CN103846631B - A kind of control method of aero-engine carburized gears grinding crack - Google Patents
A kind of control method of aero-engine carburized gears grinding crack Download PDFInfo
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- CN103846631B CN103846631B CN201310406607.5A CN201310406607A CN103846631B CN 103846631 B CN103846631 B CN 103846631B CN 201310406607 A CN201310406607 A CN 201310406607A CN 103846631 B CN103846631 B CN 103846631B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
Abstract
The present invention relates to the control method of a kind of aero-engine carburized gears grinding crack.The method mainly includes two aspects: time one, in view of gear grinding, too high surface temperature will necessarily make top layer metallographic structure change, this will cause the change of gear surface microhardness, therefore controls the microhardness on gear surface to be ground between 56～60HRC.Two, it is the result that structural stress and thermal stress superposition produce in view of grinding crack, therefore improves the distribution situation of surface stress, make residual stress be balanced or reduce.Beneficial effects of the present invention: by substantial amounts of experiment, it was demonstrated that use the gear grinding surface after said method to have no grinding crack.This method can popularization and application to the control of other model aero-engine gear grinding crackle, for the technical experience that the research accumulation of new model aero-engine is valuable.
Description
Technical field
The present invention relates to the control method of a kind of aero-engine carburized gears grinding crack.
Background technology
Aero-engine gear is used to transmit power and change the speed of service, and therefore in power transmission mechanism is such as decelerator, various forms of gears are widely used.
In aero-engine gear through engineering approaches manufacture process, grinding crack is the key factor affecting product quality.Grinding crack is divided into two kinds, and one is to only occur on grinding face, and the degree of depth is shallower, and the degree of depth is basically identical, and direction is perpendicular to teeth directional, and without definite shape, another kind be crackle be Carapax Et Plastrum Testudinis shape (close network shape), its degree of depth substantially 0.03～0.15mm.The maximum feature of grinding crack is immediately to manifest, and has the biggest retardance, and the existence of grinding crack can be substantially reduced the fatigue behaviour of matrix material.
Before improvement, the control of aero-engine carburized gears grinding crack realizes by reducing stock removal and reduction grinding speed, but all cannot fundamentally stop the generation of grinding crack, and the removal of grinding crack is dependent on manual grinding and throwing is repaiied.The existence of grinding crack makes product manufacturing cycle length, manufacturing cost high, more seriously affects product quality and produces payment.
Summary of the invention
It is an object of the invention to: provide a kind of and control the method that aero-engine carburized gears grinding crack produces, overcome prior art cannot effectively control grinding crack, affect product quality so that product manufacturing cycle length, the deficiency that cost is high.
First, the mechanism of production of analysis aero-engine gear grinding crackle:
The generation of grinding crack is caused by grinding heat, and during grinding, the temperature of gear surface may be up to 820～840 DEG C or higher.If its surface quickly heats up to about 100 DEG C and cools down rapidly, necessarily generation being shunk, this contraction occurs over just surface, and its matrix is still in swelling state, so that surface layer bears tension and produces the first crackle；When temperature rises to 300 DEG C, surface produces contraction again, thus produces the second crackle.If cool down insufficient when grinding, then the heat produced due to grinding, it is sufficient to making grinding skin thin layer reaustenitizing, quenching becomes quenched martensite the most again.Thus make surface layer produce additional structural stress, adding the heat that grinding formed makes the temperature of piece surface raise to be exceedingly fast, and the superposition of this structural stress and thermal stress results in grinding skin and grinding crack occurs.
Combine in above-mentioned analysis, the new control method of the determination aero-engine gear grinding crackle of the present invention, mainly include two aspects:
One, in view of gear grinding time, too high surface temperature will necessarily make top layer metallographic structure change, and this will cause the change of gear surface microhardness, therefore controls the microhardness on gear surface to be ground between 56～60HRC.
Two, it is the result that structural stress and thermal stress superposition produce in view of grinding crack, therefore improves the distribution situation of surface stress, make residual stress be balanced or reduce.
