CN106625398A - Assembling method and device of aero-engine rotor - Google Patents
Assembling method and device of aero-engine rotor Download PDFInfo
- Publication number
- CN106625398A CN106625398A CN201710000470.1A CN201710000470A CN106625398A CN 106625398 A CN106625398 A CN 106625398A CN 201710000470 A CN201710000470 A CN 201710000470A CN 106625398 A CN106625398 A CN 106625398A
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- rotor
- platform
- assembling
- regulation
- aeroengine
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/02—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same
- B25B27/026—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same fluid driven
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Testing Of Balance (AREA)
Abstract
The invention relates to an assembling method and device of an aero-engine rotor. The device comprises a circular run-out measuring instrument (1), a transmission rod (3), a pressing plate (5), a support plate (8), a support cylinder (9), a compressing cylinder (11), a center and tilting regulating table (12) and a precise rotary table (13), wherein the pressing plate (5) is fixed on an upper plate (4) connected with the transmission rod (3), the transmission rod (3) penetrates the center of a support column (7), and the support cylinder (9) is connected with the support plate (8). By the assembling method and device of the aero-engine rotor, the aero-engine rotor can be assembled, assembling precision can be increased, assembling times are reduced, work efficiency is increased, and assembling quality is guaranteed.
Description
Technical field
The present invention relates to a kind of aeroengine rotor assembly method and device, belong to mechanical assembly field.
Background technology
The assembling process of aero-engine accounts for more than half of full machine production work, and assembling quality works aero-engine
Stability influence it is very big.Aeroengine rotor is under high temperature and high pressure environment and works, and rotates along with high speed, if assembling
During cause that concentricity is overproof, bolt pretightening is uneven, rotor rotation imbalance phenomenon can be caused, produce vibration and make an uproar
Sound, or even cause electromotor to shut down phenomenon.
It is connected by the seam of interference fit between aero-engine rotor at different levels, at present first to heat parts during assembling
Or refrigeration is processed, then carry out hand assembled.Part can be made during matching somebody with somebody due to hot charging to produce deformation, after bolt fastening, rotor is same
Axle degree is difficult to reach permissible value, needs being dismounted for multiple times just can meet the requirements.And due to adding the flatness error on man-hour surface, cause
Composition surface contact area makes rotor rigidity poor less than 20%, and bolt pretightening reduces serious, the dress of same assembly method with the time
It is unstable with quality.So the assembly method efficiency of current aerospace engine rotor is low, quality is unstable, affects electromotor work
Performance, needs a kind of efficient, stable measurement assembling integrated apparatus and assembly method.
When aeroengine rotor is assembled, need the faying face in two rotors to smear chilli oil, enter again after once assembling
Row dismounting, to detect the fitting area between two rotors.When being detected in this way, high labor intensive, efficiency is low, dress
It is unstable with quality.
Shanghai Communications University proposes a kind of aero-engine drum formula rotor assembling apparatus and assembly method（Aero-engine
Drum formula rotor assembling apparatus and assembly method.Publication number：CN 105443169 A）.Measurement apparatus are located at air-float turntable both sides,
The topographical information of Assembly part can be gathered.The method has problems in that：Still need to hand assembled, an assembly yield
It is low.
Shenyang dawn aero-engine（Group）Co., Ltd propose a kind of bicyclic compression fit equipment of rotor and
Method（A kind of bicyclic compression fit device and method of rotor.Publication number：CN 104440761 A）.The method is by using two
The operation and adjustment of equipment is suppressed in outside, and two independent hydraulic systems are operated in control hold down gag, and pressure is slow
And be delivered evenly in two load-carrying surfaces of rotor inner and outer rings, finally realize the elastic conjunction of disc, it is ensured that assembling quality.Should
Method has problems：Seal face size is fixed, and hydraulic coupling can be delivered at base fluid cylinder pressure.
