CN216657220U - Aeroengine four-axis anchor clamps convenient to quick location - Google Patents

Abstract

The utility model discloses a four-axis clamp of an aircraft engine, which is convenient for quick positioning and comprises a base, a first bearing seat, a second bearing seat, a driving device, a connecting part and a first four-axis clamp body, wherein the first bearing seat is arranged on the base; the first bearing seat and the second bearing seat are respectively arranged on two sides of the base, the driving device is arranged on the first bearing seat, one end of the connecting part is fixedly connected with the driving device, the other end of the connecting part is connected with a rotating part, the rotating part is rotatably arranged on the second bearing seat, the first four-axis clamp body is arranged on the connecting part, and the first four-axis clamp body is used for fixing the aircraft engine; the first four-axis clamp body comprises a supporting seat, a supporting plate, at least one positioning assembly and a clamping assembly, wherein the supporting seat is arranged on the connecting part, the supporting plate is arranged on the supporting seat, and the positioning assembly and the clamping assembly are arranged on the supporting plate; the utility model provides a four-axis clamp of an aero-engine, which is convenient to position quickly and aims to solve the problem that the existing four-axis clamp is low in working efficiency.

Description

Aeroengine four-axis anchor clamps convenient to quick location

Technical Field

The utility model relates to the technical field of clamps, in particular to a four-axis clamp of an aero-engine, which is convenient for quick positioning.

Background

An aero-engine (aero-engine) is a highly complex and precise thermal machine, is used as the heart of an airplane, is not only the power for flying the airplane, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aero-engine.

After centuries of development, the aero-engine has developed into a mature product with extremely high reliability, and the aero-engine in use includes various types such as a turbojet/turbofan engine, a turboshaft/turboprop engine, a ramjet engine and a piston engine, and not only is the power of military and civil aircrafts, unmanned planes and cruise missiles for various purposes, but also the gas turbine developed by the aero-engine is widely used in the fields such as ground power generation, marine power, mobile power stations, natural gas and petroleum pipeline pump stations and the like.

In the 21 st century, the development of aero-engines is further accelerated, and a new significant revolution is brought to the field of human aviation. Traditional aircraft engines are developing into gear-driven engines, variable-cycle engines, multi-electric engines, intercooling regenerative engines and open-rotor engines, non-traditional pulse detonation engines, scramjet engines, turbine-based combination engines, solar power and fuel cell power and the like are also continuously maturing, the development of the engines enables future aircrafts to be faster, taller, farther, more economical and more reliable, can meet stricter environmental requirements, and enables hypersonic aircrafts, transoceand aircrafts and reusable shuttle aircrafts to be transported to and fro on the earth.

The jig is a device for fixing a processing object to a correct position for receiving construction or inspection in a machine manufacturing process, and is also called a jig (qi a/j ǜ). In a broad sense, any device used to quickly, conveniently and safely mount a workpiece at any stage in a process may be referred to as a jig.

The fixture generally comprises a positioning element (for determining the correct position of a workpiece in the fixture), a clamping device, a tool setting guide element (for determining the relative position of the tool and the workpiece or guiding the direction of the tool), an indexing device (for enabling the workpiece to complete the processing of a plurality of stations in one-time installation, including a rotary indexing device and a linear movement indexing device), a connecting element, a fixture body (fixture base) and the like.

The clamp in the prior art can not quickly and accurately position the workpiece to be clamped, so that the time spent on clamping the workpiece is too long, and the working efficiency is influenced.

SUMMERY OF THE UTILITY MODEL

The utility model provides a four-axis clamp of an aero-engine, which is convenient to position quickly and aims to solve the problem that the existing four-axis clamp is low in working efficiency.

In order to solve the technical problems, the technical scheme adopted by the utility model is as follows:

a four-shaft clamp of an aircraft engine convenient for quick positioning comprises a base, a first bearing seat, a second bearing seat, a driving device, a connecting part and a first four-shaft clamp body;

the first four-axis clamp body is arranged on the connecting part and used for fixing the aircraft engine;

first four-axis anchor clamps body includes supporting seat, backup pad, at least one locating component and clamping component, and the supporting seat is installed on connecting portion, and the backup pad setting is on the supporting seat, and locating component and clamping component install in the backup pad, and clamping component includes first cylinder, a supporting bench, clamp splice, stopper and fixed block, and first cylinder and a supporting bench are installed in the backup pad, and the clamp splice tip is articulated with the expansion end of first cylinder, and the fixed block is fixed to be set up on first cylinder, and the both sides of fixed block articulate respectively the stopper, two stopper upper ends are articulated with the clamp splice middle part, and the lower terminal surface of clamp splice and the up end position of a supporting bench are corresponding, and the clamp splice is used for fixed aeroengine with a supporting bench cooperation.

