CN217965412U

CN217965412U - Aviation radiator external surface positioning and cutting device

Info

Publication number: CN217965412U
Application number: CN202222205060.XU
Authority: CN
Inventors: 吕军; 张首洪; 孙德明
Original assignee: Guizhou Yonghong Aviation Machinery Co Ltd
Current assignee: Guizhou Yonghong Aviation Machinery Co Ltd
Priority date: 2022-08-22
Filing date: 2022-08-22
Publication date: 2022-12-06
Anticipated expiration: 2032-08-22

Abstract

The utility model provides an outer profile positioning cutting device of radiator for aviation, includes base and support frame. A plurality of connecting bolts are detachably connected to the base and are connected with a platform of the laser cutting equipment through the connecting bolts; the lower extreme of many identical support frames can be dismantled and connect the up end at the base, and the up end of support frame hugs closely the holding surface of flange face terminal surface down, and the perpendicular distance of the up end of support frame to base up end is greater than the perpendicular distance of flange face terminal surface to the preceding terminal surface of aviation radiator under the flange face, has still pegged graft the positioning core axle on the up end of support frame, and the positioning core axle is pegged graft with the mounting hole on the flange face and is cooperated. The utility model discloses the size benchmark of existing radiator has been changed according to radiator manufacturing flow and radiator outfield installation demand, keeps unanimous with the actual installation benchmark of radiator, still can realize simultaneously terminal surface, rear end face axiality before the radiator to and flange mounting face carries out processing control and inspection to outer interface sizes such as the axial dimensions of terminal surface, rear end face before the radiator.

Description

Aviation radiator external surface positioning and cutting device

Technical Field

The utility model relates to an aviation is with elementary radiator size control device, guarantee the product fitting surface to the spatial structure size of its preceding, rear end face when mainly used radiator makes, be the finish machining composite set device of control radiator fitting dimension.

Background

As shown in figure 2, the aviation radiator is mainly used for cooling high-temperature and high-pressure gas exhausted from a machine body, is assembled in the machine body, is of a cylinder rotary structure as a whole, is round at the front end face and the rear end face, and has an inner diameter about that of the radiator

The axial length is close to 1000mm, and the dimensional tolerance is large and is not easy to control. The radiator is in a horizontal posture when installed on the machine, and the specific requirements of the space size of an external interface thereof are as follows:

1) Radiator waist cambered surface 3

The nozzle and the machine body are assembled without interference;

2) The butt joint clearance between the rear end face of the radiator cylinder and the end face of the machine body is not more than 4mm.

Currently, in the actual process of manufacturing the radiator, the size and manufacturing reference surface is the front end surface of the radiator, and the installation reference of the radiator at the final installation interface is the flange surface of the waist part of the radiator. Because the processing measuring reference and the mounting reference of the radiator are not unified, manual marking and repairing are carried out according to the height dimension by taking the front end face of the bottom as the reference during the processing of the assembly, meanwhile, the whole radiator is assembled and connected by all parts and components by using a welding method, the deformation condition and the manual repairing error are large after welding, the flatness of the repairing end face of the radiator is insufficient, and the flatness of the front end face and the rear end face of a product can not be effectively ensured. And because the benchmark is not uniform, the dimension measurement has errors, and finally, the radiator has poor harmony and consistency when a host is installed, and the conditions of out-of-tolerance of the front end surface and the rear end surface and the like occur when a plurality of sets of products are installed.

In summary, in order to solve the problems of installation compatibility and consistency of the front end face interface and the rear end face interface of the radiator, the measurement precision and efficiency of the radiator processing process are improved, and meanwhile, the production labor intensity is reduced, an end face laser cutting control device needs to be designed, and the problems are comprehensively solved.

Disclosure of Invention

The utility model aims at providing a radiator external profile location cutting device for aviation through the design manufacturing a mechanical structure's assembled location laser cutting anchor clamps, makes the size benchmark that flow and radiator outfield installation demand changed current radiator according to the radiator, keeps unanimous with the actual installation benchmark of radiator. Furthermore, the coaxiality of the front end face and the rear end face of the radiator, the axial size from the flange mounting surface to the front end face and the rear end face of the radiator and other external interface sizes can be simultaneously processed, controlled and checked.

