CN109483465A - Component and preparation method thereof for engine turbine disk dismantling - Google Patents
Component and preparation method thereof for engine turbine disk dismantling Download PDFInfo
- Publication number
- CN109483465A CN109483465A CN201811409382.8A CN201811409382A CN109483465A CN 109483465 A CN109483465 A CN 109483465A CN 201811409382 A CN201811409382 A CN 201811409382A CN 109483465 A CN109483465 A CN 109483465A
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- Prior art keywords
- matrix
- tooth
- component
- turbine disk
- chamber
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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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A kind of component for engine turbine disk dismantling, it includes type block portion, fixed block and handle, the type block portion is formed by connecting by the matrix stacking of multiple uniform thickness, each matrix is provided with straight-tooth chamber, the type block portion includes that the interior helical teeth chamber formed is stacked by the straight-tooth chamber of the matrix, the fixed block be provided with axially through handle hole, the handle connect with the fixed block.Component provided by the present invention for engine turbine disk dismantling, the parts of tooth of helical teeth is made of multiple direct tooth types in involute, is enormously simplified manufacturing process, is improved preparation efficiency.The present invention also provides the preparation methods of above-mentioned component.
Description
Technical field
The present invention relates to Fixture Design manufacturing technology field, in particular to a kind of turbine disk for aero-engine into
One specific component of the device of row dismantling and the preparation method of the component.
Background technique
Aero-engine is when installation, test or overhaul are maintained, it will usually need to disassemble the turbine disk, scheme
1 is a kind of existing principle schematic diagram for being used for the component that engine turbine disk is disassembled, and is the section view of the component on the left of Fig. 1
Structural schematic diagram, right side are the left view structural representation of left side schematic cross-sectional view, and Fig. 2 is the tooth form knot of the interior teeth portion of Fig. 1
Structure schematic illustration, Fig. 2 include the A-A office of the main view of interior teeth portion, the B in main view to part-structure view, in B direction view
Portion's schematic cross-sectional view, as shown in Figure 1 and Figure 2, the component are used to cooperate with other component (not regarding out in figure), to engine
The turbine disk is disassembled, which includes the vertical tube part 1 and handle 2 being detachably connected, and the vertical tube part 1, which is provided with, to be used for and whirlpool
The interior teeth portion 11 that wheel disc connects and the middle through-hole 12 for reserving operating space.Since the tooth form of the interior teeth portion 11 is involute
Interior helical teeth.The processing method of the existing interior teeth portion 11 to the component is that dedicated spiral shell is being housed with dedicated helical teeth slotting tool
It revolves and is processed on the gear shapping machine of guide rail.Difficulty of processing is big, low efficiency, at high cost.The specificity of cutter and equipment is required very high.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of component for engine turbine disk dismantling and its preparation sides
Method, the problem of being formerly mentioned is reduced or avoided.
In order to solve the above technical problems, the invention proposes a kind of components for engine turbine disk dismantling comprising
Type block portion, fixed block and handle, the type block portion are formed by connecting by the matrix stacking of multiple uniform thickness, and each matrix is provided with
Straight-tooth chamber, the type block portion include that the interior helical teeth chamber formed is stacked by the straight-tooth chamber of the matrix, and the fixed block is provided with axis
To the handle hole of perforation, the handle is connect with the fixed block.
Preferably, the thickness of the matrix is not more than 3mm.
Preferably, the minute of angle ε of the straight-tooth tooth form of the adjacent matrix of sequential connection is
ε=360 × (H/N)/(M × Z) × tg σ
In above formula, H is the thickness of the type block portion
N is the quantity of the matrix
M is the modulus of the helical teeth of the interior helical teeth chamber
Z is the number of teeth
σ is the helix angle of the helical teeth of the interior helical teeth chamber.
Preferably, each matrix is provided with 2 ￠ d0 +0.012Location hole.
