CN111906504B - Finish machining method for aviation high-speed bearing retainer - Google Patents
Finish machining method for aviation high-speed bearing retainer Download PDFInfo
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- CN111906504B CN111906504B CN202010818760.9A CN202010818760A CN111906504B CN 111906504 B CN111906504 B CN 111906504B CN 202010818760 A CN202010818760 A CN 202010818760A CN 111906504 B CN111906504 B CN 111906504B
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Abstract
The invention discloses a finish machining method for an aviation high-speed bearing retainer, and relates to the field of finish machining methods for bearing retainers. The invention aims to solve the technical problem that the machining precision of the conventional aviation high-speed bearing retainer needs to be improved. The method comprises the following steps: rough turning and forming, tempering, fine turning and forming, uniformly grinding two planes, grinding the outer diameter, grinding the inner diameter, nitriding the surface, finally uniformly grinding the two planes, finally grinding the outer diameter, turning the inner step, grinding the inner step, marking, drilling and milling holes, deburring, polishing, cleaning, magnetic powder inspection, cleaning, dynamic balancing, final inspection, cleaning, silver plating, dynamic balancing, cleaning and packaging. The improved process not only improves the precision, hardness, wear resistance and fatigue resistance of the aviation high-speed bearing retainer, but also ensures that the dynamic balance procedure of the retainer is completely qualified, and all technical indexes are comprehensively improved. The method is used for preparing the aviation high-speed bearing retainer.
Description
Technical Field
The invention relates to the field of finish machining methods for bearing retainers.
Background
The main shaft bearing of the aircraft engine is one of key parts of the engine, works under the working conditions of high speed, high temperature and complex stress, and is required to have longer service life and higher reliability. In order to improve the strength of the retainer and reduce the weight, the main shaft bearing of the aero-engine mostly adopts a 40CrNiMoA steel retainer so as to adapt to the working environment with high temperature, high speed and large load, meet the same service life of the main shaft of the engine and improve the use reliability of the main shaft bearing of the aero-engine. The retainer is made of 40CrNiMoA alloy quenched and tempered steel material, the material has the characteristics of high strength, high toughness, good hardenability and good comprehensive mechanical property, and is commonly used for manufacturing important parts for bearing impact and cyclic load. The machining precision of the aviation high-speed bearing retainer is still required to be further improved.
Disclosure of Invention
The invention provides a fine machining method for an aviation high-speed bearing retainer, aiming at solving the technical problem that the machining precision of the existing aviation high-speed bearing retainer needs to be improved.
A finish machining method for an aviation high-speed bearing retainer specifically comprises the following steps:
firstly, roughly turning and molding a rough material billet to obtain a workpiece;
secondly, quenching and tempering the workpiece obtained in the first step;
thirdly, finely turning and molding the workpiece processed in the second step;
fourthly, carrying out uniform grinding two-plane treatment on the workpiece treated in the third step;
fifthly, carrying out outer diameter grinding treatment on the workpiece treated in the step four, and controlling the grinding amount of the reserved final grinding outer diameter to be 0.05-0.07 mm;
sixthly, performing inner diameter grinding treatment on the workpiece processed in the step five;
seventhly, performing surface nitriding treatment on the workpiece treated in the sixth step, and controlling the nitriding depth to be 0.18-0.3 mm;
eighthly, performing final uniform grinding two planes on the workpiece processed in the step seven;
ninth, carrying out final grinding outer diameter treatment on the workpiece treated in the eighth step, wherein the grinding amount is the grinding amount reserved in the fifth step, and the outer diameter hardness of the workpiece reaches 43 HRC-48 HRC;
tenthly, performing step processing in the lathe on the workpiece processed in the step nine;
eleven, performing inner step grinding treatment on the workpiece processed in the step ten;
twelfth, marking the workpiece processed in the eleventh step, drilling and milling a pocket hole, and performing deburring treatment;
thirteen, polishing the workpiece treated in the step twelve, and then cleaning;
fourteen, carrying out magnetic powder inspection on the workpiece treated in the thirteen steps, and then cleaning;
fifteen, carrying out a first dynamic balance process on the workpiece processed in the fourteenth step, and then carrying out final inspection and cleaning;
sixthly, silver plating is carried out on the workpiece processed in the step fifteen, then the second dynamic balancing procedure is carried out, cleaning and packaging are carried out, the aviation high-speed bearing retainer is obtained, and the finish machining method for the aviation high-speed bearing retainer is completed.
