CN115178980B - Guide vane casing machining method - Google Patents
Guide vane casing machining method Download PDFInfo
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- CN115178980B CN115178980B CN202210934708.9A CN202210934708A CN115178980B CN 115178980 B CN115178980 B CN 115178980B CN 202210934708 A CN202210934708 A CN 202210934708A CN 115178980 B CN115178980 B CN 115178980B
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- 238000003754 machining Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims abstract description 42
- 238000003801 milling Methods 0.000 claims description 9
- 238000005520 cutting process Methods 0.000 claims description 8
- 238000003672 processing method Methods 0.000 claims description 7
- 238000000227 grinding Methods 0.000 claims description 6
- 238000005242 forging Methods 0.000 claims description 5
- 238000005553 drilling Methods 0.000 description 7
- 230000007547 defect Effects 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005056 compaction Methods 0.000 description 1
- 239000006185 dispersion Substances 0.000 description 1
- 238000007667 floating Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
- B23Q3/00—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine
- B23Q3/02—Devices holding, supporting, or positioning work or tools, of a kind normally removable from the machine for mounting on a work-table, tool-slide, or analogous part
- B23Q3/06—Work-clamping means
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to the technical field of machining and discloses a guide vane casing machining method, wherein the guide vane casing is of a four-part split combined structure, a plurality of combined stepped holes are formed in the circumferential direction of the guide vane casing, and a plurality of coaxial non-equal-diameter deep and long combined through holes are distributed on the end face of the guide vane casing; the guide vane casing is firstly processed into a two-part split structure perpendicular to the axial direction of the guide vane casing, the axial dimension of the two-part split structure is reserved for allowance, the flatness is guaranteed by processing the mutually-attached surfaces of the two-part split structure, the two-part split structure is attached together to process a combined through hole and a combined step hole, and finally the guide vane casing is processed into two symmetrical parts parallel to the axial direction of the guide vane casing. After the guide vane casing is preliminarily machined into a two-part split structure, the axial dimensions of the split structure are reserved with allowance, and then the two-part split structure is combined and machined with a turning reference hole, front and rear end surfaces, an inner hole cavity and the axial dimensions, so that the coaxial and axial precision dimensions and the technical requirements of the two-part split structure reference hole can be ensured to be qualified.
Description
Technical Field
The invention relates to the technical field of machining, in particular to a machining method of a precise complex thin-wall porous split combined guide vane casing for an aeroengine.
Background
The guide vane casing of a certain aeroengine shown in figure 1 belongs to a novel combined special structure. The guide vane casing is an important component part of a compressor component, is designed into a split type precise rotating part consisting of a left half ring, a right half ring, an upper half ring and a lower half ring, and is divided into a front part and a rear part in an unequal axial manner by using the center line of a precise stepped hole of an outer ring, and a left half part and a right half part by using radial equally-divided parts. The size of the precise hole shaft is ensured under the split and integrated states. The design structure of the split combination required in the axial direction and the radial direction brings harsh requirements to the machining process of the casing.
As shown in fig. 1, the structural features of the parts mainly include the following points:
1) The parts are rotary parts formed by combining four parts in a pairwise symmetrical way, and are uniformly distributed with 40 through holes, 6 through holes and 20 threaded holes in the end face in the circumferential direction, and the whole part is of a porous weak rigid structure;
2) The 40 precise holes uniformly distributed in the circumferential direction of the part are non-integral, half-divided and combined step holes;
3) The part is an outer ring whole-surface conical thin-wall runner part, and the thinnest part is only 1.8mm;
4) In the 6 coaxial non-equal-diameter deep and long through holes uniformly distributed on the end face of the part, one end of the through hole has the size phi 4 (+ 0.04, +0.025) and the other end has the size phi 4 (+ 0.012,0) and the depth reaches 15.2.
