Aircraft casing test tool

Abstract

The utility model discloses an aircraft casing testing tool, which comprises a cylinder, a fixing screw is fixed on the inner lower surface of the cylinder, a sealing cover is sleeved on the outer side of the fixing screw, a sealing gasket is fixed at the bottom of the sealing cover, a nut is screwed on the outer side wall of the fixing screw above the sealing cover, and the sealing gasket is sleeved on the sealing cover. Two sealing rings are fixed to the lower surface of the interior of the barrel, a fixing shell is integrally formed on the outer side wall of the barrel, a plurality of piston rods are slidably connected to the interior of the fixing shell, and a movable frame is fixed to the right ends of the piston rods. The case is placed in the sealing belts, the case makes contact with the rubber strip, the movable screw rod is rotated, the movable screw rod drives the fixing plate and the piston rod to move, the piston rod drives the movable frame and the round block to move, the round block pulls the sealing belts to move, and therefore the two sealing belts are tightened to block two sets of air cooling holes in the outer portion of the case. Therefore, the air cooling holes can be conveniently blocked.

Description

Technical Field

[0001] This utility model relates to the field of casing testing fixtures, specifically an aircraft casing testing fixture. Background Technology

[0002] In aero-engines, components involving air cooling often require airflow testing under specific conditions before engine assembly to achieve precise airflow control, such as the aero-engine casing. The casing wall has three sets of circumferentially arranged, densely packed, small holes, no larger than 1 mm in diameter, for air cooling. The first set has one row of holes circumferentially, the second set has six rows, and the third set has one row. Before engine assembly, all three sets of these circumferentially arranged holes on the casing wall need to undergo airflow testing to ensure they meet design requirements.

[0003] The existing airflow test requires sealing two sets of air cooling holes. One set of air cooling holes is tested, but the sealing is done manually by applying aluminum foil tape. When testing the other set of air cooling holes, the aluminum foil tape needs to be removed and then manually resealed, which is quite cumbersome. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides an aircraft casing testing fixture, which solves the problems mentioned in the background section.

[0005] To achieve the above objectives, this utility model provides the following technical solution: an aircraft casing testing fixture, comprising a cylindrical body, a fixing screw fixed to the lower inner surface of the cylindrical body, a sealing cover sleeved on the outer side of the fixing screw, a sealing gasket fixed to the bottom of the sealing cover, a nut screwed onto the outer side wall of the fixing screw above the sealing cover, two sealing rings fixed to the lower inner surface of the cylindrical body, a fixing shell integrally formed on the outer side wall of the cylindrical body, a plurality of piston rods slidably connected inside the fixing shell, and a movable frame fixed to the right end of the piston rod;

[0006] A circular block is fixed inside the movable frame, and a sealing strip is fitted on the outside of the circular block. A fixed frame is provided on the right side of the movable frame, and two fixed rods are fixed on the left side of the fixed frame. The fixed rods are fixedly connected to the fixed shell. The sealing strip passes through the movable frame, and two circular rods are fixed inside the movable frame outside the sealing strip.

[0007] Two rubber strips are fixed to the right side of the movable frame, a fixed block is fixed to the front of the fixed shell, a movable screw is screwed into the inside of the fixed block, a fixed plate is fixed to the left side of the piston rod, the left end of the movable screw is rotatably connected to the fixed plate, and two air inlet pipes are fixed to the outer wall of the cylinder.

[0008] Preferably, a plurality of limiting rods are fixed on the lower inner surface of the cylinder.

[0009] Preferably, a pressure sensor is fixed on the lower inner surface of the cylinder, located outside the limiting rod.

[0010] Preferably, a temperature sensor is fixed on the lower inner surface of the cylinder behind the pressure sensor.

[0011] Preferably, a gas flow meter is fixed to the outer wall of the air inlet pipe.

[0012] Preferably, a motor is fixed to the left side of the fixing plate, and the output shaft of the motor is fixedly connected to the moving screw.

