CN219715013U

CN219715013U - Pressure testing tool for machining aviation parts

Info

Publication number: CN219715013U
Application number: CN202320865636.7U
Authority: CN
Inventors: 张志科
Original assignee: Suzhou Jinzhihong Precision Machinery Co ltd
Current assignee: Suzhou Jinzhihong Precision Machinery Co ltd
Priority date: 2023-04-18
Filing date: 2023-04-18
Publication date: 2023-09-19
Anticipated expiration: 2033-04-18

Abstract

The utility model relates to a pressure test tool for processing aviation parts, which comprises a box body, wherein a box door is fixed on the front surface of the box body, a visual window is fixed on the front surface of the box door, a pressure test mechanism for testing the pressure of the aviation parts with different sizes is arranged on the upper surface of the box body, a circulating mechanism for recycling water used in pressure test is arranged on the right side of the upper surface of the box body, the pressure test mechanism comprises a water tank fixed on the upper surface of the box body, an input pipe is communicated on the right side of the water tank, and a booster pump is communicated on the right side of the input pipe. This pressure testing frock of aviation spare part processing, pressure testing mechanism can carry out the pressure testing with the aviation spare part of equidimension not, and the clamping structure of controlling the side carries out the centre gripping with the left and right sides of aviation spare part and fixes, then carries the pressure testing pipe through removing the module again and carries out the pressure testing in the inside of aviation spare part and moves about, and then promotes the practicality of pressure testing frock.

Description

Pressure testing tool for machining aviation parts

Technical Field

The utility model relates to the technical field of pressure test tools, in particular to a pressure test tool for machining aviation parts.

Background

The pressure test is to carry out pressure-resistant detection on the parts, so that whether the inside of the parts is leaked or not is detected, the safety of the parts is guaranteed, and the aviation parts can bear larger pressure when being used at high altitude, so that the parts can be used after pressure test detection.

For example, CN 212059278U in chinese patent discloses a portable pressure test fixture for processing aviation parts, the base both ends symmetry fixedly connected with backup pad, two backup pad tops all fixedly connected with diaphragm, backup pad inner wall corresponds diaphragm bottom position department fixedly connected with pushing down mechanism, pushing down mechanism includes spout, slider, fly leaf, pressure case, booster pump, connecting pipe, upper cover plate, lead screw and driving motor, the structure of the utility model is scientific and reasonable, and convenient to use, is provided with spout, slider, fly leaf, pressure case, booster pump, connecting pipe, upper cover plate, lead screw and driving motor, it is rotatory to drive the lead screw through driving motor, make the lead screw promote the slider at uniform velocity and remove, make the slider carry the fly leaf at uniform velocity along the spout to promote the upper cover plate through the connecting pipe and push down, and fix the spare through placing the board cooperation, sealing rubber on the upper cover plate has improved sealed effect simultaneously, upper cover plate and placing the board in this patent are fixed size, can only carry out the pressure test to aviation parts of certain size, and then reduced the practicality of pressure test fixture.

Disclosure of Invention

Aiming at the defects of the prior art, the utility model provides a pressure test tool for processing aviation parts, which has the advantages of being capable of performing pressure test detection on aviation parts with different sizes, and the like, and solves the problem that only aviation parts with a certain size can be subjected to pressure test, thereby reducing the practicability of the pressure test tool.

In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides a pressure testing frock of aviation spare part processing, includes the box, the front of box is fixed with the chamber door, the front of chamber door is fixed with visual window, the upper surface of box is equipped with the pressure testing mechanism that is used for carrying out the pressure testing to the aviation spare part of equidimension, the right side of box upper surface is equipped with the circulation mechanism that is used for carrying out cyclic utilization to the water that uses when the pressure testing;

the utility model discloses a pressure testing mechanism, including fixing the water tank at the box upper surface, the right side intercommunication of water tank has the input tube, the right side intercommunication of input tube has the booster pump, the output of booster pump is fixed with the output tube, the roof of box inner chamber is fixed with the removal module, the lower fixed surface of removal module has first electric putter, the left and right sides that removes the module lower surface and be located first electric putter all is fixed with the bracing piece, the outside of first electric putter output shaft and the bottom mounting of left and right sides bracing piece have the pressure testing pipe, the lower surface intercommunication of pressure testing pipe has a quantity not less than two shower nozzle, the one end and the right side intercommunication of pressure testing pipe of booster pump are kept away from to the output tube, the inside of box is equipped with coupling assembling.

