CN115338619B - Aircraft engine blade equipment frock - Google Patents
Aircraft engine blade equipment frock Download PDFInfo
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- CN115338619B CN115338619B CN202211252937.9A CN202211252937A CN115338619B CN 115338619 B CN115338619 B CN 115338619B CN 202211252937 A CN202211252937 A CN 202211252937A CN 115338619 B CN115338619 B CN 115338619B
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- driving
- feeding
- pipe
- adjusting
- wheel disc
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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
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
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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
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/001—Article feeders for assembling machines
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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
- B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
- B23P2700/01—Aircraft parts
Abstract
The invention discloses an aircraft engine blade assembling tool, and relates to the technical field of aircraft accessory assembling. The automatic checking machine comprises a workbench, an adjusting table, a feeding box and a checking mechanism, wherein a working shaft is arranged in the adjusting table, and meanwhile, the two opposite side surfaces of the adjusting table are connected with the feeding box and a front checking block through adjusting columns. According to the invention, the feeding box and the checking mechanism are arranged on the inner surface of the adjusting table, and the adjusting column, the driven cavity and the driving cavity are connected together, so that after the blades are installed on the feeding box, the blades automatically enter the checking mechanism for installation quality along with station transfer to participate in quality detection and timely correction, efficient and automatic installation and assembly of the blades are ensured, and meanwhile, the installation condition can be timely detected and corrected, and the success rate is improved.
Description
Technical Field
The invention belongs to the technical field of aircraft accessory assembly, and particularly relates to an aircraft engine blade assembly tool.
Background
The aircraft engine is also called an aircraft engine, is a main driving device in an aircraft structure, and generally needs to provide stable output power before the aircraft takes off and flies; because the aircraft engine mainly acts on the air fluid, the surface of an output shaft of the aircraft engine is usually provided with a plurality of groups of air guide impellers, so that the aircraft engine continuously provides propelling force for the aircraft; as is well known, the surface of the air guide impeller comprises a plurality of blades, and the connection mode of the blades and the impeller wheel disc is generally simple tenon-and-mortise connection, so that in the working environment of the prior art, the installation of the blades is generally manually completed by an operator; although the accuracy of blade installation can be ensured to a certain extent, the working efficiency is seriously influenced because more blades are installed on a plurality of groups of impeller wheel discs and the workload is often large in the actual installation and assembly process; if the assembly and installation are carried out in a mechanical automation mode and the like, the problems of low precision and easy installation quality occur; in order to solve the problems, the blade assembling tool for the aircraft engine is designed.
Disclosure of Invention
The invention aims to provide an aircraft engine blade assembling tool, which solves the problems of low working efficiency and low mechanical installation precision of the existing manual installation of blades.
In order to solve the technical problems, the invention is realized by the following technical scheme:
the invention relates to an aircraft engine blade assembling tool which comprises a workbench, an adjusting table, a feeding box and a checking mechanism, wherein the checking mechanism comprises a front checking block and a rear checking block, and the upper surface of the workbench is welded and fixed with the adjusting table; the two opposite side surfaces of the adjusting table are slidably clamped with four adjusting columns, the feeding box and the prepositive checking block are fixedly bolted with the two adjusting columns, and the feeding box and the prepositive checking block are respectively arranged on the two opposite sides of the adjusting table; the two adjusting columns on the same side are oppositely arranged, so that the balance of the mechanism can be ensured when the feeding box and the front check block are adjusted; the front check block and the rear check block have the same structure and are opposite in position, wherein the front check block and the rear check block are both in a step block structure, and the upper bottom surfaces of the two step blocks are opposite in position;
four driven cavities and two driving cavities are formed in the adjusting table, wherein the four driven cavities are divided into two groups, and the two groups are opposite in position; the two driven cavities in the same group are communicated with each other through a driving cavity; the adjusting column extends to the interior of the driven cavity and forms a piston structure with the driven cavity; the upper surface and the lower surface of the adjusting platform are both connected with hydraulic driving pipes through flanges, a pressure connecting pipe is welded and communicated between the two hydraulic driving pipes, and the other ends of the hydraulic driving pipes extend and are communicated to the interior of the driving cavity; the driven cavities of the upper group and the lower group are communicated with each other through the two driving cavities, the hydraulic driving pipes and the pressure connecting pipe, so that an electric hydraulic cylinder is arranged at one of the hydraulic driving pipes to simultaneously drive the four adjusting columns to stretch and retract;
the inner bearing of the adjusting platform is connected with a working shaft, and two opposite ends of the working shaft extend to the outside of the adjusting platform; tooth grooves are formed in the peripheral side face of one end of the working shaft and are arranged into installation sections; the mounting section is occluded with the impeller wheel disc, and the impeller wheel disc is arranged between the front calibration block and the rear calibration block; the outer edge of the impeller wheel disc is provided with the mounting grooves of the blades, so that the mounting grooves of the blades are over against a gap between the front check block and the rear check block during actual mounting and assembling;
a feeding port is formed in one side face of the feeding box, is arranged in the lower half section of the feeding box and is attached to the impeller wheel disc; a feeding groove pipe is fixedly welded on the other side surface of the feeding box, and a track pipe is fixedly welded on the inner surface of the feeding groove pipe; a pushing pipe is clamped between the feeding groove pipe and the track pipe in a sliding manner, and the pushing pipe, the feeding groove pipe and the track pipe form a piston structure; and a material pushing plate is welded at one end of the material pushing pipe and arranged inside the feeding box.
