CN109967967A - A kind of blade forming method with complex internal type chamber - Google Patents
A kind of blade forming method with complex internal type chamber Download PDFInfo
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- CN109967967A CN109967967A CN201711443921.5A CN201711443921A CN109967967A CN 109967967 A CN109967967 A CN 109967967A CN 201711443921 A CN201711443921 A CN 201711443921A CN 109967967 A CN109967967 A CN 109967967A
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- 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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- Turbine Rotor Nozzle Sealing (AREA)
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Abstract
A kind of blade forming method with complex internal type chamber, belonging to inner cavity is complex curved surface part technical field.The manufacturing process of the blade includes: its structure to be divided into multiple thin layers, and the corresponding structure of each thin layer is corresponded to and is worked into the three-dimensional sub- workpiece of multiple rectangles firstly, according to the overall structure of the blade；Then multiple sub- workpiece with leaf structure are stacked in sequence, and positioning pin progress position is set on the quadrangle of the sub- workpiece and is fixed；The sub- workpiece being stacked then is welded as by unified entirety by welding manner, forms the cuboid workpiece of integral type；Finally, using the short transverse of cuboid workpiece as the axial direction of the blade, since the upper surface of the cuboid workpiece according to the shape and structure of the cross section of the blade by machining mode by cuboid work pieces process at the production blade with inner-cavity structure.
Description
Technical field
The present invention relates to a kind of blade forming methods with complex internal type chamber, and belonging to inner cavity is complex curved surface part skill
Art field.
Background technique
Currently, complicated internal cavity is completed by the way of numerical control processing, casting and 3D printing substantially.Numerical control processing is tight
It is limited again by inner-cavity structure, it is excessively complicated or inner cavity is too deep is unable to complete；What casting repeatedly increased and decreased sectional dimension
Complex-curved and large size, thin walled part has significant limitation, demoulds extremely difficult；3D printing is subject to processing the limit of area's size
System, is unable to complete the processing of large-size workpiece.By taking airfilm cooling blade as an example, elongated structure makes it can only be by the side of casting
Formula completes processing, but due in casting process it is difficult to ensure that the uniformity of workpiece material, rejection rate is relatively high, but with me
The continuous development of state's aviation aerospace industry, the workpiece with complex internal type chamber gradually increase, and existing processing technology receives
Stern challenge, so needing a kind of processing method with general applicability to solve the processing and manufacturing of complicated inner cavity curved surface.
Summary of the invention
The present invention asks to solve the technology that yield rate is too low in the existing blade Work piece processing method with complicated inner cavity
Topic, proposes a kind of blade forming method with complex internal type chamber, the technical solution taken is as follows:
A kind of blade forming method with complex internal type chamber, the manufacturing process of the blade include: firstly, according to institute
Its structure is divided into multiple thin layers, and the corresponding structure correspondence of each thin layer is worked into multiple squares by the overall structure for stating blade
The three-dimensional sub- workpiece of shape；Then multiple sub- workpiece with leaf structure are stacked in sequence, and in the son
Positioning pin progress position is arranged on the quadrangle of workpiece to fix；Then the sub- workpiece being stacked is welded as by welding manner
It is unified whole, form the cuboid workpiece of integral type；Finally, using the short transverse of cuboid workpiece as the axial direction of the blade
Direction passes through machining side according to the shape and structure of the cross section of the blade since the upper surface of the cuboid workpiece
Formula is by cuboid work pieces process at the production blade with inner-cavity structure.
Further, the detailed process of the blade forming are as follows:
Step 1: the planform of the blade is divided into along cross-sectional direction according to the structure feature of the blade more
A thin layer with structure feature；
Step 2: the corresponding structure feature of thin layer described in each step 1 is corresponding in turn to processing and is united in multiple sizes
On the sub- workpiece of one cuboid；
Step 3: will have the sub- workpiece of the multiple cuboid of step 2 according to every layer of sequence after blade layering
It is stacked up, and setting location hole is multiple rectangular by what is be stacked up by positioning pin on the quadrangle of the sub- workpiece of each cuboid
Body workpiece carries out position and fixes；
Step 4: the sub- workpiece end face of cuboid on two end faces up and down of the heap poststack described in step 3 by grinding or
The mode of polishing carries out mirror surface treatment；
Step 5: by way of Diffusion Welding that the sub- job stacking body of the cuboid after mirror surface treatment is each rectangular
Body workpiece carries out welding fixed, forms the sub- job stacking body of a cuboid；
Step 6: existing structure feature on the sub- job stacking body of the cuboid according to step 5 passes through machining
Mode the blade cuts are come out, complete the manufacture of entire blade.
