CN103846631A - Method for controlling grinding cracks of carburized gear of aircraft engine - Google Patents
Method for controlling grinding cracks of carburized gear of aircraft engine Download PDFInfo
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- CN103846631A CN103846631A CN201310406607.5A CN201310406607A CN103846631A CN 103846631 A CN103846631 A CN 103846631A CN 201310406607 A CN201310406607 A CN 201310406607A CN 103846631 A CN103846631 A CN 103846631A
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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
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- Mechanical Engineering (AREA)
- Solid-Phase Diffusion Into Metallic Material Surfaces (AREA)
- Heat Treatment Of Articles (AREA)
- Gears, Cams (AREA)
Abstract
The invention relates to a method for controlling grinding cracks of a carburized gear of an aircraft engine. The method mainly comprises two aspects: 1, in consideration of the condition that a surface-layer metallographic structure is inevitably changed by excessively high surface temperature to further cause changes in the microscopic hardness of the surface of the gear during the grinding of the gear, the microscopic hardness of the surface to be ground of the gear is controlled to be 56 to 60HRC; 2, the grinding cracks are resulted from the superimposition of structural stress and thermal stress, so that the distribution condition of surface stress is improved to balance or reduce residual stress. The method has the beneficial effects that a lot of experiments show that the grinding cracks in the ground surface of the gear are eliminated; the method can be popularized and applied to control over the grinding cracks of gears of aircraft engines of other types, and valuable technical experiences are accumulated for researches on aircraft engines of new types.
Description
Technical field
The present invention relates to a kind of control method of aero-engine carburized gears grinding crack.
Background technology
Aero-engine gear be used for transferring power and change the speed of service, therefore power transmission mechanism as decelerator in, various forms of gears are used in a large number.
In aero-engine gear through engineering approaches manufacture process, grinding crack is the key factor that affects product quality.Grinding crack is divided into two kinds, and one is to only occur on grinding face, and the degree of depth is more shallow, and the degree of depth is basically identical, direction is perpendicular to teeth directional, and without definite shape, another kind is that crackle is tortoise plastron shape (close network shape), and its degree of depth is roughly 0.03～0.15mm.The maximum feature of grinding crack is immediately to manifest, and has very large retardance, and the existence of grinding crack can reduce the fatigue behaviour of matrix material greatly.
Before improvement, the control of aero-engine carburized gears grinding crack is by reducing stock removal and reducing grinding speed and realize, but the generation that all cannot fundamentally stop grinding crack, and the removal of grinding crack is to rely on manual grinding and throwing to repair.The existence of grinding crack remains high product manufacturing cycle length, manufacturing cost, more seriously affects product quality and produces and pay.
Summary of the invention
The object of the invention is: a kind of method that aero-engine carburized gears grinding crack produces of controlling is provided, and overcoming prior art cannot effectively control grinding crack, affects product quality, makes the deficiency that the product manufacturing cycle is long, cost is high.
First, analyze the mechanism of production of aero-engine gear grinding crackle:
The generation of grinding crack causes by grinding heat, when grinding, the temperature of gear surface may be up to 820～
840 ℃ or higher.If its surface is quickly heated up to 100 ℃ of left and right rapid when cooling, must produce and shrink, this contraction occurs over just surface, and its matrix is still in swelling state, thereby makes superficial layer bear tension and produce the first crackle; In the time that temperature rises to 300 ℃, surface produces contraction again, thereby produces the second crackle.If cooling insufficient in the time of grinding, the heat producing due to grinding, is enough to make the reaustenitizing of grinding skin thin layer, again quenches and becomes quenched martensite subsequently.Thereby make superficial layer produce additional structural stress, and to add heat that grinding forms and the temperature of piece surface is raise be exceedingly fast, the superposition of this structural stress and thermal stress just causes grinding skin to occur grinding crack.
Combine in above-mentioned analysis, the new control method of definite aero-engine gear grinding crackle of the present invention, mainly comprises two aspects:
One, while considering gear grinding, too high surface temperature will inevitably make top layer metallographic structure change, and this will cause the variation of gear surface microhardness, and therefore the microhardness on control gear surface to be ground is between 56～60HRC.
Two, consider that grinding crack is the result that structural stress and thermal stress superposition produce, therefore improve the distribution situation of surface stress, make residual stress be able to balance or reduction.
Particularly, technical scheme of the present invention is: a kind of control method of aero-engine carburized gears grinding crack, specifically comprises the steps:
Step 1: gear is carried out to first and second Carburization Treatment, guarantee that gear surface microhardness to be ground is 56～60HRC; Specifically, while needing to guarantee gear to carry out first and second Carburization Treatment, setting carbon potential is 1.1%～1.3%, meets above-mentioned requirements thereby reach surface microhardness;
Step 2: the gear after Carburization Treatment is carried out to grinding;
Step 3: the gear after grinding is carried out to low temperature de-stress processing.