The difficulties existing in the existing part processing mainly include the following points:
1) Aiming at the characteristics of the axial and radial four-part dispersion structure of the part, the processing scheme of the combined process has the difficulties of process flow and combined tool, and the precision requirements of the axial length of each part, the precision requirements of the axial combined precision hole before and after combination and the technical condition requirements of shape and position are required;
2) In the 6 coaxial non-equal-diameter deep through holes, the aperture phi 4 (+0.04, +0.025) at one end of the through hole is in clearance fit with the connecting step pin; the aperture phi 4 (+ 0.012,0) at the other end of the through hole is smaller and is in interference fit with the connecting step pin, the step hole phi 4.6 (+0.1, 0) is arranged between the two apertures, and the depth is 1; the two-part pore size has the following difficulties in processing: a) The coaxial machining is required to be combined, but one-knife machining cannot be carried out in place, and different diameters are required to be ensured respectively; b) The split processing is needed, so that the step hole size is ensured; c) The depth of the combined hole reaches 15.2, and the processing of the too small aperture has high requirements on the suspension length and rigidity of tools such as boring, reamer and the like;
3) The diameter tolerance of the uniformly distributed precise holes is difficult to ensure because the hole diameter tolerance of the uniformly distributed precise holes is large because the hole diameter is influenced by axial combination looseness of the parts due to excessive milling force, and the diameter of the uniformly distributed precise holes is 8.4 (+ 0.015,0) at 40 parts which are uniformly distributed on the outer flow surface of the parts in the circumferential direction.
The patent No. CN2018114641451 discloses a processing method of a through hole of an angular combination device, which is also used for processing the combined hole, can well solve the matching error generated by the separate processing of the through hole, and meets the high-precision through requirement of two holes under the complex angular matching requirement. But the main emphasis of the technical scheme is that a tool is adopted to clamp the first assembly and the second assembly and process the through hole, and the key control point is in the clamping process, so that the technical problem can not be solved by reference.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, innovates in the aspects of optimizing and improving a process route, and aims to solve the problems of coaxial non-equal-diameter deep and long hole machining, circumferential uniformly distributed combined precise hole machining difficulties and the like, and provides a guide vane casing machining method.
The invention aims at realizing the following technical scheme:
the guide vane casing is of a four-part split combined structure, a plurality of combined stepped holes are formed in the circumference of the guide vane casing, a plurality of coaxial non-equal-diameter deep and long combined through holes are distributed in the end face of the guide vane casing, the combined through holes are used for inserting connecting pins, one end of each combined through hole is an interference fit end with each connecting pin, and the other end of each combined through hole is a clearance fit end with each connecting pin, and the processing method comprises the following steps:
s1, rough machining, allowance removing and semi-finishing are carried out on a guide vane case forging blank to obtain a reference size;
s2, linearly cutting the guide vane casing into a two-part split structure along the direction perpendicular to the axial direction of the guide vane casing, wherein the axial dimension of the two-part split structure is reserved with allowance;
s3, grinding the mutually-attached surfaces of the two split structures in the S2 to ensure flatness;
s4, assembling the two-part split structure in the S3 by using a clamp, and processing an inner hole cavity and an axial dimension by using the combined two parts;
s5, processing pre-holes at all combined through holes of the guide vane casing;
s6, processing an outer ring runner and a combined step hole;
s7, machining the combined through hole at the pre-hole in the S5 in place;
s8, cutting the guide vane casing into two symmetrical parts along the direction parallel to the axis of the guide vane casing.
Further, the pre-hole in S5 is formed by combining two parts of split structures of the guide vane casing.
Furthermore, the processing combined step hole in S6 is clamped by adopting a mode that two parts of split structures are tightly adhered and the whole surface is pressed tightly.
Still further, the combined step hole is rough machined by helical milling.
Still further, the finish machining process route of the combined step hole is rough boring, semi-finish boring, first finish boring and second finish boring.
Still further, the rough boring procedure is to remove the rough machining large allowance of the combined step hole, the semi-finish boring procedure ensures that the allowance of the follow-up twice finish boring is within 0.15, and the reserved allowance of the first finish boring is 0.02-0.04.