The present invention also provides the preparation methods of above-mentioned component comprising following steps:
Step A calculates the quantity N of the matrix of the uniform thickness needed according to the thickness H of the interior helical teeth chamber 31, makes
The thickness of each matrix is not more than 3mm,
Step B, according to the tooth form of the straight-tooth chamber of each matrix of the sizecalculation for the interior helical teeth chamber 31 that need to be formed
Dimensional parameters,
Step C processes each matrix according to the dimensional parameters of the step B matrix calculated,
Step D, all matrix that step C is processed are attached using the location hole by positioning pin,
It is that the matrix forms the type block portion 3, processes the mounting hole for screw connection in the type block portion 3 later, then lead to
It crosses screw and connect the type block portion 3 with the fixed block 4, then again connect the handle 5 with the fixed block 4, complete
The preparation of the component.
Preferably, in step C, in process, for each matrix, 2 ￠ d are processed in first right boring0 +0.012
Location hole centering is straightened, then in the hole at tooth form center and using this two centrical lines of location hole as horizontal reference
The heart is set to coordinate origin, and by linear cutter direct tooth type face, according to the order of connection of each matrix, sequence is processed each
The matrix.
Preferably, in step C, the tooth form of each of sequential connection matrix is according to the step B minute of angle ε's calculated
The deflection of integral multiple.
Component provided by the present invention for engine turbine disk dismantling, helical teeth in involute
Parts of tooth be made of multiple direct tooth types, that is to say, that the present invention using fragment cut, the method for indexing combination.Common
Monolithic cutting goes out direct tooth type face on wire cutting machine tool, and final combination forms helical teeth in involute, manufactures to enormously simplify
Journey improves preparation efficiency.
Detailed description of the invention
The following drawings are only intended to schematically illustrate and explain the present invention, not delimit the scope of the invention.Wherein,
Fig. 1 is a kind of principle schematic diagram of existing component for engine turbine disk dismantling；
Fig. 2 is the tooth-shape structure schematic illustration of the interior teeth portion of Fig. 1；
Fig. 3 is a kind of structure of component for engine turbine disk dismantling of a specific embodiment according to the present invention
Schematic illustration；
Fig. 4 is the principle schematic diagram for being used to form the single matrix of type block portion of Fig. 3；
Fig. 5 is the manufacturing theory schematic diagram for being used to form multiple single matrix of type block portion of Fig. 3.
Specific embodiment
For a clearer understanding of the technical characteristics, objects and effects of the present invention, this hair of Detailed description of the invention is now compareed
Bright specific embodiment.Wherein, identical component uses identical label.
Fig. 1 is a kind of principle schematic diagram of existing component for engine turbine disk dismantling；Fig. 2 is Fig. 1's
The tooth-shape structure schematic illustration of interior teeth portion；Fig. 3 is that one kind of a specific embodiment according to the present invention is used for engine whirlpool
The principle schematic diagram of the component of wheel disc dismantling；Left side is the schematic cross-sectional view of the component, and right side is left side section view knot
The left view structural representation of structure schematic diagram, Fig. 4 are the principle schematic diagram for being used to form the single matrix of type block portion of Fig. 3；
Including front view and side view, Fig. 5 is the manufacturing theory schematic diagram for being used to form multiple single matrix of type block portion of Fig. 3.
Referring to shown in Fig. 1-5, a kind of component for engine turbine disk dismantling provided by the present invention comprising type block
Portion 3, fixed block 4 and handle 5, the type block portion 3 are formed by connecting by the matrix stacking of multiple uniform thickness, and each matrix is provided with
Straight-tooth chamber, the type block portion 3 include that the interior helical teeth chamber 31 formed is stacked by the straight-tooth chamber of the matrix, and the fixed block 4 is arranged
Have axially through handle hole 41, the handle 5 connect with the fixed block 4.
The size of the interior helical teeth chamber 31 is consistent with the size of the interior teeth portion 11 of Fig. 1, that is to say, that nominal diameter,
Modulus M, tooth number Z, pressure angle of graduated circle a, backlash size e, root diameter D1, tip diameter D2, helix angle σ, type chamber
Thickness H etc. is all the same.
