CN115178980A - Machining method of guide vane casing - Google Patents
Machining method of guide vane casing Download PDFInfo
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- CN115178980A CN115178980A CN202210934708.9A CN202210934708A CN115178980A CN 115178980 A CN115178980 A CN 115178980A CN 202210934708 A CN202210934708 A CN 202210934708A CN 115178980 A CN115178980 A CN 115178980A
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- 238000000034 method Methods 0.000 title claims abstract description 54
- 238000003754 machining Methods 0.000 title claims abstract description 47
- 238000005520 cutting process Methods 0.000 claims description 9
- 238000000227 grinding Methods 0.000 claims description 6
- 238000005242 forging Methods 0.000 claims description 5
- 238000003672 processing method Methods 0.000 claims description 4
- 238000007730 finishing process Methods 0.000 claims 1
- 238000003801 milling Methods 0.000 description 8
- 238000005553 drilling Methods 0.000 description 6
- 238000007514 turning Methods 0.000 description 5
- 230000007547 defect Effects 0.000 description 4
- 230000003044 adaptive effect Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000004323 axial length Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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- 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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Abstract
The invention relates to the technical field of machining and discloses a method for machining a guide vane casing, wherein the guide vane casing is of a four-part split combined structure, a plurality of combined step holes are formed in the circumferential direction of the guide vane casing, and a plurality of coaxial non-equal-diameter deep-long combined through holes are distributed in the end face of the guide vane casing; the guide vane casing is firstly processed into a two-part split structure perpendicular to the axis direction of the guide vane casing, allowance is reserved for the axial dimension of the two-part split structure, the mutual attaching surfaces of the two-part split structure are processed to ensure the flatness, then 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 axis direction of the guide vane casing. After the guide vane casing is preliminarily processed into a two-part split structure, allowance is reserved for the axial dimension of the split structure, and then the two-part split structure is combined and processed to turn a reference hole, front and rear end faces, an inner hole cavity and the axial dimension, so that the coaxial and axial precise dimensions and technical requirements of the reference holes of the two split structures can 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 type guide vane casing for an aircraft engine.
Background
The guide vane casing of the aero-engine of a certain type shown in figure 1 belongs to a novel combined special structure. The guide vane casing is an important component of a compressor part, and is designed into a split type precise rotating piece consisting of a left half ring, a right half ring, an upper half ring and a lower half ring in order to be convenient for dismounting in a limited space in the casing, specifically, the guide vane casing is divided into a front part and a rear part in an unequal axial direction by using the central line of an outer ring precise stepped hole, and is divided into a left part and a right part by using a radial equal part. The sizes of the precision hole shafts need to be ensured in the splitting and integrating states. The design structure which needs to be split and combined in the axial direction and the radial direction puts severe requirements on the machining process of the casing.
As shown in fig. 1, the structural features of the component mainly include the following points:
1) The part is a rotating piece formed by combining four parts which are symmetrical two by two, 40 through holes are uniformly distributed in the circumferential direction of the part, 6 through holes and 20 threaded holes are uniformly distributed on the end surface of the part, and the whole part is of a porous weak-rigid structure;
2) 40 precision holes uniformly distributed in the circumferential direction of the part are non-integral, halved and combined step holes;
3) The part is an outer ring whole surface conical thin-wall flow passage part, and the thinnest part is only 1.8mm;
4) In 6 coaxial non-equal diameter deep and long through holes which are uniformly distributed on the end surface of the part, the size of one end of each through hole is phi 4 (+ 0.04, + 0.025), the size of the other end of each through hole is phi 4 (+ 0.012,0), and the depth reaches 15.2.
