange body |
| CN113789431A (en) * | 2021-08-31 | 2021-12-14 | 贵州群建精密机械有限公司 | Manufacturing method of harmonic flexible gear |
| CN115029524A (en) * | 2022-04-29 | 2022-09-09 | 沈阳鼓风机集团往复机有限公司 | Cryogenic treatment process for S51740 material |
| CN115029524B (en) * | 2022-04-29 | 2024-01-19 | 沈阳鼓风机集团往复机有限公司 | Cryogenic treatment process for S51740 material |
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Application publication date: 20130206 |