Aerospace sealing ring multi-dimensional pressure tightness testing device

Abstract

The utility model relates to sealing ring testing arrangement technical field, and disclose a kind of aerospace sealing ring multidimensional pressure tightness testing device, including fixed bottom plate and the support frame of being fixed in its top rear side, the output end of electric cylinder is located in the upper portion of the testing mechanism and is provided with axial pressure mechanism, the fixed bottom plate top is located in the lower portion of the testing mechanism and is installed with the radial pressure mechanism being communicated with it, and the electric cylinder is linked with the radial pressure mechanism;By the cooperation of axial pressure mechanism and sealing test cylinder piece, transparent scale guard plate, an axial sealing performance test system is constructed, the system can accurately simulate and control the bolt pretightening force acting on sealing ring, and the leakage condition is observed qualitatively and quantitatively through visual structure, to realize the quick, intuitive and reliable evaluation of the axial sealing performance of sealing ring, provide direct basis for determining optimal installation pretightening force.

Description

Technical Field

[0001] This utility model relates to the technical field of sealing ring testing devices, and more specifically, to a multi-dimensional pressure sealing performance testing device for aerospace sealing rings. Background Technology

[0002] In high-precision fields such as aerospace and aviation, sealing rings are key basic components that ensure the sealing of fuel systems, hydraulic systems and cabin structures. The reliability of their sealing performance is directly related to the safety and success of the entire equipment. Therefore, it is crucial to conduct rigorous ground sealing tests on the sealing rings before assembly.

[0003] Existing testing equipment has limited functionality and cannot simulate complex load conditions. In practice, sealing rings often bear both axial bolt preload and radial internal medium pressure simultaneously. However, most existing testing equipment has limited functionality, either only testing the sealing performance of the sealing ring under axial clamping force or only testing its ability to withstand internal pressure. These two tests usually need to be performed on different equipment, which is not only cumbersome and inefficient, but more importantly, it cannot reproduce the real complex working conditions of axial and radial loads acting together. This leads to deviations between test results and actual performance, and cannot provide a comprehensive and accurate basis for the selection and installation process of sealing rings. Utility Model Content

[0004] To overcome the shortcomings of existing technologies, this utility model provides a multi-dimensional pressure sealing performance testing device for aerospace sealing rings, which has the advantage of applying controllable axial and radial loads simultaneously or independently.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a multi-dimensional pressure sealing performance testing device for aerospace sealing rings, comprising a fixed base plate and a support frame fixed to the rear side of its top end. The fixed base plate and the support frame are arranged in an L-shape. An electric cylinder is installed on the upper part of the support frame, and a testing mechanism is provided on the front side of the support frame. An axial pressure mechanism is provided on the upper part of the testing mechanism at the output end of the electric cylinder. A radial pressure mechanism is installed on the top end of the fixed base plate at the lower part of the testing mechanism and communicates with it. The electric cylinder is linked with the radial pressure mechanism.

[0006] As a preferred technical solution of this utility model, the testing mechanism includes an L-shaped seat fixedly installed on the front side of the support frame in the vertical direction, and a cylindrical component fixedly installed on the top of the L-shaped seat in the horizontal direction. A transparent scale guard plate is installed on the outer side of the L-shaped seat in the horizontal direction.

[0007] As a preferred technical solution of this utility model, a number of through holes are arranged in an annular array at the bottom inner side of the cylindrical part away from the axis, and the inner side of the cylindrical part is connected to the inner side of the transparent scale guard plate through the number of through holes. The sealing ring is placed at the bottom inner side of the cylindrical part and covers the number of through holes.

[0008] As a preferred technical solution of this utility model, the axial pressure mechanism includes an externally threaded sleeve fixedly sleeved on the outside of the electric cylinder output shaft, and a slide rod that slides through the bottom end of the externally threaded sleeve. A pressure plate is fixedly installed at the bottom end of the slide rod to press the sealing ring placed inside the cylinder.

[0009] As a preferred embodiment of this utility model, a slip ring is slidably mounted on the outer side of the slide rod, and a pressure spring is sleeved on the outer side of the slide rod. The two ends of the pressure spring abut against the slip ring and the pressure plate, respectively. An internally threaded sleeve is threadedly mounted on the outer side of the externally threaded sleeve to limit the movement of the slip ring.