Further, the coupling assembling is including fixing the backup pad in the inside of box, the circulation mouth that quantity was not less than two has been seted up to the lower surface of backup pad, the inside of circulation mouth is fixed with the filter screen, the left and right sides of backup pad upper surface all is fixed with the clamping structure.

Further, the support rod comprises a first movable rod, and a second movable rod is connected inside the first movable rod in a sliding mode.

Further, the clamping structure comprises connecting plates fixed on the left side and the right side of the upper surface of the supporting plate, two second electric pushing rods are fixed on the opposite sides of the connecting plates, clamping plates are fixed on the outer sides of output of the second electric pushing rods, and rubber pads are fixed on the opposite sides of the clamping plates.

Further, the upper surface of water tank intercommunication has the inlet tube, the upper surface of inlet tube is fixed with the tube cap, the inlet tube is located the longitudinal axis of water tank.

Further, circulation mechanism is including fixing the water pump on the box upper surface and being located the booster pump right side, the output of water pump is fixed with the back flow, the one end that the water pump was kept away from to the back flow communicates with the right side of water tank upper surface, the input of water pump is fixed with the connecting pipe, the one end that the water pump was kept away from to the connecting pipe communicates with the downside on box right side.

Further, the return pipe and the connecting pipe are rubber pipes, and the length of the connecting pipe is larger than that of the return pipe.

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

1. this pressure testing frock of aviation spare part processing, pressure testing mechanism can carry out the pressure testing with the aviation spare part of equidimension not, and the clamping structure of controlling the side carries out the centre gripping with the left and right sides of aviation spare part and fixes, then carries the pressure testing pipe through removing the module again and carries out the pressure testing in the inside of aviation spare part and moves about, and then promotes the practicality of pressure testing frock.

2. This pressure testing frock of aviation spare part processing, the water after the pressure testing is done flows the diapire of box inner chamber through two filter screen of quantity not less than, can start the water pump of box upper surface at this moment, then pumps the inside of water tank with the inside diapire of box, can circulate the inside water of water tank and use, saves the water resource.

Drawings

FIG. 1 is a schematic diagram of the structure of the present utility model;

FIG. 2 is a schematic diagram of a pressure testing mechanism according to the present utility model;

FIG. 3 is a schematic view of a circulation mechanism according to the present utility model.

In the figure: 1 box, 2 chamber door, 3 visual window, 4 pressure testing mechanism, 401 water tank, 402 input module, 403 booster pump, 404 output tube, 405 mobile module, 406 first electric putter, 407 bracing piece, 408 pressure testing tube, 409 shower nozzle, 410 backup pad, 411 circulation mouth, 412 filter screen, 413 clamping structure, 5 circulation mechanism, 501 water pump, 502 back flow, 503 connecting pipe.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Please refer to fig. 1, a pressure testing tool for processing aviation parts in this embodiment, which comprises a box body 1, the front of the box body 1 is fixed with a box door 2, the front of the box door 2 is fixed with a visual window 3, the upper surface of the box body 1 is provided with a pressure testing mechanism 4 for testing the pressure of aviation parts with different sizes, the pressure testing mechanism 4 can test the pressure of aviation parts with different sizes, the right side of the upper surface of the box body 1 is provided with a circulating mechanism 5 for circulating water used during pressure testing, and the circulating mechanism 5 saves water resources for carrying out pressure testing.