[0013] Preferably, a display screen is fixed to the top of the fixed shell.

[0014] Beneficial effects

[0015] This utility model provides a testing fixture for aircraft casings. Compared with the prior art, it has the following advantages:

[0016] This aircraft casing testing fixture, consisting of a piston rod, a moving screw, a fixed plate, a moving frame, a fixed frame, a sealing block, a rubber strip, and a sealing band, places the casing inside the sealing band, with the casing in contact with the rubber strip. Rotating the moving screw moves the fixed plate and piston rod, which in turn moves the moving frame and circular block. The circular block pulls the sealing band, causing two of the sealing bands to tighten and block two sets of air cooling vents on the outside of the casing. This facilitates the blocking of the air cooling vents and allows for airflow testing of one set of air cooling vents. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of this utility model;

[0018] Figure 2 This is a side view of the middle cylinder of this utility model;

[0019] Figure 3 This is a schematic diagram of the piston rod, the movable frame, and the fixed frame in this utility model;

[0020] Figure 4 This is a side view of the piston rod, the movable frame, and the fixed frame in this utility model.

[0021] In the diagram: 1. Piston rod; 2. Moving screw; 3. Fixed plate; 4. Motor; 5. Fixed block; 6. Inlet pipe; 7. Gas flow meter; 8. Cylinder; 9. Sealing gasket; 10. Fixed screw; 11. Nut; 12. Sealing strip; 13. Sealing cover; 14. Limiting rod; 15. Sealing ring; 16. Fixed shell; 17. Fixed rod; 18. Fixed frame; 19. Round rod; 20. Rubber strip; 21. Moving frame; 22. Round block; 23. Display screen; 24. Air pressure sensor; 25. Temperature sensor. Detailed Implementation

[0022] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0023] Please see Figures 1 to 4 This utility model provides a technical solution: an aircraft casing testing fixture, including a cylindrical body 8. A fixing screw 10 is fixed to the lower inner surface of the cylindrical body 8. A sealing cover 13 is sleeved on the outer side of the fixing screw 10. A sealing gasket 9 is fixed to the bottom of the sealing cover 13. A nut 11 is screwed onto the outer wall of the fixing screw 10 above the sealing cover 13. Two sealing rings 15 are fixed to the lower inner surface of the cylindrical body 8. A fixing shell 16 is integrally formed on the outer wall of the cylindrical body 8. Multiple piston rods 1 are slidably connected inside the fixing shell 16. A movable frame 21 is fixed to the right end of the piston rod 1. A round block 22 is fixed inside the movable frame 21. A sealing strip is sleeved on the outer side of the round block 22. 12. A fixed frame 18 is provided on the right side of the movable frame 21. Two fixed rods 17 are fixed on the left side of the fixed frame 18. The fixed rods 17 and the fixed shell 16 are fixedly connected. The sealing strip 12 passes through the movable frame 21. Two round rods 19 are fixed inside the movable frame 21 outside the sealing strip 12. Two rubber strips 20 are fixed on the right side of the movable frame 21. A fixed block 5 is fixed in front of the fixed shell 16. A movable screw 2 is screwed into the inside of the fixed block 5. A fixed plate 3 is fixed on the left side of the piston rod 1. The left end of the movable screw 2 is rotatably connected to the fixed plate 3. Two air inlet pipes 6 are fixed on the outer wall of the cylinder 8, which facilitates the sealing of the air cooling holes outside the casing.

[0024] Furthermore, multiple limiting rods 14 are fixed to the lower inner surface of the cylinder 8. The mounting hole socket of the casing is fixed to the limiting rods 14 to limit the casing and prevent it from moving or rotating. A pressure sensor 24 is fixed to the lower inner surface of the cylinder 8 outside the limiting rods 14 to detect the internal pressure of the cylinder 8. A temperature sensor 25 is fixed to the lower inner surface of the cylinder 8 behind the pressure sensor 24 to detect the internal temperature of the cylinder 8. A gas flow meter 7 is fixed to the outer wall of the air inlet pipe 6 to detect the gas flow. A motor 4 is fixed to the left side of the fixing plate 3. The output shaft of the motor 4 is fixedly connected to the moving screw 2 to facilitate the rotation of the moving screw 2. A display screen 23 is fixed to the top of the fixing shell 16 to display the test data.