The invention has the beneficial effects as follows: by a large amount of experiments, prove to adopt the gear grinding surface after said method to have no grinding crack.This method can be applied to the control of other model aero-engine gear grinding crackle, for the research of new model aero-engine accumulates valuable technical experience.
The specific embodiment
Embodiment mono-:
The control method of the aero-engine carburized gears grinding crack in the present embodiment, specifically comprises the steps:
Step 1: gear is carried out to first and second Carburization Treatment, guarantee 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) ℃/± 5 ℃, (750～1150) ℃/± 10 ℃;
The process of in the present embodiment, gear being carried out to first and second Carburization Treatment comprises following sub-step:
Sub-step 1: setting vacuum cementation furnace carbon potential is 1.1%;
Sub-step 2: set carburizing temperature and temperature retention time and be respectively 905 ℃, 6.5H;
Sub-step 3: set secondary carburizing temperature and temperature retention time and be respectively 905 ℃, 4H;
After coming out of the stove, check the microhardness on gear surface to be ground, three times test value is respectively: 56,56,56, and mean value: 56;
Step 2: the gear after Carburization Treatment is carried out to grinding;
Step 3: the gear after grinding is carried out to low temperature de-stress processing, cooling medium is air, in the present embodiment, and testing equipment: low hot-well formula tempering furnace RJJ-36-6, device parameter: effective heating area is φ 450mm × 500mm, temperature uniformity is (100～350) ℃/± 5 ℃;
Setting low temperature destressing holding temperature is 150 ℃, and setting low temperature destressing temperature retention time is 1.5H; After coming out of the stove, after gear is cooled to room temperature, applies TS-5 type dehydrated oil on gear grinding surface and carry out antirust processing.
Embodiment bis-:
The control method of the aero-engine carburized gears grinding crack in the present embodiment, specifically comprises the steps:
Step 1: gear is carried out to first and second Carburization Treatment, guarantee that gear surface microhardness to be ground is 56～60HRC; The process of in the present embodiment, gear being carried out to first and second Carburization Treatment comprises following sub-step:
Sub-step 1: setting vacuum cementation furnace carbon potential is 1.3%;
Sub-step 2: set carburizing temperature and temperature retention time and be respectively 905 ℃, 6.5H;
Sub-step 3: set secondary carburizing temperature and temperature retention time and be respectively 905 ℃, 4H;
After coming out of the stove, check the microhardness on gear surface to be ground, three times test value is respectively: 57,61,62, and mean value: 60;
Step 2: the gear after Carburization Treatment is carried out to grinding;
Step 3: the gear after grinding is carried out to low temperature de-stress processing.
Adopt the gear grinding surface after method in embodiment mono-and embodiment bis-to have no grinding crack, verified thus the validity of this method.
Claims (2)
1. a control method for aero-engine carburized gears grinding crack, is characterized in that: comprise the steps:
Step 1: gear is carried out to first and second Carburization Treatment, guarantee that gear surface microhardness to be ground is 56～60HRC;
Step 2: the gear after Carburization Treatment is carried out to grinding;
Step 3: the gear after grinding is carried out to low temperature de-stress processing.
2. the control method of an aero-engine carburized gears grinding crack as claimed in claim 1, it is characterized in that: described step 1 middle gear surface microhardness to be ground requires when gear is carried out to first and second Carburization Treatment, set carbon potential and be 1.1%～1.3% and reach.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| CN103846631A true CN103846631A (en) | 2014-06-11 |
| CN103846631B CN103846631B (en) | 2016-08-03 |
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| CN201310406607.5A Active CN103846631B (en) | 2013-09-09 | 2013-09-09 | A kind of control method of aero-engine carburized gears grinding crack |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109202664A (en) * | 2018-09-20 | 2019-01-15 | 孙佑军 | A kind of grinding processing method for eliminating grinding crack |
Citations (4)
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| 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 |
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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 |
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| 余华俐等: "冷作模具的磨削裂纹分析与防护", 《机械研究与应用》 * |
| 李志义等: "渗碳淬火件磨削裂纹形成的原因和防止措施", 《国外金属热处理》 * |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109202664A (en) * | 2018-09-20 | 2019-01-15 | 孙佑军 | A kind of grinding processing method for eliminating grinding crack |
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| CN103846631B (en) | 2016-08-03 |
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| DD01 | Delivery of document by public notice |
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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| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
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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| CP01 | Change in the name or title of a patent holder |