Aero-engine pressure resistance testing device

Abstract

The utility model discloses an aero-engine pressure resistance testing device, which belongs to the technical field of aero-engine production, and comprises a box body, the top of the box body is provided with an extrusion mechanism, the box body is provided with a feeding and discharging mechanism, the side part of the box body is fixedly connected with a heating box, and the side part of the heating box is fixedly sleeved with an air inlet pipe. According to the aero-engine pressure resistance testing device, when a pressure resistance test is carried out on an aero-engine in the box body, water in the water tank is pumped into the atomization spray head through the water pump to be atomized and sprayed out, so that the humidity in the box body is adjusted, and gas in the box body circulates in the gas inlet pipe, the heating box and the gas return pipe; the gas passing through the heating box is heated by the electric heating tube, so that the temperature in the box body is adjusted, the temperature and humidity of the inner cavity of the box body are detected by using the temperature and humidity sensor, the pressure resistance test of the aero-engine in different environments is realized, and the working quality of the pressure resistance test device of the aero-engine is improved.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft engine production, and more specifically to an aircraft engine pressure resistance testing device. Background Art

[0002] The engine high-pressure withstand test is a test conducted to detect the performance and reliability of the engine's high-pressure system. Through the test, it can be detected whether the performance indicators of the engine's high-pressure system, such as sealing, air-carrying and reliability, meet the standard requirements.

[0003] After searching, the utility model patent with announcement number CN217878340U discloses an aircraft engine pressure test device, including a box body and a placement plate, a placement plate is provided on the top of the box body, an electric telescopic rod is provided on the top of the placement plate, the electric telescopic rod and the placement plate are fixedly connected, a push plate is provided at one end of the electric telescopic rod, a slide groove is provided on the inner wall of the box body, a first slider is provided on one side of the placement plate, the first slider and the slide groove are slidably connected, a first spring is provided at the bottom of the placement plate, the first spring is fixedly connected to the box body, and two first springs are provided. Through the provided placement plate, electric telescopic rod and push plate, the engine is fixed, making it more stable during detection, and through the provided spring, the buffering function during detection is achieved to prevent the engine from being damaged under impact force.

[0004] However, the above patents still have the following shortcomings: it is not convenient to adjust the temperature and humidity in the box, and it is not possible to test the pressure resistance performance of the engine in different environments, which is not practical; and generally, the aircraft engine is heavy and not convenient to put into the box. For this reason, we propose an aircraft engine pressure resistance test device. Utility Model Content

[0005] In view of the problems existing in the prior art, the utility model aims to provide an aircraft engine pressure resistance testing device.

[0006] In order to solve the above problems, the utility model adopts the following technical solutions:

[0007] An aircraft engine pressure test device comprises a box body, a squeezing mechanism is arranged on the top of the box body, a loading and unloading mechanism is arranged on the box body, a heating box is fixedly connected to the side of the box body, an air intake pipe is fixedly sleeved on the side of the heating box, an end of the air intake pipe extends to the inner cavity of the box body, an electric heating pipe is fixedly installed in the inner cavity of the heating box, an exhaust fan is fixedly installed on the top surface of the heating box, an input end of the exhaust fan extends to the inner cavity of the heating box, an output end of the exhaust fan is fixedly connected to a return air pipe, an end of the return air pipe is fixedly sleeved to the inner cavity of the box body, a water tank is fixedly connected to the side of the box body, a water pump is fixedly installed on the top surface of the water tank, water guide pipes are fixedly connected to both ends of the water pump, one end of the water guide pipe extends to the inner cavity of the water tank, and another end of the water guide pipe extends to the inner cavity of the box body and is fixedly installed with an atomizing nozzle, a one-way valve is fixedly installed on the water guide pipe, a temperature and humidity sensor is fixedly installed on the top of the inner cavity of the box body, and an air pressure sensor is fixedly installed on the top of the inner cavity of the box body.