Furthermore, a feeding cylinder is fixedly bolted on one surface of the feeding box, and one end of the feeding cylinder is communicated with the pushing pipe through a pipeline; a driving rod is arranged in the feeding cylinder, and the driving rod and the feeding cylinder form a piston structure; a feeding shaft is connected to a rotating shaft on one surface of the feeding box, and an eccentric wheel disc is welded on the circumferential side surface of the feeding shaft; an eccentric connecting rod is hinged between the eccentric wheel disc and the driving rod, and the eccentric connecting rod is eccentrically hinged with the eccentric wheel disc; the eccentric wheel disc, the driving rod and the eccentric connecting rod form a crank connecting rod structure together, so that when the feeding shaft drives the eccentric wheel disc to rotate, the driving rod can be driven to do reciprocating piston motion in the feeding cylinder.
Furthermore, a driving worm is connected to a surface bearing of the workbench, a driven worm wheel is welded to one end of the feeding shaft, and the driving worm is meshed with the driven worm wheel; a transmission shaft is connected to a surface bearing of the adjusting table, a transmission worm wheel is welded to one end of the transmission shaft, and the transmission worm wheel is meshed with the driving worm; the other end of the transmission shaft is welded with a driving chain wheel, the other end of the working shaft is welded with a driven chain wheel, and the driving chain wheel is in transmission fit with the driven chain wheel through a mounting chain;
in the structure, the driving worm is a main body driving component in the integral structure, when the driving worm rotates, on one hand, the driven worm wheel and the driving worm are utilized to drive the feeding shaft to rotate, so that the eccentric wheel disc rotates, and the crank connecting rod structure is utilized to drive the driving rod to do reciprocating piston motion in the feeding cylinder; on the other hand, the transmission shaft, the transmission worm wheel and the chain wheel and chain structure drive the working shaft to rotate, so that the impeller wheel disc rotates, and the station of the blade mounting groove on the surface of the impeller wheel disc rotates.
Furthermore, a clamping groove is formed in one surface of the workbench, and a clamping frame is clamped in the clamping groove in a sliding manner; one surface of the clamping frame is fixedly welded with the rear check block; an adjusting bolt is rotationally clamped on the inner surface of the clamping groove; the adjusting bolt penetrates through the clamping frame and extends to the outside of the workbench, and the clamping frame and the adjusting bolt form a screw rod structure; when the adjusting bolt rotates, the clamping frame is driven to slide in the clamping groove by the screw rod structure formed by the clamping frame and the adjusting bolt, and the impeller wheel disc is supported and clamped by the clamping frame.
Further, the working shaft penetrates through the clamping frame and is in rotating fit with the clamping frame; a plurality of balls are rotationally clamped on one surface of the clamping frame, and the balls are arranged in an annular array by taking the working shaft as a circle center and are in contact with the impeller wheel disc; wherein the ball can support tightly the impeller rim plate on the one hand and support, and on the other hand constitutes bearing structure with holding frame and impeller rim plate self, the rotation of the impeller rim plate of being convenient for self.
