CN218800614U - Benchmark hole processing frock of aircraft engine exhaust nozzle spare part roof beam - Google Patents
Benchmark hole processing frock of aircraft engine exhaust nozzle spare part roof beam Download PDFInfo
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- CN218800614U CN218800614U CN202223194274.8U CN202223194274U CN218800614U CN 218800614 U CN218800614 U CN 218800614U CN 202223194274 U CN202223194274 U CN 202223194274U CN 218800614 U CN218800614 U CN 218800614U
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- 238000003780 insertion Methods 0.000 description 11
- 230000037431 insertion Effects 0.000 description 11
- 230000000694 effects Effects 0.000 description 10
- 238000005553 drilling Methods 0.000 description 5
- 238000012805 post-processing Methods 0.000 description 4
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Abstract
The utility model provides a pair of benchmark spot facing work frock of aircraft engine tail nozzle spare part roof beam. The ear positioning device comprises a bottom plate, wherein three drill sleeves are respectively arranged on the front side and the rear side of the bottom plate, first fixing blocks are respectively movably connected to the left side bottom plates of the two left side drill sleeves, and an ear positioning block is arranged on the bottom plate between the two first fixing blocks; a second fixing block is movably connected to the bottom plate on the outer side of each of the two middle drill bushings, and a screw automatic centering device is arranged between each of the middle drill bushings and the right drill bushing; a rotary positioning block is movably arranged on the right bottom plate of the right drill bushing; the lug positioning block is movably provided with a positioning center-dividing block. The utility model has the advantages of
And
in the process of machining, the beam-precision casting piece is well positioned in the center, and the machined
And
has good position degree and symmetry degree, and is adopted in the post-process processing
And
the machining method has the advantages that the machining method is used as a reference hole for machining, the part beam is good in quality, the product precision and the qualified rate are high, and the beneficial effects of high efficiency, precision and machining of typical parts of the aero-engine are achieved.
Description
Technical Field
The utility model relates to an aircraft engine exhaust nozzle spare part processing field especially relates to a benchmark hole processing frock of aircraft engine exhaust nozzle spare part roof beam.
Background
The tail nozzle is one of the components of the turbojet engine of the jet plane, and mainly has the functions of ejecting products generated after fuel oil of the jet plane is combusted, exhausting waste gas and pushing the jet plane by utilizing the reaction force generated by air during ejection.
The jet nozzle adjustable tail jet pipe is adopted, so that the engine can obtain good performance in various working states. For a part beam (55.031) in the existing 10-series adjustable tail spray pipe, a precision casting, a complex integral frame structure, a difficult-to-machine material and the like are adopted, and in the machining process of the part beam, a boss of the precision casting-beam needs to be machined
And
however, due to the structural particularity of the precision casting piece-beam, in the existing machining process, the splayed end of the precision casting piece-beam is easy to deform, so that the machining size is uncontrollable, the quality and the reliability of the tail nozzle are seriously affected, and the solution is urgently needed.
Therefore, it is necessary to provide a datum hole machining tool for an aircraft engine exhaust nozzle component beam to solve the technical problem.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft engine tail nozzle spare part roof beam's benchmark spot facing work frock. The utility model is provided with
And &>
In the processing, the beam-fine casting centering positioning effect is good, and the processed->
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Has good position degree and symmetry degree, and is adopted in the post-process processing
And &>
The machining is carried out by taking the part beam as a reference hole, the quality of the part beam is good, the product precision and the qualification rate are high, and the characteristics of high efficiency, precision and machining of typical parts of the aero-engine are realized.
In order to solve the technical problem, the utility model provides a datum hole machining tool for an aircraft engine tail nozzle part beam, which comprises a bottom plate, wherein three drill sleeves are respectively arranged on the front side and the rear side of the bottom plate, first fixed blocks are respectively movably connected on the left side bottom plates of two left side drill sleeves, and an ear positioning block is arranged on the bottom plate between the two first fixed blocks; a second fixed block is movably connected to the bottom plate on the outer side of each of the two middle drill bushings, and a screw automatic centering device is arranged between each of the middle drill bushings and the right drill bushing; a rotary positioning block is movably arranged on the right bottom plate of the right drill bushing;
the lug piece locating block is movably provided with a locating middle dividing block which comprises an assembling block, the lower end of the assembling block is provided with an assembling groove in a penetrating mode from left to right, an inserting block is arranged in the middle of the upper end of the right side face of the assembling block, the included angle of the front side face and the rear side face of the inserting block is 2-6 degrees, and the distance between the left ends of the front side face and the rear side face of the inserting block is larger than that between the right ends of the inserting block.