The content of the invention
It is an object of the invention to provide a kind of aeroengine rotor assembly method and device, to solve aero-engine
The problems such as axiality is low, composition surface contact area is little after rotor assembling, to reduce working strength, improves rotor assembling quality
Purpose.
A kind of aeroengine rotor assembling device is the technical scheme is that, is constituted as follows：Circle jump measuring instrument 1,
Lead column 2, drive link 3, upper plate 4, pressing plate 5, aeroengine rotor 6, support column 7, gripper shoe 8, shoring 9, fixture 10, pressure
Tight cylinder 11, regulation of mental activities adjusts incline platform 12, precision rotating platform 13, granite base 14, fiber grating string 15；The concentricity measuring instrument 1
It is connected in lead column 2, the regulation of mental activities adjusts the platform 12 that inclines to be connected on precision rotating platform 13, fixture 10 is adjusted in regulation of mental activities and inclined on platform 12
Side, the drive link 3 is connected to upper plate 4 in the center of support column 7, lower end connection hold-down cylinder 11, upper end connection upper plate 4, pressing plate 5
On, the shoring 9 is connected with gripper shoe 8, and the lower end seam of rotor 6 is connected with gripper shoe 8, and the fiber grating string 15 is pasted onto
Part circumference to be assembled.
A kind of aeroengine rotor assembly method, it is characterised in that：The first order of aeroengine rotor 6 is turned
Son is fixed on regulation of mental activities and is adjusted and inclined on platform 12 by fixture 10, by circle jump measuring instrument 1 and first order rotor contact, precision rotating platform 13
Slowly run, measurement axial direction, circular runout, according to circle pulsation measurement result, adjust position and inclination angle that regulation of mental activities adjusts the platform 12 that inclines, make
The axial datum level and radial reference face of the axial datum level of aeroengine rotor 6 and radial reference face with precision rotating platform 13
Overlap；Again by the second level rotor heat treated of aeroengine rotor 6, by the angle of assembling that vector stacking method measurement is obtained
It is placed on the first order rotor of aeroengine rotor 6, the pressurization of shoring 9 makes the rotor driven 6 of gripper shoe 8 move upwards, more
Changing pressing plate 5 makes the lower end of pressing plate 5 be less than 5cm with the distance of the upper surface of rotor 6, and hold-down cylinder 11 connects upper plate 4 and transports downwards with dynamic pressure plate 5
It is dynamic, the second level rotor and first order rotor of rotor 6 are compressed, the impaction state of more than 1 minute is kept, by fiber grating string 15
Measurement deformation, determines whether thrust is uniform, under impaction state, tightens connecting bolt；After tightening, stop to the He of shoring 9
The input air pressure of hold-down cylinder 11, adjusts the platform 12 that inclines to contact rotor 6 and regulation of mental activities, is rotated by the rotor driven 6 of precision rotating platform 13,
Using the circle measurement assembling quality of jump measuring instrument 1, after passed examination, this process of repetition completes the assembling of rotor.
A kind of aeroengine rotor assembling device has two independent pneumatic control systems, and hold-down cylinder 11 is provided
Thrust axially downwardly, shoring 9 provides holding power upwards, and according to rotor structure forms at different levels and material properties dress is calculated
With thrust required during every grade of rotor, shoring 9 can make aeroengine rotor 6 adjust the platform 12 that inclines to separate with regulation of mental activities, constitute
Passive constraint, prevents thrust from adjusting the platform 12 that inclines to produce impact to regulation of mental activities, finally realizes the elastic conjunction of rotor, improves assembling quality.
The upper plate 4 is attached with drive link 3 by nut, before being assembled, upper plate 4 of dismantling, then aviation is sent out
Motivation rotor 6 is slowly hung in assembly equipment.
A kind of aeroengine rotor assembling device center platen 5 can be changed, according to assembling not at the same level turning
Son, selects different length, the pressing plate of diameter specifications, to meet the range demands of hold-down cylinder 11.
