CN103643014B - The straightening method of labyrinth assembly matrix internal ring before aero-engine supports - Google Patents
The straightening method of labyrinth assembly matrix internal ring before aero-engine supports Download PDFInfo
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- CN103643014B CN103643014B CN201310594775.1A CN201310594775A CN103643014B CN 103643014 B CN103643014 B CN 103643014B CN 201310594775 A CN201310594775 A CN 201310594775A CN 103643014 B CN103643014 B CN 103643014B
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- labyrinth assembly
- assembly matrix
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- internal ring
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Abstract
The invention provides a kind of straightening method of labyrinth assembly base member internal ring before aero-engine supports, its composition specifically includes that and designs and produces a tool part for flatulence of heat type school shape labyrinth assembly matrix internal ring matched with labyrinth assembly matrix internal ring, the line of material thermal coefficient of expansion of described tool part is more than the line of material thermal coefficient of expansion of labyrinth assembly matrix, tool part is placed in labyrinth assembly matrix internal ring one be placed in annealing device, annular strain school shape in being realized labyrinth assembly matrix by tool part thermal expansion in labyrinth assembly annealing heat treatment process, annealing heat treatment takes out labyrinth assembly from annealing device after terminating, tool part is exited from labyrinth assembly matrix internal ring after cooling, i.e. complete the school shape of annular strain in labyrinth assembly matrix.The inventive method improves the sizing precision of annular strain in labyrinth assembly matrix, simplifies postprocessing working procedures, improves post processing work efficiency, reduce processing cost.
Description
Technical field
The present invention relates to labyrinth assembly processing technique field before aero-engine supports, more specifically
Say, relate to a kind of deformation school shape side of labyrinth assembly matrix internal ring before aero-engine supports
Method.
Background technology
Before aero-engine supports, labyrinth assembly is the assembly for airtight engine front support of obturaging, its
Structure is as it is shown in figure 1, be designed with one layer of honeycomb texture at the cannelure inside-and-outside ring wall of its matrix.
Described honeycomb layer is typically with the mode of vacuum brazing and is welded on cannelure wall.Obturage
The cell wall of assembly matrix cannelure is the thinnest, and particularly internal ring cell wall is thinner, and therefore the intensity of cell wall is very
Low, honeycomb layer is welded on cannelure wall, owing to brazing temperature is high, up to 1000 DEG C
Above, and in brazing process, labyrinth assembly is heated uneven, in labyrinth assembly matrix cannelure
After welding honeycomb layer on outer ring cell wall, the internal ring wall of labyrinth assembly matrix cannelure would generally
There is the biggest deformation, and the stress that remnants are bigger.Meeting during residual stress release afterwards
There is bigger deformation in the annular thin wall making matrix further, the form accuracy of part will be further
Reduce.
For the problems referred to above, labyrinth assembly will be to it after welding honeycomb layer on cannelure wall
Carry out post processing.Traditional post processing after honeycomb layer soldering, including deformation school shape and elimination
Residual stress, wherein deformation school shape is to use cold-extruded and beat annular thin wall, makes labyrinth assembly matrix
The deformation of internal ring wall obtains school shape, and the residual stress using the mode of high annealing to make soldering produce obtains
To eliminating.The deformation school shape mode of prior art, its existing problem, one is to cause annular
Thin-walled surface damages, and two is that deformation school shape is the most accurate, it is impossible to fundamentally solve size distortion problem,
Three is that school shape is the most time-consuming, and processing cost is high.I.e. after the honeycomb layer soldering of prior art
Post-processing approach, not only treatment process is various, time-consuming, and processing cost is high, and deforms
School shape poor processing effect.In consideration of it, the production practices of labyrinth assembly are badly in need of developing a kind of new honeycomb
Post-processing approach after structure sheaf soldering.
Summary of the invention
The deficiency existed for the post-processing approach after the honeycomb layer soldering of prior art, the present invention
Purpose aim to provide the post-processing approach after a kind of new honeycomb layer soldering, to realize disappearing
Except realizing while Welding residual stress that the deformation of labyrinth assembly matrix internal ring is carried out accurate school
Shape, simplifies the postprocessing working procedures after honeycomb layer soldering.