Referring to fig. 2, in order to test the aviation components with different sizes, in this embodiment, the pressure test mechanism 4 includes a water tank 401 fixed on the upper surface of the box 1, an input pipe 402 is connected on the right side of the water tank 401, a booster pump 403 is connected on the right side of the input pipe 402, an output pipe 404 is fixed at the output end of the booster pump 403, a mobile module 405 is fixed on the top wall of the inner cavity of the box 1, a first electric push rod 406 is fixed on the lower surface of the mobile module 405, support rods 407 are fixed on the left and right sides of the mobile module 405, a pressure test tube 408 is fixed on the outer side of the output shaft of the first electric push rod 406 and the bottom ends of the left and right support rods 407, the lower surface of the pressure test tube 408 is connected with a spray nozzle 409 with a number not less than two, the first electric push rod 406 is started, the first electric push rod 406 moves the pressure test tube 408 downward into the aviation components, then starts the booster pump 403, pumps the water in the water tank 401 into the input pipe 402, then flows into the output pipe 404, and then flows out of the two spray nozzles 408 from the two spray nozzles 408, and is connected with the inner sides of the pressure test tube 408, and the pressure test component 408 is connected with the two ends of the aviation components 1.

In this embodiment, coupling assembling is including fixing the backup pad 410 in the inside of box 1, the circulation mouth 411 that is not less than two in quantity has been seted up to the lower surface of backup pad 410, the inside of circulation mouth 411 is fixed with filter screen 412, the left and right sides of backup pad 410 upper surface all is fixed with clamping structure 413, when carrying out the pressure testing to aviation spare part, open the positive chamber door 2 of box 1, place aviation spare part on backup pad 410 upper surface and lie in about between the opposite one side of side clamping structure 413, then start left and right sides clamping structure 413, the left and right sides clamping structure 413 of left and right sides carries out the centre gripping with aviation spare part and fixes the upper surface at backup pad 410, then close chamber door 2, the back of chamber door 2 is fixed with the sealing washer, can increase its sealing performance of box 1, the bracing piece 407 includes first movable rod, the inside sliding connection of first movable rod has the second movable rod, clamping structure 413 is including the connecting plate of fixing in the left and right sides of backup pad upper surface, the opposite one side of left and right sides connecting plate is fixed with the second electric putter of quantity, the opposite one side of left and right sides clamping structure 413, the outside of left and right sides electric putter is fixed with the water inlet tube 401, the opposite one side is fixed with the water inlet tube 401, the water tank is fixed with the opposite one side of the water inlet tube.

It should be noted that, the mobile module 405 is started, the mobile module 405 moves back and forth, and then drives the spray heads 409 with the number not less than two to move back and forth, and then carries out comprehensive pressure test on the interior of the aviation component, and then can carry out pressure test on the interior of the aviation component with different sizes.

Referring to fig. 3, in order to save water resources, water can be recycled, in this embodiment, the recycling mechanism 5 includes a water pump 501 fixed on the upper surface of the tank 1 and located on the right side of the booster pump 403, an output end of the water pump 501 is fixed with a return pipe 502, one end of the return pipe 502 away from the water pump 501 is communicated with the right side of the upper surface of the water tank 401, an input end of the water pump 501 is fixed with a connecting pipe 503, one end of the connecting pipe 503 away from the water pump 501 is communicated with the lower side of the right side of the tank 1, water after pressure test flows to the bottom wall of the inner cavity of the tank 1 through at least two filter screens 412, at this time, the water pump 501 on the upper surface of the tank 1 can be started, and then water on the bottom wall of the tank 1 is pumped into the connecting pipe 503.

In this embodiment, the return pipe 502 and the connection pipe 503 are rubber pipes, and the length of the connection pipe 503 is greater than that of the return pipe 502.

The water in the connection pipe 503 flows into the water tank 401 through the return pipe 502, so that the water in the water tank 401 can be recycled, and water resources can be saved.

The working principle of the embodiment is as follows:

(1) When the pressure test is carried out on the aviation components, the front box door 2 of the box body 1 is opened, the aviation components are placed on the upper surface of the supporting plate 410 and positioned between the opposite sides of the left and right side clamping structures 413, then the left and right side clamping structures 413 are started, the left and right sides of the aviation components are clamped and fixed on the upper surface of the supporting plate 410 by the left and right side clamping structures 413, then the box door 2 is closed, the back surface of the box door 2 is fixedly provided with a sealing ring, the sealing performance of the box body 1 can be improved, then the first electric push rod 406 is started, the first electric push rod 406 downwards moves the pressure test tube 408 to the inside of the aviation components, then the booster pump 403 is started, the water in the water tank 401 is pumped to the inside of the input tube 402, then flows to the inside of the output tube 404, then flows to the inside of the pressure test tube 408, then the spray nozzles 409 are sprayed out from the number of not less than two, then the inside of the aviation components is tested, the mobile module 405 is started, the mobile module 405 is moved back and forth, the number of the mobile module 405 is driven to move left and right, the number of the aviation components can be tested in advance, the inside the two aviation components are not less than the inside the aviation components, and then the inside the aviation components can be tested completely.

