CN111375992B - Manufacturing method of large efficient steering oar shell - Google Patents
Manufacturing method of large efficient steering oar shell Download PDFInfo
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- CN111375992B CN111375992B CN201911322100.5A CN201911322100A CN111375992B CN 111375992 B CN111375992 B CN 111375992B CN 201911322100 A CN201911322100 A CN 201911322100A CN 111375992 B CN111375992 B CN 111375992B
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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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Abstract
The invention provides a method for manufacturing a large-scale efficient rudder propeller shell, which comprises the following steps: the method comprises the steps of sand blasting, rough machining, aging treatment, finish machining, magnetic powder inspection and drilling and reaming; the intersection angle of the axis of the bearing inner hole of the shell is theta, theta is corresponding to (0, 90) and U (90 and 180), a tool flange conversion method is adopted in the method, the machining allowance is determined by comparing the measurement result on a machine tool with the size of a theoretical drawing, the center of the inner hole is aligned, multiple clamping correction is avoided, the efficiency is improved, and the machining quality of a workpiece is ensured.
Description
Technical Field
The invention relates to a rudder propeller shell processing technology, in particular to a preparation technology for processing a large shell with a non-90-degree included angle.
Background
At present, when a rudder propeller box is produced, due to requirements of a ship body, a ship shape, hydrodynamic force and the like, the meshing angle of the bevel gear is not 90 degrees, the transmission mode necessarily causes that a bearing hole in the box is changed along with the meshing angle, and the intersection angle of the axes of corresponding bearing inner holes is also changed.
At the moment, the traditional box body processing technology cannot meet the generation requirement, and in the box body processing process, on one hand, the difficulty of clamping correction exists, and on the other hand, the selection and the conversion of the reference in the rough machining and finish machining process are difficult to realize.
Disclosure of Invention
The invention aims to provide a method for manufacturing a large efficient steering oar shell, aiming at the problems of difficult shell clamping correction and difficult reference selection in the machining process when the meshing angle of a bevel gear is not 90 degrees.
The technical scheme of the invention is as follows:
the invention provides a method for manufacturing a large-scale efficient rudder propeller shell, which comprises the following steps: the method comprises the steps of sand blasting, rough machining, aging treatment, finish machining, magnetic powder inspection and drilling and reaming; the intersection angle of the bearing inner hole axis of the shell is theta, theta is belonged to (0, 90 degrees) and U (90 degrees and 180 degrees), and the rough machining step specifically comprises the following steps:
s1, mounting process legs on the outer sides of the shell workpieces, flattening the shell workpieces by using equal-height blocks on a workbench of the horizontal machining center, and firmly pressing and correcting the shell workpieces through the process legs by the workbench;
s2, arranging a positioning reference piece below the side of the shell workpiece, wherein the positioning reference piece is circular;
s3, milling the bottom surface A of the shell workpiece to form a smooth surface, and trial boring the inner hole of the first bearing; measuring and recording distances d1 and d2, wherein the distance d1 represents the distance between the bottom surface A of the shell workpiece and the horizontal tangent of the bottom surface of the positioning reference piece, and the distance d2 represents the distance between the axis of the inner hole of the first bearing and the vertical tangent of the outer side surface of the positioning reference piece;
s4, rotating the workbench clockwise by theta ', wherein theta' is 180-theta to trial bore the milled surface of the side surface B of the shell workpiece and the inner hole of the second bearing to form a smooth surface; measuring and recording distances d3 and d4, wherein the distance d3 represents the distance between the axis of the inner hole of the second bearing and the tangent of the bottom surface of the positioning reference piece parallel to the axis, and the distance d4 represents the distance between the side surface B of the shell workpiece and the horizontal tangent of the outer side of the positioning reference piece parallel to the side surface B;
s5, calculating theoretical distances d3 'and d 4' according to the distances d1 and d2 acquired in the step S3, calculating machining allowances delta d3 of the side face B, namely d3-d3 'and delta d4, namely d4-d 4' according to the theoretical distances d3 ', d 4' and the actually measured distances d3 and d4, and if negative values exist in the machining allowances delta d3 and delta d4, enabling the original casting of the shell workpiece to be unqualified and stopping machining, otherwise, continuing to be S6;
s6, rotating the workbench clockwise by 180 degrees, and trial boring the milled surface of the side surface D of the shell workpiece and the inner hole of the third bearing;
s7, rotating the workbench in the anticlockwise direction theta ', wherein theta' is 180-theta to trial bore the milled surface of the top surface C of the shell workpiece and the inner hole of the fourth bearing; finishing rough machining;
correspondingly, the finish machining step respectively performs reference alignment on the first bearing inner hole, the second bearing inner hole, the third bearing inner hole and the fourth bearing inner hole of the shell workpiece according to S2.3, S2.4, S2.6 and S2.7, and finish boring is performed to corresponding accuracy.
