CN117300969A - Diversified assembling device and assembling method for high-pressure compressor rotor of aero-engine - Google Patents
Diversified assembling device and assembling method for high-pressure compressor rotor of aero-engine Download PDFInfo
- Publication number
- CN117300969A CN117300969A CN202311365729.4A CN202311365729A CN117300969A CN 117300969 A CN117300969 A CN 117300969A CN 202311365729 A CN202311365729 A CN 202311365729A CN 117300969 A CN117300969 A CN 117300969A
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- China
- Prior art keywords
- pressure compressor
- assembly
- compressor rotor
- rotor
- diversified
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Links
- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000007514 turning Methods 0.000 claims description 13
- 239000011248 coating agent Substances 0.000 claims description 9
- 238000000576 coating method Methods 0.000 claims description 9
- 238000001035 drying Methods 0.000 claims description 7
- 239000003292 glue Substances 0.000 claims description 7
- 238000000227 grinding Methods 0.000 claims description 7
- 239000000463 material Substances 0.000 claims description 6
- 238000007789 sealing Methods 0.000 claims description 6
- 239000000956 alloy Substances 0.000 claims description 4
- 229910045601 alloy Inorganic materials 0.000 claims description 4
- 238000004026 adhesive bonding Methods 0.000 claims description 3
- 238000005498 polishing Methods 0.000 claims description 3
- 244000126211 Hericium coralloides Species 0.000 claims 1
- 230000006872 improvement Effects 0.000 abstract description 2
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 239000002023 wood Substances 0.000 description 4
- NIXOWILDQLNWCW-UHFFFAOYSA-N acrylic acid group Chemical group C(C=C)(=O)O NIXOWILDQLNWCW-UHFFFAOYSA-N 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 239000000565 sealant Substances 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 208000027418 Wounds and injury Diseases 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000010073 coating (rubber) Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000003801 milling Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
Abstract
The invention discloses a diversified assembling device and an assembling method for a rotor of a high-pressure compressor of an aeroengine. The assembly device has multiple functions of transportation and the like, achieves the aim of convenient assembly of each procedure when the device is adopted for assembly, and achieves the expectations of reliable assembly quality, convenient transportation, convenient hoisting and improvement of assembly efficiency.
Description
Technical Field
The invention belongs to the technical field of assembly of high-pressure compressor rotors of aero-engines, and particularly relates to an assembly tool, equipment and an assembly method for core engine parts of aero-engines.
Background
The high-pressure air compressor rotor of the aeroengine is the most complex part in the assembly of the core engine part of the aeroengine, the process flow is complex, not only is the assembly process performed, but also various combined turning, milling and grinding working procedures are interweaved, so that the rotor is inevitably subjected to repeated transportation and fixture disassembly and assembly, the quality risks of collision injury and scratch of the high-pressure air compressor rotor are increased, and the assembly efficiency of the high-pressure air compressor rotor is greatly reduced.
At present, procedures such as drum barrel before assembling high-pressure air compressor rotor of aeroengine, three-stage disc, one to nine-stage blade assembly, one to three-stage disc mortises coating sealant, blade tip pre-grinding assembly fixture, grating tooth pre-turning assembly, hard alloy pre-coating assembly, final four to nine-stage blade assembly, locking pin assembly and the like need to operate the high-pressure air compressor rotor back and forth, the high-pressure air compressor rotor is repeatedly hoisted on a high-pressure air compressor rotor transfer trolley during movement, repeated disassembly and assembly need more personnel, long time and high scratch risk, and the high-pressure air compressor rotor assembly period is greatly prolonged. And because the high-pressure rotor is the rotor, needs workman round trip movement in the assembly process of assembly blade and rubber coating and locking pin, and fixed frock is only wood pier, and the factor of safety risk is high.
The rotor of the high-pressure compressor is complex in shape, the number of assembled blades is large, the repeated hoisting risk is high, so that the traditional assembly platform and the tooling are not only time-consuming and labor-consuming in construction and assembly, but also are high in safety risk, low in assembly efficiency, low in assembly continuity and low in product quality consistency.
Disclosure of Invention
Aiming at a plurality of problems brought by the traditional assembly tool and route, the invention aims to design a diversified assembly device and an assembly method for the rotor of the high-pressure compressor of the aero-engine, wherein the assembly device has the functions of transportation and other functions, so that the assembly of each procedure is convenient, and the purposes of reliable assembly quality, convenient transportation, convenient hoisting and improvement of assembly efficiency are achieved.
