CN210499981U - Front ring dismounting vehicle for aircraft engine - Google Patents
Front ring dismounting vehicle for aircraft engine Download PDFInfo
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- CN210499981U CN210499981U CN201921348673.0U CN201921348673U CN210499981U CN 210499981 U CN210499981 U CN 210499981U CN 201921348673 U CN201921348673 U CN 201921348673U CN 210499981 U CN210499981 U CN 210499981U
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- front ring
- aircraft engine
- upper frame
- saddle
- stop lever
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Abstract
The utility model belongs to the technical field of an airplane assembly auxiliary device and discloses an airplane engine front ring dismounting vehicle which comprises an underframe, a lifting mechanism, an upper frame and a fixed frame; four corners of the bottom frame are respectively provided with a roller; the lifting mechanism comprises a telescopic bracket and a power mechanism, wherein the telescopic bracket is respectively connected with the bottom frame and the upper frame, and the power mechanism is used for controlling the telescopic bracket to stretch; the fixing frame comprises a saddle and a stop lever, the saddle is fixedly arranged at the top of the upper frame, the stop lever is hinged to the upper frame, and a stop lever adjusting mechanism is arranged on one side of the stop lever, which deviates from the saddle. The aircraft engine front ring dismounting vehicle is simple in structure, strong in practicability, safe and reliable, the existing manual dismounting mode is replaced by the hydraulic lifting dismounting mode, the working efficiency is greatly improved, and the labor intensity is reduced.
Description
Technical Field
The utility model belongs to the technical field of aircraft assembly auxiliary device, concretely relates to ring dismouting car before aircraft engine.
Background
The steel cable that the in-process all adopted hoists before ring when dismouting before current aircraft engine, then carries out the dismouting by the manual work, and the steel cable hoist and mount damages the front ring easily, and working strength is big moreover, and the dismouting is efficient.
SUMMERY OF THE UTILITY MODEL
In order to solve the above-mentioned one or more technical problem that prior art exists, the utility model provides an aircraft engine front ring dismouting car.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
an aircraft engine front ring dismounting vehicle comprises a bottom frame, a lifting mechanism, an upper frame and a fixed frame; four corners of the bottom frame are respectively provided with a roller; the lifting mechanism comprises a telescopic bracket and a power mechanism, wherein the telescopic bracket is respectively connected with the bottom frame and the upper frame, and the power mechanism is used for controlling the telescopic bracket to stretch; the fixing frame comprises a saddle and a stop lever, the saddle is fixedly arranged at the top of the upper frame, the stop lever is hinged to the upper frame, and a stop lever adjusting mechanism is arranged on one side of the stop lever, which deviates from the saddle.
Furthermore, a plurality of landing mechanisms are arranged on the side part of the underframe.
Further, the telescopic bracket comprises two sets of scissors forks arranged in parallel, each set of scissors forks comprises a first movable rod and a second movable rod, the middle part of the first movable rod is hinged and connected with the middle part of the second movable rod, the bottom end of the first movable rod is hinged and connected with the chassis, the top end of the first movable rod is connected with the upper frame through a first connecting rod, and the bottom end of the second movable rod is connected with the chassis through a sliding connection.
Furthermore, the power mechanism comprises a hydraulic pump arranged on the bottom frame, the output end of the hydraulic pump is respectively connected with two hydraulic cylinders arranged on the second connecting rod, and the output ends of the two hydraulic cylinders are respectively hinged with the first connecting rod.
Further, the hydraulic pump is a hand pump.
Furthermore, the saddle is of a wood structure, a supporting groove for supporting a front ring of the engine is arranged in the middle of the saddle, and an anti-collision layer is arranged on the surface of the supporting groove.
Furthermore, binding belts are arranged on two sides of the saddle.