By combining the structural characteristics and the actual processing condition of the parts, the difficulty in the current part processing mainly comprises the following points:
1) Aiming at the characteristics of the four parts of the part in the axial and radial directions, the combined process processing scheme has the process flow and the combined tooling difficulty, and the dimensional precision requirements and the form and position technical condition requirements of the axial length precision sizes of the parts and the axial combined precision holes before and after combination need to be ensured;
2) In the 6 coaxial non-equal-diameter deep and long through holes, the aperture phi 4 (+ 0.04, + 0.025) at one end of each through hole is in clearance fit with the pin of the connecting step; the aperture phi 4 (+ 0.012,0) at the other end of the through hole is smaller and is in interference fit with the pin of the connecting step, a 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 combination and coaxial processing are needed, but the processing can not be completed in one step, and different diameters need to be respectively guaranteed; b) Splitting and processing are required, and the size of the step hole is ensured; c) The combined hole depth reaches 15.2, and the undersized hole diameter processing has high requirements on the hanging length and rigidity of cutters such as boring cutters, reamers and the like;
3) 40 combined precise holes phi 8.4 (+ 0.015,0) are circumferentially and uniformly distributed on the outer runner surface of the part, the factors are large, the tolerance is tight, the problem that the hole diameter size is influenced due to axial combination looseness of the part caused by overlarge milling force exists, and the hole diameter tolerance of the uniformly distributed precise holes is difficult to guarantee.
The patent with the patent number of CN2018114641451 discloses a method for machining a through hole of an angular combination device, which is also used for machining a combination hole, can well solve the matching error generated by separately machining the through hole, and meets the high-precision through requirement of two holes under the complex angular matching requirement. However, the technical scheme of the patent mainly focuses on clamping the first assembly and the second assembly by adopting a tool and processing through holes, and the key control point lies in the clamping process and cannot be used for reference to solve the technical problems.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, innovates in aspects of optimization and improvement of a process route and the like, and provides a method for machining a guide vane casing aiming at the problems of difficult machining of coaxial non-equal-diameter deep long holes and circumferentially uniformly distributed combined precise holes and the like.
The purpose of the invention is realized by the following technical scheme:
a processing method of a guide vane casing is characterized in that the guide vane casing is of a four-part split combined structure, a plurality of combined step holes are formed in the circumferential direction 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 used for inserting connecting pins, one end of each combined through hole is in interference fit with the corresponding connecting pin, and the other end of each combined through hole is in clearance fit with the corresponding connecting pin, and the processing method comprises the following steps:
s1, rough machining is carried out on a guide vane casing forging blank to remove allowance and semi-finish machining is carried out to obtain a reference size;
s2, cutting the guide vane casing line into a two-part split structure along the direction perpendicular to the axis of the guide vane casing, and reserving allowance for the axial dimension of the two-part split structure;
s3, grinding the mutual binding surfaces of the two split structures in the step S2 to ensure the flatness;
s4, assembling the two split structures in the step S3 by using a clamp, and processing an inner hole cavity and the axial size of the combined two parts by using a single piece;
s5, processing pre-holes at each combined through hole of the guide vane casing;
s6, processing an outer ring flow channel and a combined step hole;
s7, processing 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.
Furthermore, the machining of the pre-hole in the S5 is combined machining of the two parts of the guide vane casing.
Furthermore, the combined step hole processed in the step S6 is clamped in a mode that two parts of split structures are tightly attached and the whole surface is supported and pressed.
Still further, the combined step hole is roughly machined by adopting a spiral milling machine.
And further, the finish machining process route of the combined stepped hole is rough boring → semi-finish boring → first finish boring → second finish boring.
And further, the rough boring process is to remove a large allowance of rough machining of the combined stepped hole, the semi-fine boring process ensures that the allowance of the subsequent two-time fine boring is within 0.15, and the allowance of the first-time fine boring is 0.02-0.04.
And further, in the first fine boring process, determining a numerical value N capable of equally dividing the total number according to the total number of the combined stepped holes, measuring the aperture of the combined stepped holes every N holes, and comparing the aperture of the combined stepped holes with the aperture of the first hole to adjust the cutter compensation.
Further, the combined through hole in the step S7 is combined and processed, and is processed in a layered manner, where the layered processing is: the size of the interference fit end is machined in place by a small reamer, and then the size of the clearance fit end is machined in place by a large reamer.
Furthermore, the combined through holes are processed for multiple times, and a plurality of uniformly distributed combined through holes are selected each time to be inserted with positioning pins to 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 processed into a two-part split structure, allowance is reserved for the axial dimension of the two-part split structure, and then the two-part split structure is subjected to combined processing to turn a reference hole, front and rear end faces, an inner hole cavity and the axial dimension, so that the coaxial and axial precise dimension of the reference hole of the two-part split structure is qualified, and the technical requirement is qualified;
2) The combined through hole is formed by processing a pre-hole in a way of combining and processing the two parts of split structures and still adopting a combined processing way after a flow channel and a precise step hole are processed, so that the position and the coaxiality of the combined through hole are ensured;
3) The combined step hole is processed by adopting the spiral milling instead of drilling, so that the problem that the split structure is attached due to the drift of a drill bit and the overlarge drilling force is avoided, and the aperture and the position degree of the combined step hole can be effectively ensured by matching the spiral milling and the double fine boring process.
