CN106825654B - A kind of rotor stack replacement benefit processing method - Google Patents
A kind of rotor stack replacement benefit processing method Download PDFInfo
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- CN106825654B CN106825654B CN201611055413.5A CN201611055413A CN106825654B CN 106825654 B CN106825654 B CN 106825654B CN 201611055413 A CN201611055413 A CN 201611055413A CN 106825654 B CN106825654 B CN 106825654B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B35/00—Methods for boring or drilling, or for working essentially requiring the use of boring or drilling machines; Use of auxiliary equipment in connection with such methods
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Abstract
A kind of rotor stack replacement benefit processing method: first by analyzing aircraft engine working rotor principle and design feature, and application three dimension coordinate measurement technology compares measurement to the associated joint of rotor related components, and analyzes the interchangeability of each related components after the failure part replacement needed replacing；Then it is tested by actual processing, the reasonability and feasibility of practical set after work are added in verifying；Accurately to estimate and guarantee the parts and components of rotor after replacement and the matching of former platform components assembly, to meet the reliability and stability of rotor stack used.The invention proposes a kind of very strong rotor stack replacements of operability to mend processing method, it is with obvious superior technique effect, the industrial treatment for traditional simple hand repair being become specification, with more huge economic value and social value expected from volume.
Description
Technical field
The present invention relates to the maintenance of parts and components of rotor and processing technique fields, specifically provide a kind of rotor stack replacement
Mend processing method.
Background technique
Aircraft engine rotor part is the core in machine assembly and work, especially in aviation field.Start
The quality of machine core component is the critical issue for guaranteeing engine and using.Each components of engine can all produce after long-term use
Various forms of failures such as raw abrasion, deformation, need to return in engine repair shop and repair renovation.Rotor part is due to being hair
The core of motivation, at work by being influenced maximum, therefore the failure that rotor part occurs is most.The low-pressure compressor of engine
Rotor will appear part deformation, the overproof serious failure of abrasion returning repair in shop reason often, need to carry out more related components part
It changes.Using traditional combination fraising repair method, since the structure and foozle of former platform components are big, mending machining allowance has
Limit, is unable to satisfy the repairing of low-pressure compressor rotor string part, and the limitation without new product spare part causes to replace components and adds work and repair
Reason is difficult, therefore needs to study more advanced service technique, to improve rotor stack replacement technical quality and reliability.People compel
It cuts hope and obtains a kind of rotor stack replacement benefit processing method.
Summary of the invention
It is replaced the object of the present invention is to provide a kind of rotor stack that technical effect is excellent and mends processing method.The present invention is logical
The practical operation verifying of experimental method is crossed, effectively solve or significantly improve following technical problems: engine is in repair procedures
It is middle because all kinds of overproof failures are scrapped, replacement components are combined processing repairing rotor component service performance and reliability；It reduces
Engine maintenance cost, while a kind of technical thought ginseng with directive significance is provided for the repairing of the following rotor type component
It examines.
It is replaced the present invention provides a kind of rotor stack and mends processing method；It is characterized by:
First by analyzing aircraft engine working rotor principle and design feature, and apply three dimension coordinate measurement
Technology compares measurement to the associated joint of rotor related components, and analyzes the failure part replacement needed replacing
The interchangeability of each related components afterwards；
Then it is tested by actual processing, the reasonability and feasibility of practical set after work are added in verifying；So that energy is accurate
It estimates and guarantees that the parts and components of rotor after replacement and original platform components (refer to not replacing but close with the components newly replaced
Other relevant Surrounding Parts) assembly matching, to meet the reliability and stability of rotor stack used.
Processing method is mended in the rotor stack replacement, it is characterised in that: processing method is mended in the rotor stack replacement
In, the rotor stack needed replacing is aircraft engine low pressure rotor sub-assembly；Work side is added in the rotor stack replacement
The specific requirement of method is:
Firstly, measuring a second level drum barrel sub-assembly 1, the three-level that low pressure rotor needs replacing using metering three-coordinate measuring machine
The position degree of 40 bolt hole relative engagement seam allowances of 2 connecting portion of disk, theoretical value require position degree required precision 0.3mm with
It is interior；
Secondly, matching relative position degree difference according to three dimension coordinate measurement result is less than 0.15mm, what corresponding position degree required
A related fit dimension also qualified second level drum barrel sub-assembly 1 or three-level disk 2；
Again, it is calculated according to apolegamy 40 bolt hole relative position degrees of part and mends machining allowance, according to three coordinate above-mentioned
Measurement result adjusts the theoretical position (critical process) of Combined machining bolt hole by position degree complementation；See Fig. 3；
Finally, by the position coordinate value of complementary 40 bolts hole adjusted, by way of jig boring machine programming processing,
And it is required that calibration coordinate value adds work behaviour to guarantee that bolt hole reaches position degree requirement, to complete the rotor stack replacement
Make.
