CN102500996A - Assembling method for three-fulcrum bearing of aircraft engine - Google Patents
Assembling method for three-fulcrum bearing of aircraft engine Download PDFInfo
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- CN102500996A CN102500996A CN201110293886XA CN201110293886A CN102500996A CN 102500996 A CN102500996 A CN 102500996A CN 201110293886X A CN201110293886X A CN 201110293886XA CN 201110293886 A CN201110293886 A CN 201110293886A CN 102500996 A CN102500996 A CN 102500996A
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Abstract
The invention discloses an assembling method for a three-fulcrum bearing of an aircraft engine, belonging to the technical field of engine overhaul. The assembling method comprises the following steps that: a central bevel gear is placed in a heating oven for heating, and a bearing outer ring is assembled in the central bevel gear; a spring ring is mounted on the central bevel bear for fixing the bearing, and the bearing is mounted in a manner that a marking face of the bearing faces to the spring ring; the bearing is cooled to achieve the temperature of an ambient medium, the maximum diameter and the minimum diameter of a runway of the bearing outer ring mounted in the central bevel gear are measured, then diameters on four planes of the runway of the bearing outer ring are measured, and then an average value is obtained; a bearing retainer and a bearing rolling rod are mounted in an inner ring of the bearing outer ring, and the bearing retainer is mounted in an manner that a marking face of the bearing retainer faces to the spring ring; a bearing inner ring is mounted on a low-pressure turbine shaft, and numbers in sets face to the front end face of the low-pressure turbine shaft; the bearing inner ring is cooled, and the low-pressure turbine shaft is cooled to obtain the temperature of ambient environment; and the maximum diameter and the minimum diameter are determined by measuring the diameters on six planes of a runway of the bearing inner ring, and then the bearing assembling play is calculated.
Description
Technical field
The invention belongs to the engine overhaul technical field, particularly relate to a kind of assembly method of aero-engine three fulcrum rollers.
Background technology
Aero-engine three fulcrum rollers place the Low Pressure Turbine Rotor front end, are the important component parts of engine mounting system.Three fulcrum rollers are cylinder roller bearing, are made up of inner ring, outer ring, rolling element and retainer.Inner ring is assemblied on the axle of low whirlpool, rotates with low whirlpool axle, and rotate with high potential assembly on being assemblied in and encircling in the central cone gear outer ring.Therefore this bearing, is bearing comparatively complicated alternate load in the course of the work because the relation of rigging position causes inner ring and outer ring working speed inconsistent; Add that its lubricating oil lubricant effect is relatively poor, the probability that causes this fulcrum roller to break down is many greatly than other bearing.
The major failure pattern of three fulcrum rollers is the scratch wear-out failure that first heavy load abrasion and back underloading are skidded and superposeed and form.Mainly show as: wide about 5mm wearing and tearing are arranged on the whole circumference in the middle of the inner ring, and wherein about 127mm length has scuff mark; In addition, on polishing scratch, there is the initial stage that is about 20mm, wide about 1mm scope to peel off; Complete excellent working face wearing and tearing, the retainer eccentric wear, retainer internal diameter interposition is equipped with wear trace.
From the bearing working Analysis on Mechanism, the main cause of heavy load abrasion is that the practical set play is less than normal, and local pressure is bigger in the running to cause bearing, the wearing and tearing of aggravation bearing roller and raceway.Along with the aggravation of wearing and tearing, the working gap of bearing progressively increases, and the suffered load of bearing also just progressively reduces, and the underloading sipping fault has just very easily taken place, and has so just formed the stack fault that heavy load abrasion and underloading are skidded.
The wear-out failure of three fulcrum rollers can cause a large amount of bearings to be scrapped in the engine overhaul process, has increased the cost of engine overhaul greatly.In addition, because the frequent change new product has caused increasing extra engine test checking number of times, limited the repairing efficient of engine.
Summary of the invention
To the problem that prior art exists, the present invention provides a kind of assembly method that can reduce aero-engine three fulcrum rollers of bearing fault rate greatly.