[0008] As a preferred solution of the utility model, the loading and unloading mechanism includes two square tubes fixedly connected to the back of the box body, and the ends of the two square tubes are respectively fixedly installed with servo motors, and the output shafts of the two servo motors extend to the inner cavity of the square tubes and are fixedly connected with screws, and the outer sides of the two screws are respectively threaded with moving columns, and the ends of the two moving columns extend to the inner cavity of the box body and are fixedly connected with moving seats, and the top surface of the moving seat is fixedly connected with multiple springs, and the top ends of the multiple springs are fixedly connected with a placement plate, and the inner wall of the placement plate is fixedly installed with two electric push rods, and the ends of the two electric push rods are respectively fixedly connected with clamping plates.

[0009] As a preferred solution of the utility model, the extrusion mechanism includes an electric hydraulic rod fixedly installed on the top surface of the box body, and the output end of the electric hydraulic rod extends to the inner cavity of the box body and is fixedly connected to a pressure plate.

[0010] As a preferred solution of the utility model, a sealed box door is hinged on the front of the box body, and a perspective plate is fixedly sleeved on the sealed box door.

[0011] As a preferred solution of the utility model, the side surface of the movable column is in contact with the inner wall of the square tube.

[0012] As a preferred solution of the utility model, a plurality of sliding tubes are fixedly connected to the top surface of the movable seat, and sliding rods are movably sleeved on the plurality of sliding tubes, the top of the sliding rod is connected to the bottom surface of the placement plate, and the inner wall of the sliding tube is in contact with the side of the sliding rod.

[0013] As a preferred solution of the utility model, an air pump is fixedly installed on the side of the box body, an output end of the air pump is fixedly connected to an air duct, and an end of the air duct extends to the inner cavity of the box body.

[0014] Compared with the prior art, the advantages of the present invention are:

[0015] (1) In the utility model, when the aircraft engine is subjected to a pressure test in a box, water in the water tank is pumped into the atomizing nozzle by a water pump and sprayed out in the atomizing nozzle, thereby adjusting the humidity in the box. In addition, the gas in the box is circulated in the air intake pipe, the heating box, and the return air pipe, and the gas passing through the heating box is heated by the electric heating tube, thereby adjusting the temperature in the box. The temperature and humidity of the inner cavity of the box are detected by a temperature and humidity sensor, thereby enabling the aircraft engine to be subjected to a pressure test in different environments, thereby improving the working quality of the aircraft engine pressure test device.

[0016] (2) In the present invention, a servo motor is used to drive the screw to rotate, and the threaded cooperation between the screw and the moving column can drive the moving seat and the placement plate to extend to the outside of the box, so as to facilitate the placement of the aircraft engine on the placement plate, and the cooperation between the screw and the moving column can move the aircraft engine on the placement plate to the inner cavity of the box, thereby realizing the function of convenient loading of the engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the overall structure of the utility model;

[0018] Figure 2 It is a cross-sectional schematic diagram of the utility model;

[0019] Figure 3 It is a cross-sectional schematic diagram of the box body of the utility model;

[0020] Figure 4 It is a cross-sectional schematic diagram of the mobile seat of the utility model;

[0021] Figure 5 It is a cross-sectional schematic diagram of the water tank of the utility model;

[0022] Figure 6 It is a cross-sectional schematic diagram of the heating box of the utility model.

[0023] Description of the numbers in the figure:

[0024] 1. Box body; 2. Loading and unloading mechanism; 3. Extrusion mechanism; 4. Heating box; 5. Inlet pipe; 6. Exhaust fan; 7. Return air pipe; 8. Electric heating pipe; 9. Water tank; 10. Water pump; 11. Water guide pipe; 12. Atomizing nozzle; 13. One-way valve; 14. Square tube; 15. Servo motor; 16. Screw; 17. Moving column; 18. Moving seat; 19. Spring; 20. Placement plate; 21. Electric push rod; 22. Clamp; 23. Sliding pipe; 24. Sliding rod; 25. Sealed box door; 26. Transparent plate; 27. Air pump; 28. Air duct; 29. ​​Electric hydraulic rod; 30. Pressing plate; 31. Temperature and humidity sensor; 32. Air pressure sensor. DETAILED DESCRIPTION

[0025] The following will clearly and completely describe the technical solutions in the embodiments of the utility model in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0026] In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "top / bottom" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are used for descriptive purposes only, and cannot be understood as indicating or implying relative importance.