In order to achieve the above purpose, the present invention adopts the following technical scheme:
the rotor diversified assembly device of the high-pressure compressor of the aero-engine comprises,
the vehicle underframe is provided with rollers at the lower end;
the vehicle bottom plate is fixedly connected to the upper end of the vehicle underframe, and a hollowed-out operation area is formed between the lower end of the vehicle bottom plate and the upper end of the vehicle underframe;
the turntable is rotationally connected to the vehicle bottom plate through a thrust ball bearing;
and the clamp is arranged above the turntable and rotates synchronously with the turntable.
Further, the idler wheel comprises a pair of fixed wheels and a pair of movable wheels, the fixed wheels do not rotate or translate relative to the chassis and only rotate around the rotating shaft of the idler wheel, and the movable wheels can rotate relative to the chassis while rotating around the rotating shaft of the idler wheel, so that steering of the chassis is realized.
Further, be provided with the bearing frame on the bottom plate, thrust ball bearing assembles in the bearing frame, and thrust ball bearing's pedestal and bearing housing cooperation, and the balancing weight is installed to the bearing housing upper end, the carousel is fixed on the balancing weight.
Further, a support is arranged on the balancing weight and located on the outer side of the turntable, the upper end of the support is connected with the supporting plate, and a part of the clamp is fixed on the supporting plate.
Further, the balancing weight is further provided with a hand pulling positioner, the hand pulling positioner comprises a locking pin which moves up and down, the vehicle bottom plate is provided with a pin hole, and the pin hole is positioned on a path of the locking pin which moves up and down.
Further, the surfaces of the hoops, which are in contact with the high-pressure compressor rotor of the aero-engine, are covered with a flexible material layer.
Further, the back plate is further connected to the vehicle bottom plate, and the vehicle handle and the storage box are arranged on the back plate.
Further, an oil receiving box is arranged in the hollowed-out operation area.
The assembling method of the rotor of the high-pressure compressor of the aero-engine adopts the diversified assembling device and comprises the following steps:
the method comprises the steps of installing a high-pressure compressor rotor, firstly opening a clamp, hoisting the high-pressure compressor rotor to a rotary table, enabling the small end of a drum shaft of the high-pressure compressor to be downward and contact with the rotary table, and locking the clamp after the high-pressure compressor rotor is installed in place, wherein the clamp is clamped at a step in the middle of the drum shaft;
maintaining the drum shaft of the high-pressure compressor rotor in a fixed state, and performing the assembly of a third-stage high-pressure compressor disc assembly, the assembly of a front drum assembly, the coating of sealing glue on a third-stage disc mortises, the coating of sealing glue on a second-stage mortises, the assembly of blades, the deburring of the blades and the polishing of locking pins;
the rotor of the high-pressure compressor is driven to be in a rotating state by a turntable, and gluing, matching and assembling of two-level blade mortises, burr removal after blade tips are polished, and polishing and mounting of locking pins are carried out;
and implementing a front assembling clamp of the rotor turning comb teeth, a front assembling clamp coated with hard alloy and a front assembling clamp of the turning blades in a hollowed-out operation area between the turning bottom plate and the turning underframe.
The assembling method of the high-pressure compressor rotor of the aero-engine further comprises the step of not disassembling the high-pressure compressor rotor which is already installed on the diversified assembling device, and sending the high-pressure compressor rotor and the high-pressure compressor rotor into drying equipment together for drying treatment of the high-pressure compressor rotor.
In the existing assembly method, the assembly work of the high-pressure compressor is completed by adopting the combination of the wood piers, the transfer trolley, the lifting rigging and the like, the back and forth lifting and the multi-person cooperation operation are needed, the assembly risk is high, the quality is not effectively ensured, and the assembly efficiency is low.
Compared with the prior art, the assembly device and the assembly method have the following characteristics:
(1) the multi-station assembly is diversified, and the multi-station assembly integrated function is realized;
(2) the radial fixing and the rotation along the axis of the rotor of the high-pressure compressor are realized;
(3) the vertical integrated clamping function of the horizontal turning clamp of the high-pressure compressor rotor is realized;
(4) realizing the integration of the transportation and assembly of the high-pressure compressor rotor;
(5) the rotor blade and the locking pin are assembled, and the mortise sealant can be performed at fixed points;
(6) compared with the traditional assembly mode, the safety coefficient is greatly improved;
(7) reducing the lifting and transferring times among the working procedures;
(8) and the assembly efficiency of the rotor of the high-pressure compressor is greatly improved.