To achieve these goals, the present invention adopts following technical scheme, and a kind of assembly method of aero-engine three fulcrum rollers comprises the steps:
Step 1: the central cone gear is put into pot arch heat;
Step 2: bearing outer ring is assembled in the central cone gear;
Step 3: turn is installed on the central cone gear bearing fixing, and bearing is installed towards turn with index face;
Step 4: after bearing is cooled to ambient temperature, measures the maximum gauge and the minimum diameter of the bearing outer ring runway in the central cone gear of packing into, and on 4 planes of bearing outer ring runway, record diameter, obtain the mean value of 4 diameters;
Step 5: pack retainer and bearing roller in the inner ring of bearing outer ring into, retainer is installed towards turn with index face;
Step 6: be installed to bearing inner race on the low-pressure turbine shaft, complete number is towards low-pressure turbine shaft front end face one side;
Step 7: the cooling bearing inner ring, and be cooled to ambient temperature to low-pressure turbine shaft;
Step 8: on 6 planes of bearing inner race runway, measure diameter, confirm maximum gauge and minimum diameter through the diameter that records on 6 planes;
Step 9: calculation bearing assembling play.
The detailed process of the calculation bearing assembling play described in the step 9 is following:
According to the maximum gauge and the minimum diameter of the bearing inner race runway of gained in the maximum gauge of the bearing outer ring runway of gained in the step 4 and minimum diameter and the step 8, confirm the assembling play of bearing by following formula:
Minimal fit play=outer ring minimum diameter-2 times bearing roller maximum gauge-inner ring maximum gauge,
Maximum assembling play=outer ring maximum gauge-2 times bearing roller maximum gauge-inner ring minimum diameter,
In the formula: outer ring maximum gauge and outer ring minimum diameter are the maximum gauge and the minimum diameter of bearing outer ring runway, and 2 times of bearing roller maximum gauges are the summation of the roller diameter of two diameter maximums in the complete bearing; Inner ring maximum gauge and inner ring minimum diameter are maximum outside diameter and the minimum outer diameter that bearing is pressed into low-pressure turbine shaft rear bearing inner track.
For guaranteeing the bearing assembling play described in the step 9, specifically adopt following steps:
Step 1: to central bevel gear endoporus Φ 130mm size place, promptly carry out reconditioning, guarantee that this size is beated and ovality satisfies specification requirement with the bearing outer ring cooperation place;
Step 2: the inside and outside circle of bearing is carried out chromium plating repair, guarantee itself and the requirement that cooperates of counterpart.
Beneficial effect of the present invention:
The assembly method of three fulcrum rollers of the present invention reduces the actual radial load that bears of bearing to reach, and then reduces the purpose of bearing fault through control bearing practical set play.Can reduce the bearing fault rate greatly, and operate simple and easyly, respond well, China's aviation development played the meaning of outbalance.After the test run, bearing is carried out coherence check, satisfy the installation specification requirement, can play the effect of effective control bearing fault rate.
Description of drawings
Fig. 1 is the structural representation of central cone gear assembly of the present invention;
Fig. 2 is the structural representation of low-pressure turbine shaft of the present invention;
Fig. 3 is the assembling sketch map of central cone gear assembly and low-pressure turbine shaft;
Fig. 4 is the local enlarged diagram of Fig. 3;
Fig. 5 is a reconditioning principle sketch map in the reconditioning central cone gear process;
Among the figure, 1-central cone gear assembly, 2-low-pressure turbine shaft, 3-bearing inner race, 4-retainer, 5-bearing roller, 6-bearing outer ring.
The specific embodiment
A kind of assembly method of aero-engine three fulcrum rollers comprises the steps:
Step 1: the central cone gear is put into pot arch, be warmed to 150 degree;
Step 2: with special tooling and forcing press bearing outer ring is assembled in the central cone gear, guarantee to cooperate require for-0.022mm～+ 0.014mm;
Step 3: with pliers turn is installed on the central cone gear bearing fixing, bearing is installed towards turn with index face;
Step 4: after bearing is cooled to ambient temperature; With digital universal length meter measurement pack into the maximum gauge and the minimum diameter of the bearing outer ring runway in the central cone gear; And on 4 planes of bearing outer ring runway, record diameter, obtain the mean value of 4 diameters;
Step 5: pack retainer and bearing roller in the inner ring of bearing outer ring into special fixture, retainer is installed towards turn with index face;
Step 6: be installed to bearing inner race on the low-pressure turbine shaft, complete number is towards low-pressure turbine shaft front end face one side, guarantee to cooperate for+0.020mm～+ 0.039mm, when bearing inner race is installed, do not allow to use impulsive force;
Step 7: the cooling bearing inner ring, and be cooled to ambient temperature to low-pressure turbine shaft, with infrared thermography appearance inspection temperature;
Step 8: on 6 planes of bearing inner race runway, measure diameter with standard component and passameter (100～125), confirm maximum gauge and minimum diameter through the diameter that records on 6 planes, ovality should be not more than 0.01mm;
Step 9: calculation bearing assembling play, require to be 0.003mm～0.015mm, working control is 0.005mm～0.012mm.
