CN113369830A - Machining method for forging low-pressure turbine blade - Google Patents
Machining method for forging low-pressure turbine blade Download PDFInfo
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- CN113369830A CN113369830A CN202110741535.4A CN202110741535A CN113369830A CN 113369830 A CN113369830 A CN 113369830A CN 202110741535 A CN202110741535 A CN 202110741535A CN 113369830 A CN113369830 A CN 113369830A
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- 238000005242 forging Methods 0.000 title claims abstract description 19
- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000003754 machining Methods 0.000 title claims description 56
- 238000003801 milling Methods 0.000 claims description 30
- 210000002268 wool Anatomy 0.000 claims description 18
- 238000007789 sealing Methods 0.000 claims description 17
- 238000005498 polishing Methods 0.000 claims description 7
- 238000009825 accumulation Methods 0.000 abstract description 4
- 238000006243 chemical reaction Methods 0.000 abstract description 4
- 238000003672 processing method Methods 0.000 abstract description 4
- 238000005516 engineering process Methods 0.000 abstract description 3
- 238000012797 qualification Methods 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
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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
- B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
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- Milling Processes (AREA)
Abstract
The invention provides a processing method for forging a low-pressure turbine blade, which is characterized in that reference surfaces are positioned at two ends of a cuboid blank, and positioning processing is carried out through the reference surfaces at the two ends in all subsequent processing procedures, so that conversion of the processing reference surfaces is effectively reduced, processing steps are simplified, meanwhile, the processing references at the two ends are always consistent with the processing reference of a blade body, the accumulation of processing errors is small in the processing process, the processing efficiency is greatly improved through the processing reference end surfaces at the two ends of a blade workpiece, the processing period is shortened, meanwhile, the processing of blade structural components can be simultaneously carried out according to the processing end surfaces at the two ends of the blade workpiece, a blade structural component does not need to be added, a reference end surface is processed, the processing technology is greatly simplified, and the qualification rate of blade processing is improved.
Description
Technical Field
The invention relates to the technical field of machining of turbine blades of aero-engines, in particular to a machining method for forging low-pressure turbine blades.
Background
At present, the main steps for machining the turbine blade are as follows: the die forging blank is adopted, firstly, the datum planes are processed on the upper edge plate and the lower edge plate, then the datum planes are used for positioning, the upper edge plate and the lower edge plate are processed, and then the upper edge plate and the lower edge plate are used for positioning, and the blade body is processed. The main disadvantages of the processing method are: 1) the processing technology is complex, the processing steps are multiple, the processing period is long, and the processing efficiency is low; 2) the machining benchmark conversion is more, the machining error accumulation is large, and the qualified rate is low.
Disclosure of Invention
The invention provides a machining method for forging low-pressure turbine blades, aiming at the problems of complex machining process, multiple machining steps, long machining period, low machining efficiency, multiple machining benchmark conversion, large accumulation of machining errors and low yield in the machining of the turbine blades in the prior art.
The invention is realized by the following technical scheme:
a machining method for forging a low-pressure turbine blade comprises the following steps:
step 1, milling a reference surface: clamping the cuboid wool on a linear cutting machine, and respectively positioning and processing the reference surface at two ends of the long edge of the cuboid wool;
step 4, carrying out vacuum stress relief on the roughly milled blade workpiece;
and 7, polishing the blade workpiece to a final size by using a polishing machine to obtain the low-pressure turbine blade.
Preferably, in the step 2, the rectangular wool is processed into the shape of the blade by positioning the reference surfaces at the two ends of the rectangular wool, and the processing allowance is 5 mm.
Preferably, in step 3, the air inlet edge and the air outlet edge of the blade workpiece and the upper edge plate, the lower edge plate and the blade body of the blade basin side are processed through reference surfaces at two ends of the blade workpiece, wherein the processing allowance of the air inlet edge and the air outlet edge of the blade basin side is 1.3 mm; the machining allowance of the inner surfaces of the upper edge plate and the lower edge plate on the blade basin side is 2.5 mm.
Preferably, in step 3, the upper edge plate, the lower edge plate and the blade body on the blade back side of the blade workpiece are machined through the reference surfaces at the two ends of the blade workpiece, wherein the machining allowance of the blade body on the blade back side is 1.3mm, and the machining allowance of the inner surfaces of the upper edge plate and the lower edge plate on the blade back side is 2.5 mm.