Further, in the first fine boring process, a numerical value N which can equally divide the total number is determined according to the total number of the combined step holes, the aperture of the combined step holes is measured once every N holes, and the aperture of the combined step holes is compared with the aperture of the first hole so as to adjust the cutter compensation.
Further, in S7, the combined through holes are processed in combination and are processed in layers, and the processing in layers is: the size of the interference fit end is machined in place by adopting a small reamer, and then the size of the clearance fit end is machined in place by adopting a large reamer.
Furthermore, the processing of the combined through holes is performed in a plurality of times, and a plurality of uniformly distributed combined through holes are selected each time to insert positioning pins and serve as positioning references for processing other combined through holes.
Compared with the prior art, the invention has the following beneficial effects:
1) After the guide vane casing is preliminarily machined into a two-part split structure, the axial dimensions of the two-part split structure are reserved with allowance, and then the two-part split structure is combined and machined to form a turning reference hole, front and rear end surfaces, an inner hole cavity and the axial dimensions, so that the coaxial and axial precision dimensions of the reference hole of the two-part split structure can be ensured to be qualified;
2) After the pre-holes are machined through the combination of the two split structures, after the runner and the precise step holes are machined, the combination through holes are machined through a combination machining mode, so that the position and the coaxiality of the combination through holes are ensured;
3) The combined step hole is machined by adopting the spiral milling to replace drilling, so that the problem that the floating of a drilling bit and the overlarge drilling force affect the lamination of a split structure is avoided, and the aperture and the position degree of the combined step hole can be effectively ensured by adopting the cooperation of the spiral milling and the double fine boring technology.
Drawings
FIG. 1 is a schematic perspective view of a vane casing according to various embodiments;
FIG. 2 is a schematic view (side view) of the four-part split-combination structure of FIG. 1;
FIG. 3 is a schematic view of a combined stepped hole on the A3/A4 portion of FIG. 1;
FIG. 4 is a schematic view of the axial precision structure of the outer race of FIG. 1;
FIG. 5 is a schematic view of the combined via of FIG. 1;
FIG. 6 is a schematic view of the outer ring flow channel of FIG. 1;
FIG. 7 is a schematic view of the combination stepped hole of FIG. 1;
FIG. 8 is a schematic view of a combined through hole and axial precision dimension of a vane case according to various embodiments;
FIG. 9 is an enlarged view of portion E of FIG. 8;
FIG. 10 is a schematic view of a combined stepped bore of a vane case according to various embodiments;
FIG. 11 is a process flow of a guide vane case combined stepped hole in embodiment 3;
fig. 12 is a process flow of the vane casing in embodiment 3.
Detailed Description
The present invention will now be described further in connection with the following detailed description, wherein the drawings are for purposes of illustration only and are not intended to be limiting; for the purpose of better illustrating embodiments of the invention, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the size of the actual product; it will be appreciated by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.
Example 1
The guide vane casing is a precise complex thin-wall split combined guide vane casing of an aeroengine, as shown in fig. 1 and 2, the guide vane casing is of a four-part split combined structure (A1, A2, A3 and A4 respectively), a plurality of combined stepped holes 1 shown in fig. 3, 7 and 10 are formed in the circumferential direction, a plurality of coaxial non-equal-diameter deep and long combined through holes 2 shown in fig. 5, 8 and 9 are distributed on the end face of the guide vane casing, the combined through holes are used for inserting connecting pins, one end of each combined through hole is an interference fit end 21 with each connecting pin, and the other end of each combined through hole is a clearance fit end 22 with each connecting pin, as shown in fig. 8.
According to the traditional process experience, after the guide vane casing is divided into two parts, each split structure is processed, and the buckling tolerance ensures the axial precise dimension through dimension conversion. However, in the implementation process, it is found that the two parts of split structure reference holes B (see figure 8) are not coaxial after being cut and ground on line, and the apertures of the two parts of split structure reference holes B become elliptic; in FIG. 8, the left split structure thin-wall single piece has insufficient rigidity, low grinding efficiency and large turning deformation; ultimately resulting in parts with axially precise dimensions that are difficult to guarantee.