Furthermore, the stop lever adjusting mechanism comprises two adjusting rods, one ends of the two adjusting rods, which are opposite to each other, are connected through an adjusting screw rod, and an adjusting handle is arranged on the adjusting screw rod; one end of one of the adjusting rods, which is far away from the adjusting screw rod, is hinged with the upper frame, and the other end of the other adjusting rod, which is far away from the adjusting screw rod, is connected with the stop lever.
Furthermore, the top of the upper frame is located the saddle with still the symmetry is provided with two cushion between the pin, two the one end of cushion respectively with the upper frame is articulated to be connected, two one side that the cushion is mutually carried on the back mutually is provided with the lift adjustment pole respectively.
Furthermore, a towing rod is further arranged on the aircraft engine front ring dismounting vehicle.
Compared with the prior art, the utility model provides a technical scheme has following beneficial effect or advantage:
the utility model provides an aircraft engine front ring dismouting car simple structure, the practicality is strong, safe and reliable, the dismouting mode that adopts hydraulic pressure to go up and down replaces current artifical dismouting mode, has improved work efficiency widely and has alleviateed intensity of labour.
Specific embodiments of the present invention are disclosed in detail with reference to the following description and the accompanying drawings, which specify the manner in which the principles of the invention may be employed. It should be understood that the embodiments of the present invention are not so limited in scope. The embodiments of the invention include many variations, modifications and equivalents within the spirit and scope of the appended claims.
Features that are described and/or illustrated with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments, in combination with or instead of the features of the other embodiments.
It should be emphasized that the term "comprises/comprising" when used herein, is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps or components.
Drawings
In order to illustrate the embodiments of the present invention or the technical solutions in the prior art more clearly, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without inventive exercise.
Fig. 1 is a schematic structural diagram of an aircraft engine front ring dismounting vehicle provided by an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a bottom frame in an embodiment of the present invention;
fig. 3 is a schematic structural view of an expansion bracket according to an embodiment of the present invention;
fig. 4 is a schematic structural view of the fixing frame according to the embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
It should be noted that, in the present invention, the embodiments and features of the embodiments may be combined with each other without conflict.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the embodiments of the present invention, it should be noted that the indication of the position or the positional relationship is based on the position or the positional relationship shown in the drawings, or the position or the positional relationship that the utility model is usually placed when using, or the position or the positional relationship that the skilled person conventionally understands, or the position or the positional relationship that the utility model is usually placed when using, and is only for the convenience of describing the present invention and simplifying the description, but does not indicate or suggest that the indicated device or element must have a specific position, be constructed and operated in a specific position, and thus, cannot be understood as limiting the present invention.
In the description of the embodiments of the present invention, it should be further noted that unless otherwise explicitly stated or limited, the terms "disposed" and "connected" should be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; may be directly connected or indirectly connected through an intermediate. For those skilled in the art, the drawings of the above terms in the embodiments with specific meanings in the present invention can be understood in specific situations, and the technical solutions in the embodiments of the present invention are clearly and completely described, and it is obvious that the described embodiments are some embodiments of the present invention, not all embodiments. The components of embodiments of the present invention, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations. Furthermore, the terms "first" and "second" are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
As shown in fig. 1, an embodiment of the present invention provides an aircraft engine front ring dismounting vehicle, which includes an underframe 100, a lifting mechanism 200, an upper frame 300 and a fixed frame 400; four corners of the bottom of the chassis 100 are respectively provided with rollers 110; the lifting mechanism 200 comprises a telescopic bracket and a power mechanism for controlling the telescopic bracket to extend and retract, wherein the telescopic bracket is respectively connected with the underframe 100 and the upper frame 300; the fixing frame 400 comprises a saddle 410 and a stop lever 420, the saddle 410 is fixedly arranged at the top of the upper frame 300, the stop lever 420 is hinged with the upper frame 300, and a stop lever adjusting mechanism 430 is arranged on one side of the stop lever 420, which is far away from the saddle 410.
It should be noted that the roller 110 in the embodiment of the present invention includes two sizing rollers disposed on one side and a universal roller disposed on the other side. The universal idler wheels are arranged, so that the forward or backward direction of the aircraft engine front ring dismounting vehicle can be adjusted conveniently.
