CN115383402B - Impeller assembly machining method - Google Patents
Impeller assembly machining method Download PDFInfo
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- CN115383402B CN115383402B CN202210967390.4A CN202210967390A CN115383402B CN 115383402 B CN115383402 B CN 115383402B CN 202210967390 A CN202210967390 A CN 202210967390A CN 115383402 B CN115383402 B CN 115383402B
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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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- 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
- B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
Abstract
The disclosure provides a processing method of an impeller assembly, and belongs to the field of propellers. The processing method comprises the following steps: rough turning is carried out on the inner hole wall and the end surfaces of the two ends of the hub of the impeller, the outer peripheral wall of the rim of the impeller and the end surfaces of the two ends; rough milling is carried out on blades of the impeller; a plurality of first dovetail grooves are processed on the peripheral wall of the rim; sleeving the rotor assembly outside the rim; sleeving the outer circle sheath outside the rotor assembly; coaxially arranging two annular end plates at two ends of the outer circle sheath, and welding the annular end plates with the outer circle sheath and the rim; and (3) carrying out finish machining on the blades, the hub, the rim, the outer circle sheath and the annular end plate. Because the rough machining is performed before the assembly, a certain machining allowance is reserved, and the finish machining is not performed yet, the influence of assembly errors in the assembly process and welding deformation in the welding process on the whole impeller assembly can be eliminated through subsequent finish machining, and the whole precision of the impeller assembly is ensured.
Description
Technical Field
The disclosure relates to the field of propellers, and in particular relates to a processing method of an impeller assembly.
Background
The propeller is an important component in the power system of a ship. Impellers are an important structure of a propeller to power a ship by rotation.
The electric propeller is a novel propeller driven by electric power, in the electric propeller, an impeller and a rotor are integrated together to form an impeller assembly, the structure is complex, and the requirements on the process are high. The processing technology of the impeller in the traditional propeller cannot ensure the precision of the impeller component, so that the performance of the electric propeller is greatly limited.
Disclosure of Invention
The embodiment of the disclosure provides a processing method of an impeller assembly, which can improve the processing precision of the impeller assembly and is beneficial to further improving the performance of an electric propeller. The technical scheme is as follows:
the embodiment of the disclosure provides a processing method of an impeller assembly, wherein the impeller assembly comprises an impeller, a rotor assembly, an outer circle sheath and two annular end plates, the impeller comprises a hub, a rim and a plurality of blades, the rim is coaxially sleeved outside the hub, and the blades are positioned between the hub and the rim and are respectively connected with the hub and the rim;
the rotor assembly comprises a magnetic yoke and a plurality of magnetic steels, the magnetic yoke is coaxially sleeved outside the rim, and the magnetic steels are circumferentially arranged on the magnetic yoke;
the outer circle sheath is coaxially sleeved outside the rotor assembly, and the two annular end plates are respectively positioned at two ends of the outer circle sheath and are connected with the outer circle sheath and the rim;
the processing method comprises the following steps:
providing an impeller, and roughly turning the inner hole wall and two end surfaces of a hub of the impeller, the outer peripheral wall of a rim of the impeller and the two end surfaces;
rough milling is carried out on the blades of the impeller;
a plurality of first dovetail grooves are processed on the peripheral wall of the rim, the first dovetail grooves extend from one end of the rim to the other end, and the plurality of first dovetail grooves are distributed along the circumferential direction of the impeller;
sleeving the rotor assembly outside the rim, enabling parts between adjacent first dovetail grooves on the rim to be clamped into second dovetail grooves on the inner peripheral wall of the magnetic yoke, and enabling parts between adjacent second dovetail grooves on the inner peripheral wall of the magnetic yoke to be clamped into the first dovetail grooves;
sleeving the outer circular sheath outside the rotor assembly;
coaxially arranging the two annular end plates at two ends of the outer circular sheath, and welding the annular end plates with the outer circular sheath and the rim;
and finishing the blades, the hub, the rim, the outer circular sheath and the annular end plate.
Optionally, after the rough milling of the blades of the impeller, the processing method further includes:
and carrying out dye check on the impeller.