Aiming at the technical defects, the embodiment provides a new technical scheme: the method comprises the steps of firstly processing a guide vane casing into a two-part split structure (namely, A1 and A2 are part split structures and A3 and A4 are part split structures) perpendicular to the axial direction of the guide vane casing, reserving allowance for the axial dimension of the two-part split structure, respectively processing mutually-bonded surfaces of the two-part split structure to ensure flatness (the mutually-bonded surfaces are the surfaces indicated by reference numeral 3 in fig. 8), bonding the two-part split structure together to process a combined through hole 2 and a combined stepped hole 1, and finally processing the guide vane casing into symmetrical two parts (namely, A1 and A3 parts, A2 and A4 parts) parallel to the axial direction of the guide vane casing.
Specifically, the processing steps of the guide vane casing are as follows:
s1, rough machining, allowance removing and semi-finishing are carried out on a guide vane case forging blank to obtain a reference size;
s2, linearly cutting the guide vane casing into a split structure of A1+A2 and A3+A4 along the direction perpendicular to the axis of the guide vane casing, wherein the axial dimension of the split structure of the two parts is reserved with allowance;
s3, grinding the mutually-attached surfaces 3 of the two split structures in the S2, so as to ensure the flatness;
s4, assembling the two-part split structure in the S3 by using a clamp, processing the two combined parts by one piece, and turning a reference hole B, front and rear end surfaces, an inner hole cavity and axial dimensions of the combined part;
s5, processing pre-holes at all combined through holes of the guide vane casing;
s6, processing an outer ring runner and a combined step hole 1;
s7, machining the combined through hole 2 at the pre-hole in the S5 in place;
s8, cutting the guide vane casing into two symmetrical parts along the direction parallel to the axis of the guide vane casing.
The embodiment abandons the traditional single-piece separate processing mode, avoids the characteristic of weak rigidity of parts, combines the two parts of split structures together in the S4 and integrally carries out the numerical processing, and can ensure that the B reference hole is coaxial and has the axial precision dimensions of 27.3+/-0.05, 47.6+/-0.05, the reference runout requirement of 0.035 and other related parameters and technical requirements are qualified.
Example 2
This embodiment differs from embodiment 1 in that: the processing of the combined through holes 2 is improved. According to the traditional process experience, after the two parts of split structures (namely A1+A2 and A3+A4) are combined, six axial precise holes (namely combined through holes in the technical scheme) on the end face are machined to a precise pre-hole phi 3 (+0.021 and +0.035) so as to be used as precise positioning connecting holes; after the step holes of the guide casing outer ring runner (see fig. 6) and the outer ring axial precision structure (see fig. 4) are processed, the two split structures are split so as to respectively align the precision pre-holes and process the split structures to the final design size; however, during the subsequent thin-wall processing of a single piece, the position degree of the axial precise hole is difficult to ensure, and the coaxiality of the axial precise holes of the two-part split structure is respectively processed with deviation.
In this embodiment, aiming at the defect of the combined through hole processing, the combined through hole 2 in S7 is processed in a combined manner, and simultaneously, is processed in a layered manner. In S5, combining two parts of split structures, processing phi 3 positioning connection pre-holes at the positions of six groups of uniformly distributed combined through holes, and then after uniformly boring at the pre-holes (namely positioning connection pre-holes) in S7, reaming by adopting different diameter reamers for layering processing, wherein the layering processing is specifically as follows: the size of the interference fit end 21 is machined in place by adopting a small reamer, the size of an interference precise hole is guaranteed, the size of the clearance fit end 22 is machined in place by adopting a large reamer by setting the reaming depth, and the size of the clearance precise hole is guaranteed. The layered boring and reaming can ensure that the size and the position degree phi 0.03 of the combined through hole (coaxial non-equal diameter precision hole) meet the technical requirements.