Further, the corresponding structure feature of thin layer described in each step 1 is corresponding in turn to processing described in step 2
Specific steps on the sub- workpiece of the unified cuboid of multiple sizes are as follows: firstly, before and after each sub- workpiece of cuboid
Multiple semicircular arc grooves, uniform a pair in position of all semicircular arc grooves are processed at same position in two plate faces
It answers；Then, the leaf cross-section side is processed at the same position on the sub- workpiece surface of cuboid with multiple grooves
Upward ring structure.
Further, the sub- workpiece of the cuboid uses the sub- workpiece of plate, and the plate thickness of the sub- workpiece of plate is
0.1mm or 10mm.
Further, the blade includes front and rear panels, by arc-shaped at the both sides of the edge of the front and rear panels
Side wall is connected to a ring-shaped cavity；The front and rear panels are all made of arc board face structure, also, the arc length of the foreboard is small
In the arc length of back plate, the circular arc of the front and rear panels is towards the same as a direction；The arc-shaped side wall of the front and rear panels two sides
In, the arc length of the arc-shaped side wall of side is greater than the arc length of the arc-shaped side wall in the other side；Different described arc-shaped of two arc length
Side wall and the front and rear panels, which are an integral structure, makes the blade form the ring that one end is narrow, the other end is wide along cross-sectional direction
Shape structure；The front and rear panels are equipped with the through-hole of array distribution, also, the through-hole of the front and rear panels corresponds.
The invention has the advantages that:
Blade forming method proposed by the present invention can effectively improve the yield rate of blade, be not higher than 70% from casting
Yield rate be increased to 98% or more；The defects count of blade is reduced, Diffusion Welding, which is that one kind is intermetallic, to be connected, and is acted on
Molecular level, once welding is completed, defect is not present in blade interior, and casts because technological reason must be allowed for depositing for defect
?；The efficiency of batch production is improved, the process time of casting is longer, and the pre-treatments used time such as moulding, coremaking is longer, knockout, nothing
The post-processing task such as damage detection is heavy, but after diffusion technology for welding sizing, need to only carry out the sampling observation of limited quantity, contract significantly
The short process time of blade.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of blade of the present invention.
Fig. 2 is the hierarchical design structural schematic diagram of blade processing process of the present invention.
Fig. 3 is for blade processing process of the present invention and after the layering of that, contained every layer of blade of every straton workpiece row
The schematic diagram of structure feature.
Fig. 4 is the corresponding structure feature schematic diagram of blade contained on blade of the present invention individually sub- workpiece.
Specific embodiment
The present invention will be further described combined with specific embodiments below, but the present invention should not be limited by the examples.
Embodiment 1:
A kind of blade with complex internal type chamber, as shown in Figure 1, the blade includes front and rear panels, the foreboard
A ring-shaped cavity is connected to by arc-shaped side wall at the both sides of the edge of back plate；The front and rear panels are all made of arc panel
Face structure, also, the arc length of the foreboard is less than the arc length of back plate, and the circular arc of the front and rear panels is towards the same as a direction；Institute
It states in the arc-shaped side wall of front and rear panels two sides, the arc length of the arc-shaped side wall of side is greater than the arc of the arc-shaped side wall in the other side
It is long；The different arc-shaped side wall of two arc length and the front and rear panels, which are an integral structure, makes the blade along cross section
Direction forms the cyclic structure that one end is narrow, the other end is wide；The front and rear panels are equipped with the through-hole of array distribution, also, institute
The through-hole for stating front and rear panels corresponds.
The forming process of the blade includes: to be divided into its structure multiple thin firstly, according to the overall structure of the blade
Layer, and the corresponding structure of each thin layer is corresponded to and is worked into the three-dimensional sub- workpiece of multiple rectangles；Then leaf structure will be had
Multiple sub- workpiece be stacked in sequence, and on the quadrangle of the sub- workpiece be arranged positioning pin carry out position fix；
The sub- workpiece being stacked then is welded as by unified entirety by welding manner, forms the cuboid workpiece of integral type；Most
Afterwards, using the short transverse of cuboid workpiece as the axial direction of the blade, since the upper surface of the cuboid workpiece
According to the shape and structure of the cross section of the blade by way of machining by cuboid work pieces process at inner-cavity structure
Production blade.