The present invention has following novelty and advantage：
1. the present invention is compressed using air pressure or hydraulic pressure.Because part composition surface has flatness error, add and compress link,
Axial compression is carried out to rotor can increase composition surface contact area, and the increase of fitting area can improve the reliability of rotor motion
Property, rotor rigidity is improved, mitigate the impact of bolt creep, it is ensured that the uniformity of bolt pretightening；
2. thrust of the present invention using shoring offer upwards, the downward thrust of hold-down cylinder offer, thrust is converted into
Internal force between rotor, prevents thrust to be delivered to regulation of mental activities and adjusts the platform that inclines, in order to avoid adjust platform performance of inclining to produce impact to regulation of mental activities；
3. the present invention measures rotor surface microstrain using fiber grating string, Applied Computer Techniques fitting rotor engagement face
Fitting area, certainty of measurement is high, and without the need for repeating dismounting fitting area is can determine that, reusable, to build-up member performance without
Affect；
4. assembly equipment and measuring apparatus are arranged in same station by the present invention, and side assembling becomes measurement, an assembly yield
Height, saves space, reduces because workpiece moves consumed man-hour, improves work efficiency.
Description of the drawings
Fig. 1 is aeroengine rotor hold down gag schematic diagram.
Fig. 2 is fiber grating measurement arrangement schematic diagram.
Specific embodiment
The present invention is conducted further description with reference to the accompanying drawings, a kind of aeroengine rotor assembles device,
Constitute as follows：Circle jump measuring instrument 1, lead column 2, drive link 3, upper plate 4, pressing plate 5, aeroengine rotor 6, support column 7,
Fagging 8, shoring 9, fixture 10, hold-down cylinder 11, regulation of mental activities adjust incline platform 12, precision rotating platform 13, granite base 14；It is described concentric
Degree measuring instrument 1 is connected in lead column 2, and the regulation of mental activities adjusts the platform 12 that inclines to be connected on precision rotating platform 13, and fixture 10 is adjusted in regulation of mental activities
Incline above platform 12, the drive link 3 connects in the center of support column 7, lower end connection hold-down cylinder 11, upper end connection upper plate 4, pressing plate 5
On upper plate 4, the shoring 9 is connected with gripper shoe 8, and the lower end seam of rotor 6 is connected with gripper shoe 8.
A kind of aeroengine rotor assembly method, it is characterised in that：The first order of aeroengine rotor 6 is turned
Son is fixed on regulation of mental activities and is adjusted and inclined on platform 12 by fixture 10, by circle jump measuring instrument 1 and first order rotor contact, precision rotating platform 13
Slowly run, measurement axial direction, circular runout, according to circle pulsation measurement result, adjust position and inclination angle that regulation of mental activities adjusts the platform 12 that inclines, make
The axial datum level and radial reference face of the axial datum level of aeroengine rotor 6 and radial reference face with precision rotating platform 13
Overlap；Again by the second level rotor heat treated of aeroengine rotor 6, by the angle of assembling that vector stacking method measurement is obtained
It is placed on the first order rotor of aeroengine rotor 6, the pressurization of shoring 9 makes the rotor driven 6 of gripper shoe 8 move upwards, more
Changing pressing plate 5 makes the lower end of pressing plate 5 be less than 5cm with the distance of the upper surface of rotor 6, and hold-down cylinder 11 connects upper plate 4 and transports downwards with dynamic pressure plate 5
It is dynamic, the second level rotor and first order rotor of rotor 6 are compressed, the impaction state of more than 1 minute is kept, by fiber grating string 15
Measurement deformation, determines whether thrust is uniform, under impaction state, tightens connecting bolt；After tightening, stop to the He of shoring 9
The input air pressure of hold-down cylinder 11, adjusts the platform 12 that inclines to contact rotor 6 and regulation of mental activities, is rotated by the rotor driven 6 of precision rotating platform 13,
Using the circle measurement assembling quality of jump measuring instrument 1, after passed examination, this process of repetition completes the assembling of rotor.