In a specific implementation process, since the aircraft engine front ring dismounting vehicle is used for assisting in dismounting the aircraft engine front ring, the stability of the aircraft engine front ring dismounting vehicle must be ensured, so in order to improve the stability of the aircraft engine front ring dismounting vehicle in the working process, in a further embodiment, the embodiment of the present invention further provides a plurality of landing mechanisms 120 on the side portion of the underframe 100, as shown in fig. 2. Through setting up the mechanism that lands, can effectively improve this aircraft engine front ring dismouting car in the course of the work stability. It should be noted that the landing mechanism in the embodiment of the present invention is an existing conventional landing mechanism, and specifically includes a landing screw rod in threaded connection with an underframe, a landing disc is disposed at the bottom of the landing screw rod, and an adjusting hand wheel is disposed at the top of the landing screw rod.
In specific implementation, the kind of telescopic bracket has a lot, in further implementation scheme, the embodiment of the utility model discloses adopt telescopic bracket includes parallel arrangement's two sets of scissors forks, every group the scissors fork all includes first movable rod 211 and second movable rod 212, as shown in fig. 3, the middle part of first movable rod 211 is connected with the middle part of second movable rod 212 is articulated, the bottom of first movable rod 211 is connected with chassis 100 is articulated, the top and the upper ledge 300 sliding connection of first movable rod 211, the bottom and the chassis 100 sliding connection of second movable rod 212, the top and the upper ledge 300 of second movable rod 212 are articulated to be connected, two sets of connect through first connecting rod 213 between the first movable rod 211 of scissors fork, two sets of connect through second connecting rod 214 between the second movable rod 212 of scissors fork. It should be noted that, in the embodiment of the present invention, the top end of the first movable rod 211 and the upper frame 300 may be slidably connected to each other by a sliding rail disposed on the upper frame 300, a sliding seat disposed on the sliding rail, and the top end of the first movable rod 211 is hinged to the sliding seat, and the telescopic bracket is in the telescopic process, the first movable rod 211 is driven by the power mechanism to slide along the sliding rail. Of course, other methods may be used, and are not limited herein. In addition, the bottom end of the second movable rod 212 is connected to the bottom frame 100 in a sliding manner, and the top end of the first movable rod 211 is connected to the upper frame 300 in a sliding manner, which is not described herein again.
In specific implementation, can drive the flexible power unit of telescopic bracket has a lot of, in further embodiment, in the embodiment of the utility model provides an in power unit including setting up the hydraulic pump 220 on the chassis, the output of hydraulic pump 220 is connected with two pneumatic cylinders 230 that set up on second connecting rod 214 respectively, and the output of two pneumatic cylinders 230 is connected with first connecting rod 213 is articulated respectively.
In a specific implementation process, furthermore, the type and the kind of the hydraulic pump 220 are many, and in a further implementation scheme, the hydraulic pump 220 in the embodiment of the present invention specifically adopts a hand pump. Of course, an automatic hydraulic pump may be used, and is not limited herein.
In specific implementation, in order to prevent the front ring of the engine from being collided or scraped during the assembling, disassembling and transporting processes, in a further embodiment, the saddle 410 in the embodiment of the present invention adopts a wooden structure, and the middle part of the saddle 410 is provided with a bearing groove 411 for bearing the front ring of the engine, and the surface of the bearing groove 411 is provided with an anti-collision layer, as shown in fig. 4. The saddle adopting the wood structure and the surface of the bearing groove 411 are provided with the anti-collision layers, so that the front ring of the engine can be effectively prevented from being collided or scraped in the processes of disassembly, assembly and transportation. It should be noted that, the anti-collision layer in the embodiment of the present invention may be a rubber, or may be other materials, such as a sponge, and is not limited herein. In addition, the side of the stop lever 420 contacting the front ring of the engine is also provided with an anti-collision layer having the same surface as the bearing groove 411.