Embodiment 2
The present embodiment proposes a kind of forming method with complex internal type chamber blade, the specific mistake of the blade forming
Journey are as follows:
Step 1: the planform of the blade is divided into along cross-sectional direction according to the structure feature of the blade more
A thin layer with structure feature；
Step 2: the corresponding structure feature of thin layer described in each step 1 is corresponding in turn to processing and is united in multiple sizes
On the sub- workpiece of one cuboid；
Step 3: will have the sub- workpiece of the multiple cuboid of step 2 according to every layer of sequence after blade layering
It is stacked up, and setting location hole is multiple rectangular by what is be stacked up by positioning pin on the quadrangle of the sub- workpiece of each cuboid
Body workpiece carries out position and fixes；
Step 4: the sub- workpiece end face of cuboid on two end faces up and down of the heap poststack described in step 3 by grinding or
The mode of polishing carries out mirror surface treatment；
Step 5: by way of Diffusion Welding that the sub- job stacking body of the cuboid after mirror surface treatment is each rectangular
Body workpiece carries out welding fixed, forms the sub- job stacking body of a cuboid；
Step 6: existing structure feature on the sub- job stacking body of the cuboid according to step 5 passes through machining
Mode the blade cuts are come out, complete the manufacture of entire blade.
Further, the corresponding structure feature of thin layer described in each step 1 is corresponding in turn to processing described in step 2
Specific steps on the sub- workpiece of the unified cuboid of multiple sizes are as follows: firstly, before and after each sub- workpiece of cuboid
Multiple semicircular arc grooves, uniform a pair in position of all semicircular arc grooves are processed at same position in two plate faces
It answers；Then, the leaf cross-section side is processed at the same position on the sub- workpiece surface of cuboid with multiple grooves
Upward ring structure.
Wherein, the sub- workpiece of the cuboid uses the sub- workpiece of plate, the plate thickness of the sub- workpiece of plate be 0.1mm or
10mm。
Embodiment 3
The present embodiment proposes a kind of processing method of blade with complex internal type chamber, and the technical solution taken is such as
Under:
First step hierarchical design: by complicated inner cavity workpiece according to feature, such as mesa-shaped section, radial hole is layered.For
Inner cavity is divided into multiple sub- workpiece with simple geometry feature at discontinuous place by discontinuous inner cavity contour line, for multiple
Workpiece, according to actual processing ability, need to be divided into multiple thin layers, form zigzag by miscellaneous continuous curve surface according to the thought of differential
Contour curve, approximate fits are at required full curve.
Second step layering processing: since the outer profile of complicated inner cavity workpiece is unlikely to be the rule of adaptation Diffusion Welding completely
Shape, therefore need to be by the feature machining of hierarchical design on the unified plate of size, and processed in the quadrangle of the plate of uniform sizes
Then location hole out is stacked along the third direction of workpiece.It, can for the feature on plate, such as hole need to be processed
With the separate machined in two neighboring plane, i.e., a kind of upper half of special characteristic is processed in the lower plane of upper plate, in lower plate
Upper plane machining go out corresponding lower half, needed in process it is whole the surface of workpiece is protected, avoid generating
Defect need to carry out mirror surface treatment to the upper and lower end face of workpiece, to be diffused welding after processing is completed.For diffusion welding (DW)
Attachment in addition is such as brazed, can be without the mirror surface treatment of end face.
Third step Diffusion Welding: the sub- workpiece of layering processing is stacked in a certain order, utilizes positioning pin
The relative position of workpiece is fixed, the complicated inner cavity structure that need to process is formed, be placed in Diffusion Welding equipment carry out it is connected, will point
The sub- work pieces process of layer completes the processing of complicated inner cavity at a unified entirety.
The processing of 4th one-step forming: it is machined according to the outer profile size of complicated inner cavity workpiece, completes entire workpiece
Manufacture.
Although the present invention has been disclosed in the preferred embodiment as above, it is not intended to limit the invention, any to be familiar with this
The people of technology can do various changes and modification, therefore protection of the invention without departing from the spirit and scope of the present invention
Range should subject to the definition of the claims.
Claims (5)
1. a kind of blade forming method with complex internal type chamber, which is characterized in that the manufacturing process of the blade includes: head
First, according to the overall structure of the blade, its structure is divided into multiple thin layers, and the corresponding structure of each thin layer is corresponded into processing
To the three-dimensional sub- workpiece of multiple rectangles；Then multiple sub- workpiece with leaf structure are stacked in sequence, and
Positioning pin progress position is arranged on the quadrangle of the sub- workpiece to fix；The sub- work being then stacked by welding manner
Part is welded as unified entirety, forms the cuboid workpiece of integral type；Finally, using the short transverse of cuboid workpiece as the leaf
The axial direction of piece passes through machine according to the shape and structure of the cross section of the blade since the upper surface of the cuboid workpiece
Tool processing method is by cuboid work pieces process at the production blade with inner-cavity structure.