Optionally, the machining a plurality of first dovetail grooves on the outer peripheral wall of the rim includes:
a first dovetail groove is processed on the peripheral wall of the rim by adopting linear cutting through a numerical control machine tool;
checking the one first dovetail groove;
if the first dovetail groove is qualified, machining the rest first dovetail groove on the peripheral wall of the rim;
and if the inspection of the first dovetail groove is not qualified, trimming the first dovetail groove, and after adjusting a processing program for processing the first dovetail groove based on the inspection result, processing the rest first dovetail groove on the outer peripheral wall of the rim.
Optionally, the checking the first dovetail groove at least includes checking a machining size and machining precision of the first dovetail groove.
Optionally, the annular end plate is welded with the outer circular sheath and the rim by laser.
Optionally, the finishing the blades, the hub, the rim, the outer cylindrical jacket, and the annular end plate includes:
respectively carrying out finish milling on two sides of the blade according to the three-dimensional model and the leaf surface model value of the impeller;
finish turning is carried out on the inner hole wall and the end surfaces of the two ends of the hub;
and carrying out finish turning on the end surfaces of the two ends of the rim, the peripheral wall of the outer circle sheath and the surfaces of the two annular end plates far away from the rotor assembly.
Optionally, the method further comprises:
and carrying out dye check on the finish machining parts of the blades, the hub, the rim, the outer circle sheath and the annular end plate.
Optionally, the single-side allowance of the impeller blade is 0.8 mm-1.2 mm when the impeller blade is rough milled.
Optionally, the processing method further comprises:
screw holes are machined in the hub.
Optionally, a water lubricated support bearing and a thrust disc are mounted in the hub.
The technical scheme provided by the embodiment of the disclosure has the beneficial effects that at least:
the rough machining of the impeller is completed by rough turning the hub and the rim of the impeller and then rough milling the blades. And then, a first dovetail groove for assembling the rotor assembly is processed on the rim, the rotor assembly is sleeved outside the rim, and the magnetic yoke of the rotor assembly and the rim are assembled together through the first dovetail groove and the second dovetail groove. After the rotor assembly is assembled, an outer circular sheath is sleeved outside the rotor assembly, and two annular end plates are assembled and welded. After the welding is finished, the impeller is finished, and the outer circular sheath and the annular end plate are finished. Through carrying out the equipment of impeller subassembly after impeller rough machining, then weld and finish machining, owing to carry out the rough machining before the equipment, leave certain machining allowance, still do not carry out finish machining, consequently the assembly error in the equipment in-process, the welding deformation in the welding process is to the holistic influence that produces of impeller subassembly, can obtain the elimination through subsequent finish machining, makes the holistic precision of impeller subassembly obtain guaranteeing, is favorable to further promoting electric propeller's performance.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings required for the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and other drawings may be obtained according to these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 is a schematic structural view of an impeller assembly of a propeller provided in an embodiment of the present disclosure;
FIG. 2 is a cross-sectional view of the impeller assembly shown in FIG. 1;
FIG. 3 is a flow chart of a method of machining an impeller assembly provided by an embodiment of the present disclosure;
FIG. 4 is a schematic view of an impeller according to an embodiment of the present disclosure;
FIG. 5 is a flow chart of a method for machining a first dovetail groove provided in an embodiment of the present disclosure;
FIG. 6 is a partial schematic view of an impeller assembly provided in an embodiment of the present disclosure;
FIG. 7 is an enlarged partial schematic view of FIG. 2;
fig. 8 is a flow chart of a finishing process provided by an embodiment of the present disclosure.
Detailed Description
For the purposes of clarity, technical solutions and advantages of the present disclosure, the following further details the embodiments of the present disclosure with reference to the accompanying drawings.
Unless defined otherwise, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this invention belongs. The terms "first," "second," and the like in the description and in the claims, are not used for any order, quantity, or importance, but are used for distinguishing between different elements. Likewise, the terms "a" or "an" and the like do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprising" or "comprises", and the like, is intended to mean that elements or items that are present in front of "comprising" or "comprising" are included in the word "comprising" or "comprising", and equivalents thereof, without excluding other elements or items. The terms "connected" or "connected," and the like, are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "upper", "lower", "left", "right", etc. are used merely to denote relative positional relationships, which may also change accordingly when the absolute position of the object to be described changes.