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-type structure of FIG. 1;
FIG. 3 is a schematic view of the combined stepped bore at section A3/A4 of FIG. 1;
FIG. 4 is a schematic view of an axial precision structure of the outer ring shown in FIG. 1;
FIG. 5 is a schematic view of the assembled 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 bore of FIG. 1;
FIG. 8 is a schematic view of the vane casing assembly through-hole and axial precision dimensions of the various embodiments;
FIG. 9 is an enlarged view of portion E of FIG. 8;
FIG. 10 is a schematic view of a vane casing combination stepped bore according to various embodiments;
FIG. 11 is a flow chart of a process for machining a stepped hole of the vane casing assembly according to embodiment 3;
FIG. 12 is a flow chart of the vane casing manufacturing process according to example 3.
Detailed Description
The present invention will be further described with reference to the following detailed description, wherein the drawings are provided for illustrative purposes only and are not intended to be limiting; to better illustrate the embodiments of the present invention, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood 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 aero-engine, as shown in fig. 1 and fig. 2, the guide vane casing is of a four-part split combined structure (A1, A2, A3 and A4 respectively), the guide vane casing is circumferentially provided with a plurality of combined step holes 1 shown in fig. 3, fig. 7 and fig. 10, the end face of the guide vane casing is distributed with a plurality of coaxial non-equal-diameter deep-long combined through holes 2 shown in fig. 5, fig. 8 and fig. 9, the combined through holes are used for inserting connecting pins, as shown in fig. 8, one end of each combined through hole is a fitting end 21 with the connecting pin in an interference manner, and the other end of each combined through hole is a fitting end 22 with the connecting pin in a clearance manner.
According to the traditional process experience, generally, after a guide vane casing is divided into two parts, each split structure is processed respectively, and the axial precise size is ensured by tight fastening tolerance through size conversion. However, in the implementation process, the two parts of the split structure reference hole B (shown in figure 8) are not coaxial after being cut and ground on line, and the hole diameters of the two parts of the split structure reference hole B are changed into ellipses; in the figure 8, the thin-wall single piece of the left split structure has insufficient rigidity, low grinding efficiency and large turning deformation; finally, the axial precision dimension of the part is difficult to guarantee.
In the embodiment, a new process scheme is provided for the process defects: the guide vane casing is firstly processed into a two-part split structure perpendicular to the axial direction of the guide vane casing (namely A1 and A2 are one part of split structure, A3 and A4 are one part of split structure), allowance is reserved for the axial size of the two-part split structure, then the mutual binding surfaces of the two-part split structure are respectively processed to ensure the flatness (the mutual binding surfaces are shown as the surface indicated by the reference numeral 3 in FIG. 8), then the two-part split structure is bound together to process a combined through hole 2 and a combined step hole 1, and finally the guide vane casing is processed into two symmetrical parts (namely the A1 and A3 parts, the A2 and the A4 part) 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 is carried out on a guide vane casing forging blank to remove allowance and semi-finish machining is carried out to obtain a reference size;
s2, cutting the guide vane casing line into a split structure of A1+ A2 and A3+ A4 along the direction perpendicular to the axis of the guide vane casing, and reserving allowance for the axial size of the split structure of the two parts;
s3, grinding the mutual binding surface 3 of the two split structures in the S2 to ensure the flatness;
s4, assembling the two split structures in the step S3 by using a clamp, processing the combined two parts of single pieces, and turning a reference hole B, front and rear end faces, an inner hole cavity and the axial dimension of the assembly;
s5, processing pre-holes at each combined through hole of the guide vane casing;
s6, processing an outer ring flow channel and a combined step hole 1;
s7, processing the combined through hole 2 at the pre-hole in the S5 in place;
s8, cutting the guide vane casing line into two symmetrical parts along the direction parallel to the axis of the guide vane casing.