Processing method is mended in the rotor stack replacement, it is characterised in that: needs replacing the rotor stack hole for adding work
Diameter is Φ 8.2 to Φ 8.5mm, and benefit machining allowance is 0.3mm；As shown in Figure 4, if analysis position degree require 0.15mm with
It is interior, then it carries out adding work reparation by aperture location degree complementation method of adjustment；If position degree is greater than 0.15mm, by more
Renew product accessory to complete to add work reparation again later.
The invention proposes a kind of very strong rotor stack replacements of operability to mend processing method, has obvious more preferable
Technical effect, traditional simple hand repair become specification industrial treatment, with more huge expected from volume
Economic value and social value.
Detailed description of the invention
With reference to the accompanying drawing and embodiment the present invention is described in further detail:
Fig. 1 is low pressure rotor sub-assembly entirety simplified schematic diagram；
Fig. 2 is the partial enlarged view in Fig. 1 at I；
Fig. 3 is that bolt hole mends one of Working position degree impact analysis schematic diagram；
Fig. 4 is that bolt hole mends the two of Working position degree impact analysis schematic diagram.
Specific embodiment
Appended drawing reference 1 indicates one second level drum barrel of low pressure rotor, referred to as " level-one disk "；Appended drawing reference 2 is low pressure rotor three-level
Disk, referred to as " three-level disk ".Appended drawing reference 3 indicates connection bolt.
Embodiment 1
A kind of rotor stack replacement benefit processing method；Its requirement is as follows:
First by analyzing aircraft engine working rotor principle and design feature, and apply three dimension coordinate measurement
Technology compares measurement to the associated joint of rotor related components, and analyzes the failure part replacement needed replacing
The interchangeability of each related components afterwards；
Then it is tested by actual processing, the reasonability and feasibility of practical set after work are added in verifying；So that energy is accurate
It estimates and guarantees that the parts and components of rotor after replacement and original platform components (refer to not replacing but close with the components newly replaced
Other relevant Surrounding Parts) assembly matching, to meet the reliability and stability of rotor stack used.
The rotor stack replacement is mended in processing method, and the rotor stack needed replacing is that aircraft engine low pressure turns
Sub-assemblies；The specific requirement that processing method is mended in the rotor stack replacement is:
Firstly, measuring a second level drum barrel sub-assembly, the three-level that low pressure rotor needs replacing using metering three-coordinate measuring machine
The position degree of 40 bolt hole relative engagement seam allowances of disk connecting portion, theoretical value require position degree required precision 0.3mm with
It is interior；
Secondly, matching relative position degree difference according to three dimension coordinate measurement result is less than 0.15mm, what corresponding position degree required
A related fit dimension also qualified second level drum barrel sub-assembly or three-level disk；
Again, it is calculated according to apolegamy 40 bolt hole relative position degrees of part and mends machining allowance, according to three coordinate above-mentioned
Measurement result adjusts the theoretical position (critical process) of Combined machining bolt hole by position degree complementation；See Fig. 3；
Finally, by the position coordinate value of complementary 40 bolts hole adjusted, by way of jig boring machine programming processing,
And it is required that calibration coordinate value adds work behaviour to guarantee that bolt hole reaches position degree requirement, to complete the rotor stack replacement
Make.
Needing replacing and adding the rotor stack aperture of work is Φ 8.2mm to Φ 8.5mm, and benefit machining allowance is 0.3mm；It presses
Shown in Fig. 4, if analysis position degree requires within 0.15mm, carry out adding work by aperture location degree complementation method of adjustment
It repairs；If position degree is greater than 0.15mm, by completing to add work reparation again after replacement new product accessory.
There are also following the description requirements for the present embodiment:
1, specific embodiment is described as follows:
Firstly, replacing a second level drum barrel sub-assembly, the connection of three-level disk using metering three-coordinate measuring machine measurement low pressure rotor
The position degree of the 40 bolt hole relative engagement seam allowances in position, ginseng as shown in FIGS. 1 and 2；Appended drawing reference 1 indicates one second level of low pressure rotor
Drum barrel, referred to as " level-one disk "；Appended drawing reference 2 is low pressure rotor three-level disk, referred to as " three-level disk ".Appended drawing reference 3 indicates connection spiral shell
Bolt.
Two steps, a, second level of related fit dimension qualification small according to three dimension coordinate measurement result apolegamy relative position degree difference
Drum barrel sub-assembly 1 or three-level disk 2.