In the reference hole machining tool for the aircraft engine tail nozzle part beam, the machining tool is of a front-back symmetrical structure.
In the reference hole machining tool for the aircraft engine tail nozzle part beam, the first fixing block is movably connected to the bottom plate through a rotating shaft.
In the reference hole machining tool for the aircraft engine tail nozzle part beam, the relative outer sides of the two second fixing blocks are respectively connected with the movable pins, the movable pins are respectively and movably connected with the pin bosses, and the pin bosses are respectively and fixedly connected to the bottom plate.
In the reference hole machining tool for the part beam of the tail nozzle of the aircraft engine, the automatic centering device for the screw rod comprises a screw rod, two first limiting blocks are arranged on the outer surface of the screw rod in parallel, second limiting blocks are respectively arranged on the left side and the right side of the screw rod between the two first limiting blocks, the second limiting blocks are fixedly connected to the bottom plate, the second limiting blocks are both positioned between the two first limiting blocks, and the screw rod is movably connected with the second limiting blocks;
the screw rods on the opposite outer sides of the two first limiting blocks are respectively provided with a third limiting block, the screw rods on the opposite outer sides of the two third limiting blocks are respectively provided with threads, the threads on the two sides of the screw rods are respectively a left thread and a right thread, the screw rods on the front side and the rear side are respectively in threaded movable connection with a centering retaining block, the left side and the right side of the centering retaining block are respectively in groove movable connection with a fourth limiting block, and the fourth limiting blocks are fixedly connected onto the bottom plate.
In the reference hole machining tool for the aircraft engine tail nozzle part beam, the screw automatic centering device is arranged in parallel with the left side and the right side of the bottom plate.
In the reference hole machining tool for the aircraft engine tail nozzle part beam, the right end face of the rotary positioning block is connected with a positioning screw rod, the positioning screw rod is connected with a connecting block through threads, and the connecting block is fixed on the bottom plate.
In the reference hole machining tool for the aircraft engine tail nozzle part beam, the lug positioning block is in interference fit with the positioning centering block through the assembling groove.
In the reference hole machining tool for the aircraft engine tail nozzle part beam, the machining tool is used for machining a precision casting piece-beam boss
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The beam-precision casting has the structure that: the front and back symmetrical structure, the front and back both sides of concrete are equipped with the crossbeam respectively, the cross section of the crossbeam is the I-shaped structure, the overall length of crossbeam is 405mm, there are first longeron, second longeron, third longeron, fourth longeron and fifth longeron sequentially from left to right between the crossbeam of both sides, the crossbeam of both sides of first longeron and second longeron takes the form of the outer splay, and the open end of the outer splay sets up to the left, the distance from left end to first longeron of the crossbeam is 175mm, the interval of the crossbeam of both sides is 85mm before and after the first longeron; the distance between the left ends of the two cross beams is 135mm, the left side of the first longitudinal beam is symmetrically provided with two lug plates, and the distance between the two lug plates is 7mm; the cross beams on the two sides of the third longitudinal beam, the fourth longitudinal beam and the fifth longitudinal beam are arranged in parallel, and the right end faces of the fifth longitudinal beam and the cross beams are flush; bosses are respectively arranged on the cross beams on the front side and the rear side of the first longitudinal beam, the second longitudinal beam and the fifth longitudinal beam, and the bosses on the left side and the right side of the cross beam are processed>
Processing on a central boss>
A well and is used in a post-processing operation>
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The holes were machined as reference holes.