[0027] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "provided with", "set / connected", "connected", etc. should be understood in a broad sense. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.

[0028] Example:

[0029] See also Figure 1-6A pressure test device for an aircraft engine comprises a box body 1, a squeezing mechanism 3 is arranged on the top of the box body 1, a loading and unloading mechanism 2 is arranged on the box body 1, a heating box 4 is fixedly connected to the side of the box body 1, an air intake pipe 5 is fixedly sleeved on the side of the heating box 4, the end of the air intake pipe 5 extends to the inner cavity of the box body 1, an electric heating pipe 8 is fixedly installed in the inner cavity of the heating box 4, an exhaust fan 6 is fixedly installed on the top surface of the heating box 4, the input end of the exhaust fan 6 extends to the inner cavity of the heating box 4, the output end of the exhaust fan 6 is fixedly connected to the return air pipe 7, and the end of the return air pipe 7 The upper part of the water pump 10 is fixedly connected to the inner cavity of the box body 1, the side of the box body 1 is fixedly connected to a water tank 9, the top surface of the water tank 9 is fixedly installed with a water pump 10, both ends of the water pump 10 are respectively fixedly connected with water pipes 11, one end of the water pipe 11 extends to the inner cavity of the water tank 9, the other end of the water pipe 11 extends to the inner cavity of the box body 1 and is fixedly installed with an atomizing nozzle 12, a one-way valve 13 is fixedly installed on the water pipe 11, a temperature and humidity sensor 31 is fixedly installed on the top of the inner cavity of the box body 1, and an air pressure sensor 32 is fixedly installed on the top of the inner cavity of the box body 1.

[0030] In this embodiment, the one-way valve 13 can only guide the water in the water tank 9 into the box body 1, and the inner cavity of the water tank 9 is provided with water.

[0031] For details, please refer to Figures 2 to 4 The loading and unloading mechanism 2 includes two square tubes 14 fixedly connected to the back of the box body 1, and servo motors 15 are fixedly installed at the ends of the two square tubes 14. The output shafts of the two servo motors 15 extend to the inner cavity of the square tubes 14 and are fixedly connected to screws 16. The outer sides of the two screws 16 are respectively threaded with moving columns 17. The ends of the two moving columns 17 extend to the inner cavity of the box body 1 and are fixedly connected to moving seats 18. The top surface of the moving seat 18 is fixedly connected with multiple springs 19, and the top ends of the multiple springs 19 are fixedly connected with a placement plate 20. Two electric push rods 21 are fixedly installed on the inner wall of the placement plate 20, and the ends of the two electric push rods 21 are respectively fixedly connected with clamping plates 22.

[0032] In this embodiment, the bottom surface of the splint 22 fits with the top surface of the placement plate 20 to ensure the stability of the splint 22. In addition, the bottom surface of the movable seat 18 fits with the top surface of the inner cavity of the box body 1 to ensure the stability of the movable seat 18 in the box body 1.

[0033] For details, please refer to Figure 1 and Figure 2 The extrusion mechanism 3 includes an electric hydraulic rod 29 fixedly mounted on the top surface of the box body 1 , and the output end of the electric hydraulic rod 29 extends to the inner cavity of the box body 1 and is fixedly connected to a pressing plate 30 .

[0034] In this embodiment, the electric hydraulic rod 29 is used to drive the pressing plate 30 to move downward, and the pressing plate 30 is used to squeeze and fix the engine placed on the placement plate 20.