Claims (2)
1. a kind of aeroengine rotor assembly method and device, it is characterised in that：The aeroengine rotor measurement assembling
Integrated apparatus constitute as follows：Circle jump measuring instrument（1）, lead column（2）, drive link（3）, upper plate（4）, pressing plate（5）, aviation send out
Motivation rotor（6）, support column（7）, gripper shoe（8）, shoring（9）, fixture（10）, hold-down cylinder（11）, regulation of mental activities adjusts and inclines platform（12）、
Precision rotating platform（13）, granite base（14）, fiber grating string（15）；The lead column（2）In granite base（14）It is left
Right two ends respectively have one, circle jump measuring instrument（1）In each lead column（2）On have two, respectively measure axial circular bounce and footpath
To circle bounce；The regulation of mental activities adjusts the platform that inclines（12）It is connected to precision rotating platform（13）On, fixture（10）The platform that inclines is adjusted in regulation of mental activities（12）On
Side, the drive link（3）In support column（7）Center, lower end connection hold-down cylinder（11）, upper end connection upper plate（4）, pressing plate（5）Even
It is connected on upper plate（4）On, the shoring（9）With gripper shoe（8）Connection, rotor（6）Lower end seam and gripper shoe（8）Connection；Institute
State fiber grating string（15）It is pasted onto part circumference to be assembled.
2. a kind of aeroengine rotor assembly method and device, it is characterised in that：By aeroengine rotor（6）The first order
Rotor passes through fixture（10）It is fixed on regulation of mental activities and adjusts the platform that inclines（12）On, by circle jump measuring instrument（1）With first order rotor contact, precision
Rotary table（13）Slowly run, measurement axial direction, circular runout, according to circle pulsation measurement result, adjustment regulation of mental activities adjusts the platform that inclines（12）'s
Position and inclination angle, make aeroengine rotor（6）Axial datum level and radial reference face and precision rotating platform（13）Axial direction
Datum level and radial reference face overlap；Again by aeroengine rotor（6）Second level rotor heat treated, by vector stacking side
The angle of assembling that method measurement is obtained is placed on aeroengine rotor（6）First order rotor on, shoring（9）Pressurization makes support
Plate（8）Rotor driven（6）Move upwards, change pressing plate（5）Make pressing plate（5）Lower end and rotor（6）The distance of upper surface is less than
5cm, hold-down cylinder（11）Connection upper plate（4）Band dynamic pressure plate（5）Move downward, compress rotor（6）Second level rotor and the first order
Rotor, keeps the impaction state of more than 1 minute, by fiber grating string（15）Measurement deformation, determines whether thrust is uniform；
Under impaction state, connecting bolt is tightened；After tightening, stop to shoring（9）And hold-down cylinder（11）Input air pressure, by rotor（6）
The platform that inclines is adjusted with regulation of mental activities（12）Contact, by precision rotating platform（13）Rotor driven（6）Rotated, using circle jump measuring instrument
（1）Measurement assembling quality, after passed examination, this process of repetition completes the assembling of rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710000470.1A CN106625398B (en) | 2017-01-03 | 2017-01-03 | A kind of aeroengine rotor assembly method and device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710000470.1A CN106625398B (en) | 2017-01-03 | 2017-01-03 | A kind of aeroengine rotor assembly method and device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106625398A true CN106625398A (en) | 2017-05-10 |