Compared with the prior art, the utility model discloses following beneficial effect has:
referring to fig. 1-2, the existing tool is in a front-back symmetrical structure, and the existing tool is used for aligning beams and precision casting
And
the method comprises the steps of processing a reference hole, namely placing a beam-precision casting on a tool bottom plate, wherein the left side and the right side of a cross beam of the beam-precision casting are respectively positioned on a screw automatic centering device, the distance between the screw automatic centering device on the left side and a first longitudinal beam is 160mm, the screw automatic centering device on the right side is positioned on a fourth longitudinal beam, the left end of an lug piece of the beam-precision casting abuts against a lug positioning block on the bottom plate, the right end of the beam-precision casting is rotationally fixed through a rotary positioning block on the processing tool bottom plate, the screw automatic centering devices on the left side and the right side respectively center and clamp and fix the cross beams on the left side and the right side through rotating screws, and the screw automatic centering device on the right side respectively centers and clamps and fixes the cross beams on the right side of the beam-precision casting, and the cross beams on the right side are not prone to deform under the action that the cross beams on the two sides of the third longitudinal beam, the fourth longitudinal beam and the fifth longitudinal beam are arranged in parallel; then, a left cross beam of the left boss enters the cross beam by rotating the first fixing block, cross beams on the front side and the rear side of the second longitudinal beam are inserted into the second fixing block respectively, the cross beam is pressed and fixed on the bottom plate by the first fixing block and the second fixing block, and thenThe existing tool is turned over, so that the beam-precision casting is positioned below a tool bottom plate and passes through the & on tool>
And &>
The drill bushing correspondingly processes the boss on the beam-precision casting in a drilling, expanding and hinging mode. However, the following technical problems exist in the process of machining the existing tool: because the crossbeams on the two sides of the first longitudinal beam and the second longitudinal beam are in the shape of the splayed outer beams, the opening ends of the splayed outer beams are arranged leftwards, the distance from the left end of each crossbeam to the first longitudinal beam is 175mm, the distance between the crossbeams on the two sides of the first longitudinal beam is 85mm, the distance between the left ends of the crossbeams on the two sides is 135mm, the distance between the automatic screw rod centering device on the left side and the first longitudinal beam is 160mm, and the automatic screw rod centering device on the left side is used for centering and clamping the crossbeams
And &>
Is poor in the position and symmetry, and subsequent processing is->
And
the machining is carried out as a reference hole, so that the quality of a part beam is poor, the product precision and the qualified rate are low, the whole size is not controllable, the quality and the reliability of the tail nozzle are seriously influenced, and the solution is urgently needed.
The processing tool of the utility model is characterized in that a beam-precision casting is placed on a tool bottom plate, the beam-precision casting is positioned on a screw automatic centering device on the right side of the bottom plate, and the left end of an lug of the beam-precision casting is close to a lug positioning block on the bottom plate; divide the positioning intoThe inserting block on the block is inserted between the two lugs of the beam-precision casting, and because the distance between the two lugs of the beam-precision casting is the size of the blank, the distance between the two lugs of each piece is different, and under the action that the included angle between the front side surface and the rear side surface of the inserting block is 2-6 degrees, and the distance between the left ends of the front side surface and the rear side surface of the inserting block is larger than the distance between the right ends of the front side surface and the rear side surface of the inserting block, after the inserting block enters between the two lugs, the front side surface and the rear side surface of the inserting block are ensured to be tightly close to the two lugs by changing the depth of the inserting block between the two lugs, so that the condition that a gap exists between the inserting block and the two lugs or the inserting block cannot be inserted between the two lugs is avoided; then, workers rotate the positioning centering blocks around the lug plates, the positioning centering blocks are assembled on lug plate positioning blocks through assembling grooves, the right ends of the beam-precision castings are fixed through the rotary positioning blocks on the processing tool bottom plate, rubber rods are used for tapping the positioning centering blocks rightwards, the front side faces and the rear side faces of the inserting blocks are guaranteed to be close to the lug plates again, centering positioning on the left sides of the beam-precision castings through the positioning centering blocks is achieved, the automatic screw centering device on the right sides of the beam-precision castings is used for centering and clamping fixing the beam-precision castings through the right side cross beams, good centering positioning effect of the beam-precision castings is achieved, and the phenomenon that due to structural particularity of the beam-precision castings, the splayed ends on the left sides of the cross beams are prone to deformation due to stress, centering clamping on the left sides of the cross beams cannot be achieved accurately, positioning effect in centering of the beam-precision castings is poor, and processing is caused is avoided
And &>
The positional degree and the symmetry degree of (2) are poor.