The sum of the matrix is N, and for each matrix, the dimensional parameters of the tooth form of straight-tooth chamber can be by described interior oblique
The size of tooth cavity 31 calculates as follows:
Reference diameter D=M × Z
Due to thickness=type total the piece number of chamber thickness ÷ (namely H/N) of every matrix, stacking forms the interior helical teeth chamber
When 31, the thickness of monolithic matrix is likely to result in the dimensional discrepancy of accumulation, it is therefore necessary to must repair to reference circle backlash
Just, correction value can be set according to following formula,
Thickness H/N × tg σ of the matrix of correction value β=every
Therefore reference circle backlash e1=(e+ β)
The calculation formula of helix angle and lead are as follows: lead=reference diameter × tg helix angle
By: lead/material thickness=360 °/minute of angle
: minute of angle ε is ε=360 × (H/N)/(M × Z) × tg σ
The type block portion 3 is formed by connecting by the matrix stacking of multiple uniform thickness, that is to say, that and the present invention is cut using fragment,
Index combined method.For the interior teeth portion 11 in background technique, type block is decomposed into N piece by thickness, every with a thickness of H/N,
Partition machining, according to the tooth profile parameter provided, monolithic cutting goes out direct tooth type face on common wire cutting machine tool.By the inclination of helical teeth
The thickness of angle and monolithic can calculate minute of angle, and N piece monolithic is carried out indexing combination according to its minute of angle and is fixed.To combine
At the type block portion 3 comprising helical teeth chamber in involute.
The manufacturing process of each matrix can carry out in accordance with the following steps:
Step A calculates the quantity N of the matrix of the uniform thickness needed according to the thickness H of the interior helical teeth chamber 31, makes
The thickness of each matrix is not more than 3mm,
Since the flute profile of the interior helical teeth chamber 31 is formed by the straight-tooth of the matrix stacked, control the type
The thickness of piece can ensure that the flute profile of the interior helical teeth chamber 31 can effectively cooperate with the flute profile of engine turbine disk no more than 3mm.
Step B, according to the tooth form of the straight-tooth chamber of each matrix of the sizecalculation for the interior helical teeth chamber 31 that need to be formed
Dimensional parameters, for example, work as the interior helical teeth chamber 31 nominal diameter, modulus M, tooth number Z, pressure angle of graduated circle a, backlash size
E, after the parameters such as root diameter D1, tip diameter D2, helix angle σ, type chamber thickness H determine.
The sum that the matrix is calculated by step A is N, and for each matrix, the dimensional parameters of the tooth form of straight-tooth chamber can
It is calculated by the size of the interior helical teeth chamber 31 as follows:
Reference diameter D=M × Z
Due to thickness=type total the piece number of chamber thickness ÷ (namely H/N) of every matrix, stacking forms the interior helical teeth chamber
When 31, the thickness of monolithic matrix is likely to result in the dimensional discrepancy of accumulation, it is therefore necessary to must repair to reference circle backlash
Just, correction value can be set according to following formula,
Thickness H/N × tg σ of the matrix of correction value β=every
Therefore reference circle backlash e1=(e+ β)
The calculation formula of helix angle and lead are as follows: lead=reference diameter × tg helix angle
By: lead/material thickness=360 °/minute of angle
: minute of angle ε is ε=360 × (H/N)/(M × Z) × tg σ.
Step C processes each matrix according to the dimensional parameters of the step B matrix calculated, in process
In, it, can 2 ￠ d of first right boring processing for each matrix0 +0.012Location hole, and it is centrical with this two location holes
Line is horizontal reference, and centering is straightened, and is then set to coordinate origin with the hole center at tooth form center, passes through linear cutter straight-tooth
Type face sequentially processes each matrix according to the order of connection of each matrix.
As shown in figure 5, the tooth form of each of sequential connection matrix has certain deflection.Calculated according to step B
Minute of angle ε integral multiple deflection, to can ensure that the tooth profile parameter of the interior helical teeth chamber 31 formed after combination.