[0010] As a preferred technical solution of this utility model, the radial pressure mechanism includes a connecting plate fixed to the outside of the electric cylinder output shaft, and air inlet cylinders symmetrically installed on both sides of the top of the fixed base plate. A liquid cylinder is fixedly connected between the two air inlet cylinders, and an upper liquid pipe connected to the inner side of the liquid cylinder is installed on the inner side of the liquid cylinder.

[0011] As a preferred embodiment of this utility model, the lower sides of the inner cavities of the two air inlets are connected to the inner side of the liquid cylinder. Pressure tubes that slide against the inner sides of the two air inlets are symmetrically installed on both sides of the bottom end of the connecting plate. Two return springs are placed on the inner sides of the two air inlets respectively, and the two ends of the two return springs abut against the bottom end of the inner side of the air inlet and the pressure tube respectively.

[0012] Compared with the prior art, the beneficial effects of this utility model are as follows: 1. This utility model constructs an axial sealing performance testing system by combining an axial pressure mechanism with a sealing test cylinder and a transparent scale guard plate. This system can accurately simulate and control the bolt preload acting on the sealing ring, and qualitatively and quantitatively observe the leakage through a visual structure, thereby realizing a rapid, intuitive and reliable evaluation of the axial sealing performance of the sealing ring, and providing a direct basis for determining the optimal installation preload.

[0013] 2. This utility model constructs an independent radial pressure testing system by using an electric cylinder to drive a pressure tube to apply pressure to the liquid cylinder. This system can apply precise and controllable radial pressure to the inside of the sealing ring, perfectly simulating the internal medium pressure conditions. It also works in conjunction with the axial testing system to realize the sealing performance test of the sealing ring under axial and radial combined loads on a single device, greatly expanding the testing functions. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the front elevation of the entire utility model; Figure 2 This is a schematic diagram of the front elevation cross-sectional structure of the entire utility model; Figure 3 This is a schematic diagram of the connection structure between and in this utility model; Figure 4 This is a schematic diagram of the cross-sectional connection structure of [the two components] in this utility model; Figure 5 This is a schematic diagram of the front elevation cross-sectional structure of this utility model.

[0015] In the diagram: 1. Fixed base plate; 2. Support frame; 3. Electric cylinder; 4. Testing mechanism; 41. L-shaped seat; 42. Cylinder; 43. Transparent scale guard plate; 44. Through hole; 5. Axial pressure mechanism; 51. External threaded sleeve; 52. Internal threaded sleeve; 53. Sliding rod; 54. Pressure plate; 55. Slip ring; 56. Pressure spring; 7. Radial pressure mechanism; 71. Connecting plate; 72. Liquid cylinder; 721. Upper liquid pipe; 73. Air inlet cylinder; 74. Pressure pipe; 75. Return spring. Detailed Implementation

[0016] 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.

[0017] like Figures 1 to 5 As shown, this utility model provides a multi-dimensional pressure sealing performance testing device for aerospace sealing rings, including a fixed base plate 1 and a support frame 2 fixed to the rear side of its top. The fixed base plate 1 and the support frame 2 are arranged in an L-shape. An electric cylinder 3 is installed on the upper part of the support frame 2, and a testing mechanism 4 is provided on the front side of the support frame 2. An axial pressure mechanism 5 is provided on the upper part of the testing mechanism 4 at the output end of the electric cylinder 3. A radial pressure mechanism 7 connected to the fixed base plate 1 is installed on the top of the testing mechanism 4 at the lower part of the fixed base plate 1, and the electric cylinder 3 and the radial pressure mechanism 7 are linked together. In practical use, after placing the sealing ring in the testing area 4, a settable and adjustable axial clamping force is applied to the sealing ring via 5 to simulate the preload of flange bolts. Simultaneously, a pressure medium is injected into the chamber inside the testing mechanism 4 that is in radial contact with the sealing ring via the radial pressure mechanism 7. When the axial pressure mechanism 5 and the radial pressure mechanism 7 apply stable axial and radial pressures respectively, a multi-dimensional pressure environment consistent with the actual sealing scenario of aerospace equipment is formed inside the testing mechanism 4. At this point, if the sealing performance of the sealing ring meets the requirements, its sealing interface with the testing mechanism 4 can effectively block the penetration of the radial pressure medium. If the sealing ring has a sealing defect, the pressure medium will break through the sealing interface and flow out along the preset leakage channel.