Drawings
FIG. 1 is a front view of a multiple assembly device of the present invention;
FIG. 2 is a left side view of FIG. 1;
FIG. 3 is a perspective view of a high pressure compressor rotor multiplex assembly device;
in the figure: 1. the bicycle comprises a bicycle lower frame, a back plate, an oil receiving box, a bicycle bottom plate, a bearing seat, a bearing sleeve, a turntable, a balancing weight, a clamping hoop, a supporting plate, a supporting column, a document box, an acrylic box, a wheel backing plate, a bicycle handle, a thrust ball bearing, a first bolt, a second bolt, a fixed wheel, a driving wheel and a hand pulling positioner.
Detailed Description
The present invention will be further described with reference to the drawings and the specific embodiments, but it should not be construed that the scope of the subject matter of the present invention is limited to the following embodiments, and various modifications, substitutions and alterations made according to the ordinary skill and familiar means of the art to which this invention pertains are included within the scope of the present invention without departing from the above technical idea of the invention.
As shown in fig. 1 to 3, the diversified assembling device for the high-pressure compressor rotor of the aeroengine designed by the invention can also be regarded as a multifunctional transportation device, and the assembling device mainly comprises a chassis 1, a back plate 2, an oil receiving box 3, a chassis 4, a bearing pedestal 5, a bearing sleeve 6, a turntable 7, a balancing weight 8, a clamp 9, a supporting plate 10, a supporting column 11, a file box 12, an acrylic box 13, a wheel pad 14, a handle 15, a thrust ball bearing 16, a first bolt 17, a second bolt 18, a fixed wheel 19, a moving wheel 20, a hand-pulled positioner 21 and the like.
The diversified assembly device takes an assembly vehicle body (a vehicle bottom plate 4) and a turntable 7 with a lockable bearing as main structures, a high-pressure compressor rotor is placed in a clamp 9, and the contact surface of the clamp 9 and the high-pressure compressor rotor adopts flexible pollution-free contact materials, so that the high-pressure compressor rotor is fixed, and toppling and contact scratches are prevented; the rotation of carousel 7 relies on bearing frame 5, thrust ball bearing 16, balancing weight 8, the cooperation of bearing housing 6 to realize, bearing frame 5, balancing weight 8 and bearing housing 6 are annular structure and through first bolt 17 and the combined installation of second bolt 18, the bearing frame 5 is installed on bottom plate 4, thrust ball bearing 16 is installed on bearing frame 5, thereby the pedestal bore of thrust ball bearing 16 is installed to one part of bearing housing 6, thereby another part compresses tightly at thrust ball bearing 16's pedestal face and supports balancing weight 8, balancing weight 8 is used for adjusting the focus position when high-pressure compressor rotor rotates, ensure not to take place the tipping. The supporting plate 10 is arranged on the balancing weight 8 through a plurality of support posts 11, the upper end surface of the supporting plate 10 is fixed with the non-movable part of the clamp 9, and the movable part of the clamp 9 rotates around the non-movable part, so that the clamp 9 is opened and locked. The function of rotating the high-pressure compressor rotor around the axis is realized through the turntable 7, and the rotation stopping and moving of the high-pressure compressor rotor are realized by means of the hand-pulled positioner 21 through manually controlling the on and off of the locking pin (the hand-pulled positioner 21 is fixed on the balancing weight 8, and the locking pin can move up and down, so that the pin control on the vehicle bottom plate 4 is inserted or pulled out); the clamp (core rod type heavy clamp) for horizontal rotation processing of the high-pressure compressor rotor depends on the hollowed-out operation space of the lathe bottom plate 4, so that the clamp is convenient to mount and dismount, the safety coefficient is greatly improved, and an oil receiving box 3 is also arranged in the hollowed-out operation space; the software data of the high-pressure compressor rotor can be placed in the file box 12 and the sub-Ke Li box 13, the chassis 1 is designed into a trolley with fixed wheels 19 and movable wheels 20, the transportation among the assembly procedures can be realized, the integrated drying function of the high-pressure compressor rotor can also be realized, the chassis 1 is connected with the fixed wheels 19 and the movable wheels 20 through the wheel pad 14, the fixed wheels 19 can only rotate, and the movable wheels 20 can rotate relative to the chassis 1 besides rotating, so that the steering of the diversified assembly device is realized; the underframe 1 and the underframe 4 adopt steel plates as material structures, so that the structural strength of the assembly device is enhanced, and the fixed wheels 19 and the movable wheels 20 adopt high-temperature resistant materials, so that the fixed wheels 19 and the movable wheels 20 are prevented from being damaged by drying. The back plate 2 is also connected to the vehicle bottom plate 4 and is used for installing a handle 15 for pushing the diversified assembly devices, and a file box and an acrylic box 13.