The detailed process of the calculation bearing assembling play described in the step 9 is following:
According to the maximum gauge and the minimum diameter of the bearing inner race runway of gained in the maximum gauge of the bearing outer ring runway of gained in the step 4 and minimum diameter and the step 8, confirm the assembling play of bearing by following formula:
Minimal fit play=outer ring minimum diameter-2 times bearing roller maximum gauge-inner ring maximum gauge,
Maximum assembling play=outer ring maximum gauge-2 times bearing roller maximum gauge-inner ring minimum diameter,
In the formula: outer ring maximum gauge and outer ring minimum diameter are the maximum gauge and the minimum diameter of bearing outer ring runway, and 2 times of bearing roller maximum gauges are the summation of the roller diameter of two diameter maximums in the complete bearing; Inner ring maximum gauge and inner ring minimum diameter are maximum outside diameter and the minimum outer diameter that bearing is pressed into low-pressure turbine shaft rear bearing inner track.
For guaranteeing the bearing assembling play described in the step 9, specifically adopt following steps:
Step 1: to central bevel gear endoporus Φ 130mm size place, promptly carry out reconditioning, guarantee that this size is beated and ovality satisfies specification requirement with the bearing outer ring cooperation place;
The ovality at central cone bore Φ 130mm size place requires to be not more than 0.006mm, joins play for Control Shaft takes up, and controls it as and is not more than 0.004mm.Its concrete thinning technique is following:
This central cone gear of reconditioning need select for use precision grinder to grind processing, and the reconditioning principle need guarantee that this face is not more than 0.02mm with respect to beating of B face, and the face of cylinder of reconditioning is not more than 0.02mm with respect to the perpendicularity of A end face, and is as shown in Figure 4.
The central cone gear is contained on the grinding machine MGD2120B with anchor clamps 3B501-31-793, and centering C surface jitter is not more than 0.005mm, and the B surface jitter is not more than 0.01mm; Centering central cone gear D surface jitter is not more than 0.01mm, and the B surface jitter is not more than 0.01mm, and the C surface jitter is not more than 0.015mm.On precision grinder,, guarantee that ovality is not more than 0.004mm with minimum dimension reconditioning central cone bore Φ 130mm size.
Step 2: the inside and outside circle of bearing is carried out chromium plating repair, guarantee itself and the requirement that cooperates of counterpart,
The inside and outside circle size of bearing is measured; By cooperating requirement; The inside and outside circle of bearing is carried out chromium plating repairs, guarantee bearing inner race and low-pressure turbine shaft be engaged in+0.020mm～+ 0.039mm between, bearing outer ring and central cone gear matched-0.022mm～+ 0.014mm; Through the adjustment to above-mentioned fit dimension, the practical set play that comes to guarantee indirectly bearing is in the scope of regulation.
Through to central bevel gear reconditioning with to the inside and outside circle chromium plating repairing of bearing, guarantee that the assembling play is between 0.005mm～0.012mm.Through the test of many times checking, bearing clearance is controlled at this scope, both can effectively avoid heavy load abrasion, can reduce the generation of underloading sipping fault again.
Claims (3)
1. the assembly method of aero-engine three fulcrum rollers is characterized in that, comprises the steps:
Step 1: the central cone gear is put into pot arch heat;
Step 2: bearing outer ring is assembled in the central cone gear;
Step 3: turn is installed on the central cone gear bearing fixing, and bearing is installed towards turn with index face;
Step 4: after bearing is cooled to ambient temperature, measures the maximum gauge and the minimum diameter of the bearing outer ring runway in the central cone gear of packing into, and on 4 planes of bearing outer ring runway, record diameter, obtain the mean value of 4 diameters;
Step 5: pack retainer and bearing roller in the inner ring of bearing outer ring into, retainer is installed towards turn with index face;
Step 6: be installed to bearing inner race on the low-pressure turbine shaft, complete number is towards low-pressure turbine shaft front end face one side;
Step 7: the cooling bearing inner ring, and be cooled to ambient temperature to low-pressure turbine shaft;
Step 8: on 6 planes of bearing inner race runway, measure diameter, confirm maximum gauge and minimum diameter through the diameter that records on 6 planes;
Step 9: calculation bearing assembling play.