Under the effect that the cross section of crossbeam is the I-shaped structure, then respectively through rotating first fixed block and get into in the crossbeam, the second fixed block is inserted respectively to the crossbeam of both sides around the second longeron, and first fixed block and second fixed block compress tightly the crossbeam and fix on the bottom plate, then will the utility model discloses processing frock upset makes roof beam-precision casting be located frock bottom plate below, through processing the effect on the frock
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The drill bushing processes the lug boss on the beam-precision casting correspondingly in a drilling, expanding and hinging mode. Realize on the boss on the counter beam-precision casting->
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In the processing process, the beam-precision casting has good centering and positioning effect and is well reserved>
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Has good position degree and symmetry degree, and is adopted in post-process processing>
And &>
The machining is carried out by taking the part beam as a reference hole, the quality of the part beam is good, the product precision and the qualification rate are high, and the high-efficiency, precise and machining of typical parts of the aero-engine are realized.
The utility model is provided with
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In the processing, the beam-fine casting centering positioning effect is good, and the processed->
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Degree of location of andgood symmetry, and is adopted in post-processing
And &>
The machining is carried out by taking the part beam as a reference hole, the quality of the part beam is good, the product precision and the qualification rate are high, and the beneficial effects of high efficiency, precision and machining of typical parts of the aircraft engine are realized.
Drawings
FIG. 1 is a schematic structural view of a current machining tool for a datum hole of a part beam of an aircraft engine tail nozzle of the present invention;
FIG. 2 is a schematic view of a clamping beam-precision casting of a current machining tool for a reference hole of a component beam of an aircraft engine tail nozzle of the present invention;
FIG. 3 is a schematic structural view of a reference hole machining tool for a beam of a tail nozzle component of an aircraft engine according to the present invention;
FIG. 4 is a schematic structural view of the datum hole processing tool for the jet nozzle part beam of the aircraft engine of the present invention after the positioning and centering block is removed;
FIG. 5 is a front view of a datum hole processing tool-positioning centering block of a jet nozzle component beam of the aircraft engine of the present invention;
FIG. 6 is a left side view of a reference hole processing tool-positioning centering block of a jet nozzle component beam of the aircraft engine of the present invention;
FIG. 7 is a top view of a datum hole processing fixture-positioning centering block of a jet nozzle component beam of an aircraft engine of the present invention;
FIG. 8 is a perspective view of a datum hole processing fixture-positioning centering block of a jet nozzle component beam of the aircraft engine of the present invention;
fig. 9 is a schematic diagram of the datum hole processing tool clamping beam-precision casting of the aircraft engine tail nozzle component beam of the present invention.
Reference numbers in the figures: 1-bottom plate, 2-screw automatic centering device, 21-fourth limiting block, 22-first limiting block, 23-second limiting block, 24-screw, 25-centering retaining block, 26-thread, 27-third limiting block, 3-first fixing block, 4-rotary positioning block, 5-lug positioning block, 51-centering dividing block, 511-inserting block, 512-assembling block, 513-assembling groove, 6-drilling sleeve, 7-second fixing block, 8-beam-precision casting, 81-cross beam, 82-lug, 83-first longitudinal beam, 84-second longitudinal beam, 85-third longitudinal beam, 86-fourth longitudinal beam, 87-fifth longitudinal beam and 88-lug boss.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and embodiments.