Wherein, uniformly grinding the two planes refers to uniformly grinding the upper end face and the lower end face.
Further, in the second step, the quenching and tempering process comprises the following steps: controlling the preheating temperature to be 585-595 ℃, the preheating time to be 45-51 min, the final heating temperature to be 830-840 ℃, and the preheating time to be 45-51 min; then carrying out tempering treatment: the temperature is controlled to be 605-610 ℃, the treatment time is 120-130 min, and the hardness of the treated workpiece reaches 29-34 HRC.
And further, the surface nitriding treatment process in the seventh step comprises the steps of cleaning the workpiece, heating to 440-460 ℃, preserving heat for 25-30 hours, and cooling along with the furnace.
The invention has the beneficial effects that:
1) the quenching and tempering treatment is carried out on the retainer before nitriding, and the purpose is to obtain a uniform and compact sorbite structure and enable the core part of the retainer to have enough strength.
2) The surface nitriding process is added after the 'inside diameter grinding' process, so that the surface of a workpiece can obtain high hardness and wear resistance without other heat treatment; the nitrided workpiece surface has high corrosion resistance; the workpiece after nitriding has small deformation and high precision; and the surface fatigue strength of the workpiece is improved by 15-35%. The outer diameter of the cage is a guide surface, so that the nitriding treatment of the outer diameter surface is increased, thereby improving the hardness and wear resistance of the guide surface of the cage. The process adopts a machining concept of full-surface nitriding by an increased allowance method, a certain machining allowance is reserved at a position which does not need nitriding, the allowance is more than one time larger than the depth of a nitriding layer, the surface which does not need nitriding is machined and removed after the nitriding process is finished, and meanwhile, the deformation of the outer diameter surface of the retainer after nitriding is also trimmed. It should be noted that the outer diameter of the retainer is a guide surface, and the grinding amount of the outer diameter of the finish grinding after nitriding is 0.05-0.07 mm.
3) Before the nitriding process, the surfaces of the plane, the inner diameter and the outer diameter are ground, so that the dispersion of the dimension of the plane, the inner diameter and the outer diameter of each batch of the retainer is controlled within 0.005mm, the dimension is unified, and the depth consistency and the uniformity of a nitriding layer are better. In addition, the processing precision of the wall thickness difference is improved, and a foundation is laid for the subsequent dynamic balance process without removing the unbalance.
4) The purpose of grinding the outer diameter and the inner step after the nitriding process is to improve the processing precision of the wall thickness difference and lay a foundation for the subsequent dynamic balancing process without removing the unbalance.
5) The theory of the axial position of the pocket hole is that the center of two planes of the retainer is used, but the actual processing and the theory have certain difference, in order to ensure that the axial position of the pocket hole is processed more accurately and is as close to the center of the two planes as possible, the process increases the procedure of 'grinding two planes evenly finally', the consistency of the plane size is improved, the processing dispersion is reduced, the tolerance of the plane size is controlled within 0.005mm, and the center of a workpiece is aligned for tool setting by using a photoelectric edge finder, the previous manual visual inspection tool setting or manual calculation tool setting is adopted, the deviation is larger and inaccurate, the tool setting is adjusted frequently and repeatedly, the adjusting time is longer, and 1 or 2 tool setting wastes are generated, the working principle of the photoelectric edge finder is that the conductivity of the workpiece is utilized, when a ball head contacts the surface of the workpiece, the current forms a loop, a sound and light alarm signals are sent out, the ball head is connected with the body by using a spring, the coordinate position of the surface to be measured can be obtained through the photoelectric edge finder indicator lamp and the machine tool coordinate position, the photoelectric edge finder indicator lamp and the machine tool coordinate position are clamped on a spindle of a CNC (computer numerical control) machining center by utilizing the characteristics, the photoelectric edge finder indicator lamp can be used for aligning, centering and measuring workpieces, the machine tool spindle does not rotate when the photoelectric edge finder aligns or measures the workpieces, the safety is high, the surfaces of the workpieces cannot be damaged, meanwhile, the accuracy of aligning and centering is high, and the axial position accuracy of the pocket is improved.