Furthermore, the driving worm is externally connected with a driving motor and is fixedly connected with an output shaft of the driving motor; the hydraulic driving pipe is externally connected with an electric hydraulic cylinder, and an output shaft of the electric hydraulic cylinder extends to the inside of the hydraulic driving pipe; the inside of hydraulic drive pipe, pressure pipe and feeding cylinder all is filled with hydraulic oil, utilizes the hydraulic transmission structure can improve the support intensity between the structure, combines the reciprocating piston motion that the actuating lever was done in feeding cylinder inside, can utilize hydraulic oil to promote to push away material pipe and scraping wings reciprocal slip between pay-off box and pay-off groove pipe, and then pushes the blade inside the blade mounting groove of impeller rim plate.
Preferably, the method for assembling the blade by using the blade assembling tool for the aircraft engine comprises the following steps:
the method comprises the following steps that firstly, an impeller wheel disc to be assembled is nested on the surface of an installation section, then a screw rod structure is utilized to push a clamping frame and a rear check block to tightly abut against the impeller wheel disc through a rotary adjusting bolt, and the impeller wheel disc is supported and clamped;
step two, starting the electric hydraulic cylinder, adjusting the hydraulic pressure in the hydraulic driving pipe and the pressure connecting pipe through an output shaft of the electric hydraulic cylinder, and under the action of hydraulic transmission, adjusting the position of the feeding box and the preposed check block by sliding the adjusting column in the driven cavity, so that the feeding port and the preposed check block are opposite to the blade mounting groove on the surface of the impeller wheel disc;
stacking the blades to be installed inside the feeding box, and enabling the insertion ends of the blades to face the blade installation grooves; then starting a driving motor, driving a driving shaft of the driving motor to drive a driving worm to rotate, on one hand, driving a feeding shaft to rotate by utilizing a driven worm wheel and the driving worm, further enabling an eccentric wheel disc to rotate, and driving a driving rod to do reciprocating piston motion in a feeding cylinder by utilizing a crank connecting rod structure; the piston motion of the driving rod can push the material pushing pipe and the material pushing plate to slide between the feeding box and the feeding groove pipe in a reciprocating mode by utilizing hydraulic oil, and then the blades are pushed into the blade mounting grooves of the impeller wheel disc; on the other hand, the working shaft is driven to rotate through the transmission shaft, the transmission worm wheel and the chain wheel and chain structure, so that the impeller wheel disc is rotated, and the station of the blade mounting groove on the surface of the impeller wheel disc is rotated;
after the bottom layer blade is pushed into the blade mounting groove by the material pushing pipe, the material pushing pipe can be quickly reset due to reciprocating motion, so that the blade moves down one layer; meanwhile, under the rotation action of the impeller wheel disc, the next blade mounting groove moves to a mounting station; after the process is circulated for many times, when the installed blade rotates to the checking mechanism, the front checking block and the rear checking block of the step block structure press the blade which is raised because the blade is not installed in place into the blade installation groove.
The invention has the following beneficial effects:
according to the invention, the feeding box and the checking mechanism are arranged on the inner surface of the adjusting table, and the adjusting column, the driven cavity and the driving cavity are connected together, so that after the blades are installed on the feeding box, the blades automatically enter the checking mechanism for installation quality along with station transfer to participate in quality detection and timely correction, and the installation condition can be timely detected and corrected while efficient and automatic installation and assembly of the blades are ensured, thereby improving the success rate;
the feeding device comprises a feeding cylinder, a driving worm, a driven worm wheel, a driving worm, a driving rod, an eccentric wheel disc, a crank connecting rod structure and a driving shaft, wherein the driving worm is arranged, so that the driven worm wheel and the driving worm are used for driving the feeding shaft to rotate, the eccentric wheel disc is further rotated, and the driving rod is driven to reciprocate in the feeding cylinder by the crank connecting rod structure; on the other hand, the transmission shaft, the transmission worm wheel and the chain wheel and chain structure drive the working shaft to rotate, so that the impeller wheel disc rotates, and the station of the blade mounting groove on the surface of the impeller wheel disc rotates.
Of course, it is not necessary for any product in which the invention is practiced to achieve all of the above-described advantages at the same time.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a left side schematic structural view of an aircraft engine blade assembly fixture of the present invention;
FIG. 2 is a partial view of portion A of FIG. 1;
FIG. 3 is a top view of an aircraft engine blade assembly fixture of the present invention;
FIG. 4 is a schematic structural view of section B-B of FIG. 3;
FIG. 5 is a schematic structural view of section C-C of FIG. 3;
FIG. 6 is a schematic structural view of section D-D in FIG. 3;
FIG. 7 is a partial view of portion F of FIG. 6;
FIG. 8 is a front view of an aircraft engine blade assembly fixture of the present invention;
FIG. 9 is a schematic structural view of section G-G of FIG. 8;
FIG. 10 is a schematic view of the structure of section H-H in FIG. 8;
FIG. 11 is a partial view of portion I of FIG. 10;
FIG. 12 is a schematic structural view of the front side of an aircraft engine blade assembly fixture of the present invention;
fig. 13 is a partial display view of portion K in fig. 12.