The embodiment is as follows: referring to fig. 3-9 in combination, the structure for the beam-precision casting 8 is: the front and rear symmetrical structure, the front and rear sides are respectively provided with a crossbeam 81, the cross section of the crossbeam 81 is an I-shaped structure, the total length of the crossbeam 81 is 405mm, a first longitudinal beam 83, a second longitudinal beam 84, a third longitudinal beam 85, a fourth longitudinal beam 86 and a fifth longitudinal beam 87 are sequentially arranged between the crossbeams 81 on the two sides from left to right, the crossbeams 81 on the two sides of the first longitudinal beam 83 and the second longitudinal beam 84 are in an outer splayed shape, the opening end of the outer splayed shape is arranged leftwards, the distance from the left end of the crossbeam 81 to the first longitudinal beam 83 is 175mm, and the distance between the crossbeams 81 on the front and rear sides of the first longitudinal beam 83 is 85mm; the distance between the left ends of the two cross beams 81 is 135mm, the left side of the first longitudinal beam 83 is symmetrically provided with two lug plates 82, and the distance between the two lug plates 82 is 7mm; the cross beams 81 on the two sides of the third longitudinal beam 85, the fourth longitudinal beam 86 and the fifth longitudinal beam 87 are arranged in parallel, and the right end faces of the fifth longitudinal beam 87 and the cross beams 81 are flush; bosses 88 are respectively arranged on the cross beams 81 at the front side and the rear side of the first longitudinal beam 83, the second longitudinal beam 84 and the fifth longitudinal beam 87, and bosses 88 at the left side and the right side of the cross beam 81 are processed
Machining on the centrally located boss 88
A well and is used in a post-processing operation>
And &>
The holes were machined as reference holes.
A datum hole machining tool for a tail nozzle part beam of an aircraft engine comprises a bottom plate 1, wherein three drill bushings 6 are respectively arranged on the front side and the rear side of the bottom plate 1, first fixing blocks 3 are respectively and movably connected to the left bottom plates 1 of the two left drill bushings 6, and a lug positioning block 5 is arranged on the bottom plate 1 between the two first fixing blocks 3; a second fixing block 7 is movably connected to the bottom plate 1 on the outer side of each of the two middle drill bushings 6, and a screw automatic centering device 2 is arranged between each of the middle drill bushings 6 and the right drill bushing 6; a rotary positioning block 4 is movably arranged on the right bottom plate 1 of the right drill bushing;
the lug positioning block 5 is movably provided with a positioning center-dividing block 51, the positioning center-dividing block 51 comprises an assembly block 512, the lower end of the assembly block 512 is provided with an assembly groove 513 in a penetrating manner from left to right, an insertion block 511 is arranged in the middle of the upper end of the right side face of the assembly block 512, the included angle of the front side face and the rear side face of the insertion block 511 is 2-6 degrees, and the left end distance of the front side face and the rear side face of the insertion block 511 is larger than the right end distance.
The processing tool takes the bottom surface and the boss ground by the beam-8 front process of the precision casting as the reference surface, divides the center and the clamping, and processes by adopting the mode of drilling, expanding and hinging
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The hole and the beam-casting-finishing 8 are used in the post-processing>
And &>
As a reference hole.
Specifically, the processing tool of the utility model is characterized in that the beam-precision casting 8 is placed on the tool bottom plate 1, the beam-precision casting 8 is positioned on the screw automatic centering device 2 on the right side of the bottom plate 1, and the left end of the lug 82 of the beam-precision casting 8 is close to the lug positioning block 5 on the bottom plate 1; inserting the inserting block 511 on the positioning dividing block 51Between the two lugs 82 of the beam-precision casting 8, because the distance between the two lugs 82 of the beam-precision casting 8 is the size of the blank, the distance between the two lugs 82 of each piece is different, under the action that the included angle between the front side surface and the rear side surface of the insertion block 511 is 2-6 degrees, and the distance between the left ends of the front side surface and the rear side surface of the insertion block 511 is larger than the distance between the right ends, after the insertion block 511 enters between the two lugs 82, the depth of the insertion block 511 inserted between the two lugs 82 is changed, so that the front side surface and the rear side surface of the insertion block 511 are ensured to be tightly abutted against the two lugs, and the condition that a gap exists between the insertion block 511 and the two lugs 82 or the insertion block 511 cannot be inserted between the two lugs 82 is avoided; then, a worker rotates the positioning centering block 51 around the lug 82, the positioning centering block 51 is assembled on the lug positioning block 5 through the assembling groove 513, the right end of the beam-precision casting 8 is fixed through the rotary positioning block 4 on the processing tool bottom plate 1, a rubber rod is used for lightly tapping the positioning centering block 51 rightwards, the front side face and the rear side face of the insertion block 511 are ensured to be close to the lug 82 again, centering and positioning on the left side of the beam-precision casting 8 through the positioning centering block 51 are achieved, the automatic screw centering device 2 on the right side of the beam-precision casting 8 enables the automatic screw centering device 2 to center and clamp the beam-precision casting 8 through the right cross beam 81 through the rotation screw 24, centering and clamping of the beam-precision casting 8 are achieved, the phenomenon that the beam-precision casting 8 centering and positioning effects are good, the phenomenon that the left cross beam 81 is prone to deform due to structural particularity of the beam-precision casting 8, the left cross beam 81 is prone to be stressed in an outwards splayed shape, so that the left side of the cross beam 81 cannot be accurately centered and clamped, and the beam-precision casting 8 centering and positioning effects are poor, which result in processing
And
the positional degree and the symmetry degree of (2) are poor.