[0035] For details, please refer to Figure 3 A sealed box door 25 is hinged on the front of the box body 1, and a perspective plate 26 is fixedly sleeved on the sealed box door 25.

[0036] In this embodiment, the engine is loaded and disassembled by opening the sealed box door 25, and the situation in the box body 1 is controlled through the perspective plate 26.

[0037] For details, please refer to Figure 3 , the side surface of the movable column 17 is in contact with the inner wall of the square tube 14 .

[0038] In this embodiment, the inner wall of the square tube 14 is used to limit the movable column 17 , so that the movable column 17 can only move along the axial direction of the screw rod 16 .

[0039] For details, please refer to Figure 4 The top surface of the movable seat 18 is fixedly connected with a plurality of slide tubes 23, and slide rods 24 are movably sleeved on the plurality of slide tubes 23. The top of the slide rod 24 is connected to the bottom surface of the placement plate 20, and the inner wall of the slide tube 23 is in contact with the side surface of the slide rod 24.

[0040] In this embodiment, the placement plate 20 is limited by the cooperation between the sliding tube 23 and the sliding rod 24, so that the placement plate 20 can only move up and down.

[0041] For details, please refer to Figure 1 An air pump 27 is fixedly installed on the side of the box body 1, and an output end of the air pump 27 is fixedly connected to an air duct 28, and the end of the air duct 28 extends to the inner cavity of the box body 1.

[0042] In this embodiment, high-pressure air is charged into the box body 1 through the air pump 27 and the air duct 28 .

[0043] Working principle: When in use, first start the two servo motors 15 to drive the two screws 16 to rotate, and use the threaded cooperation between the screw 16 and the moving column 17 to drive the two moving columns 17 to move from the inner cavity of the square tube 14 to the inner cavity of the box body 1. At this time, use the moving column 17 to drive the moving seat 18 and the placement plate 20 to extend from the front of the box body 1, so as to place the aircraft engine on the placement plate 20, and then start the electric push rod 21 to drive the clamping plate 22 to move and squeeze and fix the aircraft engine placed on the placement plate 20, and start the two servo motors 15 to reverse, and use the threaded cooperation between the screw 16 and the moving column 17 to make the moving column 17 move the moving seat 18, the placement plate 20 and the aircraft engine to the inner cavity of the box body 1, and then close the sealed box door 25, start the electric hydraulic rod 29 to drive the pressure plate 30 to move downward, and use the pressure plate 30 to squeeze the top of the aircraft engine to perform a pressure test on the engine. In addition, the air pump can be started 27 makes the air duct 28 inject high-pressure gas into the inner cavity of the box body 1, and the high pressure in the inner cavity of the box body 1 is used to perform pressure testing on the aircraft engine. During the test, the water pump 10 can be started to pump water in the water tank 9 to the atomizing nozzle 12 for atomization and spraying, thereby adjusting the humidity in the box body 1. In addition, the exhaust fan 6 is started to exhaust air from the heating box 4, and the air inlet pipe 5 on the side of the heating box 4 exhausts air from the box body 1. The gas exhausted by the exhaust fan 6 is guided back to the inner cavity of the box body 1 from the return pipe 7. The gas passing through the heating box 4 is heated by the electric heating tube 8, thereby adjusting the temperature in the box body 1, and the temperature and humidity sensor 31 is used to detect the temperature and humidity of the inner cavity of the box body 1, and the pressure sensor 32 is used to measure the pressure of the inner cavity of the box body 1, so as to realize testing under different temperatures and humidities. Finally, after the pressure test, the servo motor 15 is started again to drive the moving seat 18 and the placement plate 20 to extend out of the inner cavity of the box body 1, so that the tested engine can be removed.