In the drawings, the components represented by the respective reference numerals are listed below:
1. a work table; 2. an adjusting table; 3. a feeding box; 4. a pre-check block; 5. a post check block; 6. an adjustment column; 7. a driven chamber; 8. a drive chamber; 9. a hydraulic drive tube; 10. a pressure connecting pipe; 11. a working shaft; 12. a feed port; 13. a feed trough pipe; 14. a track pipe; 15. pushing the material pipe; 16. a material pushing plate; 17. a feeding cylinder; 18. a drive rod; 19. a feed shaft; 20. an eccentric wheel disc; 21. an eccentric link; 22. a drive worm; 23. a driven worm gear; 24. a drive shaft; 25. a drive worm gear; 26. a drive sprocket; 27. a driven sprocket; 28. a clamping groove; 29. a clamping frame; 30. adjusting the bolt; 31. and a ball.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "upper", "middle", "outer", "inner", and the like, indicate orientations or positional relationships, are used for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the referenced components or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present invention.
Referring to fig. 1-13, the present invention is an aircraft engine blade assembly fixture, including a workbench 1, an adjusting table 2, a feeding box 3 and a checking mechanism, where the checking mechanism includes a front checking block 4 and a rear checking block 5, and is characterized in that: the upper surface of the workbench 1 is welded and fixed with the adjusting platform 2; four adjusting columns 6 are slidably clamped on two opposite side surfaces of the adjusting table 2, the feeding box 3 and the preposed check block 4 are bolted and fixed with the two adjusting columns 6, and the feeding box 3 and the preposed check block 4 are respectively arranged on two opposite sides of the adjusting table 2; the two adjusting columns 6 on the same side are oppositely arranged, so that the balance of the mechanism can be ensured when the feeding box 3 and the front check block 4 are adjusted; the front check block 4 and the rear check block 5 have the same structure and are opposite in position, wherein the front check block 4 and the rear check block 5 are both in a step block structure, and the upper bottom surfaces of the two step blocks are opposite in position;
four driven cavities 7 and two driving cavities 8 are formed in the adjusting table 2, wherein the four driven cavities 7 are divided into two groups, and the two groups are opposite in position; the two driven cavities 7 in the same group are communicated with each other through a driving cavity 8; the adjusting column 6 extends into the driven cavity 7 and forms a piston structure with the driven cavity 7; the upper surface and the lower surface of the adjusting platform 2 are both connected with hydraulic driving pipes 9 through flanges, a pressure through pipe 10 is welded and communicated between the two hydraulic driving pipes 9, and the other ends of the hydraulic driving pipes 9 extend and are communicated to the interior of the driving cavity 8; the upper and lower groups of driven cavities 7 are communicated with each other through two driving cavities 8, hydraulic driving pipes 9 and a pressure connecting pipe 10, so that an electric hydraulic cylinder is arranged at one hydraulic driving pipe 9 to simultaneously drive the four adjusting columns 6 to stretch and retract;
the inner bearing of the adjusting platform 2 is connected with a working shaft 11, and two opposite ends of the working shaft 11 extend to the outside of the adjusting platform 2; a tooth socket is arranged on the circumferential side surface of one end of the working shaft 11 and is arranged as an installation section; the mounting section is occluded with the impeller wheel disc, and the impeller wheel disc is arranged between the front calibration block 4 and the rear calibration block 5; the outer edge of the impeller wheel disc is provided with the mounting grooves of the blades, so that the mounting grooves of the blades are over against a gap between the front check block 4 and the rear check block 5 during actual mounting and assembling;
a feeding port 12 is formed in one side face of the feeding box 3, and the feeding port 12 is arranged in the lower half section of the feeding box 3 and is attached to the impeller wheel disc; a feeding groove pipe 13 is fixedly welded on the other side surface of the feeding box 3, and a track pipe 14 is fixedly welded on the inner surface of the feeding groove pipe 13; a pushing pipe 15 is clamped between the feeding groove pipe 13 and the track pipe 14 in a sliding manner, and the pushing pipe 15, the feeding groove pipe 13 and the track pipe 14 form a piston structure; a material pushing plate 16 is welded at one end of the material pushing pipe 15, and the material pushing plate 16 is arranged inside the feeding box 3.