| CN106625398B CN106625398B (en) | 2019-05-14 |
Family
ID=58838640
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710000470.1A Active CN106625398B (en) | 2017-01-03 | 2017-01-03 | A kind of aeroengine rotor assembly method and device |
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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107363779A (en) * | 2017-09-04 | 2017-11-21 | 中国航发南方工业有限公司 | The attaching/detaching apparatus of aero-engine high pressure joint rotor |
| CN107883902A (en) * | 2017-10-25 | 2018-04-06 | 中国航发动力股份有限公司 | A kind of turbine rotor assembles jitter detection apparatus |
| CN107900675A (en) * | 2017-11-01 | 2018-04-13 | 中国航发南方工业有限公司 | A kind of aeroengine rotor assembly method |
| CN108036720A (en) * | 2017-11-09 | 2018-05-15 | 中国科学院上海光学精密机械研究所 | Precise rotating platform axial direction and radial pulsation measurement device and measuring method |
| CN108318182A (en) * | 2017-12-27 | 2018-07-24 | 中国航发四川燃气涡轮研究院 | Multistage Low Pressure Turbine Rotor subassembly is without tooling balance method |
| CN109099834A (en) * | 2017-06-20 | 2018-12-28 | 中国航发上海商用航空发动机制造有限责任公司 | A kind of device of bolt hole alignment detection |
| CN109297446A (en) * | 2018-12-18 | 2019-02-01 | 中国航发沈阳发动机研究所 | A kind of aero-engine multistage Low Pressure Turbine Rotor alignment measurement device and method |
| CN109579770A (en) * | 2019-01-25 | 2019-04-05 | 中国科学院工程热物理研究所 | A kind of pneumatic table and the method for assembling turbine rotor |
| CN109871947A (en) * | 2019-03-21 | 2019-06-11 | 哈尔滨工业大学 | Multistage components initial unbalance, stacking method and device step by step are equipped in large high-speed revolution based on convolutional neural networks |
| CN110530306A (en) * | 2019-08-27 | 2019-12-03 | 大连理工大学 | A kind of typical revolving parts characterizing method based on actual measurement bounce data |
| CN110595690A (en) * | 2019-01-07 | 2019-12-20 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment measurement and intelligent learning assembly method and device based on centroid, gravity center and inertia center vector minimization |
| CN112254967A (en) * | 2020-08-03 | 2021-01-22 | 清华大学 | Aircraft engine rotor assembly simulation test system |
| CN112247522A (en) * | 2020-05-29 | 2021-01-22 | 中国航发沈阳发动机研究所 | Rotor press-fitting equipment |
| CN112254966A (en) * | 2020-08-03 | 2021-01-22 | 清华大学 | Assembly quantity measuring method for aircraft engine rotor simulation assembly process |
| CN112824844A (en) * | 2019-11-20 | 2021-05-21 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment assembly clamping force measuring device based on laser ultrasound |
| CN113124792A (en) * | 2019-12-31 | 2021-07-16 | 哈尔滨工业大学 | Method for measuring bonding area of large-scale high-speed rotating equipment based on non-contact ultrasound |
| CN113510475A (en) * | 2021-04-23 | 2021-10-19 | 哈尔滨工业大学 | Non-continuous rotor hot jacket assembly device |
| CN114161185A (en) * | 2021-12-17 | 2022-03-11 | 上海杭和智能科技有限公司 | Clamping and calibrating platform for revolving body casting |
| CN114535982A (en) * | 2022-04-02 | 2022-05-27 | 中国航发沈阳发动机研究所 | Aeroengine doublestage high whirlpool stator unit body assembly fixture |
| CN116519314A (en) * | 2023-06-25 | 2023-08-01 | 西北工业大学 | Engine rotor over-rotation test tool and assembly method |
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| CN107363779A (en) * | 2017-09-04 | 2017-11-21 | 中国航发南方工业有限公司 | The attaching/detaching apparatus of aero-engine high pressure joint rotor |
| CN107883902B (en) * | 2017-10-25 | 2019-10-18 | 中国航发动力股份有限公司 | A kind of turbine rotor assembly jitter detection apparatus |