Preferably, in step 5, the surface of the inner flow channel of the upper edge plate, the blade body, the air inlet edge, the air outlet edge, the surface of the inner flow channel of the lower edge plate and the lower edge plate of the blade workpiece are subjected to finish milling through the reference surfaces at the two ends of the blade workpiece.
Further, in finish milling, the machining allowance of the surface of the inner flow channel of the upper edge plate and the surface of the inner flow channel of the lower edge plate is 0-0.5 mm; the machining allowance of the blade body, the air inlet edge and the air exhaust edge is 0-0.02 mm.
Preferably, in step 6, the reference surfaces at two ends of the blade workpiece correspond to the bottom surfaces of the sealing teeth arranged on the upper edge plate of the blade workpiece and the bottom surfaces of the pin holes arranged on the lower edge plate of the blade workpiece respectively; and processing and removing the reference surfaces at the two ends, wherein the processing allowance is 1-1.35 mm.
Preferably, in step 6, the center of the end face of the upper edge plate and the radial center face of the pin hole of the lower edge plate are positioned by taking the center as a reference, the positioning is clamped on a four-coordinate machining center, the bottom surfaces of the sealing teeth of the upper edge plate and the bottom surfaces of the pin hole of the lower edge plate are milled, and the milling is performed until the working size is reached.
Furthermore, the bottom surfaces of the sealing teeth and the pin holes are all arc surfaces.
Preferably, the low-pressure turbine blade comprises a lower edge plate, a blade body and an upper edge plate which are sequentially connected and arranged; the upper edge plate and the lower edge plate are of circumferential arc-shaped mounting plate structures, and the end face, facing the blade body, of the lower edge plate is the surface of an inner flow channel of the lower edge plate; the end surface of the upper edge plate facing the blade body is the surface of an inner flow passage of the upper edge plate; the mounting part of the lower edge plate is provided with a pin hole, and the upper edge plate is sequentially provided with sealing teeth along the plate surface; the two sides of the blade body are respectively provided with an air inlet edge and an air outlet edge.
Compared with the prior art, the invention has the following beneficial technical effects:
the invention provides a processing method for forging a low-pressure turbine blade, which is characterized in that reference surfaces are positioned at two ends of a cuboid blank, and positioning processing is carried out through the reference surfaces at the two ends in all subsequent processing procedures, so that conversion of the processing reference surfaces is effectively reduced, processing steps are simplified, meanwhile, the processing references at the two ends are always consistent with the processing reference of a blade body, the accumulation of processing errors is small in the processing process, the processing efficiency is greatly improved through the processing reference end surfaces at the two ends of a blade workpiece, the processing period is shortened, meanwhile, the processing of blade structural components can be simultaneously carried out according to the processing end surfaces at the two ends of the blade workpiece, a blade structural component does not need to be added, a reference end surface is processed, the processing technology is greatly simplified, and the qualification rate of blade processing is improved.
Drawings
FIG. 1 is a schematic structural view of a low pressure turbine blade being processed in accordance with the present invention;
FIG. 2 is a side view of a low pressure turbine blade machined in accordance with the present invention;
FIG. 3 is a schematic illustration of the desired wool structure for a low pressure turbine blade being processed in accordance with the present invention.
In the figure: 1-a lower flange plate; 2-the surface of the inner runner of the lower edge plate; 3-leaf body; 4-air inlet side; 5-surface of inner flow channel of upper edge plate; 6-sealing teeth; 7-upper edge plate; 8-exhaust edge; 9-pin hole.
Detailed Description
The present invention will now be described in further detail with reference to specific examples, which are intended to be illustrative, but not limiting, of the invention.
The invention provides a processing method for forging a low-pressure turbine blade, which comprises the following steps:
step 1, milling a reference surface: clamping the cuboid wool on a linear cutting machine, and respectively positioning and processing the reference surface at two ends of the long edge of the cuboid wool;
step 4, carrying out vacuum stress relief on the roughly milled blade workpiece;
and 7, polishing the blade workpiece to a final size by using a polishing machine to obtain the low-pressure turbine blade.