Preferably, a feeding cylinder 17 is bolted and fixed on one surface of the feeding box 3, and one end of the feeding cylinder 17 is communicated with the pushing pipe 15 through a pipeline; a driving rod 18 is arranged in the feeding cylinder 17, and the driving rod 18 and the feeding cylinder 17 form a piston structure; a feeding shaft 19 is rotatably coupled to one surface of the feeding box 3, and an eccentric wheel disc 20 is welded to the circumferential side of the feeding shaft 19; an eccentric connecting rod 21 is hinged between the eccentric wheel disc 20 and the driving rod 18, and the eccentric connecting rod 21 is eccentrically hinged with the eccentric wheel disc 20; the eccentric wheel disc 20, the driving rod 18 and the eccentric connecting rod 21 together form a crank connecting rod structure, so that when the feeding shaft 19 drives the eccentric wheel disc 20 to rotate, the driving rod 18 can be driven to do reciprocating piston motion in the feeding cylinder 17.
Preferably, a driving worm 22 is connected to one surface of the workbench 1 in a bearing manner, a driven worm wheel 23 is welded to one end of the feeding shaft 19, and the driving worm 22 is meshed with the driven worm wheel 23; a transmission shaft 24 is connected to one surface of the adjusting platform 2 in a bearing mode, a transmission worm wheel 25 is welded to one end of the transmission shaft 24, and the transmission worm wheel 25 is meshed with the driving worm 22; a driving chain wheel 26 is welded at the other end of the transmission shaft 24, a driven chain wheel 27 is welded at the other end of the working shaft 11, and the driving chain wheel 26 is in transmission fit with the driven chain wheel 27 through a mounting chain;
in the above structure, the driving worm 22 is a main driving member in the whole structure, when the driving worm 22 rotates, on one hand, the driven worm wheel 23 and the driving worm 22 are used to drive the feeding shaft 19 to rotate, so that the eccentric wheel disc 20 rotates, and the crank connecting rod structure is used to drive the driving rod 18 to make reciprocating piston motion in the feeding cylinder 17; on the other hand, the transmission shaft 24, the transmission worm gear 25 and the chain wheel and chain structure drive the working shaft 11 to rotate, so that the impeller wheel disc rotates, and the station of the blade mounting groove on the surface of the impeller wheel disc rotates.
Preferably, a clamping groove 28 is formed on one surface of the workbench 1, and a clamping frame 29 is slidably clamped in the clamping groove 28; one surface of the clamping frame 29 is fixedly welded with the rear check block 5; an adjusting bolt 30 is rotationally clamped on the inner surface of the clamping groove 28; the adjusting bolt 30 penetrates through the clamping frame 29 and extends to the outside of the workbench 1, and the clamping frame 29 and the adjusting bolt 30 form a screw rod structure; when the adjusting bolt 30 is rotated, the screw rod structure formed by the clamping frame 29 and the adjusting bolt 30 drives the clamping frame 29 to slide in the clamping groove 28, so that the clamping frame 29 supports and clamps the impeller wheel disc.
Preferably, the working shaft 11 penetrates the holding frame 29 and is rotatably engaged with the holding frame 29; a plurality of balls 31 are rotatably clamped on one surface of the clamping frame 29, and the balls 31 are arranged in an annular array by taking the working shaft 11 as a circle center and are in contact with the impeller wheel disc; wherein ball 31 can support tightly the impeller rim plate on the one hand and support, and on the other hand constitutes bearing structure with clamping frame 29 and impeller rim plate self, the rotation of the impeller rim plate of being convenient for self.
Preferably, the driving worm 22 is externally connected with a driving motor and is fixedly connected with an output shaft of the driving motor; the hydraulic driving pipe 9 is externally connected with an electric hydraulic cylinder, and an output shaft of the electric hydraulic cylinder extends to the inside of the hydraulic driving pipe 9; the hydraulic drive pipe 9, the pressure pipe 10 and the feeding cylinder 17 are filled with hydraulic oil, the hydraulic transmission structure can improve the supporting strength between the structures, the reciprocating piston motion of the driving rod 18 in the feeding cylinder 17 is combined, the hydraulic oil can be used for pushing the material pushing pipe 15 and the material pushing plate 16 to slide between the feeding box 3 and the feeding groove pipe 13 in a reciprocating mode, and then the blades are pushed into the blade mounting grooves of the impeller wheel disc.