Fig. 1 is a schematic structural view of an impeller assembly of a propeller provided in an embodiment of the present disclosure. Fig. 2 is a cross-sectional view of the impeller assembly shown in fig. 1. As shown in fig. 1 and 2, the impeller assembly includes an impeller 10, a rotor assembly 20, an outer cylindrical jacket 31, and two annular end plates 32. The impeller 10 comprises a hub 11, a rim 13 and a plurality of blades 12. The rim 13 is coaxially sleeved outside the hub 11, and a plurality of blades 12 are positioned between the hub 11 and the rim 13. The blades 12 are connected to the hub 11 and the rim 13, respectively.
The rotor assembly 20 includes a yoke 21 and a plurality of magnetic steels 22, the yoke 21 is coaxially sleeved outside the rim 13, and the plurality of magnetic steels 22 are circumferentially arranged on the yoke 21. The rotor assembly 20 may also include magnetically isolated bakelite 23, with the magnetically isolated bakelite 23 positioned between adjacent magnet steels 22.
The outer jacket 31 is coaxially sleeved outside the rotor assembly 20, and two annular end plates 32 are respectively positioned at two ends of the outer jacket 31. Both annular end plates 32 are connected to the outer jacket 31 and the rim 13.
The rim 13, outer jacket 31 and two annular end plates 32 form an annular cavity in which the rotor assembly 20 is received.
Fig. 3 is a flow chart of a method of machining an impeller assembly provided in an embodiment of the present disclosure. The machining method is used for machining the impeller assembly shown in fig. 1 and 2.
As shown in fig. 3, the processing method includes:
in step S11, an impeller 10 is provided, and the inner hole wall and both end surfaces of the hub 11 of the impeller 10, and the outer peripheral wall and both end surfaces of the rim 13 of the impeller 10 are rough-turned.
Specifically, a vertical lathe can be adopted for processing, the impeller 10 is placed on a workbench, and after clamping correction, rough turning is carried out on the hub 11 and the rim 13 of the impeller 10.
In step S12, the blades 12 of the impeller 10 are rough-milled.
For example, a five axis numerically controlled machining center may be used for machining. And placing the roughly turned impeller 10 on a workbench of a five-axis numerical control machining center, clamping and correcting, and then carrying out rough milling.
Prior to machining the impeller assembly, a three-dimensional model may be created for the impeller 10 and the impeller assembly, respectively, which may be created based on the desired dimensions of the impeller 10 and the impeller assembly, respectively. A numerical control machining program is set based on the three-dimensional model and the machining amount.
In rough milling the blade 12, the rough milling may be performed on both sides of the blade 12 based on the three-dimensional model of the impeller 10 and the blade profile value of the blade 12.
Alternatively, the single-sided margin when rough milling the blades 12 of the impeller 10 is 0.8mm to 1.2mm. For example, in the embodiment of the present disclosure, the single-side margin when the blades 12 of the impeller 10 are rough-milled is 1mm.
By providing a certain single-sided margin, the blade 12 is to be finished subsequently.
In step S13, the impeller 10 is subjected to dye inspection.
The dye check areas are rough turning and rough milling areas, and after the impeller 10 is rough turned and rough milled, 100% dye check is performed on these areas on the impeller 10, so that it is possible to detect whether or not surface damage such as cracks has been formed on the surface of the impeller 10 during rough machining.
In the process of dye check, the II-level acceptance is qualified according to the requirements in the NB/T47013.5-2015 standard.
Step S13 is an optional step, and performs dye check after rough machining, so that the quality of rough machining can be ensured, and when damage is found in the dye check process, the process can be adjusted in time, and the impeller 10 is trimmed, so that the overall machining quality of the impeller assembly is improved.
In step S14, a plurality of first dovetail grooves 13a are machined on the outer peripheral wall of the rim 13.