2. the assembly method of a kind of aero-engine three fulcrum rollers according to claim 1 is characterized in that the detailed process of the calculation bearing assembling play described in the step 9 is following:
According to the maximum gauge and the minimum diameter of the bearing inner race runway of gained in the maximum gauge of the bearing outer ring runway of gained in the step 4 and minimum diameter and the step 8, confirm the assembling play of bearing by following formula:
Minimal fit play=outer ring minimum diameter-2 times bearing roller maximum gauge-inner ring maximum gauge,
Maximum assembling play=outer ring maximum gauge-2 times bearing roller maximum gauge-inner ring minimum diameter,
In the formula: outer ring maximum gauge and outer ring minimum diameter are the maximum gauge and the minimum diameter of bearing outer ring runway, and 2 times of bearing roller maximum gauges are the summation of the roller diameter of two diameter maximums in the complete bearing; Inner ring maximum gauge and inner ring minimum diameter are maximum outside diameter and the minimum outer diameter that bearing is pressed into low-pressure turbine shaft rear bearing inner track.
3. the assembly method of a kind of aero-engine three fulcrum rollers according to claim 1 is characterized in that specifically adopting following steps for guaranteeing the bearing assembling play described in the step 9:
Step 1: to central bevel gear endoporus Ф 130mm size place, promptly carry out reconditioning, guarantee that this size is beated and ovality satisfies specification requirement with the bearing outer ring cooperation place;
Step 2: the inside and outside circle of bearing is carried out chromium plating repair, guarantee itself and the requirement that cooperates of counterpart.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201110293886XA CN102500996A (en) | 2011-09-30 | 2011-09-30 | Assembling method for three-fulcrum bearing of aircraft engine |
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| CN201110293886XA CN102500996A (en) | 2011-09-30 | 2011-09-30 | Assembling method for three-fulcrum bearing of aircraft engine |
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| CN102500996A true CN102500996A (en) | 2012-06-20 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103056653A (en) * | 2013-01-11 | 2013-04-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Bracket type core machine assembly method |
| CN104476102A (en) * | 2014-11-07 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Wear preventing method for front supporting point bearing of low-pressure turbine shaft of aero-engine |
| CN106363408A (en) * | 2016-11-25 | 2017-02-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Assembling process method for aircraft engine bearing |
| CN113530678A (en) * | 2021-06-14 | 2021-10-22 | 中国航发沈阳发动机研究所 | Method for determining and controlling intermediate bearing deflection angle of double-rotor aero-engine |
| CN114688100A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Assembly method of gas compressor of gas turbine engine |
| CN115935535A (en) * | 2022-11-10 | 2023-04-07 | 中国航发沈阳发动机研究所 | Method for calculating static load of low-pressure rotor pivot of large-bypass-ratio aircraft engine |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103056653A (en) * | 2013-01-11 | 2013-04-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Bracket type core machine assembly method |
| CN103056653B (en) * | 2013-01-11 | 2015-12-02 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of bracket type core machine assembly method |
| CN104476102A (en) * | 2014-11-07 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Wear preventing method for front supporting point bearing of low-pressure turbine shaft of aero-engine |
| CN104476102B (en) * | 2014-11-07 | 2016-08-17 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of method preventing aero-engine low-pressure turbine shaft front fulcrum bearing wear |
| CN106363408A (en) * | 2016-11-25 | 2017-02-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Assembling process method for aircraft engine bearing |
| CN106363408B (en) * | 2016-11-25 | 2019-12-13 | 中国航发沈阳黎明航空发动机有限责任公司 | assembly process method of aeroengine bearing |
| CN113530678A (en) * | 2021-06-14 | 2021-10-22 | 中国航发沈阳发动机研究所 | Method for determining and controlling intermediate bearing deflection angle of double-rotor aero-engine |
| CN114688100A (en) * | 2022-05-31 | 2022-07-01 | 成都中科翼能科技有限公司 | Assembly method of gas compressor of gas turbine engine |
| CN115935535A (en) * | 2022-11-10 | 2023-04-07 | 中国航发沈阳发动机研究所 | Method for calculating static load of low-pressure rotor pivot of large-bypass-ratio aircraft engine |
| CN115935535B (en) * | 2022-11-10 | 2023-11-28 | 中国航发沈阳发动机研究所 | Large bypass ratio aero-engine low-pressure rotor fulcrum static load calculation method |
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Application publication date: 20120620 |