Further, the surface treatment grade reaches Sa2.5; the area outside the machining area was primed within 4 hours after blasting.
Further, the circular positioning reference part adopts a flange.
Furthermore, when trial boring is carried out on the first bearing inner hole, the second bearing inner hole, the third bearing inner hole and the fourth bearing inner hole, allowance is reserved on single sides, and the allowance is 3-7mm, preferably 5 mm.
Further, the bottom surface a, the top surface C, and the end faces of the side surfaces B, D of the case workpiece are milled with a margin of 0.5 to 1.5mm, preferably 1 mm.
Further, the aging treatment steps are as follows: standing the roughly machined shell workpiece for a certain time; is 36 to 60 hours, preferably 48 hours.
Further, the magnetic powder inspection comprises the following steps: and (4) carrying out magnetic powder inspection or dye check inspection on the machined surface and the bearing inner hole after machining.
Further, the drilling and reaming steps are as follows: and after the magnetic powder inspection is qualified, flattening the process legs again, correcting the inner holes and end face runout of the bearings on the end faces, rotationally positioning the workbench according to the rough machining step, further machining end face through holes, screw holes and pin holes in the bottom surface A, the top surface C and the side surface B, D, and milling end face sealing grooves, chamfers and R angles of all parts.
Further, the method for correcting the inner bore of the bearing at each end face and the end face run-out comprises the following steps: horizontally placing a shell workpiece, rotationally positioning a workbench according to the rough machining step, and correcting the inner hole and each end face of the bearing by using a dial indicator, wherein the correction precision of the dial indicator is less than or equal to 0.02 mm.
Furthermore, the process legs are arranged on two sides of the shell workpiece and are positioned outside the processing area.
The invention has the beneficial effects that:
aiming at the processing difficulty of the large box body with the included angle of not 90 degrees, the process legs are arranged on the outer side of the shell workpiece, and the workbench is used for firmly pressing and correcting the shell workpiece through the process legs. Because the box body is not in a common 90-degree form, the box body is a cast box body, and auxiliary support is not easy to increase through welding during processing, the stability of milling surface and boring on a horizontal processing center is ensured through reasonably designing the process legs during casting and clamping and correcting the process legs.
According to the invention, the four end surfaces and the four bearing holes are respectively machined through the rotation of the workbench, the problems of machining deformation and the like are considered, the machining process is divided into rough machining and finish machining, the aging treatment is required after the rough machining, and then the finish machining is carried out, so that the machining quality and the precision are effectively improved.
The flange is used as a positioning reference piece, the machining allowance is determined by comparing the measurement result on the machine tool with the size of a theoretical drawing, and the problems of allowance distribution and reference determination in machining are solved; the center of the inner hole is aligned, multiple times of clamping and correction are avoided, the efficiency is improved, and the processing quality of the workpiece is ensured.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout.
Fig. 1 shows a schematic view of the housing workpiece structure of the present invention.
In the figure: 1. a work table; 2. a process leg; 3. a housing workpiece; 4. positioning a reference piece; 5. a first bearing bore; 6. a second bearing inner bore; 7. a third bearing bore; 8. the fourth bearing hole.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. While the preferred embodiments of the present invention are shown in the drawings, it should be understood that the present invention may be embodied in various forms and should not be limited to the embodiments set forth herein.
A method for manufacturing a large-sized high-efficiency rudder propeller shell is characterized in that the intersection angle of the axes of inner holes of a bearing of the shell is theta, theta is belonged to (0, 90 degrees) and U (90 degrees and 180 degrees), and 87 degrees are taken as an example, the following steps are adopted:
step 1 (blasting): carrying out sand blasting on the shell workpiece 3, wherein the surface treatment grade reaches Sa2.5; the area outside the machining area was primed within 4 hours after blasting.