Example (b):
the embodiment is an assembling method and a part of working principles of the assembling tool for the blades of the aircraft engine, which are disclosed by the invention:
it should be noted that, the blade assembly fixture and the assembly method according to the present invention are suitable for an aircraft engine structure in which an impeller disk is engaged with the surface of an engine output shaft through a tooth slot, and therefore, in the actual assembly and installation process, the following steps are included:
step one, nesting an impeller wheel disc to be assembled on the surface of an installation section, then pushing a clamping frame 29 and a rear check block 5 to tightly abut against the impeller wheel disc by rotating an adjusting bolt 30 through a screw rod structure, and supporting and clamping the impeller wheel disc;
step two, starting the electric hydraulic cylinder, adjusting the hydraulic pressure in the hydraulic driving pipe 9 and the pressure connecting pipe 10 through an output shaft of the electric hydraulic cylinder, and under the action of hydraulic transmission, adjusting the position of the feeding box 3 and the preposed check block 4 by sliding the adjusting column 6 in the driven cavity 7, so that the feeding port 12 and the preposed check block 4 are opposite to the blade mounting groove on the surface of the impeller wheel disc;
stacking the blades to be installed inside the feeding box 3, and enabling the insertion ends of the blades to face the blade installation grooves; then, a driving motor is started, a driving shaft of the driving motor drives a driving worm 22 to rotate, on one hand, a driven worm wheel 23 and the driving worm 22 are used for driving a feeding shaft 19 to rotate, so that an eccentric wheel disc 20 rotates, and a crank connecting rod structure is used for driving a driving rod 18 to do reciprocating piston motion in a feeding cylinder 17; the piston motion of the driving rod 18 can utilize hydraulic oil to push the material pushing pipe 15 and the material pushing plate 16 to slide between the feeding box 3 and the feeding groove pipe 13 in a reciprocating manner, so that the blades are pushed into the blade mounting grooves of the impeller wheel disc; on the other hand, the working shaft 11 is driven to rotate through the transmission shaft 24, the transmission worm gear 25 and the chain wheel and chain structure, so that the impeller wheel disc is rotated, and the station of the blade mounting groove on the surface of the impeller wheel disc is rotated;
after the pushing pipe 15 pushes the bottom layer blade into the blade mounting groove, the pushing pipe 15 can be quickly reset due to reciprocating motion, so that the blade moves down one layer; meanwhile, under the rotation action of the impeller wheel disc, the next blade mounting groove moves to a mounting station; after the process is circulated for many times, when the installed blade rotates to the checking mechanism, the front checking block 4 and the rear checking block 5 of the step block structure press the blade which is raised because the blade is not installed in place into the blade installation groove.
It should be added that, as an alternative to the solution according to the invention, the drive member connected to the hydraulic drive tube 9 can be replaced by a manual hydraulic cylinder during the actual assembly, which provides better stability and precision in the adjustment operation.
In the description herein, references to the description of "one embodiment," "an example," "a specific example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the invention disclosed above are intended to be illustrative only. The preferred embodiments are not intended to be exhaustive or to limit the invention to the precise embodiments disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best utilize the invention. The invention is limited only by the claims and their full scope and equivalents.