The machining of six combined through holes is carried out twice, the pre-holes at the three combined through holes are selected for the first time, the positioning pins are inserted into the pre-holes at the three combined through holes, the selected three combined through holes are uniformly distributed in the circumferential direction of the end face, the three combined through holes are used as positioning references for machining the other three combined through holes, after the sizes of the three combined through holes are machined in place, the matched positioning pins are inserted into the three combined through holes again to be used as positioning references for machining the other three combined through holes, and then the positioning pins in the other three combined through holes are taken down, so that the sizes of the three combined through holes are machined in place.
Example 3
The processing method of the guide vane casing is as shown in fig. 1 and 2, the guide vane casing is of a four-part split combined structure (A1, A2, A3 and A4 respectively), a plurality of combined stepped holes 1 as shown in fig. 3, 7 and 10 are formed in the circumference of the guide vane casing, a plurality of coaxial non-equal-diameter long combined through holes 2 as shown in fig. 5, 8 and 9 are distributed on the end face of the guide vane casing, the combined through holes are used for inserting connecting pins, one end of each combined through hole is an interference fit end 21 with the connecting pin, and the other end of each combined through hole is a clearance fit end 22 with the connecting pin, as shown in fig. 8.
According to the traditional process experience, after the guide vane casing is divided into two parts, each split structure is processed, and the buckling tolerance ensures the axial precise dimension through dimension conversion. However, in the implementation process, it is found that the two parts of split structure reference holes B (see figure 8) are not coaxial after being cut and ground on line, and the apertures of the two parts of split structure reference holes B become elliptic; in FIG. 8, the left split structure thin-wall single piece has insufficient rigidity, low grinding efficiency and large turning deformation; ultimately resulting in parts with axially precise dimensions that are difficult to guarantee.
Aiming at the technical defects, a new technical scheme is provided, and the specific processing steps are as follows:
s1, rough machining, allowance removing and semi-finishing are carried out on a guide vane case forging blank to obtain a reference size;
s2, linearly cutting the guide vane casing into a split structure of A1+A2 and A3+A4 along the direction perpendicular to the axis of the guide vane casing, wherein the axial dimension of the split structure of the two parts is reserved with allowance;
s3, grinding the mutually-attached surfaces 3 of the two split structures in the S2, so as to ensure the flatness;
s4, assembling the two-part split structure in the S3 by using a clamp, processing the two combined parts by one piece, and turning a reference hole B, front and rear end surfaces, an inner hole cavity and axial dimensions of the combined part;
s5, processing pre-holes at all combined through holes of the guide vane casing;
s6, processing an outer ring runner and a combined step hole 1;
s7, machining the combined through hole 2 at the pre-hole in the S5 in place;
s8, cutting the guide vane casing into two symmetrical parts along the direction parallel to the axis of the guide vane casing.
S4, the traditional single-piece separate processing mode is abandoned, the characteristic of weak rigidity of parts is avoided, in S4, the two parts of split structures are combined together to form an integral type numerical machining, and the coaxial and axial precision dimensions 27.3+/-0.05 and 47.6+/-0.05 of the reference hole B and the requirements on relevant parameters and technical requirements such as 0.035 of the reference jump can be ensured.
In S7, the combined through holes 2 are processed in a combined manner and simultaneously processed in a layered manner. In S5, combining two parts of split structures, processing phi 3 positioning connection pre-holes at the positions of six groups of uniformly distributed combined through holes, and then after uniformly boring at the pre-holes (namely positioning connection pre-holes) in S7, reaming by adopting different diameter reamers for layering processing, wherein the layering processing is specifically as follows: the size of the interference fit end 21 is machined in place by adopting a small reamer, the size of an interference precise hole is guaranteed, the size of the clearance fit end 22 is machined in place by adopting a large reamer by setting the reaming depth, and the size of the clearance precise hole is guaranteed. The layered boring and reaming can ensure that the size and the position degree phi 0.03 of the combined through hole (coaxial non-equal diameter precision hole) meet the technical requirements.