(2) The water after the pressure test flows to the bottom wall of the inner cavity of the box body 1 through at least two filter screens 412, at this time, the water pump 501 on the upper surface of the box body 1 can be started, then the water on the bottom wall inside the box body 1 is pumped into the connecting pipe 503, then the water inside the connecting pipe 503 flows to the inside of the water tank 401 through the return pipe 502, and the water inside the water tank 401 can be recycled, so that water resources are saved.

It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.

Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a pressure testing frock of aviation spare part processing, includes box (1), its characterized in that: the pressure testing device is characterized in that a box door (2) is fixed on the front face of the box body (1), a visual window (3) is fixed on the front face of the box door (2), a pressure testing mechanism (4) used for testing the pressure of aviation components with different sizes is arranged on the upper surface of the box body (1), and a circulating mechanism (5) used for circulating water used in pressure testing is arranged on the right side of the upper surface of the box body (1);

the utility model provides a pressure testing mechanism (4) is including fixing water tank (401) at box (1) upper surface, the right side intercommunication of water tank (401) has input tube (402), the right side intercommunication of input tube (402) has booster pump (403), the output of booster pump (403) is fixed with output tube (404), the roof of box (1) inner chamber is fixed with movable module (405), the lower surface of movable module (405) is fixed with first electric putter (406), movable module (405) lower surface just is located the left and right sides of first electric putter (406) and all is fixed with bracing piece (407), the outside of first electric putter (406) output shaft and the bottom of left and right sides bracing piece (407) are fixed with pressure testing tube (408), the lower surface intercommunication of pressure testing tube (408) has shower nozzle (409) that a quantity is not less than two, the one end and the right side intercommunication of pressure testing tube (408) of booster pump (403) are kept away from to output tube (404), the inside of box (1) is equipped with coupling assembling.

2. The pressure testing tool for machining aviation components of claim 1, wherein: the connecting assembly comprises a supporting plate (410) fixed inside the box body (1), the lower surface of the supporting plate (410) is provided with at least two circulation ports (411), a filter screen (412) is fixed inside the circulation ports (411), and clamping structures (413) are fixed on the left side and the right side of the upper surface of the supporting plate (410).

3. The pressure testing tool for machining aviation components of claim 1, wherein: the support rod (407) comprises a first movable rod, and a second movable rod is connected inside the first movable rod in a sliding manner.

4. The pressure testing tool for machining aviation components of claim 2, wherein: the clamping structure (413) comprises connecting plates fixed on the left side and the right side of the upper surface of the supporting plate (410), two second electric pushing rods are fixed on the opposite sides of the connecting plates, clamping plates are fixed on the outer sides of output of the second electric pushing rods, and rubber pads are fixed on the opposite sides of the clamping plates.

5. The pressure testing tool for machining aviation components of claim 1, wherein: the upper surface of water tank (401) communicates there is the inlet tube, the upper surface of inlet tube is fixed with the tube cap, the inlet tube is located the longitudinal axis of water tank (401).

6. The pressure testing tool for machining aviation components of claim 1, wherein: circulation mechanism (5) are including fixing at box (1) upper surface and being located water pump (501) on booster pump (403) right side, the output of water pump (501) is fixed with back flow (502), one end that water pump (501) was kept away from to back flow (502) communicates with the right side of water tank (401) upper surface, the input of water pump (501) is fixed with connecting pipe (503), one end that water pump (501) was kept away from to connecting pipe (503) communicates with the downside on box (1) right side.

7. The pressure testing tool for machining aviation components of claim 6, wherein: the return pipe (502) and the connecting pipe (503) are rubber pipes, and the length of the connecting pipe (503) is greater than that of the return pipe (502).