Claims (3)
1. The utility model provides an aircraft engine blade equipment frock, includes workstation (1), adjusting station (2), pay-off box (3) and calibration mechanism, and wherein calibration mechanism includes leading calibration block (4) and rearmounted calibration block (5), its characterized in that: the upper surface of the workbench (1) is welded and fixed with the adjusting table (2); the two opposite side surfaces of the adjusting table (2) are slidably clamped with four adjusting columns (6), the feeding box (3) and the front checking block (4) are fixedly bolted with the two adjusting columns (6), and the feeding box (3) and the front checking block (4) are respectively arranged on the two opposite sides of the adjusting table (2); the structure of the front check block (4) is the same as that of the rear check block (5), and the positions of the front check block and the rear check block are opposite;
four driven cavities (7) and two driving cavities (8) are formed in the adjusting table (2), wherein the four driven cavities (7) are divided into two groups, and the two groups are opposite in position; the two driven cavities (7) in the same group are communicated with each other through a driving cavity (8); the adjusting column (6) extends into the driven cavity (7) and forms a piston structure with the driven cavity (7); the hydraulic driving pipes (9) are connected to the upper surface and the lower surface of the adjusting platform (2) in a flange mode, the pressure through pipes (10) are welded and communicated between the two hydraulic driving pipes (9), and the other ends of the hydraulic driving pipes (9) extend and are communicated to the interior of the driving cavity (8);
the inner bearing of the adjusting platform (2) is connected with a working shaft (11), and two opposite ends of the working shaft (11) extend to the outside of the adjusting platform (2); tooth grooves are formed in the circumferential side face of one end of the working shaft (11) and are arranged into mounting sections; the mounting section is occluded with the impeller wheel disc, and the impeller wheel disc is arranged between the front calibration block (4) and the rear calibration block (5);
a feeding port (12) is formed in one side face of the feeding box (3), and the feeding port (12) is arranged in the lower half section of the feeding box (3) and is attached to the impeller wheel disc; a feeding groove pipe (13) is fixedly welded on the other side surface of the feeding box (3), and a track pipe (14) is fixedly welded on the inner surface of the feeding groove pipe (13); a material pushing pipe (15) is clamped between the feeding groove pipe (13) and the track pipe (14) in a sliding manner, and the material pushing pipe (15), the feeding groove pipe (13) and the track pipe (14) form a piston structure; a material pushing plate (16) is welded at one end of the material pushing pipe (15), and the material pushing plate (16) is arranged inside the material feeding box (3);
a feeding cylinder (17) is fixedly bolted on one surface of the feeding box (3), and one end of the feeding cylinder (17) is communicated with the material pushing pipe (15) through a pipeline; a driving rod (18) is arranged in the feeding cylinder (17), and the driving rod (18) and the feeding cylinder (17) form a piston structure;
a surface of the feeding box (3) is rotatably connected with a feeding shaft (19), and an eccentric wheel disc (20) is welded on the circumferential side of the feeding shaft (19); an eccentric connecting rod (21) is hinged between the eccentric wheel disc (20) and the driving rod (18), and the eccentric connecting rod (21) is eccentrically hinged with the eccentric wheel disc (20);
a driving worm (22) is connected to one surface of the workbench (1) in a bearing mode, a driven worm wheel (23) is welded to one end of the feeding shaft (19), and the driving worm (22) is meshed with the driven worm wheel (23);
a transmission shaft (24) is connected to one surface of the adjusting platform (2) in a bearing mode, a transmission worm wheel (25) is welded to one end of the transmission shaft (24), and the transmission worm wheel (25) is meshed with the driving worm (22); a driving chain wheel (26) is welded at the other end of the transmission shaft (24), a driven chain wheel (27) is welded at the other end of the working shaft (11), and the driving chain wheel (26) is in transmission fit with the driven chain wheel (27) through a mounting chain;
a clamping groove (28) is formed in one surface of the workbench (1), and a clamping frame (29) is clamped in the clamping groove (28) in a sliding manner; one surface of the clamping frame (29) is fixedly welded with the rear check block (5); an adjusting bolt (30) is rotationally clamped on the inner surface of the clamping groove (28); the adjusting bolt (30) penetrates through the clamping frame (29) and extends to the outside of the workbench (1), and the clamping frame (29) and the adjusting bolt (30) form a screw rod structure;
the working shaft (11) penetrates through the clamping frame (29) and is in rotating fit with the clamping frame (29); a plurality of balls (31) are rotationally clamped on one surface of the clamping frame (29), and the balls (31) are arranged in an annular array by taking the working shaft (11) as a circle center and are in contact with the impeller wheel disc.
2. The aircraft engine blade assembly tool as claimed in claim 1, wherein the driving worm (22) is externally connected with a driving motor and is fixedly connected with an output shaft of the driving motor; the hydraulic driving pipe (9) is externally connected with an electric hydraulic cylinder, and an output shaft of the electric hydraulic cylinder extends into the hydraulic driving pipe (9); and hydraulic oil is filled in the hydraulic driving pipe (9), the pressure connecting pipe (10) and the feeding cylinder (17).