Further inject, locating component includes location sleeve and positioning bolt, and positioning sleeve installs in the backup pad, and positioning bolt spiro union is on positioning sleeve, and positioning bolt highly is fixed through a nut in positioning sleeve, and positioning bolt is used for locating with the locating hole cooperation on the aeroengine.

Further inject, connecting portion include first curb plate, second curb plate and bearing plate, first curb plate and drive arrangement fixed connection, second curb plate and rotation portion fixed connection, install between first curb plate and the second curb plate the bearing plate, the supporting seat is installed on the bearing plate.

Further inject, drive arrangement includes motor and fixed carousel, and fixed carousel fixed mounting is on the output shaft of motor, and first curb plate is installed on fixed carousel.

Further optimize, all be provided with the corresponding screw hole in position on fixed carousel and the first curb plate, first curb plate passes through bolt and screw hole cooperation back demountable installation with fixed carousel.

Further limiting, the first side plate and the second side plate are of L-shaped structures, the vertical parts of the first side plate and the second side plate are respectively installed on the fixed turntable and the rotating part, and the horizontal parts of the first side plate and the second side plate are fixedly connected with the bearing plate.

Further optimize, the motor bottom is provided with the connecting seat, and the connecting seat is connected with the base.

The base comprises a first base and a second base, the second base is arranged on the first base in a sliding mode through a sliding assembly, and the first bearing seat and the second bearing seat are installed on the second base.

The sliding assembly comprises a sliding groove and a sliding rail, the sliding groove is formed in the upper end face of the first base, the sliding rail is installed on the lower end face of the second base, and the first base and the second base are in sliding fit through the sliding rail and the sliding groove.

Further inject, slide rail and spout are T type structure.

Compared with the prior art, the utility model has the following beneficial effects:

the utility model mainly comprises a base, a first bearing seat, a second bearing seat, a driving device, a connecting part and a first four-axis clamp body, wherein in the actual use process, a worker clamps and fixes a positioning component according to the position of a positioning hole on an aircraft engine, stably places the aircraft engine on the positioning component, then installs the first four-axis clamp body on the connecting part according to the reserved clamping position on the aircraft engine, aligns the upper end surface of a supporting table with the lower end surface of the clamping position, aligns the lower end surface of a clamping block with the upper end surface of the clamping position, drives a first air cylinder, extends the output end of the first air cylinder, rotates the middle position of the clamping block around the hinged point of the clamping block and a limiting block at the moment, the rear end of the clamping block is lifted due to the extension of the output end of the first air cylinder, and lowers the front end of the clamping block to contact the upper end surface of the clamping position, and make the lower terminal surface of centre gripping only laminates with the brace table, presss from both sides tightly the centre gripping position of reserving on the aeroengine through brace table and clamp splice, and then presss from both sides tight aeroengine, and the benefit of setting up like this can realize the quick location and the centre gripping to aeroengine, has improved the stability of work efficiency and centre gripping.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and that those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.

FIG. 1 is a schematic structural diagram of the present invention.

Fig. 2 is a front view of the present invention.

Fig. 3 is a top view of the present invention.

Fig. 4 is a partially enlarged view of the utility model at a in fig. 1.

In the figure, 1-base, 2-first bearing seat, 3-second bearing seat, 4-driving device, 5-connecting part, 6-first four-shaft clamp body, 7-supporting seat, 8-supporting plate, 9-positioning component, 10-clamping component, 11-first air cylinder, 12-supporting table, 13-clamping block, 14-limiting block, 15-fixing block, 16-positioning sleeve, 17-positioning bolt, 18-first side plate, 19-second side plate, 20-bearing plate, 21-motor, 22-fixing rotary table, 23-connecting seat, 24-first base, 25-second base, 26-second four-shaft clamp body, 27-sliding plate, 28-fixing plate, 29-second air cylinder, 30-positioning pin, 31-pressure bar.