2. forming method described in claim 1, which is characterized in that the detailed process of the blade forming are as follows:
Step 1: the planform of the blade is divided into along cross-sectional direction by multiple bands according to the structure feature of the blade
There is the thin layer of structure feature；
Step 2: the corresponding structure feature of thin layer described in each step 1 is corresponding in turn to processing in the unification of multiple sizes
On the sub- workpiece of cuboid；
Step 3: will have and stack the sub- workpiece of the multiple cuboid of step 2 according to every layer of sequence after blade layering
Get up, and location hole is set on the quadrangle of the sub- workpiece of each cuboid and passes through positioning pin for the multiple cuboids being stacked up
Workpiece carries out position and fixes；
Step 4: the sub- workpiece end face of cuboid on two end faces up and down of the heap poststack described in step 3 passes through grinding or polishing
Mode carry out mirror surface treatment；
Step 5: by each cuboid of the sub- job stacking body of the cuboid after mirror surface treatment by way of Diffusion Welding
Workpiece carries out welding fixed, forms the sub- job stacking body of a cuboid；
Step 6: existing structure feature on the sub- job stacking body of the cuboid according to step 5 passes through the side of machining
Formula comes out the blade cuts, completes the manufacture of entire blade.
3. forming method described in claim 2, which is characterized in that by the corresponding knot of thin layer described in each step 1 described in step 2
Structure feature is corresponding in turn to the specific steps processed on the sub- workpiece of the unified cuboid of multiple sizes are as follows: firstly, each
Multiple semicircular arc grooves, all semi arches are processed at same position in former and later two plate faces of the sub- workpiece of cuboid
The position of connected in star corresponds；Then, add at the same position on the sub- workpiece surface of cuboid with multiple grooves
Work goes out the ring structure on the leaf cross-section direction.
4. forming method described in claim 2, which is characterized in that the sub- workpiece of cuboid uses the sub- workpiece of plate, described flat
The plate thickness of plank workpiece is 0.1mm or 10mm.
5. blade forming method described in claim 1, which is characterized in that the blade includes front and rear panels, the foreboard and
A ring-shaped cavity is connected to by arc-shaped side wall at the both sides of the edge of back plate；The front and rear panels are all made of arc plate face
Structure, also, the arc length of the foreboard is less than the arc length of back plate, and the circular arc of the front and rear panels is towards the same as a direction；It is described
In the arc-shaped side wall of front and rear panels two sides, the arc length of the arc-shaped side wall of side is greater than the arc of the arc-shaped side wall in the other side
It is long；The different arc-shaped side wall of two arc length and the front and rear panels, which are an integral structure, makes the blade along cross section
Direction forms the cyclic structure that one end is narrow, the other end is wide；The front and rear panels are equipped with the through-hole of array distribution, also, institute
The through-hole for stating front and rear panels corresponds.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711443921.5A CN109967967A (en) | 2017-12-27 | 2017-12-27 | A kind of blade forming method with complex internal type chamber |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711443921.5A CN109967967A (en) | 2017-12-27 | 2017-12-27 | A kind of blade forming method with complex internal type chamber |
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| CN109967967A true CN109967967A (en) | 2019-07-05 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112792507A (en) * | 2021-01-04 | 2021-05-14 | 中国航空制造技术研究院 | Preparation method of titanium alloy blisk |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1610972A1 (en) * | 1988-10-17 | 1995-01-09 | Уфимский авиационный институт им.Серго Орджоникидзе | Cooled blade for gas turbine |
| JPH0756201B2 (en) * | 1984-03-13 | 1995-06-14 | 株式会社東芝 | Gas turbine blades |
| CN103089326A (en) * | 2011-10-31 | 2013-05-08 | 通用电气公司 | Method and apparatus for cooling gas turbine rotor blades |
| CN106670736A (en) * | 2016-10-19 | 2017-05-17 | 哈尔滨工业大学 | Lamination manufacturing method for large-size and complex-structure metal component |
-
2017
- 2017-12-27 CN CN201711443921.5A patent/CN109967967A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0756201B2 (en) * | 1984-03-13 | 1995-06-14 | 株式会社東芝 | Gas turbine blades |
| SU1610972A1 (en) * | 1988-10-17 | 1995-01-09 | Уфимский авиационный институт им.Серго Орджоникидзе | Cooled blade for gas turbine |
| CN103089326A (en) * | 2011-10-31 | 2013-05-08 | 通用电气公司 | Method and apparatus for cooling gas turbine rotor blades |
| CN106670736A (en) * | 2016-10-19 | 2017-05-17 | 哈尔滨工业大学 | Lamination manufacturing method for large-size and complex-structure metal component |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112792507A (en) * | 2021-01-04 | 2021-05-14 | 中国航空制造技术研究院 | Preparation method of titanium alloy blisk |
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Application publication date: 20190705 |
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