Under the action that the cross section of the cross beam 81 is in an I-shaped structure, the cross beams 81 respectively enter the cross beam 81 by rotating the first fixing block 3, the cross beams 81 at the front side and the rear side of the second longitudinal beam 84 are respectively inserted into the second fixing block 7, the cross beam 81 is pressed and fixed up and down by the first fixing block 3 and the second fixing block 7, then the processing tool of the utility model is turned over, so that the beam-precision casting piece 8 is positioned below the tool bottom plate 1,by machining on the tool
And &>
The drill bushing 6 correspondingly processes the boss 88 on the beam-precision casting 8 in a drilling, expanding and hinging way. On the lug boss 88 of the beam-precision casting 8
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In the processing process, the beam-precision casting 8 has good centering and positioning effect, and the processed beam-precision casting is
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The position degree and the symmetry degree of the optical fiber are good.
On the boss 88 of the beam-precision casting 8
And &>
After the processing is accomplished, will the utility model discloses the processing frock upset, then rotate first fixed block 3, extract second fixed block 7, the cancellation is fixed to compressing tightly of 8 crossbeams 81 of roof beam-investment casting, then counter-rotating screw rod 24 again, make the automatic device 2 cancellation of dividing of screw rod in to the branch of 8 right side crossbeams of roof beam-investment casting, press from both sides tight fixed, divide the location on auricle locating piece 5 in block 51 and take off, then rotate rotatory locating piece 4, the cancellation is to roof beam-investment casting 8's fixed back, will process and finish the great>
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The beam-casting 8 is taken down and sent to the post-process for processing, and the post-process processing adopts the part>
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The machining is carried out by taking the part beam as a reference hole, the quality of the part beam is good, the product precision and the qualification rate are high, and the high-efficiency, precise and machining of typical parts of the aero-engine are realized.
The processing tool is of a front-back symmetrical structure, so that the beam-precision casting 8 of the front-back symmetrical structure can be conveniently centered and clamped
And &>
And (4) processing holes.
The first fixing block 3 is movably connected to the bottom plate 1 through a rotating shaft, and the first fixing block 3 rotates on the bottom plate 1 through the rotating shaft.
The opposite outer sides of the two second fixing blocks 7 are respectively connected with movable pins, the movable pins are respectively movably connected with pin bosses, and the pin bosses are respectively and fixedly connected to the bottom plate 1, so that the second fixing blocks 7 are inserted into or pulled out of the beam 81 of the beam-precision casting 8.
The automatic screw centering device 2 comprises a screw 24, two first limiting blocks 22 are arranged on the outer surface of the screw 24 in parallel, second limiting blocks 23 are respectively arranged on the left side and the right side of the screw 24 between the two first limiting blocks 22, the second limiting blocks 23 are fixedly connected to the bottom plate 1, the second limiting blocks 23 are both positioned between the two first limiting blocks 22, and the screw 24 is movably connected with the second limiting blocks 23;
the screw rods 24 on the opposite outer sides of the two first limiting blocks 22 are respectively provided with a third limiting block 27, the screw rods 24 on the opposite outer sides of the two third limiting blocks 27 are respectively provided with threads 26, the threads 26 on the two sides of the screw rods 24 are respectively a left thread and a right thread, the screw rods 24 on the front side and the rear side are respectively movably connected with a centering retaining block 25 through the threads 26, the left side and the right side of the centering retaining block 25 are respectively movably connected with a fourth limiting block 21 through grooves, and the fourth limiting block 21 is fixedly connected onto the bottom plate 1.