Detailed Description

The present invention will be further described with reference to the following examples, which are intended to illustrate only some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, other embodiments used by those skilled in the art without any creative effort belong to the protection scope of the present invention.

Example one

As shown in fig. 1-3, the embodiment discloses a four-axis clamp for an aircraft engine, which is convenient for quick positioning, and includes a base 1, a first bearing seat 2, a second bearing seat 3, a driving device 4, a connecting portion 5, and a first four-axis clamp body 6;

the aircraft engine fixing device comprises a base 1, a first bearing seat 2, a second bearing seat 3, a driving device 4, a connecting part 5, a rotating part, a first four-axis clamp body 6, a second four-axis clamp body 6 and a base, wherein the first bearing seat 2 and the second bearing seat 3 are respectively installed on two sides of the base 1;

the first four-axis clamp body 6 comprises a supporting seat 7, a supporting plate 8, at least one positioning component 9 and a clamping component 10, the supporting seat 7 is installed on the connecting portion 5, the supporting plate 8 is arranged on the supporting seat 7, the positioning component 9 and the clamping component 10 are installed on the supporting plate 8, the clamping component 10 comprises a first air cylinder 11, a supporting table 12, a clamping block 13, limiting blocks 14 and a fixing block 15, the first air cylinder 11 and the supporting table 12 are installed on the supporting plate 8, the end portion of the clamping block 13 is hinged to the movable end of the first air cylinder 11, the fixing block 15 is fixedly arranged on the first air cylinder 11, the limiting blocks 14 are hinged to two sides of the fixing block 15 respectively, the upper ends of the two limiting blocks 14 are hinged to the middle portion of the clamping block 13, the lower end face of the clamping block 13 corresponds to the upper end face of the supporting table 12 in position, and the clamping block 13 is matched with the supporting table 12 to fix the aero-engine;

the utility model mainly comprises a base 1, a first bearing seat 2, a second bearing seat 3, a driving device 4, a connecting part 5 and a first four-axis clamp body 6, wherein in the actual use process, a worker clamps and fixes a positioning assembly 9 according to the position of a positioning hole on an aero-engine as required, stably places the aero-engine on the positioning assembly 9, then installs the first four-axis clamp body 6 on the connecting part 5 according to the clamping position reserved on the aero-engine, aligns the upper end surface of a support table 12 with the lower end surface of the clamping position, aligns the lower end surface of a clamping block 13 with the upper end surface of the clamping position, drives a first cylinder 11, extends the output end of the first cylinder 11, at the moment, the middle position of the clamping block 13 rotates around the hinged point of the clamping block 13 and a limiting block 14, and raises the rear end of the clamping block 13 due to the extension of the output end of the first cylinder 11, the front end of clamp splice 13 descends the contact the up end of clamping position, and make the lower terminal surface and the brace table 12 of centre gripping only laminate, come to press from both sides tight the clamping position who reserves on the aeroengine through brace table 12 and clamp splice 13, and then press from both sides tight aeroengine, and drive arrangement 4 can drive connecting portion 5 and drive tight aeroengine rotation of clamp, adjusts suitable angle, and the benefit that sets up like this can realize fixing a position fast and the centre gripping to aeroengine, has improved the stability of work efficiency and centre gripping.

Further limiting, the positioning assembly 9 comprises a positioning sleeve 16 and a positioning bolt 17, the positioning sleeve 16 is mounted on the support plate 8, the positioning bolt 17 is screwed on the positioning sleeve 16, the height of the positioning bolt 17 in the positioning sleeve 16 is fixed through a nut, and the positioning bolt 17 is used for being matched and positioned with a positioning hole in the aircraft engine;

in the actual use process, when different models of aircraft engines need to be positioned, a worker can rotate the positioning bolt 17 to be in threaded connection with the positioning sleeve 16 through the positioning bolt 17 so as to adjust the height of the positioning bolt 17 to adapt to the aircraft engines of different models.