Tests prove that the bearing retainer processed by the process has the thickness difference of the inner diameter to the outer diameter of 0.001-0.002 mm, the unbalance of 60-100 mg, the axial position degree of the pocket holes of 0.04-0.08 mm and the thickness difference of the pocket holes to the reference surface of 0.02-0.04 mm, and the precision of the bearing retainer is remarkably improved.
In conclusion, the improved process not only improves the hardness, the wear resistance and the fatigue resistance of the aviation high-speed bearing retainer, but also ensures that the dynamic balance process of the retainer is completely qualified without removing the unbalance, so that the processing method comprehensively improves various technical indexes of the retainer and achieves the expected research effect.
The method is used for preparing the aviation high-speed bearing retainer.
Drawings
FIG. 1 is a front sectional view of an aviation high-speed bearing cage according to one embodiment;
FIG. 2 is a top sectional view of the aviation high-speed bearing retainer according to the first embodiment.
Detailed Description
The technical solution of the present invention is not limited to the specific embodiments listed below, and includes any combination of the specific embodiments.
The first embodiment is as follows: a finish machining method for an aviation high-speed bearing retainer specifically comprises the following steps:
firstly, roughly turning and molding a rough material billet to obtain a workpiece;
secondly, quenching and tempering the workpiece obtained in the first step;
thirdly, finely turning and molding the workpiece processed in the second step;
fourthly, carrying out uniform grinding two-plane treatment on the workpiece treated in the third step;
fifthly, carrying out outer diameter grinding treatment on the workpiece treated in the step four, and controlling the grinding amount of the reserved final grinding outer diameter to be 0.05-0.07 mm;
sixthly, performing inner diameter grinding treatment on the workpiece processed in the step five;
seventhly, performing surface nitriding treatment on the workpiece treated in the step six, and controlling the nitriding depth to be 0.18-0.3 mm;
eighthly, performing final uniform grinding two planes on the workpiece processed in the step seven;
ninth, carrying out final grinding outer diameter treatment on the workpiece treated in the eighth step, wherein the grinding amount is the grinding amount reserved in the fifth step, and the outer diameter hardness of the workpiece reaches 43 HRC-48 HRC;
tenthly, performing step processing in the lathe on the workpiece processed in the step nine;
eleven, performing inner step grinding treatment on the workpiece processed in the step ten;
twelfth, marking the workpiece processed in the eleventh step, drilling and milling a pocket hole, and performing deburring treatment;
thirteen, polishing the workpiece treated in the step twelve, and then cleaning;
fourteen, carrying out magnetic powder inspection on the workpiece treated in the thirteen steps, and then cleaning;
fifteen, carrying out a first dynamic balance process on the workpiece processed in the fourteenth step, and then carrying out final inspection and cleaning;
sixthly, silver plating is carried out on the workpiece processed in the step fifteen, then the second dynamic balancing procedure is carried out, cleaning and packaging are carried out, the aviation high-speed bearing retainer is obtained, and the finish machining method for the aviation high-speed bearing retainer is completed.
The second embodiment is as follows: the first difference between the present embodiment and the specific embodiment is: the material of the coarse material steel billet in the first step is 40CrNiMoA alloy quenched and tempered steel material. The rest is the same as the first embodiment.
The third concrete implementation mode: the present embodiment differs from the first or second embodiment in that: the quenching and tempering process in the second step comprises the following steps: controlling the preheating temperature to be 585-595 ℃, the preheating time to be 45-51 min, the final heating temperature to be 830-840 ℃, and the preheating time to be 45-51 min; then carrying out tempering treatment: the temperature is controlled to be 605-610 ℃, the treatment time is 120-130 min, and the hardness of the treated workpiece reaches 29-34 HRC. The other is the same as in the first or second embodiment.
The fourth concrete implementation mode: the difference between this embodiment mode and one of the first to third embodiment modes is: and the surface nitriding treatment process in the seventh step is to clean the workpiece, then heat the workpiece to 440-460 ℃, preserve heat for 25-30 hours and cool the workpiece along with the furnace. The others are the same as in one of the first to third embodiments.