The utility model discloses a realize through following technical scheme:

a positioning and cutting device for the external surface of an aviation radiator comprises a front end surface and a rear end surface, a flange surface is arranged between the front end surface and the rear end surface and on the external surface of the aviation radiator, a plurality of mounting holes are arranged on the flange surface, the positioning and cutting device comprises,

the base is detachably connected with a plurality of connecting bolts;

the support frame, many identical the connection can be dismantled to the lower extreme of support frame at the up end of base, and the up end of support frame forms the holding surface of hugging closely flange face down terminal surface, and the perpendicular distance of the up end of support frame to base up end is greater than the perpendicular distance of flange face down terminal surface to terminal surface before the aviation radiator, has still pegged graft on the up end of support frame and has had the positioning core axle, and the mounting hole grafting cooperation on positioning core axle and the flange face. When the upper end surface of the supporting frame is tightly attached to the lower end surface of the flange surface, the front end surface of the aviation radiator is not contacted with the upper end surface of the base by utilizing the difference of vertical heights, namely the front end surface is in a suspended state.

Furthermore, the base is disc-shaped, a through hole is formed in the center of the base, and weight reduction grooves and weight reduction holes which are symmetrical with respect to the axis center of the base are formed in the base. The weight reduction grooves and the weight reduction holes which are arranged in a central symmetry mode not only reduce the dead weight of the whole positioning cutting device, but also avoid the problem that the rear end face is inclined due to the fact that the center of the gravity center of the base shifts when the positioning cutting device rotates, and the assembly clearance of the rear end face after cutting is influenced. Meanwhile, the through hole in the center of the base is assembled with the laser cutting platform, so that the coaxiality of the through hole and the laser cutting platform, the coaxiality of the front end face and the rear end face of the radiator are guaranteed, and the stroke accuracy of the laser cutting probe in the cutting process is guaranteed.

Further, in the present invention,

the base is provided with a threaded hole and a positioning pin hole;

the lower end of the support frame is connected with the base through an inner hexagon bolt and a positioning bolt.

Furthermore, the support frame includes lower end plate, support column and upper end plate, and lower extreme, the upper end of support column are connected with lower end plate, upper end plate respectively, and hexagon socket head cap screw and location bolt set up about the support column symmetry. The hexagon socket head cap screw and the location bolt that the symmetry set up ensure that the support column can not lead to warping because of the atress is uneven, and then influence the flange face to the uniformity of base distance.

Furthermore, the circumferential edge of the base is provided with a plurality of notches, and the notches extend towards the center of the base. The connecting bolt can move in the extending direction of the notch, so that the relative position of the base and the laser cutting platform can be conveniently adjusted.

Further, the number of the support frames is smaller than or equal to the number of the mounting holes in the flange face, and when the position of one support frame corresponds to the position of the mounting hole in the flange face, the positions of the rest support frames correspond to the positions of the mounting holes in the rest flange face one to one. The quantity of support frame can be selected the same with mounting hole quantity on the flange face, and in order to reduce dead weight and the complexity of location cutting device, the quantity of support frame also can be less than the mounting hole quantity on the flange face, nevertheless will guarantee on the support frame that the position of location dabber is unanimous with the position of mounting hole on the flange face, and the location dabber is located the perpendicular projection line of flange face mounting hole promptly.

Compared with the prior art, the utility model discloses a carry out data collection and trail at the host computer installation condition to the radiator, use this appearance cutting device processing, it is higher to have guaranteed the radiator external tapping size degree of accuracy, and the terminal surface roughness is higher, and the once only installation qualification rate of radiator promotes 90%, reduces the condition that the product installation mismatch carries out the secondary and repaiies greatly, has effectively shortened the installation cycle, has promoted the installation quality, has obtained good economic benefits, and the result is obtained host computer and customer and represents the approval.

The utility model has the following characteristics:

1. the device has simple design structure, convenient use and easy disassembly and assembly, and the split combined design is convenient for storage and transportation, namely the device can be assembled immediately after use;

2. the measuring standard and the actual installation standard of the aviation radiator assembly are unified, and the problem of poor installation matching caused by accumulated manufacturing tolerance of the radiator due to standard difference is solved.

3. The product end face flatness through laser cutting is high, and the consistency of assembly clearance can be guaranteed when assembling with the external interface, reduces the work of polishing in later stage, improves product assembly efficiency.

4. The distance between the base of the device and the flange face of the product is larger than the distance between the flange face of the product and the front end face of the product (namely, the product is installed on the device, the bottom face of the product is in a suspended state for the front end face), and the size error caused by the contact of the product and a real object in the cutting process is avoided.