In the embodiment, a traditional single-piece separate processing mode is abandoned, the characteristic of weak rigidity of parts is avoided, two parts of split structures are combined together for integral multi-lathe processing in S4, and relevant parameters and technical requirements such as coaxial and axial precise sizes of the B reference hole, 27.3 +/-0.05 and 47.6 +/-0.05, a reference run-out requirement of 0.035 and the like are qualified.
Example 2
This embodiment is different from embodiment 1 in that: the processing of the combined through hole 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 precision holes (namely the combined through holes in the technical scheme) on the end face are machined to be precise pre-holes phi 3 (+ 0.021, + 0.035) so as to be used as precise positioning connecting holes; after step holes of a flow passage (shown in figure 6) of the outer ring of the guide casing and an axial precise structure (shown in figure 4) of the outer ring are machined, the two parts of split structures are disassembled to respectively align precise pre-holes and machine the precise pre-holes to the final design size; however, during subsequent single thin-wall machining, the position degree of the axial precision hole is difficult to guarantee, and the coaxiality of the axial precision hole of the two-part split structure is respectively machined to have deviation.
In the embodiment, aiming at the defects of the combined through hole machining, the combined through hole 2 in the step S7 is selected to be subjected to combined machining, and simultaneously subjected to layered machining. Combining two parts of split structures in S5, processing phi 3 positioning connection pre-holes at the positions of six groups of uniformly distributed combined through holes, then processing S7 combination at the positions of the pre-holes (namely the positioning connection pre-holes) for unified boring, and reaming by adopting reamers with different diameters for layered processing, wherein the layered processing specifically comprises the following steps: firstly, a small reamer is adopted to process the size of the interference matching end 21 in place to ensure the size of an interference precise hole, and then a large reamer is adopted to process the size of the clearance matching end 22 in place to ensure the size of the clearance precise hole by setting the reaming depth. The layered boring and reaming can ensure that the size and the position of a combined through hole (a coaxial non-equal-diameter precision hole) phi 0.03 meet the technical requirements.
The processing of the six combined through holes is carried out twice, pre-holes at three combined through holes are selected for inserting positioning pins for the first time, the three selected combined through holes are required to be uniformly distributed in the circumferential direction of the end face and serve as positioning standards for processing the other three combined through holes, after the three combined through holes are processed in place in size, adaptive positioning pins are inserted into the three combined through holes and serve as the positioning standards for processing the other three combined through holes, then the positioning pins in the other three combined through holes are taken down, and the three combined through holes are processed in place in size.
Example 3
A method for processing a guide vane casing is characterized in that as shown in figures 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 step holes 1 shown in figures 3, 7 and 10 are formed in the circumferential direction of the guide vane casing, a plurality of coaxial non-equal-diameter deep and long combined through holes 2 shown in figures 5, 8 and 9 are distributed in the end face of the guide vane casing, the combined through holes are used for inserting connecting pins, and as shown in figure 8, one end of each combined through hole is a fitting end 21 which is in interference fit with the connecting pins, and the other end of each combined through hole is a fitting end 22 which is in clearance fit with the connecting pins.
According to the traditional process experience, generally, after a guide vane casing is divided into two parts, each split structure is processed respectively, and the axial precise size is ensured by tight fastening tolerance through size conversion. However, in the implementation process, the reference hole B (shown in figure 8) with the two-part split structure is not coaxial after being cut and ground on line, and the hole diameters of the reference hole B become oval; in the figure 8, the thin-wall single piece of the left split structure has insufficient rigidity, low grinding efficiency and large turning deformation; finally, the axial precision dimension of the part is difficult to guarantee.
Aiming at the process defects, a new process scheme is provided, and the specific processing steps are as follows:
s1, rough machining is carried out on a guide vane casing forging blank to remove allowance and semi-finish machining is carried out to obtain a reference size;
s2, cutting the guide vane casing line into a split structure of A1+ A2 and A3+ A4 along the direction perpendicular to the axis of the guide vane casing, and reserving allowance for the axial size of the split structure of the two parts;
s3, grinding the mutual binding surface 3 of the two split structures in the S2 to ensure the flatness;
s4, assembling the two split structures in the step S3 by using a clamp, processing the combined two parts by single pieces, and turning a reference hole B, front and rear end faces, an inner hole cavity and the axial size of the assembly;
s5, processing pre-holes at each combined through hole of the guide vane casing;
s6, processing an outer ring flow channel and a combined step hole 1;
s7, processing the combined through hole 2 at the pre-hole in the S5 in place;
s8, cutting the guide vane casing line into two symmetrical parts along the direction parallel to the axis of the guide vane casing.