The fifth concrete implementation mode: the difference between this embodiment and one of the first to fourth embodiments is: and step eight, finishing and grinding two planes in a final time to process and control the dimensional tolerance of the planes to be less than 0.005 mm. The other is the same as one of the first to fourth embodiments.
The sixth specific implementation mode: the difference between this embodiment and one of the first to fifth embodiments is: and in the step twelve, when the pocket drilling and milling is carried out, the control rotating speed is 2000-2500 r/min, and the feed amount f is 70-80 mm/min. The other is the same as one of the first to fifth embodiments.
The seventh embodiment: the difference between this embodiment and one of the first to sixth embodiments is: and a vertical vibration finishing machine is adopted in the finishing treatment in the step thirteen, the frequency of the finishing machine is controlled to be 15-20 Hz, the amplitude is 2-4 mm, the finishing time is 2-3 h, and the finishing material is a high-alumina ceramic material. The other is the same as one of the first to sixth embodiments.
The specific implementation mode eight: the present embodiment differs from one of the first to seventh embodiments in that: and a fourteenth magnetic powder inspection process comprises the steps of cleaning and demagnetizing the workpiece, measuring the diameter of the workpiece to determine current, pouring magnetic suspension on each surface of the workpiece, carrying out circumferential magnetization and longitudinal magnetization on the workpiece, and detecting the surface defects of the workpiece under a black light lamp. The other is the same as one of the first to seventh embodiments.
The specific implementation method nine: the present embodiment differs from the first to eighth embodiments in that: and sixthly, performing the silver plating process in an electroplating mode. The rest is the same as the first to eighth embodiments.
The silver plating process of the embodiment specifically operates as follows: incoming material inspection → stress relief → organic solvent degreasing → ultrasonic cleaning → shielding protection → mounting → electrolytic degreasing/chemical degreasing → hot water cleaning → mobile cold water washing → water film continuous inspection → strong acid etching → mobile cold water washing → weak acid etching → mobile cold water washing → hanger changing → deionized water rinsing → nickel deposition → mobile cold water washing → deionized water rinsing → pre-silver plating → mobile cold water washing → deionized water rinsing → electrolytic passivation → mobile cold water washing → deionized water rinsing → shielding → primary dehydration → secondary dehydration → drying → hanger unloading → hydrogen removal → handing → packaging.
The detailed implementation mode is ten: the present embodiment differs from one of the first to ninth embodiments in that: and sixthly, controlling the thickness of the silver coating of the workpiece to be 0.025-0.045 mm during silver coating. The other is the same as one of the first to ninth embodiments.
The following examples were employed to demonstrate the beneficial effects of the present invention:
the first embodiment is as follows:
the fine machining method for the aviation high-speed bearing retainer comprises the following steps:
firstly, roughly turning and molding a rough material billet to obtain a workpiece;
secondly, quenching and tempering the workpiece obtained in the first step;
thirdly, performing fine turning molding on the workpiece processed in the second step;
fourthly, carrying out uniform grinding two-plane treatment on the workpiece treated in the third step;
fifthly, carrying out outer diameter grinding treatment on the workpiece treated in the step four, and controlling the grinding quantity of the reserved final grinding outer diameter to be 0.06 mm;
sixthly, performing inner diameter grinding treatment on the workpiece processed in the step five;
seventhly, performing surface nitriding treatment on the workpiece treated in the step six, and controlling the nitriding depth to be 0.2 mm;
eighthly, performing final uniform grinding two planes on the workpiece processed in the step seven;
ninth, carrying out final grinding outer diameter treatment on the workpiece treated in the eighth step, wherein the grinding amount is the grinding amount reserved in the fifth step, and the outer diameter hardness of the workpiece reaches 45 HRC;
tenthly, performing step processing in the lathe on the workpiece processed in the step nine;
eleven, performing inner step grinding treatment on the workpiece processed in the step ten;
twelfth, marking the workpiece processed in the eleventh step, drilling and milling a pocket hole, and performing deburring treatment;
thirteen, polishing the workpiece treated in the step twelve, and then cleaning;
fourteen, carrying out magnetic powder inspection on the workpiece treated in the thirteen steps, and then cleaning;
fifteen, carrying out a first dynamic balance process on the workpiece processed in the fourteenth step, and then carrying out final inspection and cleaning;
sixthly, silver plating is carried out on the workpiece processed in the step fifteen, then the second dynamic balancing process is carried out, cleaning and packaging are carried out, the aviation high-speed bearing retainer is obtained, and the finish machining method for the aviation high-speed bearing retainer is completed.