According to the invention, through the positioning of the reference surfaces at the two ends of the cuboid wool, as shown in figure 3, the cuboid wool is processed into the blade shape, and the processing allowance is 5 mm.
Processing an air inlet edge 4 and an air outlet edge 8 of the blade workpiece, an upper edge plate 7, a lower edge plate 1 and a blade body 3 on the blade basin side through reference surfaces at two ends of the blade workpiece, wherein the machining allowance of the air inlet edge 4 and the air outlet edge 8 on the blade basin side is 1.3 mm; the machining allowance of the inner surfaces of the upper edge plate 7 and the lower edge plate 1 on the blade basin side is 2.5 mm.
The upper edge plate 7, the lower edge plate 1 and the blade body 3 on the blade back side of the blade workpiece are processed through the datum planes at the two ends of the blade workpiece, wherein the machining allowance of the blade body 3 on the blade back side is 1.3mm, and the machining allowance of the inner surfaces of the upper edge plate 7 and the lower edge plate 1 on the blade back side is 2.5 mm.
Finish milling is carried out on the inner flow channel surface 5, the blade body 3, the air inlet edge 4, the air exhaust edge 8, the inner flow channel surface 2 of the lower edge plate and the lower edge plate 1 of the blade workpiece through reference surfaces at two ends of the blade workpiece, wherein in the finish milling, the machining allowance of the inner flow channel surface 5 of the upper edge plate and the inner flow channel surface 2 of the lower edge plate is 0-0.5 mm; the machining allowance of the blade body 3, the air inlet edge 4 and the air exhaust edge 8 is 0-0.02 mm.
The datum planes at the two ends of the blade workpiece respectively correspond to the bottom surfaces of the sealing teeth 6 of the upper edge plate 7 of the blade workpiece and the bottom surfaces of the pin holes 9 of the lower edge plate 1 of the blade workpiece; and processing and removing the reference surfaces at the two ends, wherein the processing allowance is 1-1.35 mm.
Positioning by taking the center of the end face of the upper edge plate 7 and the radial center face of the pin hole 9 of the lower edge plate 1 as references, clamping on a four-coordinate machining center, milling the bottom surfaces of the sealing teeth 6 of the upper edge plate 7 and the pin hole 9 of the lower edge plate 1, and machining to a working size; wherein, the bottom surfaces of the sealing teeth 6 and the pin holes 9 are both arc surfaces.
According to fig. 1 and 2, the low-pressure turbine blade comprises a lower edge plate 1, a blade body 3 and an upper edge plate 7 which are sequentially connected and arranged; the upper edge plate 7 and the lower edge plate 1 are of circumferential arc-shaped mounting plate structures, and the end face, facing the blade body 3, of the lower edge plate 1 is the surface 2 of the inner flow channel of the lower edge plate; the end surface of the upper edge plate 7 facing the blade body 3 is an upper edge plate inner flow passage surface 5; the mounting part of the lower edge plate 1 is provided with a pin hole 9, and the upper edge plate 7 is sequentially provided with sealing teeth 6 along the plate surface; the two sides of the blade body 3 are respectively provided with an air inlet edge 4 and an air outlet edge 8.