5. By tracking and measuring the actual installation conditions of a plurality of sets of products, the external interface size of the aviation radiator processed and controlled by the device is more accurately controlled, the installation interchangeability and consistency are better, and the installation requirement of a host can be completely met.

Drawings

FIG. 1 is an external profile positioning and cutting apparatus;

FIG. 2 is a schematic diagram of an aircraft radiator assembly;

FIG. 3 is a support bracket assembly;

FIG. 4 is a base assembly;

FIG. 5 is a schematic view of a state that the aviation radiator assembly outer profile positioning and cutting device performs laser cutting;

in the figure, 1-a support frame, 2-a base, 11-a positioning mandrel, 12-a positioning bolt, 13-an inner hexagon bolt, 14-a support column, 22-a connecting bolt, 23-a flat washer, 24-a nut and 25-a positioning disc.

Detailed Description

The following description of the present invention will be made with reference to the accompanying drawings and specific embodiments, but it should not be understood that the scope of the present invention is limited to the following embodiments, and various modifications, substitutions and changes made according to the ordinary technical knowledge and conventional means in the art without departing from the technical spirit of the present invention are included in the scope of the present invention.

Referring to fig. 2, an overall view of an aircraft radiator is shown, the aircraft radiator includes a front end surface a at a lower end in fig. 2, a flange surface B as a mounting reference surface, and 10 positions are provided on the flange surface B

The mounting hole, the rear end face C of the uppermost end in fig. 2 is taken as a laser cutting end face, and the distance from the lower end face of the flange face B to the rear end face C is taken as an end face gap dimension D to be controlled. Due to the particularity of the design structure of the radiator, a plurality of external interfaces (3 nozzles E of the waist cambered surface of the radiator in fig. 2) exist on the whole surface, the requirement on the assembly clearance of the axial front end surface A and the axial rear end surface C of the radiator during installation is high, in addition, the radiator has large volume, the whole installation coordination and interchangeability of the radiator can be directly influenced if the processing scheme is improperly selected in the actual processing process, and the later-stage product installation period is influenced. Therefore, in order to ensure that the dimension processing of the front end surface A and the rear end surface C of the radiator can meet the design characteristic requirements and stabilize the processing consistency and interchangeability of the radiator, a positioning cutting device is required to be designed to cut the rear end surface C, ensure the mounting dimension of the axial front end surface and the axial rear end surface of the radiator, improve the manufacturing precision of the radiator and meet the mounting requirement of the radiator on a machine.

As shown in fig. 1, 3 and 4, the positioning and cutting device for the outer profile of the aviation radiator designed for solving the problems mainly comprises a supporting frame 1 and a base 2,

as shown in fig. 3, the supporting frame 1 mainly includes the following structure: positioning mandrel 11, positioning bolt 12 and inner

sixThe corner bolts

13 and 14 support the columns. As shown in figure 1, the positioning cutting device comprises 5 identical support frames 1, and one position is drilled on the upper end surface of each support frame 1

Mounting holes, see fig. 3. The positioning core shaft 11 limits the aviation radiator and the flange surface B of the support frame 1 through the mounting hole, and the support frame 1 and the base 2 are connected in a threaded mode through the hexagon socket head cap screw 13 and limited through the positioning bolt 12. The vertical height of the support frame 1 needs to be greater than the vertical distance from the front end face a to the lower end face of the flange face B, so as to ensure that the front end face a does not contact the upper end face of the base 1 when assembled on the positioning and cutting device. The main function of the support frame 1 is to assemble and position a flange surface B in an assembly for installing the flange surface of the aviation radiator, and then adjust the size from the laser cutting probe to a rear end surface C by taking the end surface of the flange surface B as a reference. Therefore, the partial structure is an important part for ensuring the mounting surface-to-end surface dimension (namely, the end surface clearance dimension D) of the aviation radiator assembly.

As shown in fig. 4, the base 2 mainly includes the following structure: a connecting bolt 22, a flat washer 23 and a nut 24. The base 2 has the main function of being connected with the laser cutting platform, the laser cutting platform drives the base 2 to rotate together when rotating, and the purpose of cutting the rear end face C of the aviation radiator when the laser cutting probe works is achieved.

