CN109590670A - A kind of aero-engine low-pressure turbine disk blind hole positioning pin replacing options - Google Patents
A kind of aero-engine low-pressure turbine disk blind hole positioning pin replacing options Download PDFInfo
- Publication number
- CN109590670A CN109590670A CN201811435546.4A CN201811435546A CN109590670A CN 109590670 A CN109590670 A CN 109590670A CN 201811435546 A CN201811435546 A CN 201811435546A CN 109590670 A CN109590670 A CN 109590670A
- Authority
- CN
- China
- Prior art keywords
- positioning pin
- pressure turbine
- turbine disk
- milling cutter
- blind hole
- 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.)
- Granted
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
- B23P6/04—Repairing fractures or cracked metal parts or products, e.g. castings
- B23P6/045—Repairing fractures or cracked metal parts or products, e.g. castings of turbine components, e.g. moving or stationary blades, rotors, etc.
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention belongs to machinery fields, and in particular to a kind of aero-engine low-pressure turbine disk blind hole positioning pin replacing options.Technical scheme is as follows: a kind of aero-engine low-pressure turbine disk blind hole positioning pin replacing options, includes the following steps: the protrusion part of 1) boring processing removal positioning pin；2) location hole is beaten in pincers worker on positioning pin；3) it is drilled on positioning pin with 4.2 drill bit of Φ；4) milling cutter removal residual positioning pin is utilized；5) low-pressure turbine disk blind hole is cleared up, new product positioning pin is installed.Aero-engine low-pressure turbine disk blind hole positioning pin replacing options provided by the invention, high production efficiency, success rate are high, save production cost.
Description
Technical field
The invention belongs to machinery fields, and in particular to a kind of aero-engine low-pressure turbine disk blind hole positioning pin replacement side
Method.
Background technique
When a kind of aero-engine overhaul, find low-pressure turbine disk on 16 positioning pins there are different degrees of fracture, split
The failures such as line, the low-pressure turbine disk for being related to this failure, which accounts for rebuild an engine, repairs 50% of number of units or so, gives engine operation
Safety causes serious hidden danger, therefore must exclude when repairing.In the form of replacing new product low-pressure turbine disk sub-assembly come
Debugging, buying expenses are very big.Using the method for replacing faulty positioning pin, expense can be saved.
Low-pressure turbine disk is key components and parts in aero-engine, and biggish alternate stress is born in work and thermal stress is made
With 16 positioning pins on disk are that step pin is as shown in Fig. 1, and major diameter is smaller, and major diameter is taken inventory with low whirlpool and is being interference fitted, small
Diameter cooperates in assembly with other parts.Positioning pin is step type, and lower section Φ 5, top Φ 4, bulge quantity is smaller, does not put forth effort
Point；And when repairing, the case where there are fracture or crackles, can not directly it extract.Positioning pin aperture is smaller, maximum Φ 5 or so, hole depth
Degree 6.5 or so.Positioning pin is mounted on the depth in blind hole about 5.5 or so, closer apart from bottom hole, has in engine working process
Sink, fitting depth may have been approached blind via bottom when overhaul, and normal handling ease of boring damages blind hole bottom surface.Using traditional brill
Processing-tapping method, easy damaged blind hole hole wall cause borehole enlargement or inner wall to damage, the cooperation data after influencing replacement.
Summary of the invention
The present invention provides a kind of aero-engine low-pressure turbine disk blind hole positioning pin replacing options, high production efficiency, successfully
Rate is high, saves production cost.
Technical scheme is as follows:
A kind of aero-engine low-pressure turbine disk blind hole positioning pin replacing options, include the following steps:
1) the protrusion part of boring processing removal positioning pin；
2) location hole is beaten in pincers worker on positioning pin；
3) it is drilled on positioning pin with 4.2 drill bit of Φ；
4) milling cutter removal residual positioning pin is utilized；Milling cutter is installed on radial drill, milling cutter gos deep into the drilling of positioning pin, protects
It is constant to hold radial drill Z axis, micro-shifting radial drill X-axis, radial drill main shaft continues to rotate at this time, in milling cutter rotation, remains positioning pin
It is attached on milling cutter cutting edge, lifts milling cutter to residual positioning pin with the power of Z axis forward direction using the upper chip removal principle of milling cutter cutting edge, it is residual
Positioning pin is stayed to separate with low-pressure turbine disk；
5) low-pressure turbine disk blind hole is cleared up, new product positioning pin is installed.