Step D, all matrix that step C is processed are attached using the location hole by positioning pin,
It is that the matrix forms the type block portion 3, processes the mounting hole for screw connection in the type block portion 3 later, then lead to
It crosses screw and connect the type block portion 3 with the fixed block 4, then again connect the handle 5 with the fixed block 4, complete
The preparation of the component.
The location hole is symmetrical arranged along the axle center of the matrix, can ensure positioning when sequence processes the matrix in this way
Benchmark, the mounting hole can make the type block using screw by the mounting hole with the setting of 90 degree of the location hole interval
Portion 3 is bonded with the fixed block 4.It need to only be preset with the symmetrically arranged threaded hole in its axle center i.e. on the fixed block 4
It can.The preparation of the fixed block 4 can be simplified in this way.
The positioning pin, handle 5, hexagon socket cap head screw all can be standard component.Such as:
Positioning pin may is that 6x22 GB/T 119.2-2000
Handle 5 may is that B8x80x10 JB/T7270.3-1994
Hexagon socket cap head screw may is that M8x16 GB/T 70.1-2000
The standard size of national standard query site associated components can be passed through in this way.
Component provided by the present invention for engine turbine disk dismantling, the parts of tooth of helical teeth is by more in involute
A direct tooth type composition, that is to say, that the present invention is cut using fragment, the method for indexing combination.It is single on common wire cutting machine tool
Piece is cut into direct tooth type face, and final combination forms helical teeth in involute, to enormously simplify manufacturing process, improves preparation effect
Rate.
It will be appreciated by those skilled in the art that although the present invention is described in the way of multiple embodiments,
It is that not each embodiment only contains an independent technical solution.So narration is used for the purpose of for the sake of understanding in specification,
The skilled in the art should refer to the specification as a whole is understood, and by technical solution involved in each embodiment
Regard as and can be combined with each other into the modes of different embodiments to understand protection scope of the present invention.
The foregoing is merely the schematical specific embodiment of the present invention, the range being not intended to limit the invention.It is any
Those skilled in the art, made equivalent variations, modification and combination under the premise of not departing from design and the principle of the present invention,
It should belong to the scope of protection of the invention.
Claims (10)
1. a kind of component for engine turbine disk dismantling, which is characterized in that it includes type block portion, fixed block and handle, institute
It states type block portion to be formed by connecting by the matrix stacking of multiple uniform thickness, each matrix is provided with straight-tooth chamber, and the type block portion includes
Stack the interior helical teeth chamber formed by the straight-tooth chamber of the matrix, the fixed block be provided with axially through handle hole, described
Hand is connect with the fixed block.
2. the component according to claim 1 for engine turbine disk dismantling, which is characterized in that the thickness of the matrix
No more than 3mm.
3. it is according to claim 1 for engine turbine disk dismantling component, which is characterized in that sequential connection it is adjacent
The minute of angle ε of straight-tooth tooth form of the matrix be
ε=360 × (H/N)/(M × Z) × tg σ
In above formula, H is the thickness of the type block portion
N is the quantity of the matrix
M is the modulus of the helical teeth of the interior helical teeth chamber
Z is the number of teeth
σ is the helix angle of the helical teeth of the interior helical teeth chamber.
4. the component according to claim 1 for engine turbine disk dismantling, which is characterized in that each matrix is equal
It is provided with 2 ￠ d0 +0.012Location hole.
5. the component according to claim 1 for engine turbine disk dismantling, which is characterized in that the type block portion and institute
Fixed block is stated to be bolted.
6. it is according to claim 1 for engine turbine disk dismantling component, which is characterized in that the handle with it is described
Fixed block is connected through a screw thread.
7. the component according to claim 3 for engine turbine disk dismantling, which is characterized in that each of sequential connection
The integral multiple of the equal minute of angle ε of the tooth form of the matrix is deflected.