As shown in fig. 5, when the rear end surface C of the aviation radiator needs to be cut, the following steps are performed:

1. the positioning cutting device is fixed on a rotating platform of the laser cutting equipment through the connecting bolt 22, the nut 24 and the flat washer 23, redundant materials on the surface of the support frame 1 are cleaned, and if the relative installation position of the base 2 and the laser cutting equipment needs to be adjusted, the positioning cutting device can be achieved by adjusting the position of the connecting bolt 22 in a notch on the edge of the base 2. The aviation radiator component is assembled on the positioning cutting device, the front end face A of the radiator and the upper end face of the base 2 are suspended, the fact that the front end face A of the component cannot be in contact with the base 2 is guaranteed, and then the radiator is rotated to enable 10 positions on the flange face B to be located

5 mounting holes in the supporting frame 1

The mounting holes are concentric and then the positioning mandrel 11 is inserted. The radiator is a large sheet metal welding part, and the flatness of the front end surface A of the radiator is uneven due to welding reasons and tolerance accumulation. Therefore, if the front end face a of the heat sink contacts the base 2, the flatness of the finally cut back end face C may be greatly different.

2. And checking whether the parameters in the laser cutting program are correct or not, and performing simulated cutting processing on cutting software to ensure that the simulated cutting process has no interference or offset.

3. After the steps are confirmed to be correct, the laser cutting turntable is started to drive the base 2, the support frame 1 and the radiator to rotate together, the laser cutting probe is opened, and the redundant part of the rear end face of the radiator is cut and removed by the laser beam while the radiator rotates along with the laser cutting equipment.

The utility model discloses a cutting device structure is though fairly simple, but very considerable during manpower sparingly, the time cost, and this radiator is used angle mill to polish for the manual work at present stage rear end face C's cutting, and the time is about 30 minutes, if use laser cutting, cuts one set of product time and is about 6 minutes, and the time has been practiced thrift 4 times, and efficiency has improved 240%, has saved the manpower simultaneously and has avoided leading to the product to take place to collide with, bump, the fish tail in the manual operation process.

The above-mentioned embodiment is not used for limiting the protection scope of the utility model discloses a all be in the utility model discloses a deformation, modification or equivalence replacement etc. that make on the technical scheme basis all should fall into the protection scope of the utility model.

Claims

1. The utility model provides a radiator external profile location cutting device for aviation, radiator for aviation includes preceding terminal surface and rear end face, just is provided with the flange face between preceding terminal surface and the rear end face on the radiator external profile for aviation, has a plurality of mounting holes on the flange face, its characterized in that: the positioning and cutting device comprises a positioning and cutting device,

the base (2), a plurality of connecting bolts (22) are detachably connected to the base (2);

support frame (1), many identical the up end of connection in base (2) can be dismantled to the lower extreme of support frame (1), and the up end of support frame (1) forms the holding surface of hugging closely flange face terminal surface down, and the perpendicular distance of the up end of support frame (1) to base (2) up end is greater than flange face terminal surface down and to the perpendicular distance of terminal surface before the aviation radiator, still pegs graft on the up end of support frame (1) and has location dabber (11), and location dabber (11) are pegged graft with the mounting hole on the flange face and are cooperated.

2. The aviation radiator outer surface positioning and cutting device as claimed in claim 1, wherein: the base (2) is disc-shaped, a through hole is formed in the center of the base (2), and weight reduction grooves and weight reduction holes which are symmetrical with respect to the axis center of the base (2) are formed in the base (2).

3. The external profile positioning and cutting device for the aviation radiator as claimed in claim 1, wherein:

the base (2) is provided with a threaded hole and a positioning pin hole;

the lower end of the support frame (1) is connected with the base (2) through an inner hexagon bolt (13) and a positioning bolt (12).

4. The aviation radiator outer surface positioning and cutting device as claimed in claim 3, wherein: the support frame (1) comprises a lower end plate, a support column (14) and an upper end plate, the lower end and the upper end of the support column (14) are respectively connected with the lower end plate and the upper end plate, and the inner hexagonal bolt (13) and the positioning bolt (12) are symmetrically arranged relative to the support column (14).

5. The aviation radiator outer surface positioning and cutting device as claimed in claim 1, wherein: the circumference edge of base (2) is opened has a plurality of breachs, and the breach extends towards the center of base (2).

6. The aviation radiator outer surface positioning and cutting device as claimed in claim 1, wherein: the number of the support frames (1) is less than or equal to the number of the mounting holes in the flange face, and when the position of one support frame (1) corresponds to the position of the mounting hole in the flange face, the positions of the rest support frames (1) correspond to the positions of the mounting holes in the rest flange face one to one.