Examples
The low-pressure turbine blade is made of a cuboid wool, and consists of an upper edge plate 7, an upper edge plate inner flow passage surface 5, a blade body 3, a lower edge plate inner flow passage surface 2 and a lower edge plate 1. Go up the flange plate 7 and lower flange plate 1 and be circumference circular arc type mounting plate structure, go up the flange plate 7 and go up the inboard runner surface 5 of edge and connect, go up the inboard runner surface 5 of edge and be connected with blade 3, blade 3 is connected with lower flange plate internal flow surface 2, and lower flange plate internal flow surface 2 is connected with lower flange plate 1. The processing steps are as follows:
milling a reference surface: clamping the cuboid blank on a linear cutting machine, cutting the periphery of the cuboid blank to form a reference surface, cutting the approximate shape of the blade, and reserving a machining allowance of 5mm at least;
roughly milling the upper and lower edge plates and the molded surface on the side of the leaf basin: clamping a blade workpiece with a machined datum plane on a four-coordinate machining center, positioning and roughly milling an inner flow channel surface 5 of an upper edge plate on the side of a blade basin, a blade body 3 of the side of the blade basin, an air inlet edge 4, an air outlet edge 8 and an inner flow channel surface 2 of a lower edge plate on the side of the blade basin by using datum planes at two ends, reserving 2.5mm on the inner flow channel surface of the upper edge plate and the lower edge plate on the side of the blade basin, and reserving 1.3mm machining allowance on the molded surface of the side of the blade basin;
roughly milling the upper and lower edge plates and the molded surface on the back side of the blade: clamping the blade with the machined reference surface on a four-coordinate machining center, positioning and roughly milling an inner flow channel surface 5 of an upper edge plate on the back side of the blade, a blade body 3 of the back side of the blade and an inner flow channel surface 2 of a lower edge plate on the back side of the blade by using the reference surfaces at two ends, reserving 2.5mm on the inner flow channel surface of the upper edge plate and the lower edge plate on the back side of the blade, and reserving 1.3mm machining allowance on the blade body on the back side of the blade;
vacuum stress relief: carrying out vacuum stress relief on the roughly milled blade workpiece;
finish milling blade profile, upper and lower marginal plates and pin holes: clamping the roughly milled blade on a five-coordinate machining center, positioning and finish milling an upper edge plate inner flow channel surface 5, a blade body 3, an air inlet edge 4, an air exhaust edge 8, a lower edge plate inner flow channel surface 2 and a lower edge plate 1 by using reference surfaces at two ends, reserving machining allowances of 0-0.5 mm on the upper edge plate inner flow channel surface 5 and the lower edge plate inner flow channel surface 2, machining the lower edge plate 1 and pin holes to the final size, and reserving machining allowances of 0-0.02 mm on the blade body 3, the air inlet edge 4 and the air exhaust edge 8;
wire-cutting two end faces: and (3) linear cutting the bottom surfaces of the sealing teeth 5 and the pin holes 9, removing the reference surfaces of the two surfaces, and reserving 1-1.35mm of machining allowance.
Milling the sealing teeth and the bottom surfaces of the pin holes: and positioning and clamping the end surface of the upper edge plate 7 and the center of the pin hole 9 and the end surface, clamping the end surface on a four-coordinate machining center, and milling the bottom surfaces of the sealing tooth 6 and the pin hole 9, wherein the end surface of the sealing tooth 6 and the bottom surface of the pin hole 9 are arc surfaces. And (5) processing to a final size.
Polishing the profile and the inner edge plate surface of the blade body: the airfoil profile 3, the upper edge plate inner flow surface 5 and the lower edge plate inner flow surface 2 are polished to final dimensions with a polisher.
Claims (10)
1. A machining method for forging a low-pressure turbine blade is characterized by comprising the following steps:
step 1, milling a reference surface: clamping the cuboid wool on a linear cutting machine, and respectively positioning and processing the reference surface at two ends of the long edge of the cuboid wool;
step 2, processing the shape of the blade of the cuboid wool according to the positioning of the reference surfaces at the two ends of the cuboid wool to obtain a blade workpiece;
step 3, roughly milling a structural component of the blade workpiece, clamping the blade workpiece with the reference surfaces at the two ends on a four-coordinate machining center, and machining the structural component of the blade workpiece;
step 4, carrying out vacuum stress relief on the roughly milled blade workpiece;
step 5, finely milling structural components of the blade workpiece;
step 6, linearly cutting reference surfaces at two ends of the blade workpiece, and milling the cut bottom surface;
and 7, polishing the blade workpiece to a final size by using a polishing machine to obtain the low-pressure turbine blade.
2. The machining method for forging the low-pressure turbine blade as claimed in claim 1, wherein in the step 2, the rectangular parallelepiped blank is machined according to the shape of the blade by positioning the reference surfaces at the two ends of the rectangular parallelepiped blank, and the machining allowance is 5 mm.
3. The machining method for forging the low-pressure turbine blade is characterized in that in step 3, the air inlet edge (4) and the air outlet edge (8) of the blade workpiece and the upper edge plate (7), the lower edge plate (1) and the blade body (3) of the blade basin side are machined through reference surfaces at two ends of the blade workpiece, wherein the machining allowance of the air inlet edge (4) and the air outlet edge (8) of the blade basin side is 1.3 mm; the machining allowance of the inner surfaces of the upper edge plate (7) and the lower edge plate (1) on the blade basin side is 2.5 mm.