8. a kind of preparation method for described in described in one of claim 1-3 for the component of engine turbine disk dismantling,
It is characterized in that, it includes the following steps:
Step A calculates the quantity N of the matrix of the uniform thickness needed according to the thickness H of the interior helical teeth chamber 31, makes each
The thickness of the matrix is not more than 3mm,
Step B, according to the ruler of the tooth form of the straight-tooth chamber of each matrix of the sizecalculation for the interior helical teeth chamber 31 that need to be formed
Very little parameter,
Step C processes each matrix according to the dimensional parameters of the step B matrix calculated,
Step D, all matrix that step C is processed are attached using the location hole by positioning pin, are institutes
It states matrix and forms the type block portion 3, process the mounting hole for screw connection in the type block portion 3 later, then pass through spiral shell
The type block portion 3 is connect by nail with the fixed block 4, is then again connect the handle 5 with the fixed block 4, described in completion
The preparation of component.
9. according to the method described in claim 8, it is characterized in that, in step C, in process, for each described
2 ￠ d are processed in matrix, first right boring0 +0.012Location hole draw and using this two centrical lines of location hole as horizontal reference
Then straight centering is set to coordinate origin with the hole center at tooth form center, by linear cutter direct tooth type face, according to each described
The order of connection of matrix sequentially processes each matrix.
10. according to the method described in claim 9, it is characterized in that, in step C, each of sequential connection matrix
Tooth form according to the integral multiple of the step B minute of angle ε calculated deflection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811409382.8A CN109483465B (en) | 2018-11-23 | 2018-11-23 | Component for disassembling engine turbine disc and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811409382.8A CN109483465B (en) | 2018-11-23 | 2018-11-23 | Component for disassembling engine turbine disc and preparation method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109483465A true CN109483465A (en) | 2019-03-19 |
| CN109483465B CN109483465B (en) | 2020-10-16 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811409382.8A Active CN109483465B (en) | 2018-11-23 | 2018-11-23 | Component for disassembling engine turbine disc and preparation method thereof |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1462296A (en) * | 1974-01-07 | 1977-01-19 | Chernock S P | Spark wheels method of manufacturing spark wheels and dies for use therein |
| US20150106063A1 (en) * | 2013-10-14 | 2015-04-16 | Airbus Operations Limited | Gear construction method and digital apparatus |
| TW201529210A (en) * | 2014-01-29 | 2015-08-01 | Shivam Autotech Ltd | Multi-geared hobbing method and application thereof |
| CN107436982A (en) * | 2017-07-27 | 2017-12-05 | 东北大学 | Consider the meshing characteristic analysis method of the peeling helical gear pair of MATRIX STIFFNESS amendment |
| CN108061142A (en) * | 2017-11-27 | 2018-05-22 | 电子科技大学 | There is the straight-tooth gear of overlap ratio |
| CN108071770A (en) * | 2017-11-28 | 2018-05-25 | 电子科技大学 | Assembled has the straight-tooth gear of overlap ratio |
-
2018
- 2018-11-23 CN CN201811409382.8A patent/CN109483465B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1462296A (en) * | 1974-01-07 | 1977-01-19 | Chernock S P | Spark wheels method of manufacturing spark wheels and dies for use therein |
| US20150106063A1 (en) * | 2013-10-14 | 2015-04-16 | Airbus Operations Limited | Gear construction method and digital apparatus |
| TW201529210A (en) * | 2014-01-29 | 2015-08-01 | Shivam Autotech Ltd | Multi-geared hobbing method and application thereof |
| CN107436982A (en) * | 2017-07-27 | 2017-12-05 | 东北大学 | Consider the meshing characteristic analysis method of the peeling helical gear pair of MATRIX STIFFNESS amendment |
| CN108061142A (en) * | 2017-11-27 | 2018-05-22 | 电子科技大学 | There is the straight-tooth gear of overlap ratio |
| CN108071770A (en) * | 2017-11-28 | 2018-05-25 | 电子科技大学 | Assembled has the straight-tooth gear of overlap ratio |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109483465B (en) | 2020-10-16 |
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