The aero-engine low-pressure turbine disk blind hole positioning pin replacing options, wherein the milling cutter changes milling to be special
Knife, selects 4 sword center blade type milling cutters of small filings holding chamber, and the angle of the second relief angle and third relief angle increases separately 3- by changing mill
5°。
The invention has the benefit that aero-engine low-pressure turbine disk blind hole positioning pin replacing options of the invention, raw
It produces that high-efficient, success rate is high, saves production cost.Select it is special change milling tool, select 4 sword center blade type of small filings holding chamber to mill
The angle of knife, the second relief angle and third relief angle increases separately 3-5 ° by changing mill, can effectively increase the row of milling cutter upwards
It considers power to be worth doing, improves processing success rate.
Detailed description of the invention
Fig. 1 is that low-pressure turbine disk blind hole installs positioning pin schematic diagram；
Fig. 2 is to be drilled on positioning pin schematic diagram with 4.2 drill bit of Φ；
Fig. 3 is that residual positioning pin schematic diagram is removed with milling cutter；
Fig. 4 is enlarged drawing at A in Fig. 3；
Fig. 5 is residual positioning pin schematic diagram.
In figure: 1 is low-pressure turbine disk, and 2 be positioning pin, and 3 be radial drill, and 4 be main shaft, and 5 be drill bit, and 6 be milling cutter, and 7 be residual
Stay positioning pin.
Specific embodiment
A kind of aero-engine low-pressure turbine disk blind hole positioning pin replacing options, include the following steps:
1) the protrusion part of boring processing removal positioning pin 2；Technological parameter: equipment: TK4100/2, coolant liquid: castor oil turns
Number: 400r/min, feeding: 0.04mm/r；
2) pincers worker beats location hole on positioning pin 2；
3) as shown in Fig. 2, being drilled on positioning pin 2 with 4.2 drill bit 5 of Φ；
4) as shown in Figure 3,4, residual positioning pin is removed using 4.5 milling cutter 6 of Φ；The milling cutter 6 changes milling tool, choosing to be special
With 4 sword center blade type milling cutters of small filings holding chamber, the angle of the second relief angle and third relief angle increases separately 3-5 ° by changing mill；It will
Milling cutter 6 is installed on radial drill 3, technological parameter: equipment: Z3063 × 20/1, coolant liquid: castor oil, revolution: 50-60/min, into
It gives: manually, working depth: 5max；Milling cutter 6 gos deep into the drilling of positioning pin, keeps radial drill Z axis constant, micro-shifting radial drill X
Axis, radial drill main shaft 4 continues to rotate at this time, and when milling cutter 6 rotates, residual positioning pin 7 is attached on milling cutter cutting edge, utilizes milling cutter sword
The upper chip removal principle of mouth lifts milling cutter 6, residual positioning pin 7 and low-pressure turbine disk 1 to residual positioning pin 7 with the power of Z axis forward direction
Separation；
5) 1 blind hole of low-pressure turbine disk is cleared up, new product positioning pin is installed.
Claims (2)
1. a kind of aero-engine low-pressure turbine disk blind hole positioning pin replacing options, which comprises the steps of:
1) the protrusion part of boring processing removal positioning pin；
2) location hole is beaten in pincers worker on positioning pin；
3) it is drilled on positioning pin with 4.2 drill bit of Φ；
4) milling cutter removal residual positioning pin is utilized；Milling cutter is installed on radial drill, milling cutter gos deep into the drilling of positioning pin, keeps shaking
Arm brill Z axis is constant, and micro-shifting radial drill X-axis, radial drill main shaft continues to rotate at this time, and in milling cutter rotation, residual positioning pin is attached to
On milling cutter cutting edge, milling cutter is lifted to residual positioning pin with the power of Z axis forward direction using the upper chip removal principle of milling cutter cutting edge, residual is fixed
Position pin is separated with low-pressure turbine disk；
5) low-pressure turbine disk blind hole is cleared up, new product positioning pin is installed.