The straightening method of labyrinth assembly matrix internal ring before aero-engine supports of the present invention: set
Meter make that one and labyrinth assembly matrix internal ring match in the shape labyrinth assembly matrix of flatulence of heat type school
The tool part of ring, the line of material thermal coefficient of expansion of described tool part is more than the material of labyrinth assembly matrix
Coefficient of linear thermal expansion, is placed in tool part in labyrinth assembly matrix internal ring one and is placed into annealing device
In, realized labyrinth assembly matrix by tool part thermal expansion in labyrinth assembly annealing heat treatment process
The school shape of interior annular strain, annealing heat treatment takes out labyrinth assembly from annealing device, after cooling after terminating
Exit tool part from labyrinth assembly matrix internal ring, i.e. complete the school of annular strain in labyrinth assembly matrix
Shape.
In the said method of the present invention, the diameter of tool part can be determined by following formula:
R1=R2*α1/α2
Wherein R1For the radius of tool part, R2For labyrinth assembly matrix internal ring design radial, α1For work
Piece installing coefficient of linear thermal expansion under heat treatment temperature, α2For labyrinth assembly matrix in heat treatment temperature
Under line of material thermal coefficient of expansion.
At the said method of the present invention, annealing heat treatment temperature is generally 400 DEG C～700 DEG C.
Compared with prior art, the inventive method has a following useful technique effect:
1, the present invention method use match with labyrinth assembly matrix internal ring and in heat treatment temperature
The lower line of material thermal coefficient of expansion of degree is more than the tool part of labyrinth assembly matrix material coefficient of linear thermal expansion,
The school of annular strain in being realized labyrinth assembly matrix by tool part thermal expansion in annealing heat treatment process
Shape, thus avoid tradition cold-extruded and beat the school shape mode damage to labyrinth assembly matrix internal ring thin-walled
Go bad and school shape is inaccurate, improve the accuracy of school shape.
2, the method for the present invention is to eliminate in annealing operation the school shape of annular strain in labyrinth assembly matrix
Carry out while the residual stress that soldering brings, two procedures is reduced to one procedure, improve
Working (machining) efficiency, reduces processing cost.
3, the inventive method is simple to operate, and the suitability is strong, and tool structure is simple, easily promotes.
Accompanying drawing explanation
Fig. 1 is flute profile honeycomb parts and school shape frock schematic diagram
1 outer honeycomb in figure, honeycomb in 2,3 labyrinth assembly matrixes, 4 tool parts.
Detailed description of the invention
Below by embodiment, the present invention is specifically described, it is necessary to it is pointed out here that, real
Execute example to be served only for the present invention is further described, it is impossible to be interpreted as scope
Limiting, the present invention can be made one according to the content of foregoing invention by the person skilled in the art in this field
A little nonessential improvement and adjustment, but such improvement and adjustment still fall within protection scope of the present invention.
Embodiment 1
Support the straightening method of front labyrinth assembly matrix internal ring for aero-engine described in the present embodiment,
Obturage group for flatulence of heat type school shape with what labyrinth assembly matrix 3 internal ring matched including designing and producing one
The tool part 4 of part matrix internal ring, the material of described labyrinth assembly matrix is MSRR6503, at 650 DEG C
The coefficient of linear thermal expansion α 2 of lower material is 12.0 × 10-6/ DEG C, and the material of described tool part is austenite
Rustless steel 1Cr18Ni9Ti, at 650 DEG C, the coefficient of linear thermal expansion α 1 of material is 18.4 × 10-6/ DEG C,
The diameter of tool part determines according to the following equation
R1=R2*α1/α2
R in formula1For the radius of tool part, R2For labyrinth assembly matrix internal ring design radial, α1For frock
Part material thermal expansion coefficient under heat treatment temperature, α2For the material of labyrinth assembly matrix at Re Chu
Thermal coefficient of expansion at a temperature of reason.It is placed in tool part in labyrinth assembly matrix internal ring together to insert and moves back
In fire equipment, it is at 650 DEG C in labyrinth assembly annealing heat treatment process, due to tool part 4
Thermal expansion size is more than the thermal expansion size of labyrinth assembly matrix 3, thus realizes labyrinth assembly base
The school shape of internal annular strain.Annealing heat treatment takes out labyrinth assembly, cooling from annealing device after terminating
After exit tool part from labyrinth assembly matrix internal ring, i.e. complete annular strain in labyrinth assembly matrix
School shape.