Step 2 (rough machining): as shown in figure 1 of the drawings, in which,
s1, mounting the process legs 2 on the outer sides of the shell workpieces 3, flattening the shell workpieces 3 by using equal-height blocks on a workbench 1 of the horizontal machining center, and firmly pressing and correcting the shell workpieces 3 by the workbench (1) through the process legs 2;
s2, arranging a positioning reference piece 4 below the side of the shell workpiece 3, wherein the positioning reference piece 4 is circular and adopts a flange;
s3, milling the bottom surface A of the shell workpiece 3 to form a smooth surface, and trial boring the first bearing inner hole 5; measuring and recording distances d1 and d2, wherein the distance d1 represents the distance between the bottom surface A of the housing workpiece 3 and the horizontal tangent of the bottom surface of the positioning reference piece 4, and the distance d2 represents the distance between the axis of the first bearing inner hole 5 and the vertical tangent of the outer side surface of the positioning reference piece 4;
s4, rotating the workbench 1 clockwise by 93 degrees, and trial boring the milling surface of the side surface B of the shell workpiece 3 and the inner hole 6 of the second bearing to form a smooth surface; measuring and recording distances d3 and d4, wherein the distance d3 represents the distance between the axis of the second bearing inner hole 6 and the tangent of the bottom surface of the positioning reference member 4 parallel to the axis, and the distance d4 represents the distance between the side surface B of the housing workpiece 3 and the horizontal tangent of the outer side of the positioning reference member 4 parallel to the side surface B;
s5, calculating theoretical distances d3 'and d 4' according to the distances d1 and d2 obtained in step S3, calculating the theoretical distances by using a mathematical formula, drawing in CAD to directly extract results, determining theoretical values d3 ', d 4', and field-measured values d3 and d4, wherein the difference between the theoretical values and the actual values is a machining allowance to be machined, and the machining allowance Δ d3 is d3-d3 ', and Δ d4 is d4-d 4', if negative values appear in the machining allowances Δ d3 and Δ d4, the original casting of the shell workpiece 3 is unqualified, and machining is stopped, otherwise, continuing to perform S6; ,
s6, rotating the workbench 1 clockwise by 180 degrees, and trial boring the milled surface of the side surface D of the shell workpiece 3 and the inner hole 7 of the third bearing;
s7, rotating the workbench 1 anticlockwise by theta ', wherein theta' is 180-theta to trial bore the milled surface of the top surface C of the shell workpiece 3 and the inner hole 8 of the fourth bearing; finishing rough machining;
step 3 (aging treatment): standing the roughly machined shell workpiece 3 for 48 hours;
step 4 (finishing): the finish machining step performs reference alignment on the first bearing inner hole 5, the second bearing inner hole 6, the third bearing inner hole 7 and the fourth bearing inner hole 8 of the housing workpiece 3 according to rough machining S3, S4, S6 and S7, respectively, and finish boring machining is performed to a corresponding accuracy.
Step 5 (magnetic particle inspection): and (4) carrying out magnetic powder inspection or dye check inspection on the machined surface and the bearing inner hole after machining.
Step 6 (drilling and reaming): and after the magnetic powder inspection is qualified, flattening the process legs again, correcting the inner holes and end face runout of the bearings on the end faces, rotationally positioning the workbench 1 according to the rough machining step, further machining end face through holes, screw holes and pin holes of the bottom surface A, the top surface C and the side surface B, D, and milling end face sealing grooves, chamfers and R angles of all parts.
Wherein: the method for correcting the inner hole of the bearing on each end face and the end face run-out comprises the following steps: the shell workpiece 3 is horizontally placed, the workbench 1 is rotationally positioned according to the rough machining step, and the bearing inner hole and each end face are corrected by using a dial indicator, wherein the correction precision of the dial indicator is less than or equal to 0.02 mm.
In the rough machining, when trial boring is carried out on the first bearing inner hole 5, the second bearing inner hole 6, the third bearing inner hole 7 and the fourth bearing inner hole 8, allowance is reserved on single sides, and the allowance is 3-7mm, preferably 5 mm; the bottom surface a, the top surface C and the end faces of the side surfaces B, D of the housing workpiece 3 are milled with a margin of 0.5 to 1.5mm, preferably 1 mm.
Having described embodiments of the present invention, the foregoing description is intended to be exemplary, not exhaustive, and not limited to the embodiments disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. A method of manufacturing a large high efficiency rudder propeller housing, the method comprising: the method comprises the steps of sand blasting, rough machining, aging treatment, finish machining, magnetic powder inspection and drilling and reaming; the method is characterized in that: the intersection angle of the bearing inner hole axis of the shell is theta, theta is belonged to (0, 90 degrees) and U (90 degrees and 180 degrees), and in the method, the rough machining step specifically comprises the following steps:
s1, mounting a process leg (2) on the outer side of the shell workpiece (3), flattening the shell workpiece (3) by using equal-height blocks on a workbench (1) of a horizontal machining center, and firmly pressing and correcting the shell workpiece (3) by the workbench (1) through the process leg (2);
s2, arranging a positioning reference piece (4) below the side of the shell workpiece (3), wherein the positioning reference piece (4) is circular;