Fig. 4 is a schematic structural view of an impeller according to an embodiment of the present disclosure. As shown in fig. 4, the first dovetail grooves 13a extend from one end of the rim 13 to the other end, and the plurality of first dovetail grooves 13a are distributed along the circumferential direction of the impeller 10.
The first dovetail groove 13a on the rim 13 is used to cooperate with the rotor assembly 20, and the machining quality of the first dovetail groove 13a directly affects the assembly of the rotor assembly 20 with the impeller 10. Fig. 5 is a flowchart of a processing method of a first dovetail groove according to an embodiment of the present disclosure. As shown in fig. 5, in order to secure the processing quality of the first dovetail groove 13a, the first dovetail groove 13a may be processed in the following manner:
step S141: a first dovetail groove 13a is formed in the outer peripheral wall of the rim 13 by wire cutting through a numerical control machine.
The linear cutting has higher machining precision, and the deformation of the rim 13 is reduced by adopting the linear cutting, so that the influence on the blade profile value of the blade 12 in the machining process is reduced, and the integral machining quality of the impeller assembly is improved.
In step S141, a first dovetail groove 13a is first machined, and after the wire-cut finishing process, in step S142, the machined first dovetail groove 13a is inspected.
Alternatively, in step S142, at least the machining size and machining accuracy of the first dovetail groove 13a machined in step S141 are checked.
By checking the machined first dovetail groove 13a, whether the machining process for machining the first dovetail groove 13a is proper or not can be judged according to the checking result, so that the subsequent machining process is guided.
At the time of inspection, the actual machining size and machining accuracy of the first dovetail groove 13a are compared with the designed machining size and machining accuracy to see whether or not they are within an allowable error range, so as to determine whether or not the first dovetail groove 13a is inspected to be acceptable.
If the machined first dovetail groove 13a is qualified, performing a subsequent step S143; if the machined first dovetail groove 13a is not qualified, the following step S144 is performed.
In step S143, the remaining first dovetail groove 13a is machined on the outer peripheral wall of the rim 13.
The number of first dovetail slots 13a to be machined may vary for different sized impeller assemblies. For example, in the embodiment of the present disclosure, 24 first dovetail grooves 13a are required to be machined on the rim 13, one first dovetail groove 13a is machined in step S141, and the remaining 23 first dovetail grooves 13a are continuously machined in step S143.
The inspection of the first dovetail groove 13a processed in step S141 shows that the processing method for processing the first dovetail groove 13a satisfies the processing requirements. In step S13, the processing method for processing the remaining 23 first dovetail grooves 13a is the same as that for processing the first dovetail groove 13a, so that the 23 first dovetail grooves 13a can also satisfy the requirement.
In step S144, the first dovetail groove 13a processed in step S141 is trimmed, and after the processing program for processing the first dovetail groove 13a is adjusted based on the inspection result, the remaining first dovetail groove 13a is processed on the outer peripheral wall of the rim 13.
The trimming of the first dovetail groove 13a includes trimming at least the machining dimension and machining accuracy of the first dovetail groove 13a. The machining size and machining accuracy of the first dovetail groove 13a are made to meet the design requirements by trimming.
The inspection result may be a deviation between the actually machined first dovetail groove 13a and the design requirement, where the deviation includes at least a deviation in machining dimension and a deviation in machining accuracy.
And adjusting a machining program for machining the first dovetail groove 13a according to the checking result to ensure that the machining program can machine the qualified first dovetail groove 13a. After the machining program is adjusted, the remaining first dovetail grooves 13a are machined according to the adjusted machining program, so that all the machined first dovetail grooves 13a meet the design requirements.
In step S15, the rotor assembly 20 and the impeller 10 are assembled.
Fig. 6 is a schematic view of a part of an impeller assembly according to an embodiment of the present disclosure. As shown in fig. 6, the rotor assembly 20 includes a yoke 21, a plurality of magnetic steels 22, and a plurality of magnetically isolated bakelite 23. A plurality of magnetic steels 22 and a plurality of magnetism isolating bakelite 23 are circumferentially arranged on the outer circumferential wall of the yoke 21, and the plurality of magnetism isolating bakelite 23 and the plurality of magnetic steels 22 are alternately distributed along the circumferential direction of the yoke 21. The inner peripheral wall of the yoke 21 has a plurality of second dovetail grooves 21a.