The automatic screw centering device 2 on the right side of the beam-precision casting 8 is used for centering and clamping and fixing the beam-precision casting 8 through a right side cross beam 81 or reversely rotating a screw rod 24, so that the automatic screw centering device 2 eliminates centering and clamping and fixing of the right side cross beam 81, specifically, two first limiting blocks 22 are arranged on the outer surface of the screw rod 24 in parallel, second limiting blocks 23 are respectively arranged on the left side and the right side of the screw rod 24 between the two first limiting blocks 22, the second limiting blocks 23 are fixedly connected on the bottom plate 1, the second limiting blocks 23 are both positioned between the two first limiting blocks 22, under the action of movable connection of the screw rod 24 and the second limiting blocks 23, the rotating screw rod 24 can not move back and forth in the second limiting blocks 23 on the left side and the right side, the screw rod 24 rotates in the second limiting blocks 23 on the left side and the right side, third limiting blocks 27 are respectively arranged on the screw rods 24 on the opposite outer sides of the two first limiting blocks 22, the screws 24 on the opposite outer sides of the two third limiting blocks 27 are respectively provided with threads 26, the threads 26 on the two sides of the screws 24 are respectively left threads and right threads, the screws 24 on the front side and the rear side are respectively movably connected with centering retaining blocks 25 through the threads 26, the left side and the right side of the centering retaining blocks 25 are respectively movably connected with fourth limiting blocks 21 through grooves, the fourth limiting blocks 21 are fixedly connected on the bottom plate 1, the rotating screws 24 respectively drive the centering retaining blocks 25 on the front side and the rear side to synchronously approach or synchronously move away from the fourth limiting blocks 21 through the threads 26, under the action of synchronous mutual approaching movement of the centering retaining blocks 25, the right cross beam 81 of the beam-precision casting 8 is automatically centered and clamped and fixed, the centering retaining blocks 25 synchronously move away, and the right cross beam 81 of the beam-precision casting 8 is cancelled, and (5) clamping and fixing.
The automatic screw centering device 2 is arranged in parallel with the left side and the right side of the bottom plate 1, so that the automatic screw centering device 2 can perform automatic centering, clamping and fixing on a beam-precision casting 8 in the front-rear direction
The right end face of the rotary positioning block 4 is connected with a positioning screw rod, the positioning screw rod is connected with a connecting block through threads, and the connecting block is fixed on the bottom plate; by rotating the positioning screw rod, the positioning screw rod moves leftwards or rightwards on the connecting block, so that the positioning screw rod drives the rotary positioning block 4 to rotate and move leftwards or rightwards at the same time, and the fixation or the fixation cancellation of the right end of the beam-precision casting is completed.
The lug positioning block 5 is in interference fit with the positioning centering block 51 through the assembling groove 513, so that the positioning centering block 51 is prevented from moving under the condition that the external force is not applied, and the accuracy of centering and positioning the beam-precision casting 8 left side by the positioning centering block 51 through the two lugs 82 is prevented from being influenced.
The above only is the embodiment of the present invention, not limiting the scope of the present invention, all the equivalent structures or equivalent processes of the present invention are used in the specification and the attached drawings, or directly or indirectly applied to other related technical fields, and the same principle is included in the protection scope of the present invention.