[0025] During operation, connect the two air inlet pipes 6 to the air pump, then place the casing inside the sealing strip 12, with the casing in contact with the rubber strip 20. Start the motor 4, which drives the moving screw 2 to rotate. The moving screw 2 moves the fixed plate 3 and the piston rod 1, while the piston rod 1 moves the moving frame 21 and the round block 22. The round block 22 pulls the sealing strip 12, thus tightening two of the sealing strips 12 to block two sets of air cooling holes on the outside of the casing. This makes it easier to block the air cooling holes. Start the air pump, and gas enters the interior of the cylinder 8. Through the temperature sensor 25, the gas flow meter 7, and the air pressure sensor 24, the air flow of one set of unsealed air cooling holes is tested. The measured data is displayed on the display screen 23. After this set of tests is completed, the other two sets are tested in sequence.

[0026] Furthermore, any content not described in detail in this specification is existing technology known to those skilled in the art.

[0027] It should be noted that, in this document, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, the phrase "comprising an element defined as..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0028] Although embodiments of the present invention 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 to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A test fixture for an aircraft casing, comprising a cylindrical body (8), characterized in that: A fixing screw (10) is fixed on the lower inner surface of the cylinder (8). A sealing cover (13) is sleeved on the outer side of the fixing screw (10). A sealing gasket (9) is fixed at the bottom of the sealing cover (13). A nut (11) is screwed onto the outer wall of the fixing screw (10) above the sealing cover (13). Two sealing rings (15) are fixed on the lower inner surface of the cylinder (8). A fixing shell (16) is integrally formed on the outer wall of the cylinder (8). Multiple piston rods (1) are slidably connected inside the fixing shell (16). A movable frame (21) is fixed at the right end of the piston rod (1). A circular block (22) is fixed inside the movable frame (21). A sealing strip (12) is fitted on the outside of the circular block (22). A fixed frame (18) is provided on the right side of the movable frame (21). Two fixed rods (17) are fixed on the left side of the fixed frame (18). The fixed rods (17) are fixedly connected to the fixed shell (16). The sealing strip (12) passes through the movable frame (21). Two circular rods (19) are fixed inside the movable frame (21) outside the sealing strip (12). Two rubber strips (20) are fixed on the right side of the movable frame (21), a fixed block (5) is fixed in front of the fixed shell (16), a movable screw (2) is screwed into the inside of the fixed block (5), a fixed plate (3) is fixed on the left side of the piston rod (1), the left end of the movable screw (2) is rotatably connected to the fixed plate (3), and two air inlet pipes (6) are fixed on the outer wall of the cylinder (8).

2. The aircraft casing testing fixture according to claim 1, characterized in that: Multiple limiting rods (14) are fixed on the lower inner surface of the cylinder (8).

3. The aircraft casing testing fixture according to claim 2, characterized in that: A pressure sensor (24) is fixed on the lower inner surface of the cylinder (8) outside the limiting rod (14).

4. The aircraft casing testing fixture according to claim 3, characterized in that: A temperature sensor (25) is fixed on the lower inner surface of the cylinder (8) behind the pressure sensor (24).

5. The aircraft casing testing fixture according to claim 1, characterized in that: A gas flow meter (7) is fixed to the outer wall of the air inlet pipe (6).

6. The aircraft casing testing fixture according to claim 1, characterized in that: A motor (4) is fixed to the left side of the fixed plate (3), and the output shaft of the motor (4) is fixedly connected to the moving screw (2).

7. The aircraft casing testing fixture according to claim 6, characterized in that: The top of the fixed shell (16) is fixed with a display screen (23).

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