The rotor assembly 20 is sleeved outside the rim 13, so that the part between the adjacent first dovetail grooves 13a on the rim 13 is clamped into the second dovetail groove 21a on the inner peripheral wall of the magnetic yoke 21, and the part between the adjacent second dovetail grooves 21a on the inner peripheral wall of the magnetic yoke 21 is clamped into the first dovetail groove 13a.
The first dovetail groove 13a on the rim 13 of the impeller 10 and the second dovetail groove 21a of the yoke 21 are staggered in the circumferential direction, and the impeller 10 and the yoke 21 are engaged with each other.
In step S16, the outer jacket 31 is sleeved outside the rotor assembly 20.
The outer jacket 31 is a cylindrical member that fits over the rotor assembly 20 and, together with the annular end plate 32 that is subsequently assembled, provides protection to the rotor assembly 20.
In step S17, two annular end plates 32 are coaxially arranged at both ends of the outer jacket 31, and the annular end plates 32 are welded with the outer jacket 31 and the rim 13.
Fig. 7 is an enlarged partial schematic view of fig. 2. The welded locations are shown by arrows in fig. 7. In some examples, annular end plate 32 is laser welded to outer jacket 31 and rim 13.
The conventional welding method can generate larger thermal deformation, which can greatly affect the size of the finally formed impeller assembly, and the deformation can lead to certain distortion of the whole impeller assembly, thereby affecting the symmetry of the rotor assembly 20. The common welding method can cause temperature rise in a larger range, and the higher temperature can also have a certain influence on the magnetism of the magnetic steel 22, so that the magnetism is reduced.
In the embodiment of the disclosure, the laser welding is adopted, so that the deformation is small, the temperature rise in a large range is avoided, and the magnetic influence on the magnetic steel 22 is small.
After the welding is finished, an impeller assembly is formed, and then the impeller assembly is further finished, so that the accuracy of the impeller assembly is improved, and the impeller assembly meets the design requirement. Because the sequence of rough machining, assembling into the impeller assembly and finishing is adopted, the rough machining is performed before the assembly, and the assembled impeller assembly can be ensured to have certain precision. And after the assembly, finish machining is performed, so that the integral precision of the impeller assembly is guaranteed, the finish machining of each part before the assembly is avoided, and after the assembly, the error generated by the assembly and the error generated by welding cause the integral larger error of the impeller assembly. The allowance left in rough machining enables various errors such as errors generated by assembly and errors generated by welding to be overlapped in the allowance after assembly, and has enough machining space for finish machining, so that the integral accuracy of the impeller assembly is guaranteed.
In step S18, the blades 12, hub 11, rim 13, outer cylindrical jacket 31 and annular end plate 32 are finished.
Fig. 8 is a flow chart of a finishing process provided by an embodiment of the present disclosure. As shown in fig. 8, the finishing may be specifically performed in the following manner:
in step S181, the two surfaces of the blade 12 are respectively finish-milled according to the three-dimensional model and the blade profile value of the impeller assembly.
After assembly, based on the three-dimensional model of the impeller assembly and the impeller assembly, the blade surface type value of the blade 12 is subjected to finish machining, and under the condition that the precision of the blade 12 meets the requirement, the integral precision of the impeller assembly can be ensured.
The finish milling of the blade 12 may also be performed in a five-axis numerically controlled machining center. And placing the impeller assembly on a workbench, and carrying out finish milling on two sides of the blade 12 based on a three-dimensional model and a blade profile value of the impeller assembly after clamping and correcting.
In step S182, the inner hole wall and both end surfaces of the hub 11 are finish machined.
In step S183, the both end faces of the rim 13, the outer peripheral wall of the outer jacket 31, and the surfaces of the two annular end plates 32 remote from the rotor assembly 20 are finish machined.
That is, in step S182 and step S183, both end surfaces and the outer peripheral surface of the impeller assembly, and the inner hole wall of the hub 11 are finished. Step S182 and step S183 can be carried out on a vertical lathe, the impeller assembly is placed on a workbench, and finish turning is carried out after clamping correction.