And in the step S4, the traditional single-piece separate processing mode is abandoned, the characteristic of weak rigidity of parts is avoided, the two parts of split structures are combined together in the step S4 for integral numerical turning, and the coaxial and axial precision sizes of the reference hole B can be ensured to be 27.3 +/-0.05 and 47.6 +/-0.05, the reference run-out requirement is required to be 0.035, and other related parameters and technical requirements are qualified.
And in the S7, the combined through holes 2 are processed in a combined mode, and meanwhile, layered processing is adopted. Combining two parts of split structures in S5, processing phi 3 positioning connection pre-holes at the positions of six groups of uniformly distributed combined through holes, then processing S7 combination at the positions of the pre-holes (namely the positioning connection pre-holes) for unified boring, and reaming by adopting reamers with different diameters for layered processing, wherein the layered processing specifically comprises the following steps: firstly, a small reamer is adopted to process the size of the interference matching end 21 in place to ensure the size of an interference precision hole, and then a large reamer is adopted to process the size of the clearance matching end 22 in place to ensure the size of the clearance precision hole by setting the depth of a reaming hole. The layered boring and reaming can ensure that the size and the position of a combined through hole (a coaxial non-equal-diameter precision hole) phi 0.03 meet the technical requirements.
The processing of six combined through holes is carried out twice, pre-holes at three combined through holes are selected for inserting positioning pins for the first time, the three selected combined through holes are required to be uniformly distributed in the circumferential direction of the end face, the three combined through holes are used as positioning standards for processing the other three combined through holes, after the three combined through holes are processed in place in size, adaptive positioning pins are inserted into the three combined through holes to be used as the positioning standards for processing the other three combined through holes, then the positioning pins in the other three combined through holes are taken down, and the three combined through holes are processed in place in size.
The present embodiment is different from embodiment 2 in that a process improvement is made to the machining of the combined stepped hole 1. The method is different from a general hole diameter drilling → boring → reaming method, the method adopted by the embodiment is spiral milling → rough boring → semi-fine boring → fine boring, and the method mainly comprises the following key points:
1) Whole surface is supported and pressed
The tolerance of the aperture of the combined stepped hole 1 is only 0.015, the two parts of split structures are precisely attached in the machining process, and a gap cannot exist; therefore, in S6, the two-part split structure needs to be clamped in a manner that the whole surface is supported and pressed against the whole surface, and whether a gap exists in the single fitting surface is checked by using a feeler gauge.
2) Spiral milling replaces drilling
Because the outer part of the combined through hole of the guide vane casing is an outer ring runner inclined plane, and the hole is a non-integral combined hole, if direct drilling is adopted, the drill bit can float during processing, and the split structure can be affected by overlarge drilling force, so that the hole diameter and the position degree are affected, and the combined step hole is roughly machined by adopting spiral milling.
3) Rough boring → semi-fine boring → fine boring;
due to the fact that the number of the combined through holes is large, the conventional boring method is adopted, cutting feed is adjusted respectively to guarantee the size, the working strength is high, and the stability of machining quality is not high; the finish machining process route of the combined stepped hole in the embodiment is rough boring → semi-finish boring → first finish boring → second finish boring as shown in fig. 11, and the route is mainly characterized in that 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 process is to remove large allowance of rough machining of the combined step hole, the semi-fine boring process ensures that allowance of the subsequent two times of fine boring is within 0.1-0.15, and allowance of the first time of fine boring is 0.02-0.04.
In the first fine boring process, the aperture of the combined stepped hole is determined to be measured every 10 holes according to the total number of 40 combined stepped holes, the aperture of the combined stepped hole is compared with the aperture of the first hole, and a tool compensation value (tool wear) is adjusted in time.
And the second fine boring is to perform final fine boring on the combined step hole by using another fine boring cutter, and the first fine boring is completed.