3. The assembly tool for the blades of the aircraft engine as claimed in claim 1, wherein the method for assembling the blades of the aircraft engine by using the assembly tool for the blades comprises the following steps:
step one, nesting an impeller wheel disc to be assembled on the surface of an installation section, and then pushing a clamping frame (29) and a rear check block (5) to tightly abut against the impeller wheel disc by rotating an adjusting bolt (30) through a screw rod structure to support and clamp the impeller wheel disc;
step two, starting the electric hydraulic cylinder, adjusting the hydraulic pressure in the hydraulic driving pipe (9) and the pressure connecting pipe (10) through an output shaft of the electric hydraulic cylinder, and under the action of hydraulic transmission, adjusting the position of the feeding box (3) and the preposed check block (4) by sliding the adjusting column (6) in the driven cavity (7), so that the feeding port (12) and the preposed check block (4) are opposite to a blade mounting groove on the surface of the impeller wheel disc;
stacking the blades to be installed inside the feeding box (3), and enabling the insertion ends of the blades to face the blade installation grooves; then a driving motor is started, a driving shaft of the driving motor drives a driving worm (22) to rotate, on one hand, a driven worm wheel (23) and the driving worm (22) are utilized to drive a feeding shaft (19) to rotate, so that an eccentric wheel disc (20) rotates, and a crank connecting rod structure is utilized to drive a driving rod (18) to do reciprocating piston motion in a feeding cylinder (17); the piston motion of the driving rod (18) can utilize hydraulic oil to push the material pushing pipe (15) and the material pushing plate (16) to slide between the feeding box (3) and the feeding groove pipe (13) in a reciprocating mode, and then the blades are pushed into the blade mounting groove of the impeller wheel disc; on the other hand, the working shaft (11) is driven to rotate through a transmission shaft (24), a transmission worm gear (25) and a chain wheel and chain structure, so that the impeller wheel disc is rotated, and the station of the blade mounting groove on the surface of the impeller wheel disc is rotated;
after the material pushing pipe (15) pushes the bottom layer blade into the blade mounting groove, the material pushing pipe (15) can be quickly reset due to reciprocating motion, so that the blade moves down one layer; meanwhile, under the rotation action of the impeller wheel disc, the next blade mounting groove moves to a mounting station; after the process is circulated for many times, when the installed blade rotates to the position of the checking mechanism, the front checking block (4) and the rear checking block (5) of the step block structure press the blade which is not installed in place and has a bulge into the blade installation groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211252937.9A CN115338619B (en) | 2022-10-13 | 2022-10-13 | Aircraft engine blade equipment frock |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211252937.9A CN115338619B (en) | 2022-10-13 | 2022-10-13 | Aircraft engine blade equipment frock |
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| CN115338619A CN115338619A (en) | 2022-11-15 |
| CN115338619B true CN115338619B (en) | 2023-03-24 |
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| CN211804733U (en) * | 2019-12-30 | 2020-10-30 | 贵州乾鼎科技发展有限公司 | Aeroengine low pressure turbine guide vane installation device |
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| US20150128417A1 (en) * | 2013-11-13 | 2015-05-14 | Mitsubishi Hitachi Power Systems Americas, Inc. | Turbine blade removal tool and method thereof |
| CN103769851B (en) * | 2014-01-10 | 2016-01-13 | 浦江联力机械有限公司 | Blade automatic assembly equipment on blade lock |
| CN104028988B (en) * | 2014-06-18 | 2016-08-24 | 宁波达恩克电子科技有限公司 | A kind of shaping equipment of blade inserting impeller |
| CN111922673A (en) * | 2019-05-13 | 2020-11-13 | 宁波市天超通风设备有限公司 | Device and method for automatically inserting blades of through-flow impeller into middle disk group |
| CN112665496A (en) * | 2021-01-15 | 2021-04-16 | 江苏南洋中京科技有限公司 | Quick correction gauge for automobile flange plate |
| CN113059337B (en) * | 2021-02-24 | 2022-07-05 | 德邻(广州)航空科技有限责任公司 | But aeroengine blade butt joint equipment of self-modulation butt joint angle |
| CN215316824U (en) * | 2021-06-29 | 2021-12-28 | 浙江浙能电力工程技术有限公司 | Gas turbine moving blade dismounting device |
| CN113478215B (en) * | 2021-07-09 | 2022-04-26 | 江苏兴海特钢有限公司 | Stable assembly calibration seat of stainless steel material processing equipment |
| CN114393408A (en) * | 2021-12-20 | 2022-04-26 | 湖南创研智能装备有限公司 | Blade assembly equipment |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN211804733U (en) * | 2019-12-30 | 2020-10-30 | 贵州乾鼎科技发展有限公司 | Aeroengine low pressure turbine guide vane installation device |
| CN111451738A (en) * | 2020-04-22 | 2020-07-28 | 南京丛迈信息科技有限公司 | Assembling device for impeller in gas turbine |
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