In a specific implementation, in order to prevent the engine front ring from shaking during transportation, in a further embodiment, the present invention embodiment has binding bands mounted on both sides of the saddle 410. Before the transportation, bind the ring before the engine with the binding band, can make the ring is fixed firm before the engine, prevent effectively that the ring from rocking in the transportation before the engine, avoid the ring to damage in the transportation before the engine.
In a specific implementation process, the number of the stop lever adjusting mechanisms 430 is large, and in a further embodiment, the stop lever adjusting mechanism 430 in the embodiment of the present invention includes two adjusting rods 431 and 432, ends of the two adjusting rods 431 and 432 opposite to each other are connected through an adjusting screw rod 433, and an adjusting handle 434 is disposed on the adjusting screw rod 433; one end of one of the adjusting rods 431, which is far away from the adjusting screw 433, is hinged with the upper frame 300, and one end of the other adjusting rod 432, which is far away from the adjusting screw 433, is connected with the stop lever 420. The stop lever adjusting mechanism 430 has the advantages of simple structure and convenient operation.
In specific implementation, in order to bear the engine front ring better, in further embodiment, the embodiment of the utility model provides a top at upper bracket 300 is located saddle 410 and pin 420 between still the symmetry and is provided with two cushion 440, and the one end of two cushion 440 is connected with upper bracket 300 is articulated respectively, and one side that two cushion 440 carried on the back mutually is provided with lift adjusting rod 441 respectively. It should be noted that the surfaces of the two pads 440 in the embodiment of the present invention are also provided with the same anti-collision layer as the surface of the supporting groove 411.
In specific implementation, in order to adjust the position of this aircraft engine front ring dismouting car in a convenient way, in further embodiment, the embodiment of the utility model provides a kitchen still be provided with tow bar 500 on the aircraft engine front ring dismouting car.
The embodiment of the utility model provides a use method of ring dismouting car before aircraft engine is as follows:
before use, checking whether foreign matters exist at key parts of the aircraft engine front ring dismounting vehicle, particularly the contact surface of the foreign matters and the engine front ring; checking whether the hydraulic pump operates normally.
When the dismounting vehicle is used, the dismounting vehicle for the front ring of the aircraft engine is firstly dragged to a position right below the front ring of the engine, and after the position of the dismounting vehicle for the front ring of the aircraft engine is fixed, the landing mechanism is controlled to completely land the landing mechanism, so that the stability of the working process is ensured; then adjusting the position of a saddle, shaking the hand pump, lifting the saddle, slowing down the saddle when the saddle is close to the front ring of the airplane engine, enabling the saddle to slowly attach to the surface of the front ring of the engine, and stopping shaking the hand pump; then, adjusting the joint area of the saddle surface and the front ring surface, rotating the adjusting handle, and enabling the stop lever to incline, so that the elevation angle of the stop lever is the same as that of the front ring, the front ring is perfectly jointed on the saddle and the stop lever, and meanwhile, two cushion blocks are required to be adjusted to be in the best joint position; then, the staff can begin to dismantle the engine front ring, and after the front ring is completely dismantled and stably placed on the equipment saddle, the saddle is lowered, the binding belt is tightened, the engine front ring is fixed, and then follow-up work is carried out.
The embodiment of the utility model provides an aircraft engine front ring dismouting car simple structure, the practicality is strong, safe and reliable, the dismouting mode that adopts hydraulic pressure to go up and down replaces current artifical dismouting mode, has improved work efficiency widely and has alleviateed intensity of labour.
Finally, it should be noted that: although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described in the foregoing embodiments, or equivalents may be substituted for elements thereof. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The disassembly and assembly vehicle for the front ring of the aircraft engine is characterized by comprising an underframe, a lifting mechanism, an upper frame and a fixed frame; four corners of the bottom frame are respectively provided with a roller; the lifting mechanism comprises a telescopic bracket and a power mechanism, wherein the telescopic bracket is respectively connected with the bottom frame and the upper frame, and the power mechanism is used for controlling the telescopic bracket to stretch; the fixing frame comprises a saddle and a stop lever, the saddle is fixedly arranged at the top of the upper frame, the stop lever is hinged to the upper frame, and a stop lever adjusting mechanism is arranged on one side of the stop lever, which deviates from the saddle.