Further, the connecting part 5 comprises a first side plate 18, a second side plate 19 and a bearing plate 20, the first side plate 18 is fixedly connected with the driving device 4, the second side plate 19 is fixedly connected with the rotating part, the bearing plate 20 is installed between the first side plate 18 and the second side plate 19, and the supporting seat 7 is installed on the bearing plate 20;

further, the driving device 4 comprises a motor 21 and a fixed turntable 22, the fixed turntable 22 is fixedly installed on an output shaft of the motor 21, and the first side plate 18 is installed on the fixed turntable 22;

in the actual use, motor 21 drives fixed carousel 22 and rotates, and fixed carousel 22 drives first curb plate 18, second curb plate 19 and bearing plate 20 and wholly takes place to rotate, installs first four-axis anchor clamps body 6 on bearing plate 20 and then bearing plate 20 and rotates together

Further optimize, all be provided with the corresponding screw hole in position on fixed carousel 22 and the first curb plate 18, first curb plate 18 passes through bolt and screw hole cooperation back demountable installation with fixed carousel 22.

Further, the first side plate 18 and the second side plate 19 are L-shaped, the vertical portions of the first side plate 18 and the second side plate 19 are respectively installed on the fixed turntable 22 and the rotating portion, and the horizontal portions of the first side plate 18 and the second side plate 19 are fixedly connected to the bearing plate 20.

Further preferably, the bottom of the motor 21 is provided with a connecting seat 23, and the connecting seat 23 is connected with the base 1.

The base 1 comprises a first base 24 and a second base 25, the second base 25 is arranged on the first base 24 in a sliding mode through a sliding assembly, and the first bearing seat 2 and the second bearing seat 3 are both arranged on the second base 25;

in the actual use process, the second base 25 is arranged on the first base 24 in a sliding mode, and the second base 25 can slide on the first base 24 from left to right, so that the clamped aircraft engine can be maintained by workers conveniently.

Wherein, the slip subassembly includes spout and slide rail, and the spout setting is at the up end of first base 24, and the lower terminal surface at second base 25 is installed to the slide rail, and first base 24 passes through slide rail and spout sliding fit with second base 25.

Further, the sliding rails and the sliding grooves are both of a T-shaped structure, and the sliding grooves and the sliding rails of the T-shaped structure can prevent the second base 25 from being disengaged when sliding on the first base 24.

Example two

As shown in fig. 1 to 3, the embodiment is further optimized based on the first embodiment, in the present embodiment, a second four-axis clamp body 26 is slidably disposed on the bearing plate 20, the second four-axis clamp body 26 includes a sliding plate 27, a fixed plate 28, a second cylinder 29, a positioning pin 30 and a pressing rod 31, wherein the sliding plate 27 is slidably disposed on the bearing plate 20, the fixed plate 28 is mounted on the sliding plate 27, the second cylinder 29 and the positioning pin 30 are mounted on the fixed plate 28, and the pressing rod 31 is mounted at a movable end of the second cylinder 29;

further preferably, the sliding plate 27 is provided with a protrusion, the bearing plate 20 is provided with a through groove, and the sliding plate 27 and the bearing plate 20 are in sliding fit through the protrusion and the through groove;

in actual use, the staff passes through aeroengine's another side after accomplishing quick location between locating hole and the locating pin 30, staff's drive second cylinder 29 shrink, depression bar 31 then contracts together with second cylinder 29 at this moment and fixes the aeroengine centre gripping, when using, with sliding plate 27 and bearing plate 20 sliding fit, slide second four-axis anchor clamps body 26 to the one side of keeping away from first four-axis anchor clamps body 6 during the use, the purpose of doing so is firstly in order to prevent to take place to interfere when first four-axis anchor clamps body 6 uses with second four-axis anchor clamps body 26, secondly can carry out the centre gripping to aeroengine's another side fixed, more convenient maintenance.

While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the utility model. The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the utility model, it should be noted that any modifications, equivalents and improvements made within the spirit and principle of the present invention should be included in the scope of the present invention.