4. The machining method for forging the low-pressure turbine blade as claimed in claim 1, wherein in the step 3, the upper edge plate (7), the lower edge plate (1) and the blade body (3) on the blade back side of the blade workpiece are machined by the reference surfaces of the two ends of the blade workpiece, wherein the machining allowance of the blade body (3) on the blade back side is 1.3mm, and the machining allowance of the inner surfaces of the upper edge plate (7) and the lower edge plate (1) on the blade back side is 2.5 mm.
5. The machining method for forging the low-pressure turbine blade as claimed in claim 1, wherein in the step 5, the upper edge plate inner flow passage surface (5), the blade body (3), the air inlet edge (4), the air outlet edge (8), the lower edge plate inner flow passage surface (2) and the lower edge plate (1) of the blade workpiece are subjected to finish milling through the reference surfaces of the two ends of the blade workpiece.
6. The machining method for forging the low-pressure turbine blade as claimed in claim 5, wherein in finish milling, the machining allowance of the upper edge plate inner flow passage surface (5) and the lower edge plate inner flow passage surface (2) is 0-0.5 mm; the machining allowance of the blade body (3), the air inlet edge (4) and the air exhaust edge (8) is 0-0.02 mm.
7. The machining method for forging the low-pressure turbine blade as claimed in claim 1, wherein in the step 6, the datum planes at the two ends of the blade workpiece correspond to the bottom surfaces of the sealing teeth (6) arranged on the upper edge plate (7) of the blade workpiece and the bottom surfaces of the pin holes (9) arranged on the lower edge plate (1) of the blade workpiece respectively; and processing and removing the reference surfaces at the two ends, wherein the processing allowance is 1-1.35 mm.
8. The machining method for forging the low-pressure turbine blade as claimed in claim 1, wherein in step 6, the center of the end face of the upper edge plate (7) and the radial center face of the pin hole (9) of the lower edge plate (1) are used as references for positioning, the positioning is carried out by clamping on a four-coordinate machining center, and the bottom faces of the sealing teeth (6) of the upper edge plate (7) and the bottom faces of the pin hole (9) of the lower edge plate (1) are subjected to milling machining and machined to working dimensions.
9. The machining method for forging the low-pressure turbine blade as claimed in claim 8, wherein the bottom surfaces of the sealing tooth (6) and the pin hole (9) are both arc surfaces.
10. The machining method for forging the low-pressure turbine blade as claimed in claim 1, wherein the low-pressure turbine blade comprises a lower edge plate (1), a blade body (3) and an upper edge plate (7) which are sequentially connected and arranged; the upper edge plate (7) and the lower edge plate (1) are of circumferential arc-shaped mounting plate structures, and the end face, facing the blade body (3), of the lower edge plate (1) is a lower edge plate inner flow channel surface (2); the end surface of the upper edge plate (7) facing the blade body (3) is an inner flow passage surface (5) of the upper edge plate; the mounting part of the lower edge plate (1) is provided with a pin hole (9), and the upper edge plate (7) is sequentially provided with sealing teeth (6) along the plate surface; the two sides of the blade body (3) are respectively provided with an air inlet edge (4) and an air outlet edge (8).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110741535.4A CN113369830A (en) | 2021-06-30 | 2021-06-30 | Machining method for forging low-pressure turbine blade |
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| CN202110741535.4A CN113369830A (en) | 2021-06-30 | 2021-06-30 | Machining method for forging low-pressure turbine blade |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114888610A (en) * | 2022-05-31 | 2022-08-12 | 哈尔滨汽轮机厂有限责任公司 | Tooth-shaped positioning block for positioning blade and clamping and aligning method for machining blade steam passage |
| CN116652520A (en) * | 2023-03-27 | 2023-08-29 | 重庆江增船舶重工有限公司 | A milling method for turbine blades of a marine supercharger |
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| CN116652520A (en) * | 2023-03-27 | 2023-08-29 | 重庆江增船舶重工有限公司 | A milling method for turbine blades of a marine supercharger |
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Application publication date: 20210910 |