The machining of six combined through holes is carried out twice, the pre-holes at the three combined through holes are selected for the first time, the positioning pins are inserted into the pre-holes at the three combined through holes, the selected three combined through holes are uniformly distributed in the circumferential direction of the end face, the three combined through holes are used as positioning references for machining the other three combined through holes, after the sizes of the three combined through holes are machined in place, the matched positioning pins are inserted into the three combined through holes again to be used as positioning references for machining the other three combined through holes, and then the positioning pins in the other three combined through holes are taken down, so that the sizes of the three combined through holes are machined in place.
The present embodiment differs from embodiment 2 in that the processing of the combined stepped hole 1 is improved in process. Different from the processing method of common aperture drilling, boring and reaming, the processing method adopted in the embodiment is spiral milling, rough boring, semi-fine boring and fine boring, and the processing method mainly comprises the following steps:
1) Whole surface support compaction
The aperture tolerance of the combined step hole 1 is only 0.015, the two parts of split structures are required to be attached precisely in the processing process, and gaps cannot be reserved; therefore, in S6, the two-part split structure is clamped in a manner of pressing the whole surface against the whole surface, and whether a gap exists on the single-piece joint surface is checked by using a feeler gauge.
2) Spiral milling alternative drilling
Because the outside of the guide vane casing combined through hole is an outer ring runner inclined plane, and the hole is a non-integral combined hole, if direct drilling is adopted, the drill bit processing can drift, and the drilling force is too large to influence the fit of a split structure, so that the aperture and the position degree are influenced, and therefore, the combined step hole adopts spiral milling for rough machining.
3) Rough boring, semi-fine boring, fine boring and fine boring;
because the number of the combined through holes is large, the conventional boring method is adopted to respectively adjust the feed so as to ensure the size, the working strength is large, and the stability of the processing quality is not high; the finish machining process route of the combined step hole in the embodiment is as shown in fig. 11, namely rough boring, semi-finish boring, first finish boring and second finish boring, wherein the route is characterized in that the finish boring of the first finish boring ensures the finish boring allowance of the last cutter, and the finish boring replaces reaming to ensure the final aperture size.
The rough boring procedure is to remove large allowance of rough machining of the combined step hole, the semi-fine boring procedure ensures that the allowance of the secondary fine boring is within 0.1-0.15, and the allowance of the primary fine boring is 0.02-0.04.
In the first fine boring process, according to the total number of 40 combined step holes, the hole diameter of the combined step hole is determined to be measured once every 10 holes, and is compared with the hole diameter of the first hole, and the cutter compensation value (cutter abrasion) is adjusted in time.
And the second fine boring is to carry out the final fine boring on the combined step hole by using another fine boring cutter, and the combined step hole is machined in place once.
The machining process of the combined step hole adopts a spiral milling and double fine boring technology, and can effectively ensure that the precision aperture phi 8.4 (+ 0.015,0) of the axially uniformly distributed combined step hole is 0.05 in size and position degree.
Fig. 12 shows the overall processing process flow of the guide vane casing in this embodiment, and the above-mentioned scattered process improvements are connected in series, and the whole process flow from forging blank to final inspection and warehousing is described, which is used as a supplementary explanation of the processing of the guide vane casing in this embodiment, and will not be described herein.
It is apparent that the above examples are only examples for clearly illustrating the technical solution of the present invention, and are not limiting of the embodiments of the present invention. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. Any modification, equivalent replacement, improvement, etc. which come within the spirit and principles of the invention are desired to be protected by the following claims.