2. aero-engine low-pressure turbine disk blind hole positioning pin replacing options according to claim 1, which is characterized in that institute
It states milling cutter and changes milling tool to be special, select 4 sword center blade type milling cutters of small filings holding chamber, the angle of the second relief angle and third relief angle
3-5 ° is increased separately by changing mill.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811435546.4A CN109590670B (en) | 2018-11-28 | 2018-11-28 | Method for replacing blind hole positioning pin of low-pressure turbine disc of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811435546.4A CN109590670B (en) | 2018-11-28 | 2018-11-28 | Method for replacing blind hole positioning pin of low-pressure turbine disc of aero-engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109590670A true CN109590670A (en) | 2019-04-09 |
| CN109590670B CN109590670B (en) | 2021-04-23 |
Family
ID=65959123
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811435546.4A Active CN109590670B (en) | 2018-11-28 | 2018-11-28 | Method for replacing blind hole positioning pin of low-pressure turbine disc of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109590670B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1111026A (en) * | 1994-03-24 | 1995-11-01 | 法玛通公司 | Method of replacing a centring pin of a fuel assembly and centring pin |
| CN202539630U (en) * | 2012-02-13 | 2012-11-21 | 河北钢铁股份有限公司承德分公司 | Bench drill for taking out static blade connecting pin of gas-driven generator |
| CN102886555A (en) * | 2012-08-21 | 2013-01-23 | 大连德迈仕精密轴有限公司 | Method for removing burrs in deep hole of workpiece |
| CN103862285A (en) * | 2012-12-17 | 2014-06-18 | 核动力运行研究所 | Boring and milling device for seized main bolts of pressure container |
| CN104476096A (en) * | 2014-10-27 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Intermediate casing ring repairing method |
| CN107283153A (en) * | 2017-05-27 | 2017-10-24 | 宁波帅特龙集团有限公司 | A kind of bearing pin pulling attachment and its operating method |
| CN207629961U (en) * | 2017-12-22 | 2018-07-20 | 神华集团有限责任公司 | fixed pin withdrawing device |
-
2018
- 2018-11-28 CN CN201811435546.4A patent/CN109590670B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1111026A (en) * | 1994-03-24 | 1995-11-01 | 法玛通公司 | Method of replacing a centring pin of a fuel assembly and centring pin |
| CN202539630U (en) * | 2012-02-13 | 2012-11-21 | 河北钢铁股份有限公司承德分公司 | Bench drill for taking out static blade connecting pin of gas-driven generator |
| CN102886555A (en) * | 2012-08-21 | 2013-01-23 | 大连德迈仕精密轴有限公司 | Method for removing burrs in deep hole of workpiece |
| CN103862285A (en) * | 2012-12-17 | 2014-06-18 | 核动力运行研究所 | Boring and milling device for seized main bolts of pressure container |
| CN104476096A (en) * | 2014-10-27 | 2015-04-01 | 沈阳黎明航空发动机(集团)有限责任公司 | Intermediate casing ring repairing method |
| CN107283153A (en) * | 2017-05-27 | 2017-10-24 | 宁波帅特龙集团有限公司 | A kind of bearing pin pulling attachment and its operating method |
| CN207629961U (en) * | 2017-12-22 | 2018-07-20 | 神华集团有限责任公司 | fixed pin withdrawing device |
Non-Patent Citations (1)
| Title |
|---|
| 刘瑞军: "货车折角直端塞门手把销拔芯轴铆钉拆装机的研究", 《科技创新导报》 * |
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| Publication number | Publication date |
|---|---|
| CN109590670B (en) | 2021-04-23 |
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