The machining process of the combined stepped hole utilizes spiral milling and double fine boring technologies, and can effectively ensure that the precise aperture phi of the axially and uniformly distributed combined stepped hole is 8.4 (+ 0.015,0) in size and the position phi of the combined stepped hole is 0.05.
Fig. 12 shows an overall processing process flow of the guide vane casing in this embodiment, the discrete process improvements are connected in series, and a full process flow from a forging blank to a final inspection warehouse is recorded as a supplementary description of the processing of the guide vane casing in this embodiment, which is not described herein again.
It should be understood that the above examples are only for clearly illustrating the technical solutions of the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. A processing method of a guide vane casing is characterized in that the guide vane casing is of a four-part split combined structure, a plurality of combined step holes are formed in the circumferential direction 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 used for inserting connecting pins, one end of each combined through hole is in interference fit with the corresponding connecting pin, and the other end of each combined through hole is in clearance fit with the corresponding connecting pin, and the processing method is as follows:
s1, rough machining is carried out on a guide vane casing forging blank to remove allowance and semi-finish machining is carried out to obtain a reference size;
s2, cutting the guide vane casing line into a two-part split structure along the direction perpendicular to the axis of the guide vane casing, and reserving allowance for the axial dimension of the two-part split structure;
s3, grinding the mutual binding surfaces of the two split structures in the S2 to ensure the flatness;
s4, assembling the two split structures in the step S3 by using a clamp, and processing an inner hole cavity and the axial size of the combined two parts by using a single piece;
s5, processing pre-holes at the combined through holes of the guide vane casing;
s6, processing an outer ring flow channel and a combined step hole;
s7, processing the combined through hole at the pre-hole in the S5 in place;
s8, cutting the guide vane casing line into two symmetrical parts along the direction parallel to the axis of the guide vane casing.
2. The method of claim 1, wherein the pre-hole in S5 is formed by assembling two parts of the vane casing.
3. The method for machining the guide vane casing as claimed in claim 2, wherein the step hole machined and combined in the step S6 is clamped in a manner that two parts are in split structures and are tightly attached and the whole surface is supported and pressed.
4. The method of machining a vane casing according to claim 3, wherein the combined step hole is rough machined using a helical mill.
5. The vane casing machining method according to claim 4, characterized in that the finishing process route of the combined step hole is rough boring → semi-finish boring → first finish boring → second finish boring.
6. The method of claim 5, wherein the rough boring process is a rough machining large allowance for removing the combined stepped hole, and the semi-fine boring process ensures that the fine boring allowances of the two subsequent times are within 0.15.
7. The method of machining a vane casing according to claim 6, characterized in that the allowance for the first fine boring is 0.02 to 0.04.
8. The method of machining a guide vane casing according to claim 6 or 7, wherein during the first fine boring, a number N capable of equally dividing the total number is determined according to the total number of the combined stepped holes, and the diameter of the combined stepped hole is measured every N holes and compared with the diameter of the first hole to adjust the clearance.
9. The method for machining the guide vane casing as claimed in claim 1, wherein the combined through hole in S7 is a combined machining and a layered machining, and the layered machining is: the size of the interference fit end is processed in place by adopting a small reamer, and then the size of the clearance fit end is processed in place by adopting a large reamer.
10. The method of claim 9, wherein the machining of the combined through holes is performed in multiple times, and a plurality of uniformly distributed combined through holes are selected each time to insert the positioning pins as a positioning reference for machining other combined through holes.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210934708.9A CN115178980B (en) | 2022-08-04 | 2022-08-04 | Guide vane casing machining method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210934708.9A CN115178980B (en) | 2022-08-04 | 2022-08-04 | Guide vane casing machining method |
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| CN115178980A true CN115178980A (en) | 2022-10-14 |
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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 |
| CN105328399A (en) * | 2015-11-11 | 2016-02-17 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method for split casing type parts of aero-engines |
| CN107962354A (en) * | 2017-11-24 | 2018-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of processing technology of opposite opened casing |
| 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 |
| 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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Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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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 |
| CN105328399A (en) * | 2015-11-11 | 2016-02-17 | 沈阳黎明航空发动机(集团)有限责任公司 | Machining method for split casing type parts of aero-engines |
| CN107962354A (en) * | 2017-11-24 | 2018-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of processing technology of opposite opened casing |
| 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 |
| 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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| CN115178980B (en) | 2023-12-01 |
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