After the whole impeller assembly is assembled, finish machining is performed, and only rough machining is performed before assembly, so that enough allowance is provided for ensuring the whole accuracy of the impeller assembly.
In step S19, the finished parts of the blades 12, hub 11, rim 13, outer jacket 31 and annular end plate 32 are subjected to dye check.
After finishing, 100% dye check is carried out on the part of the impeller assembly, which is subjected to finishing, and whether the surface of the impeller assembly is damaged by surface such as cracks or not in the finishing process can be detected. In the process of the dye check in the step S19, the weld joint is also subjected to dye check, so that the defects of the weld joint can be found out in time and repaired in time.
In the process of dye check, the II-level acceptance is qualified according to the requirements in the NB/T47013.5-2015 standard.
Step S19 is an optional step, and the dye check is performed after finish machining, so that the quality of finish machining can be ensured, and when damage is found in the dye check process, the process can be adjusted in time, and the impeller assembly is trimmed, so that the overall machining quality of the impeller assembly is improved.
In step S20, a screw hole 11a is formed in the hub 11.
Specifically, a machining line of the screw hole 11a may be first drawn on the hub 11, the position of the screw hole 11a is determined, and then drilling is performed to drill a threaded bottom hole. Thereafter, the threaded bottom hole is tapped to form a screw hole 11a.
In step S21, a water lubricated support bearing and a thrust disc are installed in the hub 11.
The water lubricated support bearing and thrust disc may be mounted through screw holes 11a. After the installation is completed, the impeller assembly can be integrally cleaned and protected.
The rough machining of the impeller 10 is completed by first rough turning the hub 11 and rim 13 of the impeller 10 and then rough milling the blades 12. Then, a first dovetail groove 13a for assembling the rotor assembly 20 is machined on the rim 13, the rotor assembly 20 is sleeved outside the rim 13, and the yoke 21 of the rotor assembly 20 is assembled with the rim 13 through the first dovetail groove 13a and the second dovetail groove 21a. After the rotor assembly 20 is assembled, the rotor assembly 20 is sleeved with an outer jacket 31, two annular end plates 32 are assembled, and welding is performed. After the welding is completed, the impeller 10 is further finished, and the outer circular sheath 31 and the annular end plate 32 are further finished. Through carrying out the equipment of impeller subassembly after impeller 10 rough machining, then weld and finish machining, because the rough machining that carries out before the equipment, leave certain machining allowance, still do not carry out finish machining, consequently the assembly error in the equipment in-process, the welding deformation in the welding process is to the holistic influence that produces of impeller subassembly, can obtain the elimination through subsequent finish machining, makes the holistic precision of impeller subassembly obtain guaranteeing, is favorable to further promoting electric propeller's performance.
The foregoing description of the preferred embodiments of the present disclosure is provided for the purpose of illustration only, and is not intended to limit the disclosure to the particular embodiments disclosed, but on the contrary, the intention is to cover all modifications, equivalents, alternatives, and alternatives falling within the spirit and principles of the disclosure.