Particularly, the technical scheme is that the control method of a kind of aero-engine carburized gears grinding crack, specifically include following steps:
Step one: gear is carried out first and second Carburization Treatment, it is ensured that gear surface microhardness to be ground is 56～60HRC；In particular it is necessary to ensure time gear is carried out first and second Carburization Treatment, set carbon potential as 1.1%～1.3%, thus reach surface microhardness and meet above-mentioned requirements；
Step 2: the gear after Carburization Treatment is carried out grinding；
Step 3: the gear after grinding is carried out low temperature de-stress process.
The invention has the beneficial effects as follows: by substantial amounts of experiment, it was demonstrated that use the gear grinding surface after said method to have no grinding crack.This method can popularization and application to the control of other model aero-engine gear grinding crackle, for the technical experience that the research accumulation of new model aero-engine is valuable.
Detailed description of the invention
Embodiment one:
The control method of the aero-engine carburized gears grinding crack in the present embodiment, specifically includes following steps:
Step one: gear is carried out first and second Carburization Treatment, ensure that gear surface microhardness to be ground is 56～60HRC, in the present embodiment, first and second Carburization Treatment testing equipment is vacuum cementation furnace ICBP-644TH, device parameter: effective heating area 600mm × 450mm × 450mm, temperature uniformity (500～750) DEG C/± 5 DEG C, (750～1150) DEG C/± 10 DEG C；
Gear is carried out the process of first and second Carburization Treatment by the present embodiment and includes following sub-step:
Sub-step 1: set vacuum cementation furnace carbon potential as 1.1%；
Sub-step 2: set a carburizing temperature and temperature retention time is respectively 905 DEG C, 6.5H；
Sub-step 3: set secondary carburizing temperature and temperature retention time is respectively 905 DEG C, 4H；
After coming out of the stove, checking the microhardness on gear surface to be ground, three times test value is respectively as follows: 56,56,56, meansigma methods: 56；
Step 2: the gear after Carburization Treatment is carried out grinding；
Step 3: the gear after grinding is carried out low temperature de-stress process, cooling medium is air, in the present embodiment, testing equipment: low hot-well formula tempering furnace RJJ-36-6, device parameter: effective heating area is φ 450mm × 500mm, temperature uniformity be (100～350) DEG C/± 5 DEG C；
Set low temperature destressing holding temperature as 150 DEG C, set low temperature destressing temperature retention time as 1.5H；After coming out of the stove, after gear is cooled to room temperature, carry out antirust treatment at gear grinding surface-coated TS-5 type dehydrated oil.
Embodiment two:
The control method of the aero-engine carburized gears grinding crack in the present embodiment, specifically includes following steps:
Step one: gear is carried out first and second Carburization Treatment, it is ensured that gear surface microhardness to be ground is 56～60HRC；Gear is carried out the process of first and second Carburization Treatment by the present embodiment and includes following sub-step:
Sub-step 1: set vacuum cementation furnace carbon potential as 1.3%；
Sub-step 2: set a carburizing temperature and temperature retention time is respectively 905 DEG C, 6.5H；
Sub-step 3: set secondary carburizing temperature and temperature retention time is respectively 905 DEG C, 4H；
After coming out of the stove, checking the microhardness on gear surface to be ground, three times test value is respectively as follows: 57,61,62, meansigma methods: 60；
Step 2: the gear after Carburization Treatment is carried out grinding；
Step 3: the gear after grinding is carried out low temperature de-stress process.
In employing embodiment one and embodiment two, the gear grinding surface after method has no grinding crack, thus demonstrates the effectiveness of this method.
Claims (2)
1. the control method of an aero-engine carburized gears grinding crack, it is characterised in that: comprise the steps:
Step one: gear carries out first and second Carburization Treatment, wherein carries out the process of first and second Carburization Treatment and includes following sub-step gear:
Sub-step 1: set vacuum cementation furnace carbon potential；
Sub-step 2: set a carburizing temperature and temperature retention time；
Sub-step 3: set secondary carburizing temperature and temperature retention time；
After coming out of the stove, check the microhardness on gear surface to be ground, it is ensured that gear surface microhardness to be ground is 56～60HRC；
Step 2: the gear after Carburization Treatment is carried out grinding；
Step 3: the gear after grinding is carried out low temperature de-stress process.