Claims (1)
1. a straightening method for labyrinth assembly matrix internal ring before aero-engine supports, its feature exists
In, design and produce one with labyrinth assembly matrix (3) internal ring match for flatulence of heat type school shape labyrinth assembly base
The tool part (4) of internal ring, the line of material thermal coefficient of expansion of described tool part is more than the material of labyrinth assembly matrix
Stockline thermal coefficient of expansion, is placed in tool part in labyrinth assembly matrix internal ring one and is placed in annealing device,
Annular strain in being realized labyrinth assembly matrix by tool part thermal expansion in labyrinth assembly annealing heat treatment process
School shape, annealing heat treatment takes out labyrinth assembly from annealing device, after cooling in labyrinth assembly matrix after terminating
Ring exits tool part, i.e. completes the school shape of annular strain in labyrinth assembly matrix；The diameter of described tool part leads to
Cross following formula to determine:
R1=R2*α1/α2
Wherein R1For the radius of tool part, R2For labyrinth assembly matrix internal ring design radial, α1For tool part in heat
Coefficient of linear thermal expansion under treatment temperature, α2Swollen for labyrinth assembly matrix line of material heat under heat treatment temperature
Swollen coefficient；The temperature of described annealing heat treatment is 400 DEG C～700 DEG C.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310594775.1A CN103643014B (en) | 2013-11-21 | 2013-11-21 | The straightening method of labyrinth assembly matrix internal ring before aero-engine supports |
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| CN201310594775.1A CN103643014B (en) | 2013-11-21 | 2013-11-21 | The straightening method of labyrinth assembly matrix internal ring before aero-engine supports |
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| CN103643014B true CN103643014B (en) | 2016-10-05 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105219942B (en) * | 2015-08-18 | 2018-08-31 | 上海航天精密机械研究所 | A method of expanding deformation when control revolving parts heat treatment |
| CN107160025A (en) * | 2017-05-15 | 2017-09-15 | 中国船舶重工集团公司第七二五研究所 | A kind of thin-wall barrel high energy beam precision welding manufacture method |
| CN111546280A (en) * | 2020-04-23 | 2020-08-18 | 广州飞机维修工程有限公司 | Aircraft starting drive assembly equipment frock of obturating |
| CN112222544B (en) * | 2020-08-31 | 2021-11-26 | 中国航发南方工业有限公司 | Efficient machining electrode of honeycomb sealing ring and design method thereof |
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| JP2005113186A (en) * | 2003-10-06 | 2005-04-28 | Ntn Corp | Rolling bearing ring and its producing method, and rolling bearing |
| CN101760602A (en) * | 2009-12-25 | 2010-06-30 | 重庆齿轮箱有限责任公司 | Large-scale thin wall gear ring quenching deformation control method |
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| CN102069109A (en) * | 2010-11-04 | 2011-05-25 | 西安航空动力股份有限公司 | Correction device and correction method for inner ring of engine crankcase |
| CN102181620A (en) * | 2011-05-06 | 2011-09-14 | 山西北方惠丰机电有限公司 | Method for heat treatment of perforated laminating parts |
| CN102794334A (en) * | 2012-07-17 | 2012-11-28 | 湖北三江航天江北机械工程有限公司 | Diameter and shape precision control method of thin-walled cylinder and special tool thereof |
| CN102888499A (en) * | 2012-10-09 | 2013-01-23 | 首都航天机械公司 | Adjustable internal support device for deformation control in heat treatment |
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| JP2005113186A (en) * | 2003-10-06 | 2005-04-28 | Ntn Corp | Rolling bearing ring and its producing method, and rolling bearing |
| CN101760602A (en) * | 2009-12-25 | 2010-06-30 | 重庆齿轮箱有限责任公司 | Large-scale thin wall gear ring quenching deformation control method |
| CN101906524A (en) * | 2010-08-16 | 2010-12-08 | 重庆齿轮箱有限责任公司 | Normalizing correction method for deformed large thin-walled gear ring |
| CN102069109A (en) * | 2010-11-04 | 2011-05-25 | 西安航空动力股份有限公司 | Correction device and correction method for inner ring of engine crankcase |
| CN102181620A (en) * | 2011-05-06 | 2011-09-14 | 山西北方惠丰机电有限公司 | Method for heat treatment of perforated laminating parts |
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| CN103643014A (en) | 2014-03-19 |
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