The material of the coarse material steel billet in the first step is 40CrNiMoA alloy quenched and tempered steel material;
the quenching and tempering process in the second step comprises the following steps: controlling the preheating temperature to be 580 ℃, the preheating time to be 48min, the final heating temperature to be 835 ℃, and the preheating time to be 48 min; then carrying out tempering treatment: the temperature is controlled to be 610 ℃, the processing time is 125min, and the hardness of the processed workpiece reaches 30 HRC.
And seventhly, cleaning the workpiece, heating to 450 ℃, preserving heat for 28 hours, and cooling along with the furnace.
And step eight, finishing and grinding two planes in a final time to process and control the dimensional tolerance of the planes to be less than 0.005 mm.
And in the step twelve, the rotating speed is controlled to be 2300r/min when the pocket is drilled and milled, and the feed amount f is 75 mm/min.
And step thirteen, adopting a vertical vibration finishing machine for finishing treatment, controlling the frequency of the finishing machine to be 20Hz, the amplitude to be 3mm, and the finishing time to be 2.5h, wherein the finishing material is a high-alumina ceramic material.
And a fourteenth magnetic powder inspection process comprises the steps of cleaning and demagnetizing the workpiece, measuring the diameter of the workpiece to determine current, pouring magnetic suspension on each surface of the workpiece, carrying out circumferential magnetization and longitudinal magnetization on the workpiece, and detecting the surface defects of the workpiece under a black light lamp.
And sixthly, performing the silver plating process in an electroplating mode.
And sixthly, controlling the thickness of the silver coating of the workpiece to be 0.030mm during silver coating. After silver plating, the surface of the workpiece has no phenomena of bubbling, layering and the like, and the color is uniform and consistent. The surface silvering binding force is qualified at 100%.
The process test of the bearing retainer of the type of 3 batches processed in this example was carried out, and the test results were as follows:
S1-S2: pocket axial position degree, S-S1: thickness difference of pocket to reference plane, Kc: the difference in wall thickness of the inner diameter to the outer diameter.
According to the test results, the precision of the bearing retainer processed by the process is obviously improved.
Claims (7)
1. A finish machining method for an aviation high-speed bearing retainer is characterized by comprising the following steps:
firstly, roughly turning and molding a rough material billet to obtain a workpiece;
secondly, quenching and tempering the workpiece obtained in the first step;
thirdly, finely turning and molding the workpiece processed in the second step;
fourthly, uniformly grinding the workpieces processed in the third step to obtain two planes;
fifthly, carrying out outer diameter grinding treatment on the workpiece treated in the step four, and controlling the grinding amount of the reserved final grinding outer diameter to be 0.05-0.07 mm;
sixthly, performing inner diameter grinding treatment on the workpiece processed in the step five;
seventhly, performing surface nitriding treatment on the workpiece treated in the sixth step, and controlling the nitriding depth to be 0.18-0.3 mm;
eighthly, performing final uniform grinding two planes on the workpiece processed in the step seven;
ninth, carrying out final grinding outer diameter treatment on the workpiece treated in the eighth step, wherein the grinding amount is the grinding amount reserved in the fifth step, and the outer diameter hardness of the workpiece reaches 43 HRC-48 HRC;
tenthly, performing step processing in the lathe on the workpiece processed in the step nine;
eleven, performing inner step grinding treatment on the workpiece processed in the step ten;
twelfth, marking the workpiece processed in the eleventh step, drilling and milling a pocket hole, and performing deburring treatment;
thirteen, polishing the workpiece treated in the step twelve, and then cleaning;
fourteen, carrying out magnetic powder inspection on the workpiece treated in the thirteen steps, and then cleaning;
fifteen, carrying out a first dynamic balance process on the workpiece processed in the fourteenth step, and then carrying out final inspection and cleaning;
sixthly, silver plating is carried out on the workpiece treated in the step fifteen, then a second dynamic balance procedure is carried out, cleaning and packaging are carried out, the aviation high-speed bearing retainer is obtained, and the finish machining method for the aviation high-speed bearing retainer is completed;
the material of the coarse material steel billet in the first step is 40CrNiMoA alloy quenched and tempered steel material;
the surface nitriding treatment process in the seventh step is that the workpiece is cleaned firstly, then the temperature is raised to 440-460 ℃, the temperature is kept for 25-30 hours, and the workpiece is cooled along with the furnace;
and step eight, finishing and grinding two planes in a final time to process and control the dimensional tolerance of the planes to be less than 0.005 mm.