When the high-pressure compressor rotor is assembled, the clamp 9 is opened, the high-pressure compressor rotor is hoisted to the turntable 7 of the vehicle bottom plate 4 by using a hoisting tool, and the small end of the drum barrel of the high-pressure compressor is downward contacted with the turntable 7; the clamp 9 is locked after the assembly is in place, and the clamp 9 is clamped at the step in the middle of the drum shaft, so that the potential safety hazard caused by placing the high-pressure compressor rotor on a wood pier during traditional assembly is solved, and the risks of ageing and artificial bumping caused by the wood pier are effectively prevented. And in the same way, the procedures of fixing the middle part of the drum shaft for assembly can be performed on the diversified assembly device, and the procedures of assembling the third-stage high-pressure compressor disc assembly, assembling the front drum assembly, coating the sealing glue on the three-stage disc mortises, coating the sealing glue on the two-stage mortises, assembling the blades, deburring the blades, repairing and grinding the locking pins and the like can be performed on the assembly device. The high-pressure compressor is fixed on the diversified assembly device and is locked by the clamp 9, and the rotor of the high-pressure compressor can rotate around the axis through the driving of the turntable 7, so that the process contents that the rotor can be rotated to better perform and improve the efficiency are realized, such as gluing of a two-level blade mortises, matching and assembling work of four-level and nine-level blades, burr removing work after the blade tips are ground, grinding and installing work of locking pins, the assembling work efficiency can be greatly improved after the high-pressure compressor has a self-rotation function on the device, and the safety risk can be greatly reduced.
The vehicle bottom plate 1 of the diversified assembly device is designed into a middle hollow structure, so that the installation and the disassembly of the vehicle and the grinding clamp can be realized, the times of hoisting the high-pressure compressor rotor back and forth are reduced, and the assembly period is shortened. Therefore, the assembling clamp before turning the comb teeth and the assembling clamp before coating the hard alloy and the assembling clamp before turning and grinding the blades of the high-pressure compressor rotor can be carried out on a diversified assembling device.
The diversified assembly device is designed into a trolley structure, so that transportation among assembly links can be realized on the diversified assembly device, and the safety is high. The wheels of the diversified assembly device have steering function and are designed to be made of high-temperature resistant materials, so that the high-pressure compressor rotor can be directly pushed out for drying after being coated with glue on the diversified assembly device, convenience and rapidness can be realized, and quality and efficiency can be improved.
What is not described in detail in the description of the invention belongs to the prior art known to those skilled in the art. While the foregoing describes illustrative embodiments of the present invention to facilitate an understanding of the present invention by those skilled in the art, it should be understood that the present invention is not limited to the scope of the embodiments, but is to be construed as protected by the accompanying claims insofar as various changes are within the spirit and scope of the present invention as defined and defined by the appended claims.
Claims (10)
1. Diversified assembly device of aeroengine high-pressure compressor rotor, its characterized in that: the vehicle comprises a vehicle underframe (1), wherein rollers are arranged at the lower end of the vehicle underframe (1);
the vehicle bottom plate (4), the vehicle bottom plate (4) is fixedly connected to the upper end of the vehicle underframe (1), and a hollowed-out operation area is formed between the lower end of the vehicle bottom plate (4) and the upper end of the vehicle underframe (1);
the turntable (7) is rotationally connected to the vehicle bottom plate (4) through a thrust ball bearing (16); and the clamp (9) is arranged above the turntable (7) and rotates synchronously with the turntable (7).