| CN107883902A (en) * | 2017-10-25 | 2018-04-06 | 中国航发动力股份有限公司 | A kind of turbine rotor assembles jitter detection apparatus |
| CN107900675A (en) * | 2017-11-01 | 2018-04-13 | 中国航发南方工业有限公司 | A kind of aeroengine rotor assembly method |
| CN108036720B (en) * | 2017-11-09 | 2019-10-18 | 中国科学院上海光学精密机械研究所 | Precise rotating platform axial direction and radial pulsation measurement device and measurement method |
| CN108036720A (en) * | 2017-11-09 | 2018-05-15 | 中国科学院上海光学精密机械研究所 | Precise rotating platform axial direction and radial pulsation measurement device and measuring method |
| CN108318182A (en) * | 2017-12-27 | 2018-07-24 | 中国航发四川燃气涡轮研究院 | Multistage Low Pressure Turbine Rotor subassembly is without tooling balance method |
| CN109297446A (en) * | 2018-12-18 | 2019-02-01 | 中国航发沈阳发动机研究所 | A kind of aero-engine multistage Low Pressure Turbine Rotor alignment measurement device and method |
| CN110595690A (en) * | 2019-01-07 | 2019-12-20 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment measurement and intelligent learning assembly method and device based on centroid, gravity center and inertia center vector minimization |
| CN109579770B (en) * | 2019-01-25 | 2024-05-10 | 中国科学院工程热物理研究所 | Pneumatic platform and method for assembling turbine rotor |
| CN109579770A (en) * | 2019-01-25 | 2019-04-05 | 中国科学院工程热物理研究所 | A kind of pneumatic table and the method for assembling turbine rotor |
| CN109871947B (en) * | 2019-03-21 | 2021-10-29 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment multi-stage part initial unbalance amount step-by-step stacking method based on convolutional neural network |
| CN109871947A (en) * | 2019-03-21 | 2019-06-11 | 哈尔滨工业大学 | Multistage components initial unbalance, stacking method and device step by step are equipped in large high-speed revolution based on convolutional neural networks |
| CN110530306A (en) * | 2019-08-27 | 2019-12-03 | 大连理工大学 | A kind of typical revolving parts characterizing method based on actual measurement bounce data |
| CN112824844A (en) * | 2019-11-20 | 2021-05-21 | 哈尔滨工业大学 | Large-scale high-speed rotation equipment assembly clamping force measuring device based on laser ultrasound |
| CN113124792A (en) * | 2019-12-31 | 2021-07-16 | 哈尔滨工业大学 | Method for measuring bonding area of large-scale high-speed rotating equipment based on non-contact ultrasound |
| CN112247522A (en) * | 2020-05-29 | 2021-01-22 | 中国航发沈阳发动机研究所 | Rotor press-fitting equipment |
| CN112247522B (en) * | 2020-05-29 | 2022-02-22 | 中国航发沈阳发动机研究所 | Rotor press-fitting equipment |
| CN112254967A (en) * | 2020-08-03 | 2021-01-22 | 清华大学 | Aircraft engine rotor assembly simulation test system |
| CN112254966B (en) * | 2020-08-03 | 2022-02-01 | 清华大学 | Assembly quantity measuring method for aircraft engine rotor simulation assembly process |
| CN112254966A (en) * | 2020-08-03 | 2021-01-22 | 清华大学 | Assembly quantity measuring method for aircraft engine rotor simulation assembly process |
| CN113510475A (en) * | 2021-04-23 | 2021-10-19 | 哈尔滨工业大学 | Non-continuous rotor hot jacket assembly device |
| CN113510475B (en) * | 2021-04-23 | 2022-06-14 | 哈尔滨工业大学 | Non-continuous rotor hot jacket assembly device |
| CN114161185A (en) * | 2021-12-17 | 2022-03-11 | 上海杭和智能科技有限公司 | Clamping and calibrating platform for revolving body casting |
| CN114535982A (en) * | 2022-04-02 | 2022-05-27 | 中国航发沈阳发动机研究所 | Aeroengine doublestage high whirlpool stator unit body assembly fixture |
| CN116519314A (en) * | 2023-06-25 | 2023-08-01 | 西北工业大学 | Engine rotor over-rotation test tool and assembly method |
| CN116519314B (en) * | 2023-06-25 | 2024-02-23 | 西北工业大学 | Engine rotor over-rotation test tool and assembly method |
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