Three steps calculate according to apolegamy 40 bolt hole relative position degrees of part and mend machining allowance, adjusted by position degree complementation
Whole group closes processing bolt hole theoretical position (critical process).See Fig. 4
Finally, the position coordinate value of complementary 40 bolts hole adjusted is programmed processing correction spiral shell by jig boring machine
Keyhole position degree method is completed to add work with platform.Work aperture Φ 8.2mm to Φ 8.5mm group is added, i.e. benefit machining allowance is
0.3mm。
2, process determines
One second level drum barrel sub-assembly 1 of current factory's internal fault, three-level disk 2 examine each technical requirements by design drawing
It surveys, analyzes influence of the original state technical conditions to fault restoration, and determine process.
One second level drum barrel sub-assembly 1 of failure, three-level disk 2 are returned into measurement centre's detection bolt hole position degree and aperture ruler first
It is very little.
Then inspection data are analyzed, determines a second level drum barrel sub-assembly 1,2 Replacement procedure scheme of three-level disk.
Engineer testing is carried out using discard.
3, process flow: failure part and replacement part three dimension coordinate measurement link bolt hole aperture and position degree --- match platform aperture
Position degree analysis, selects auxiliary equipment --- work aperture location coordinate is added by mating former platform part and replacement part aperture location degree determination
System --- same group is machined to by determining to add work aperture location coordinate system and replace part to former platform part and matching and carry out bore hole benefit
Not --- sub-assembly assembly bounce checks
4, data are analyzed: failure part being analyzed and determines benefit processing scheme, needing could be really by a large amount of data comparison
Its fixed feasibility for adding work.It is as follows to one secondary component of current 5 low pressure and three-level disk measurement data: (table 1-5, number of varieties
It is mm according to default-length unit.) note: italic overstriking data are beyond calculated value in table.
Table 1 (length unit that data are defaulted in table is mm)
Table 2 (length unit that data are defaulted in table is mm)
Table 3 (length unit that data are defaulted in table is mm)
Table 4 (length unit that data are defaulted in table is mm)
Table 5 (length unit that data are defaulted in table is mm)
5, theory analysis:
It is required according to design drawing, aperture Φ 8.2mm to Φ 8.5mm group, i.e., benefit machining allowance is 0.3mm.By Fig. 4 institute
Show that analysis position degree within 0.15mm, get two or more radio stations at once by aperture location degree complementation method of adjustment and add work reparation, position
Degree of setting needs replacing the completion of new product accessory and adds work reparation when being greater than 0.15mm.
6, actual parts situation analysis
It is influenced due to adding machine tool system error and part correct error during work, position may be needed in actual processing
Degree of setting is less than technical conditions within the scope of 0.15mm, is just able to satisfy and adds work requirement.
It is up to 0.152mm from data analysis XXXXX-XXX01 hole location.XXXXX-XXX02 hole location is up to
0.16.Although two absolute fix degree are beyond 0.15mm requirement.By aperture location degree complimentary fashion, and consider hole tolerance
Upper limit 0.019mm, benefit, which is machined to Φ 8.512mm, can guarantee aperture ovality and concentricity.
If reaming according to conventional combination mends processing method, positions and ream by 2 hole of three-level disk, two matching piece bolt hole center
Away from for 0.312mm, practical fraising, which needs to be machined to Φ 8.824mm, could eliminate the coaxial of aperture ovality and two part bolts hole
Degree guarantees bolt assembly fit dimension qualification not clamping stagnation.
XXXXX-XXX03 about 26 hole locations are greater than 0.15mm, and maximum is more than 0.3mm.
XXXXX-XXX04 only has 4 hole locations to be less than 0.20mm, and maximum is more than 0.4mm.
2 bolt hole position degree of XXXXX-XXX05 three-level disk is up to 0.158mm all in acceptability limit.
XXXXX-XXX03, XXXXX-XXX04 and calculated value error are larger, therefore are not able to satisfy processing request.
Mono- second level disk component of XXXXX-XXX01/02 and XXXXX-XXX05 three-level disk satisfaction add work and calculate requirement, therefore can
To carry out step processing.
7, processing experiment and result are mended
Choose the second level drum barrel sub-assembly 1 that number is XXXXX-XXX01 and the three-level disk 2 that number is XXXXX-XXX05
Accessory processing test, test result data such as the following table 6,7.Position error is in 0.02mm, it is desirable that aperture
It is practical mend needed for a second level drum barrel sub-assembly 1 after processing is completed and three-level disk 2 totally 40 diameters of bolt hole in Φ
8.51- Φ 8.519mm, actual processing result meet aperture size requirement.
