CN106825654B - A kind of rotor stack replacement benefit processing method - Google Patents

A kind of rotor stack replacement benefit processing method Download PDF

Info

Publication number
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
Authority
CN
China
Prior art keywords
rotor
degree
processing
replacement
rotor stack
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201611055413.5A
Other languages
Chinese (zh)
Other versions
CN106825654A (en
Inventor
李希顺
袁慧义
孙汕民
王洪明
孙文岩
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AECC Shenyang Liming Aero Engine Co Ltd
Original Assignee
AECC Shenyang Liming Aero Engine Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AECC Shenyang Liming Aero Engine Co Ltd filed Critical AECC Shenyang Liming Aero Engine Co Ltd
Priority to CN201611055413.5A priority Critical patent/CN106825654B/en
Publication of CN106825654A publication Critical patent/CN106825654A/en
Application granted granted Critical
Publication of CN106825654B publication Critical patent/CN106825654B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B23MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23BTURNING; BORING
    • B23B35/00Methods 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

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

A kind of rotor stack replacement benefit processing method
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.
CN201611055413.5A 2016-11-25 2016-11-25 A kind of rotor stack replacement benefit processing method Active CN106825654B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201611055413.5A CN106825654B (en) 2016-11-25 2016-11-25 A kind of rotor stack replacement benefit processing method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201611055413.5A CN106825654B (en) 2016-11-25 2016-11-25 A kind of rotor stack replacement benefit processing method

Publications (2)

Publication Number Publication Date
CN106825654A CN106825654A (en) 2017-06-13
CN106825654B true CN106825654B (en) 2019-07-05

Family

ID=59146012

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201611055413.5A Active CN106825654B (en) 2016-11-25 2016-11-25 A kind of rotor stack replacement benefit processing method

Country Status (1)

Country Link
CN (1) CN106825654B (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN105414889A (en) * 2015-11-23 2016-03-23 沈阳黎明航空发动机(集团)有限责任公司 Machining and edge-removing method for holes of rotor alloy disc assembly

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
CN105414889A (en) * 2015-11-23 2016-03-23 沈阳黎明航空发动机(集团)有限责任公司 Machining and edge-removing method for holes of rotor alloy disc assembly

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
三座标测量多孔位置度;徐晨;《实用测量技术》;19950930(第5期);第200-201页
高压转子组合钻铰孔工艺方法的研究;王洪明等;《机械工程师》;20150731(第7期);第37-38页

Also Published As

Publication number Publication date
CN106825654A (en) 2017-06-13

Similar Documents

Publication Publication Date Title
CN106825654B (en) A kind of rotor stack replacement benefit processing method
CN102205488A (en) Method for processing hole in split-sleeve cold extrusion manner
CN104308334A (en) Welding method of aircraft engine conduit
US7720649B2 (en) Reverse engineering method for disk and blade attachments
Mottonen et al. Manufacturing process capability and specification limits
CN105414889A (en) Machining and edge-removing method for holes of rotor alloy disc assembly
CN102962626B (en) Method for exchanging and repairing sealing labyrinth of low-pressure turbine rotor
US9227277B2 (en) Method for repairing a turbine diaphragm and diaphragm assembly resulting therefrom
Zhang et al. Unified functional tolerancing approach for precision cylindrical components
US10648794B2 (en) Method for inspection of a machine part
CN102481636A (en) Parts Manufacturing Methods, Systems And Uses
Sahay et al. Process improvement of brake lever production using DMAIC (+)
CN104018892B (en) The restorative procedure of turbine high-pressure steam valve valve bonnet seal face pit
Nielsen Specifications, operators and uncertainties
Vijayakumar et al. Application of six sigma methodology for a manufacturing cell—A case study
CN102922210B (en) Method for repairing threads on liquid seal shell
CN104384640A (en) Method for removing damaged blade of stator component of aero-engine
CN106493503A (en) A kind of rear housing precision bolt hole Combined machining process that repairs to the longevity
CN110595320B (en) Method for machining composite part without reference in circumferential direction
CN111085819B (en) Method for preparing neutron flux measuring tube power station on site
CN214702080U (en) Compressor dovetail tongue-and-groove profile inspection is with leading no-go gage
CN109648106B (en) Reverse-fit drilling repairing method for high-precision combined shell
Bölling et al. Control of uncertainty in high precision cutting processes: Reaming of valve guides in a cylinder head of a combustion engine
Sonigra et al. Solving the problem of end float with the application of Six Sigma tools: A case study
CN103111823B (en) Reassembly method of high precision porous component

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
CB02 Change of applicant information
CB02 Change of applicant information

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

GR01 Patent grant
GR01 Patent grant