Claims (10)
1. The processing method of the impeller assembly is characterized in that the impeller assembly comprises an impeller (10), a rotor assembly (20), an outer circular sheath (31) and two annular end plates (32), the impeller (10) comprises a hub (11), a rim (13) and a plurality of blades (12), the rim (13) is coaxially sleeved outside the hub (11), and the blades (12) are positioned between the hub (11) and the rim (13) and are respectively connected with the hub (11) and the rim (13);
the rotor assembly (20) comprises a magnetic yoke (21) and a plurality of magnetic steels (22), the magnetic yoke (21) is coaxially sleeved outside the rim (13), and the plurality of magnetic steels (22) are circumferentially arranged on the magnetic yoke (21);
the outer circular sheath (31) is coaxially sleeved outside the rotor assembly (20), and the two annular end plates (32) are respectively positioned at two ends of the outer circular sheath (31) and are connected with the outer circular sheath (31) and the rim (13);
the processing method comprises the following steps:
providing an impeller (10), and performing rough turning on the inner hole wall and two end surfaces of a hub (11) of the impeller (10) and the outer peripheral wall and two end surfaces of a rim (13) of the impeller (10);
rough milling of the blades (12) of the impeller (10);
a plurality of first dovetail grooves (13 a) are machined in the peripheral wall of the rim (13), the first dovetail grooves (13 a) extend from one end of the rim (13) to the other end, and the plurality of first dovetail grooves (13 a) are distributed along the circumferential direction of the impeller (10);
sleeving the rotor assembly (20) outside the rim (13), enabling parts between adjacent first dovetail grooves (13 a) on the rim (13) to be clamped into second dovetail grooves (21 a) on the inner peripheral wall of the magnetic yoke (21), and enabling parts between adjacent second dovetail grooves (21 a) on the inner peripheral wall of the magnetic yoke (21) to be clamped into the first dovetail grooves (13 a);
sleeving the outer circular sheath (31) outside the rotor assembly (20);
coaxially arranging the two annular end plates (32) at both ends of the outer circular sheath (31), and welding the annular end plates (32) with the outer circular sheath (31) and the rim (13);
-finishing the blades (12), the hub (11), the rim (13), the outer cylindrical jacket (31) and the annular end plate (32).
2. The method of machining an impeller assembly according to claim 1, characterized in that after said rough milling of the blades (12) of the impeller (10), the method further comprises:
and (3) performing dye check on the impeller (10).
3. The method of machining an impeller assembly according to claim 1, wherein the machining a plurality of first dovetail grooves (13 a) in the outer peripheral wall of the rim (13) includes:
a first dovetail groove (13 a) is processed on the peripheral wall of the rim (13) by adopting linear cutting through a numerical control machine tool;
-checking said one first dovetail groove (13 a);
if the first dovetail groove (13 a) is qualified, machining the rest first dovetail groove (13 a) on the peripheral wall of the rim (13);
and if the one first dovetail groove (13 a) is unqualified, trimming the one first dovetail groove (13 a), adjusting a machining program for machining the first dovetail groove (13 a) based on the inspection result, and machining the rest first dovetail grooves (13 a) on the outer peripheral wall of the rim (13).
4. A method of machining an impeller assembly according to claim 3, wherein said checking said one first dovetail groove (13 a) includes at least checking a machining size and machining accuracy of said one first dovetail groove (13 a).
5. A method of machining an impeller assembly according to claim 1, characterized in that the annular end plate (32) is laser welded with the outer jacket (31) and the rim (13).
6. The method of machining an impeller assembly according to claim 1, characterized in that said finishing of the blades (12), the hub (11), the rim (13), the outer cylindrical jacket (31) and the annular end plate (32) comprises:
respectively carrying out finish milling on two sides of the blade (12) according to the three-dimensional model and the blade profile value of the impeller assembly;
finish turning is carried out on the inner hole wall and the end surfaces of the two ends of the hub (11);
finish turning is carried out on the end surfaces of the two ends of the rim (13), the peripheral wall of the outer circular sheath (31) and the surfaces of the two annular end plates (32) far away from the rotor assembly (20).
7. The method of machining an impeller assembly according to claim 1, further comprising:
-performing a dye check on the finished parts of the blades (12), the hub (11), the rim (13), the outer cylindrical jacket (31) and the annular end plate (32).
8. The method of processing an impeller assembly according to claim 1, characterized in that the single-sided margin when rough milling the blades (12) of the impeller (10) is 0.8mm to 1.2mm.
9. The method of machining an impeller assembly according to claim 1, characterized in that after finishing the blades (12), the hub (11), the rim (13), the outer cylindrical jacket (31) and the annular end plate (32), the method further comprises:
screw holes (11 a) are formed in the hub (11).
10. A method of machining an impeller assembly according to claim 9, characterized in that a water lubricated support bearing and a thrust disc are mounted in the hub (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210967390.4A CN115383402B (en) | 2022-08-12 | 2022-08-12 | Impeller assembly machining method |
Applications Claiming Priority (1)
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| US5577321A (en) * | 1994-06-02 | 1996-11-26 | Hydroplanes, Inc. | Method of propeller fabrication |
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| CN115383402A (en) | 2022-11-25 |
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