s3, milling the bottom surface A of the shell workpiece (3) to form a smooth surface, and trial boring the first bearing inner hole (5); measuring and recording distances d1 and d2, wherein the distance d1 represents the distance between the bottom surface A of the shell workpiece (3) and the horizontal tangent of the bottom surface of the positioning reference piece (4), and the distance d2 represents the distance between the axis of the first bearing inner hole (5) and the vertical tangent of the outer side surface of the positioning reference piece (4);
s4, rotating the workbench (1) clockwise by theta ', wherein theta' is 180-theta to trial bore the milled surface of the side surface B of the shell workpiece (3) and the inner hole (6) of the second bearing to form a smooth surface; measuring and recording distances d3 and d4, wherein the distance d3 represents the distance between the axis of the inner hole (6) of the second bearing and the tangent of the bottom surface of the positioning reference piece (4) parallel to the axis, and the distance d4 represents the distance between the side surface B of the shell workpiece (3) and the horizontal tangent of the outer side of the positioning reference piece (4) parallel to the side surface B;
s5, calculating theoretical distances d3 'and d 4' according to the distances d1 and d2 acquired in the step S3, calculating machining allowances delta d3 of the side face B, namely d3-d3 'and delta d4, namely d4-d 4' according to the theoretical distances d3 ', d 4' and the actually measured distances d3 and d4, and if negative values exist in the machining allowances delta d3 and delta d4, enabling the original casting of the shell workpiece (3) to be unqualified and stopping machining, otherwise, continuing to perform S6;
s6, rotating the workbench (1) clockwise by 180 degrees, and trial boring the milled surface of the side surface D of the shell workpiece (3) and the inner hole (7) of the third bearing;
s7, rotating the workbench (1) in the anticlockwise direction by theta ', wherein theta' is 180-theta to trial bore the milled surface of the top surface C of the shell workpiece (3) and the inner hole (8) of the fourth bearing; finishing rough machining;
correspondingly, the finish machining step respectively performs reference alignment on the first bearing inner hole (5), the second bearing inner hole (6), the third bearing inner hole (7) and the fourth bearing inner hole (8) of the shell workpiece (3) according to S3, S4, S6 and S7, and finish boring is performed to corresponding accuracy.
2. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 1, characterized in that: in the sand blasting step, the surface treatment grade reaches Sa2.5; the area outside the machining area was primed within 4 hours after blasting.
3. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 1, characterized in that: the circular positioning reference piece (4) adopts a flange.
4. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 1, characterized in that: when the first bearing inner hole (5), the second bearing inner hole (6), the third bearing inner hole (7) and the fourth bearing inner hole (8) are subjected to trial boring, allowance is reserved on single sides, and the allowance is 3-7 mm.
5. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 1, characterized in that: and margins are reserved on the bottom surface A, the top surface C and the end surface milling surface of the side surface B, D of the shell workpiece (3), and the margin is 0.5-1.5 mm.
6. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 1, characterized in that: the aging treatment steps are as follows: standing the roughly machined shell workpiece (3) for a certain time; is 36-60 hours.
7. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 1, characterized in that: the magnetic powder inspection comprises the following steps: and (4) carrying out magnetic powder inspection or dye check inspection on the machined surface and the bearing inner hole after machining.
8. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 1, characterized in that: the drilling and reaming steps are as follows: and after the magnetic powder inspection is qualified, flattening the process legs again, correcting the inner holes and end face runout of the bearings on the end faces, rotationally positioning the workbench (1) according to the rough machining step, further machining end face through holes, screw holes and pin holes of the bottom surface A, the top surface C and the side surface B, D, milling end face sealing grooves, and chamfering and R angles of all parts.
9. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 8, wherein the manufacturing method comprises the following steps: the method for correcting the inner hole of the bearing on each end face and the end face run-out comprises the following steps: the shell workpiece (3) is horizontally placed, the workbench (1) is rotationally positioned according to the rough machining step, the bearing inner hole and each end face are corrected by using a dial indicator, and the correction precision of the dial indicator is less than or equal to 0.02 mm.
10. The manufacturing method of the large-sized high-efficiency rudder propeller shell according to claim 1, characterized in that: the process legs (2) are arranged on two sides of the shell workpiece (3) and are positioned outside the processing area.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2814507A1 (en) * | 1977-04-01 | 1978-10-12 | Aerospatiale | METHOD OF MANUFACTURING A FASTENED TRANSITION PIPE FOR ADJUSTING ROD AND ADJUSTING ROD PRODUCED AFTER THAT |
| CN204053549U (en) * | 2014-02-24 | 2014-12-31 | 珠海格力电器股份有限公司 | Technological leg device for machining part by machine tool |
| CN105935843A (en) * | 2016-05-19 | 2016-09-14 | 武汉船用机械有限责任公司 | Welding method for structural part |
-
2019
- 2019-12-19 CN CN201911322100.5A patent/CN111375992B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2814507A1 (en) * | 1977-04-01 | 1978-10-12 | Aerospatiale | METHOD OF MANUFACTURING A FASTENED TRANSITION PIPE FOR ADJUSTING ROD AND ADJUSTING ROD PRODUCED AFTER THAT |
| CN204053549U (en) * | 2014-02-24 | 2014-12-31 | 珠海格力电器股份有限公司 | Technological leg device for machining part by machine tool |
| CN105935843A (en) * | 2016-05-19 | 2016-09-14 | 武汉船用机械有限责任公司 | Welding method for structural part |
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