Claims (10)

1. The utility model provides an aeroengine four-axis anchor clamps convenient to quick location which characterized in that: the four-shaft clamp comprises a base (1), a first bearing seat (2), a second bearing seat (3), a driving device (4), a connecting part (5) and a first four-shaft clamp body (6);

the aircraft engine fixing device comprises a base (1), a first bearing seat (2), a second bearing seat (3), a driving device (4), a connecting part (5), a first four-axis clamp body (6), a second four-axis clamp body (6), a first driving device (4), a second driving device (5), a first four-axis clamp body and a second four-axis clamp body, wherein the first bearing seat (2) and the second bearing seat (3) are respectively installed on two sides of the base (1), the driving device (4) is installed on the first bearing seat (2), one end of the connecting part (5) is fixedly connected with the driving device (4), the other end of the connecting part is connected with a rotating part, the rotating part is rotatably arranged on the second bearing seat (3), and the first four-axis clamp body (6) is used for fixing the aircraft engine;

the first four-axis clamp body (6) comprises a supporting seat (7), a supporting plate (8), at least one positioning component (9) and a clamping component (10), the supporting seat (7) is arranged on the connecting part (5), the supporting plate (8) is arranged on the supporting seat (7), the positioning component (9) and the clamping component (10) are arranged on the supporting plate (8), the clamping component (10) comprises a first air cylinder (11), a supporting table (12), a clamping block (13), a limiting block (14) and a fixing block (15), the first air cylinder (11) and the supporting table (12) are arranged on the supporting plate (8), the end part of the clamping block (13) is hinged with the movable end of the first air cylinder (11), the fixing block (15) is fixedly arranged on the first air cylinder (11), the limiting blocks (14) are hinged to two sides of the fixing block (15) respectively, the upper ends of the two limiting blocks (14) are hinged with the middle part of the clamping block (13), the lower end face of the clamping block (13) corresponds to the upper end face of the support table (12), and the clamping block (13) is matched with the support table (12) to fix the aircraft engine.

2. The aeroengine four-axis clamp convenient to quick location of claim 1, characterized in that: the positioning assembly (9) comprises a positioning sleeve (16) and a positioning bolt (17), the positioning sleeve (16) is installed on the supporting plate (8), the positioning bolt (17) is in threaded connection with the positioning sleeve (16), the height of the positioning bolt (17) in the positioning sleeve (16) is fixed through a nut, and the positioning bolt (17) is used for being matched and positioned with a positioning hole in the aircraft engine.

3. The aeroengine four-axis clamp convenient to quick location of claim 1, characterized in that: connecting portion (5) include first curb plate (18), second curb plate (19) and bearing plate (20), first curb plate (18) and drive arrangement (4) fixed connection, second curb plate (19) and rotation portion fixed connection, install between first curb plate (18) and second curb plate (19) bearing plate (20), supporting seat (7) are installed on bearing plate (20).

4. The aero-engine four-axis clamp convenient for rapid positioning as claimed in claim 3, wherein: the driving device (4) comprises a motor (21) and a fixed turntable (22), the fixed turntable (22) is fixedly installed on an output shaft of the motor (21), and the first side plate (18) is installed on the fixed turntable (22).

5. The aircraft engine four-axis clamp convenient to quick location of claim 4, characterized in that: threaded holes corresponding to the positions are formed in the fixed rotary disc (22) and the first side plate (18), and the first side plate (18) and the fixed rotary disc (22) are detachably mounted after being matched with the threaded holes through bolts.

6. The aircraft engine four-axis clamp convenient to quick location of claim 3, characterized in that: the first side plate (18) and the second side plate (19) are of L-shaped structures, the vertical parts of the first side plate (18) and the second side plate (19) are respectively installed on the fixed turntable (22) and the rotating part, and the horizontal parts of the first side plate (18) and the second side plate (19) are fixedly connected with the bearing plate (20).

7. The aircraft engine four-axis clamp convenient to quick location of claim 4, characterized in that: the bottom of the motor (21) is provided with a connecting seat (23), and the connecting seat (23) is connected with the base (1).

8. The aeroengine four-axis clamp convenient to quick location of claim 1, characterized in that: the base (1) comprises a first base (24) and a second base (25), the second base (25) is arranged on the first base (24) in a sliding mode through a sliding assembly, and the first bearing seat (2) and the second bearing seat (3) are arranged on the second base (25).

9. The aeroengine four-axis clamp convenient to quick location of claim 1, characterized in that: the sliding assembly comprises a sliding groove and a sliding rail, the sliding groove is arranged on the upper end face of the first base (24), the sliding rail is arranged on the lower end face of the second base (25), and the first base (24) and the second base (25) are in sliding fit through the sliding rail and the sliding groove.

10. The aircraft engine four-axis clamp convenient to quick location of claim 9, characterized in that: the sliding rail and the sliding groove are both of T-shaped structures.

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