2. The aircraft engine front ring disassembly and assembly vehicle of claim 1, wherein the side of the underframe is further provided with a plurality of landing mechanisms.
3. The aircraft engine front ring disassembly and assembly vehicle of claim 1, characterized in that the telescopic bracket comprises two sets of parallel scissors forks, each set of scissors forks comprises a first movable rod and a second movable rod, the middle part of the first movable rod is hinged with the middle part of the second movable rod, the bottom end of the first movable rod is hinged with the chassis, the top end of the first movable rod is connected with the upper frame in a sliding manner, the bottom end of the second movable rod is connected with the chassis in a sliding manner, the top end of the second movable rod is hinged with the upper frame, the two sets of scissors forks are connected through a first connecting rod between the first movable rods, and the two sets of scissors forks are connected through a second connecting rod between the second movable rods.
4. The aircraft engine front ring disassembly and assembly vehicle of claim 3, wherein the power mechanism comprises a hydraulic pump arranged on the underframe, the output ends of the hydraulic pump are respectively connected with two hydraulic cylinders arranged on the second connecting rod, and the output ends of the two hydraulic cylinders are respectively connected with the first connecting rod in an articulated manner.
5. An aircraft engine front ring disassembly and assembly vehicle as claimed in claim 4, wherein the hydraulic pump is a hand pump.
6. The aircraft engine front ring disassembly and assembly vehicle of claim 1, wherein the saddle is of a wood structure, a supporting groove for supporting the engine front ring is arranged in the middle of the saddle, and an anti-collision layer is arranged on the surface of the supporting groove.
7. The aircraft engine front ring disassembly and assembly vehicle of claim 6, wherein straps are mounted on both sides of the saddle.
8. The aircraft engine front ring disassembly and assembly vehicle of claim 1, wherein the stop lever adjustment mechanism comprises two adjustment rods, and ends of the two adjustment rods opposite to each other are connected through an adjustment screw rod, and an adjustment handle is arranged on the adjustment screw rod; one end of one of the adjusting rods, which is far away from the adjusting screw rod, is hinged with the upper frame, and the other end of the other adjusting rod, which is far away from the adjusting screw rod, is connected with the stop lever.
9. The aircraft engine front ring dismounting vehicle according to claim 1, characterized in that two cushion blocks are symmetrically arranged on the top of the upper frame between the saddle and the stop lever, one ends of the two cushion blocks are respectively hinged with the upper frame, and the sides of the two cushion blocks, which face away from each other, are respectively provided with a lifting adjusting rod.
10. The aircraft engine front ring disassembly and assembly vehicle of claim 1, wherein a tow bar is further provided on the aircraft engine front ring disassembly and assembly vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921348673.0U CN210499981U (en) | 2019-08-19 | 2019-08-19 | Front ring dismounting vehicle for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921348673.0U CN210499981U (en) | 2019-08-19 | 2019-08-19 | Front ring dismounting vehicle for aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN210499981U true CN210499981U (en) | 2020-05-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921348673.0U Active CN210499981U (en) | 2019-08-19 | 2019-08-19 | Front ring dismounting vehicle for aircraft engine |
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| Country | Link |
|---|---|
| CN (1) | CN210499981U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110450086A (en) * | 2019-08-19 | 2019-11-15 | 成都东科信航空自控设备有限公司 | A kind of aircraft engine front ring dismounting vehicle |
-
2019
- 2019-08-19 CN CN201921348673.0U patent/CN210499981U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110450086A (en) * | 2019-08-19 | 2019-11-15 | 成都东科信航空自控设备有限公司 | A kind of aircraft engine front ring dismounting vehicle |
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