Claims (6)
1. The guide vane casing is of a four-part split combined structure, a plurality of combined stepped holes are formed in the circumference of the guide vane casing, a plurality of coaxial non-equal-diameter deep and long combined through holes are distributed in the end face of the guide vane casing and are used for inserting connecting pins, one end of each combined through hole is an interference fit end with each connecting pin, and the other end of each combined through hole is an interference fit end with each connecting pin, and the guide vane casing is characterized in that the processing method comprises the following steps:
s1, rough machining, allowance removing and semi-finishing are carried out on a guide vane case forging blank to obtain a reference size;
s2, linearly cutting the guide vane casing into a two-part split structure along the direction perpendicular to the axial direction of the guide vane casing, wherein the axial dimension of the two-part split structure is reserved with allowance;
s3, grinding the mutually-attached surfaces of the two split structures in the S2 to ensure flatness;
s4, assembling the two-part split structure in the S3 by using a clamp, and processing an inner hole cavity and an axial dimension by using the combined two parts;
s5, processing pre-holes at all combined through holes of the guide vane casing;
s6, processing an outer ring runner and a combined step hole;
s7, machining the combined through hole at the pre-hole in the S5 in place;
s8, linearly cutting the guide vane casing into two symmetrical parts along the direction parallel to the axis of the guide vane casing;
s5, the pre-hole is processed by combining two parts of split structures of the guide vane casing;
s6, clamping the machined combined step hole in a mode that two parts of split structures are tightly adhered and the whole surface is supported and pressed;
s7, combining the through holes into combined processing and layering processing, wherein the layering processing is as follows: firstly, machining the size of an interference fit end in place by adopting a small reamer, and then machining the size of the clearance fit end in place by adopting a large reamer;
and rough machining is carried out on the combined step hole by adopting spiral milling.
2. The guide vane casing machining method according to claim 1, wherein the finish machining process route of the combined step hole is rough boring, semi-finish boring, first finish boring and second finish boring.
3. The guide vane casing machining method according to claim 2, wherein the rough boring process is to remove a large allowance of rough machining of the combined step hole, and the semi-finish boring process ensures that the allowance of the subsequent two finish boring processes is within 0.15.
4. The guide vane casing machining method according to claim 3, wherein the reserved allowance for the first fine boring is 0.02-0.04.
5. The method for machining the guide vane casing according to claim 3 or 4, wherein in the first fine boring process, a numerical value N which can equally divide the total number is determined according to the total number of combined step holes, the combined step hole aperture is measured every N holes, and the combined step hole aperture is compared with the first hole aperture to adjust the cutter compensation.
6. The method for machining the guide vane casing according to claim 1, wherein machining of the combined through holes is performed in a plurality of times, and a plurality of uniformly distributed combined through holes are selected each time to insert positioning pins as positioning references for machining of other combined through holes.
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| CN202210934708.9A CN115178980B (en) | 2022-08-04 | 2022-08-04 | Guide vane casing machining method |
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| CN115178980B true CN115178980B (en) | 2023-12-01 |
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| CN (1) | CN115178980B (en) |
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| CN110465783A (en) * | 2019-08-21 | 2019-11-19 | 无锡市润和机械有限公司 | A kind of processing method of aero-engine pin-connected panel cylinder casing |
| CN113530888A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Multi-cavity integrated guide vane casing structure with anti-icing function |
| CN113982754A (en) * | 2021-10-19 | 2022-01-28 | 无锡市润和机械有限公司 | Novel multi-lobe non-uniform combined cylindrical casing of aircraft engine and processing method |
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| CN102248380A (en) * | 2011-07-04 | 2011-11-23 | 南京航空航天大学 | Method for processing integral casing of engine |
| CN103624493A (en) * | 2013-11-26 | 2014-03-12 | 中国南方航空工业(集团)有限公司 | Method for machining half-and-half casings of gas compressor of aero-engine |
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| CN107984177A (en) * | 2017-12-19 | 2018-05-04 | 中国航发南方工业有限公司 | Split Casing simulating piece processing method |
| CN110465783A (en) * | 2019-08-21 | 2019-11-19 | 无锡市润和机械有限公司 | A kind of processing method of aero-engine pin-connected panel cylinder casing |
| CN113530888A (en) * | 2021-08-24 | 2021-10-22 | 中国航发湖南动力机械研究所 | Multi-cavity integrated guide vane casing structure with anti-icing function |
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