[0044] The above is only a preferred specific implementation method of the utility model, but the protection scope of the utility model is not limited thereto. Any technician familiar with the technical field can make equivalent substitutions or changes within the technical scope disclosed by the utility model according to the technical solution and improved ideas of the utility model, which should be included in the protection scope of the utility model.

Claims

1. An aircraft engine pressure test device, comprising a box (1), characterized in that: The top of the box (1) is provided with an extrusion mechanism (3), the box (1) is provided with a loading and unloading mechanism (2), the side of the box (1) is fixedly connected with a heating box (4), the side of the heating box (4) is fixedly sleeved with an air intake pipe (5), the end of the air intake pipe (5) extends to the inner cavity of the box (1), the inner cavity of the heating box (4) is fixedly installed with an electric heating pipe (8), the top surface of the heating box (4) is fixedly installed with an exhaust fan (6), the input end of the exhaust fan (6) extends to the inner cavity of the heating box (4), the output end of the exhaust fan (6) is fixedly connected with a return air pipe (7), the end of the return air pipe (7) is fixedly sleeved to the box The inner cavity of the box body (1) is fixedly connected to a water tank (9) on the side of the box body (1), a water pump (10) is fixedly installed on the top surface of the water tank (9), and water pipes (11) are fixedly connected to both ends of the water pump (10), one end of the water pipe (11) extends to the inner cavity of the water tank (9), and the other end of the water pipe (11) extends to the inner cavity of the box body (1) and is fixedly installed with an atomizing nozzle (12), a one-way valve (13) is fixedly installed on the water pipe (11), a temperature and humidity sensor (31) is fixedly installed on the top of the inner cavity of the box body (1), and an air pressure sensor (32) is fixedly installed on the top of the inner cavity of the box body (1).

2. The aircraft engine pressure test device according to claim 1, characterized in that: The loading and unloading mechanism (2) comprises two square tubes (14) fixedly connected to the back of the box body (1), the ends of the two square tubes (14) are respectively fixedly installed with servo motors (15), the output shafts of the two servo motors (15) respectively extend to the inner cavity of the square tube (14) and are fixedly connected with screws (16), the outer sides of the two screws (16) are respectively threadedly sleeved with moving columns (17), the ends of the two moving columns (17) respectively extend to the inner cavity of the box body (1) and are fixedly connected with moving seats (18), the top surface of the moving seats (18) are fixedly connected with a plurality of springs (19), the top ends of the plurality of springs (19) are fixedly connected with a placement plate (20), the inner wall of the placement plate (20) is fixedly installed with two electric push rods (21), and the ends of the two electric push rods (21) are respectively fixedly connected with clamping plates (22).

3. The aircraft engine pressure test device according to claim 1, characterized in that: The extrusion mechanism (3) comprises an electric hydraulic rod (29) fixedly mounted on the top surface of the box body (1), wherein the output end of the electric hydraulic rod (29) extends to the inner cavity of the box body (1) and is fixedly connected to a pressing plate (30).

4. The aircraft engine pressure test device according to claim 1, characterized in that: A sealed box door (25) is hingedly connected to the front of the box body (1), and a perspective plate (26) is fixedly sleeved on the sealed box door (25).

5. The aircraft engine pressure test device according to claim 2, characterized in that: The side surface of the movable column (17) is in contact with the inner wall of the square tube (14).

6. The aircraft engine pressure test device according to claim 2, characterized in that: The top surface of the movable seat (18) is fixedly connected with a plurality of sliding tubes (23), and sliding rods (24) are movably sleeved on the plurality of sliding tubes (23), the top ends of the sliding rods (24) are connected with the bottom surface of the placement plate (20), and the inner walls of the sliding tubes (23) are in contact with the side surfaces of the sliding rods (24).

7. The aircraft engine pressure test device according to claim 1, characterized in that: An air pump (27) is fixedly mounted on the side of the box body (1), and an output end of the air pump (27) is fixedly connected to an air duct (28), and an end of the air duct (28) extends to the inner cavity of the box body (1).

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