Disk hole and the cooperation of turnbuckle 3 are required to meet 0.013~0.042mm of gap when assembly, and calculated result meets assembly
It is required that checking bolt without clamping stagnation by practical set, low pressure rotor sub-assembly geometric tolerance 0.02mm is qualified.
The conclusion of the present embodiment:
The failure part of selection is calculated by component link bolt hole diameter and position degree actual measurement, and by theoretical coordinate system
As a result meet and mend processing request.2 turnbuckle aperture size of one second level drum barrel component 1 of low pressure and three-level disk after actual processing test
Meet drawing requirement, 3 activity of turnbuckle and meets design drawing with apertures and sub-assembly geometric tolerance after assembling test
Paper matching requirements.This mends processing method and meets low pressure rotor assembling repair requirement, can be used for the repairing of low pressure rotor part replacement.
And it can be applied on similar parts and components of rotor service technique.
Table 6 (length unit that data are defaulted in table is mm)
Table 7 (length unit that data are defaulted in table is mm)
Claims (3)
1. processing method is mended in a kind of rotor stack replacement；It is characterized by:
First by analyzing aircraft engine working rotor principle and design feature, and apply three dimension coordinate measurement technology
Measurement is compared to the processed position of the part to be processed of rotor normal docking part and replacement, and analyzes the event needed replacing
The interchangeability of normal docking part and part to be processed after barrier part replacement；
The measurement of comparison refer to normal docking part and part to be processed combination 24 bolt hole aperture sizes of assembly connection and
The measurement of comparison of position degree；
Then it is tested by actual processing, the reasonability and feasibility of practical set after work are added in verifying；Accurately to estimate
And guarantee the matching of the parts and components of rotor after replacement and the assembly of former platform components, so as to meet rotor stack use can
By property and stability.
2. being replaced according to rotor stack described in claim 1 and mending processing method, it is characterised in that: the rotor stack replacement
It mends in processing method, the rotor stack needed replacing is aircraft engine low pressure rotor sub-assembly；The rotor stack is more
The specific requirement for changing benefit processing method is:
Firstly, the second level drum barrel sub-assembly (1), the three-level disk that are needed replacing using metering three-coordinate measuring machine measurement low pressure rotor
(2) position degree of 40 bolt hole relative engagement seam allowances of connecting portion；
Secondly, matching relative position degree difference according to three dimension coordinate measurement result is less than 0.15mm, the correlation that corresponding position degree requires
A fit dimension also qualified second level drum barrel sub-assembly (1) or three-level disk (2)；
Again, it is calculated according to apolegamy 40 bolt hole relative position degrees of part and mends machining allowance, according to three dimension coordinate measurement above-mentioned
As a result the theoretical position of Combined machining bolt hole is adjusted by position degree complementation；
Finally, by the position coordinate value of complementary 40 bolts hole adjusted, by way of jig boring machine programming processing, and
It is required that calibration coordinate value mends process operation to guarantee that bolt hole reaches position degree requirement, to complete the rotor stack replacement.
3. being replaced according to rotor stack described in claim 2 and mending processing method, it is characterised in that: need replacing and add turning for work
Sub-assemblies aperture is Φ 8.2 to Φ 8.5mm, and benefit machining allowance is 0.3mm；If analyze position degree require 0.15mm with
It is interior, then it carries out adding work reparation by aperture location degree complementation method of adjustment；If position degree is greater than 0.15mm, by more
Renew product accessory to complete to add work reparation again later.
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| CN201611055413.5A CN106825654B (en) | 2016-11-25 | 2016-11-25 | A kind of rotor stack replacement benefit processing method |
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| CN106825654B true CN106825654B (en) | 2019-07-05 |
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| CN107790957A (en) * | 2017-11-24 | 2018-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of method for decomposing interference connection super large bulking value complexity drum barrel assembly |
| CN112705905B (en) * | 2021-01-08 | 2022-11-18 | 成都国营锦江机器厂 | Method for repairing BP-14 main reducer driven spiral bevel gear assembly |
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| CN102099147A (en) * | 2008-07-18 | 2011-06-15 | 斯奈克玛 | Method of repairing or reworking a turbomachine disk and repaired or reworked turbomachine disk |
| CN102962626A (en) * | 2012-09-29 | 2013-03-13 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for exchanging and repairing sealing labyrinth of low-pressure turbine rotor |
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Address after: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Applicant after: Chinese Hangfa Shenyang Liming Aero engine limited liability company Address before: 110043 Dong TA street, Dadong District, Shenyang, Liaoning Province, No. 6 Applicant before: Liming Aeroplane Engine (Group) Co., Ltd., Shenyang City |
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