2. The finish machining method for the aviation high-speed bearing retainer according to claim 1, wherein the quenching and tempering process in the second step is that the quenching and tempering process is carried out firstly: controlling the preheating temperature to be 585-595 ℃, the preheating time to be 45-51 min, the final heating temperature to be 830-840 ℃, and the preheating time to be 45-51 min; then carrying out tempering treatment: the temperature is controlled to be 605-610 ℃, the treatment time is 120-130 min, and the hardness of the treated workpiece reaches 29-34 HRC.
3. The finish machining method for the aviation high-speed bearing retainer according to claim 1, wherein the rotating speed is controlled to be 2000-2500 r/min and the feed f is controlled to be 70-80 mm/min during pocket drilling and milling in the step twelve.
4. The finish machining method for the aviation high-speed bearing retainer according to claim 1, wherein in the thirteen steps, a vertical vibration finishing machine is adopted for finishing treatment, the frequency of the finishing machine is controlled to be 15-20 Hz, the amplitude is controlled to be 2-4 mm, the finishing time is controlled to be 2-3 h, and the finishing material is high-alumina ceramic material.
5. The finish machining method of the aviation high-speed bearing retainer according to claim 1, characterized in that the fourteen-step magnetic powder inspection process comprises the steps of cleaning and demagnetizing the workpiece, measuring the diameter of the workpiece to determine current, pouring magnetic suspension on each surface of the workpiece, magnetizing the workpiece circumferentially and longitudinally at the same time, and detecting surface defects of the workpiece under a black light.
6. The finish machining method for the aviation high-speed bearing retainer according to claim 1, wherein the sixteen-step silver plating process is performed in an electroplating mode.
7. The finish machining method for the aviation high-speed bearing retainer according to claim 1, wherein in the sixteen silver plating step, the thickness of the silver coating of the workpiece is controlled to be 0.025-0.045 mm.
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| CN202010818760.9A CN111906504B (en) | 2020-08-14 | 2020-08-14 | Finish machining method for aviation high-speed bearing retainer |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103276346B (en) * | 2013-05-06 | 2016-02-03 | 青岛泰德汽车轴承股份有限公司 | A kind for the treatment of process of metal bearing retainer |
| CN104439931A (en) * | 2014-10-30 | 2015-03-25 | 吴中区光福良盛机械厂 | Round pocket hole bearing retainer machining process |
| CN106239068A (en) * | 2016-08-31 | 2016-12-21 | 中航工业哈尔滨轴承有限公司 | A kind of processing technique of ball bearing solid cage |
| CN108436393A (en) * | 2018-03-20 | 2018-08-24 | 中国航发哈尔滨轴承有限公司 | A kind of cylinder roller bearing solid cage processing method and Set and Positioning tooling |
| CN109500549A (en) * | 2018-12-06 | 2019-03-22 | 中国航发哈尔滨轴承有限公司 | A kind of cylindrical roller bearing without inner ring steel alloy solid cage processing method |
| CN109732293B (en) * | 2019-03-27 | 2021-03-26 | 中国航发哈尔滨轴承有限公司 | Thin-wall separation type solid retainer processing method |
| CN110253231B (en) * | 2019-07-19 | 2021-05-25 | 中国航发哈尔滨轴承有限公司 | Machining method for removing burrs of solid retainer |
| CN110630632A (en) * | 2019-09-30 | 2019-12-31 | 上海赛姆轴承有限公司 | Nonmagnetic bearing, coreless fixture, and method for manufacturing nonmagnetic bearing |
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