2. the control method of an aero-engine carburized gears grinding crack as claimed in claim 1, it is characterized in that: when described step one middle gear surface microhardness to be ground requires by gear is carried out first and second Carburization Treatment, set carbon potential and reach as 1.1%～1.3%.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310406607.5A CN103846631B (en) | 2013-09-09 | 2013-09-09 | A kind of control method of aero-engine carburized gears grinding crack |
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| CN201310406607.5A CN103846631B (en) | 2013-09-09 | 2013-09-09 | A kind of control method of aero-engine carburized gears grinding crack |
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| Publication Number | Publication Date |
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| CN103846631A CN103846631A (en) | 2014-06-11 |
| CN103846631B true CN103846631B (en) | 2016-08-03 |
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Families Citing this family (1)
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| CN109202664B (en) * | 2018-09-20 | 2020-11-17 | 孙佑军 | Grinding method capable of eliminating grinding cracks |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2013531A (en) * | 1978-01-26 | 1979-08-15 | Brown Gear Ind | Producing Case-Hardened Gears |
| CN102463396A (en) * | 2010-11-15 | 2012-05-23 | 江苏高齿传动机械有限公司 | Method for improving grinding crack of molding gear-grinding machine |
| CN102699642A (en) * | 2012-04-28 | 2012-10-03 | 重庆市江津区宏盛机械制造有限公司 | Process for machining rail traffic driven gear |
| CN102979884A (en) * | 2012-11-23 | 2013-03-20 | 无锡威孚中意齿轮有限责任公司 | Mine vehicle axle wheel reductor planetary gear and manufacture method thereof |
-
2013
- 2013-09-09 CN CN201310406607.5A patent/CN103846631B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2013531A (en) * | 1978-01-26 | 1979-08-15 | Brown Gear Ind | Producing Case-Hardened Gears |
| CN102463396A (en) * | 2010-11-15 | 2012-05-23 | 江苏高齿传动机械有限公司 | Method for improving grinding crack of molding gear-grinding machine |
| CN102699642A (en) * | 2012-04-28 | 2012-10-03 | 重庆市江津区宏盛机械制造有限公司 | Process for machining rail traffic driven gear |
| CN102979884A (en) * | 2012-11-23 | 2013-03-20 | 无锡威孚中意齿轮有限责任公司 | Mine vehicle axle wheel reductor planetary gear and manufacture method thereof |
Non-Patent Citations (5)
| Title |
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| 冷作模具的磨削裂纹分析与防护;余华俐等;《机械研究与应用》;20010331;第14卷(第1期);第25-26页 * |
| 刃口磨削裂纹产生机理分析;童鲁海等;《机电工程》;20080731;第25卷(第7期);第112-114页 * |
| 模具线切割裂纹和变形的探讨;许鹤鸣;《电子工艺技术》;19820630(第6期);第16-24页 * |
| 渗碳淬火件磨削裂纹形成的原因和防止措施;李志义等;《国外金属热处理》;20050228;第26卷(第1期);第46-47页 * |
| 齿轮磨齿裂纹的产生及控制;汪光旭;《中国表面工程》;19960228(第2期);第32-35页 * |
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Addressee: Xi'an Airlines Power Limited by Share Ltd. patent Manager Document name: Notice of non patent agency Addressee: Xi'an Airlines Power Limited by Share Ltd. patent Manager Document name: Notification to Make Rectification |
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Address after: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee after: AECC AVIATION POWER CO,LTD. Address before: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee before: AVIC AVIATION ENGINE Corp.,PLC Address after: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee after: AVIC AVIATION ENGINE Corp.,PLC Address before: 710021 Xu Jia Bay, Xi'an, Shaanxi, Beijiao Patentee before: XI'AN AVIATION POWER Co.,Ltd. |
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