2. The aircraft engine high pressure compressor rotor diversified assembly device of claim 1, wherein: the roller comprises a pair of fixed wheels (19) and a pair of movable wheels (20), the fixed wheels (19) do not rotate or translate relative to the chassis (1) and only rotate around a rotating shaft of the roller, and the movable wheels (20) can rotate relative to the chassis (1) while rotating around the rotating shaft of the roller, so that the steering of the chassis (1) is realized.
3. The aircraft engine high pressure compressor rotor diversified assembly device of claim 1, wherein: the novel automobile bottom plate is characterized in that a bearing seat (5) is arranged on the automobile bottom plate (4), a thrust ball bearing (16) is assembled in the bearing seat (5), a shaft collar of the thrust ball bearing (16) is matched with a bearing sleeve (6), a balancing weight (8) is arranged at the upper end of the bearing sleeve (6), and the rotary table (7) is fixed on the balancing weight (8).
4. The aircraft engine high pressure compressor rotor diversified assembling device of claim 3, wherein: the balancing weight (8) is provided with a support column (11) which is positioned outside the turntable (7), the upper end of the support column (11) is connected with the supporting plate (10), and a part of the clamp (9) is fixed on the supporting plate (10).
5. The aircraft engine high pressure compressor rotor diversified assembling device of claim 3, wherein: the balancing weight (8) is also provided with a hand-pulling positioner (21), the hand-pulling positioner (21) comprises a locking pin which moves up and down, the vehicle bottom plate (4) is provided with a pin hole, and the pin hole is positioned on a path of the locking pin which moves up and down.
6. The aircraft engine high pressure compressor rotor diversified assembly device of claim 1, wherein: the surfaces of the clamping bands (9) which are contacted with the rotor of the high-pressure compressor of the aero-engine are covered with flexible material layers.
7. The aircraft engine high pressure compressor rotor diversified assembly device of claim 1, wherein: the vehicle bottom plate (4) is also connected with a back plate (2), and the back plate (2) is provided with a vehicle handle (15) and a storage box.
8. The aircraft engine high pressure compressor rotor diversified assembly device of claim 1, wherein: an oil receiving box (3) is arranged in the hollowed-out operation area.
9. A method for assembling a rotor of a high-pressure compressor of an aeroengine is characterized by comprising the following steps of: a multiple fitting apparatus as claimed in claim 1, and comprising:
the method comprises the steps of installing a high-pressure compressor rotor, firstly opening a clamp (9), hoisting the high-pressure compressor rotor to a rotary table (7), enabling the small end of a drum shaft of the high-pressure compressor to be downward and contact with the rotary table (7), locking the clamp (9) after the high-pressure compressor rotor is installed in place, and clamping the clamp (9) at a step in the middle of the drum shaft;
maintaining the drum shaft of the high-pressure compressor rotor in a fixed state, and performing the assembly of a third-stage high-pressure compressor disc assembly, the assembly of a front drum assembly, the coating of sealing glue on a third-stage disc mortises, the coating of sealing glue on a second-stage mortises, the assembly of blades, the deburring of the blades and the polishing of locking pins;
the rotor of the high-pressure compressor is driven to be in a rotating state through a turntable (7), and gluing, matching and assembling of a two-level blade and a two-level blade, burr removal after the blade tip is ground, and grinding and mounting of a locking pin are carried out;
and (3) implementing a rotor turning comb tooth front assembly fixture, a hard alloy coated front assembly fixture and a turning blade front assembly fixture in a hollowed-out operation area between the turning base plate (4) and the turning underframe (1).
10. The aircraft engine high pressure compressor rotor assembly method of claim 9, wherein: and the high-pressure compressor rotor which is installed on the diversified assembly device is not dismounted, and the high-pressure compressor rotor are sent into the drying equipment together for drying treatment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311365729.4A CN117300969A (en) | 2023-10-20 | 2023-10-20 | Diversified assembling device and assembling method for high-pressure compressor rotor of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311365729.4A CN117300969A (en) | 2023-10-20 | 2023-10-20 | Diversified assembling device and assembling method for high-pressure compressor rotor of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117300969A true CN117300969A (en) | 2023-12-29 |
Family
ID=89246180
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311365729.4A Pending CN117300969A (en) | 2023-10-20 | 2023-10-20 | Diversified assembling device and assembling method for high-pressure compressor rotor of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117300969A (en) |
-
2023
- 2023-10-20 CN CN202311365729.4A patent/CN117300969A/en active Pending
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