Claims (7)
1. The utility model provides a benchmark spot facing work frock of aircraft engine exhaust nozzle spare part roof beam which characterized in that: the processing tool comprises a bottom plate (1), three drill bushings (6) are respectively arranged on the front side and the rear side of the bottom plate (1), first fixing blocks (3) are respectively and movably connected to the left bottom plates (1) of the two left drill bushings (6), and a lug positioning block (5) is arranged on the bottom plate (1) between the two first fixing blocks (3); a second fixed block (7) is movably connected to the bottom plate (1) on the outer side of the two middle drill bushings (6), and a screw automatic centering device (2) is arranged between the middle drill bushing (6) and the right drill bushing (6); a rotary positioning block (4) is movably arranged on the right bottom plate (1) of the right drill bushing;
the ear positioning block (5) is movably provided with a positioning center dividing block (51), the positioning center dividing block (51) comprises an assembling block (512), the lower end of the assembling block (512) is provided with an assembling groove (513) in a penetrating manner from left to right, the middle of the upper end of the right side face of the assembling block (512) is provided with an inserting block (511), the included angle of the front side face and the rear side face of the inserting block (511) is 2-6 degrees, and the left end distance of the front side face and the rear side face of the inserting block (511) is larger than the right end distance;
the processing tool is of a front-back symmetrical structure.
2. The reference hole machining tool for the aircraft engine jet nozzle part beam as claimed in claim 1, wherein the reference hole machining tool comprises: the first fixing block (3) is movably connected to the bottom plate (1) through a rotating shaft.
3. The reference hole machining tool for the aircraft engine jet nozzle part beam as claimed in claim 1, wherein the reference hole machining tool comprises: the opposite outer sides of the two second fixed blocks (7) are respectively connected with movable pins, the movable pins are respectively and movably connected with pin bases, and the pin bases are respectively and fixedly connected to the bottom plate (1).
4. The reference hole machining tool for the aircraft engine jet nozzle part beam as claimed in claim 1, wherein the reference hole machining tool comprises: the automatic screw centering device (2) comprises a screw (24), two first limiting blocks (22) are arranged on the outer surface of the screw (24) in parallel, second limiting blocks (23) are respectively arranged on the left side and the right side of the screw (24) between the two first limiting blocks (22), the second limiting blocks (23) are fixedly connected to the bottom plate (1), the second limiting blocks (23) are both positioned between the two first limiting blocks (22), and the screw (24) is movably connected with the second limiting blocks (23);
be equipped with third stopper (27) on screw rod (24) in the relative outside of two first stoppers (22) respectively, be equipped with screw thread (26) on screw rod (24) in the relative outside of two third stopper (27) respectively, screw thread (26) of screw rod (24) both sides are left hand thread and right-hand thread respectively, screw rod (24) of front and back both sides are through screw thread (26) swing joint respectively and divide centre maintenance piece (25), divide the left and right sides of centre maintenance piece (25) to have fourth stopper (21) through groove swing joint respectively, fourth stopper (21) fixed connection is on bottom plate (1).
5. The tool for machining the datum hole of the jet pipe part beam of the aircraft engine as claimed in claim 4, characterized in that: the automatic screw centering device (2) is arranged in parallel with the left side and the right side of the bottom plate (1).
6. The reference hole machining tool for the aircraft engine jet nozzle part beam as claimed in claim 1, wherein the reference hole machining tool comprises: the right end face of the rotary positioning block (4) is connected with a positioning screw rod, the positioning screw rod is connected with a connecting block through threads, and the connecting block is fixed on the bottom plate.
7. The reference hole machining tool for the aircraft engine jet nozzle part beam as claimed in claim 1, wherein the reference hole machining tool comprises: the lug positioning block (5) is in interference fit with the positioning centering block (51) through an assembling groove (513).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223194274.8U CN218800614U (en) | 2022-11-30 | 2022-11-30 | Benchmark hole processing frock of aircraft engine exhaust nozzle spare part roof beam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223194274.8U CN218800614U (en) | 2022-11-30 | 2022-11-30 | Benchmark hole processing frock of aircraft engine exhaust nozzle spare part roof beam |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218800614U true CN218800614U (en) | 2023-04-07 |
Family
ID=87262403
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223194274.8U Active CN218800614U (en) | 2022-11-30 | 2022-11-30 | Benchmark hole processing frock of aircraft engine exhaust nozzle spare part roof beam |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218800614U (en) |
-
2022
- 2022-11-30 CN CN202223194274.8U patent/CN218800614U/en active Active
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