[0018] The testing mechanism 4 includes an L-shaped seat 41 fixedly installed on the front side of the support frame 2 in the vertical direction, and a cylindrical part 42 fixedly installed on the top of the L-shaped seat 41 in the horizontal direction. A transparent scale guard plate 43 is installed on the outer side of the L-shaped seat 41 in the horizontal direction. Several through holes 44 are arranged in a ring array at the bottom inner side of the cylindrical part 42 away from the axis, and the inner side of the cylindrical part 42 is connected to the inner side of the transparent scale guard plate 43 through several through holes 44. The sealing ring is placed at the bottom inner side of the cylindrical part 42 and covers several through holes 44. With the above structure, when the sealing ring leaks under axial pressure, the leaking detection fluid can be uniformly and quickly collected into the transparent scale guard plate 43 through several through holes 44 in the annular array. This design not only ensures that the leakage signal is collected without blind spots and improves the accuracy of the test, but also allows the leakage amount to be directly read through the visualized scale, realizing a quantitative evaluation of the sealing performance of the sealing ring.

[0019] The axial pressure mechanism 5 includes an external threaded sleeve 51 fixedly sleeved on the outside of the output shaft of the electric cylinder 3, and a slide rod 53 that slides through the bottom of the inner side of the external threaded sleeve 51. A pressure plate 54 is fixedly installed at the bottom of the slide rod 53 to press the sealing ring placed inside the cylinder 42. A slip ring 55 is slidably mounted on the outside of the slide rod 53, and a pressure spring 56 is sleeved on the outside of the slide rod 53. The two ends of the pressure spring 56 abut against the slip ring 55 and the pressure plate 54 respectively. An internal threaded sleeve 52 is threaded on the outside of the external threaded sleeve 51 to limit the movement of the slip ring 55.

[0020] The limiting position of the slip ring 55 can be changed by turning the internal threaded sleeve 52, thereby pre-compressing or releasing the pressure spring 56, achieving stepless and precise adjustment of the axial clamping force applied by the pressure plate 54 to the sealing ring. This mechanical force adjustment mechanism has a simple and reliable structure, can accurately simulate different bolt preload conditions, and avoids the risk of losing clamping force due to power failure during testing.

[0021] The radial pressure mechanism 7 includes a connecting plate 71 fixed on the outside of the output shaft of the electric cylinder 3, and air inlet cylinders 73 symmetrically installed on both sides of the top of the fixed base plate 1. A liquid cylinder 72 is fixedly connected between the two air inlet cylinders 73, and an upper liquid pipe 721 connected to the inner side of the liquid cylinder 72 is installed on the inner side of the liquid cylinder 72. The lower side of the inner cavity of both air inlets 73 is connected to the inner side of the liquid cylinder 72. Pressure tubes 74 that slide against the inner side of the two air inlets 73 are symmetrically installed on both sides of the bottom end of the connecting plate 71. Two return springs 75 are placed inside the two air inlets 73 respectively. The two ends of the two return springs 75 are respectively held between the bottom end of the inner side of the air inlet 73 and the pressure tubes 74.

[0022] The electric cylinder 3 drives the connecting plate 71 to simultaneously press down the two pressure tubes 74, compressing the return spring 75 and forcing the gas into the air cylinder 73. Utilizing Pascal's principle, the pressure is transferred losslessly to the detection liquid in the liquid cylinder 72, thereby applying stable and precise radial pressure to the inside of the sealing ring through the upper liquid pipe 721. This symmetrical dual-cylinder pressurization structure ensures smooth and uniform force application, effectively preventing off-center load problems that may be caused by single-point pressure application.

[0023] It should be noted that, in this document, relational terms such as "first" and "second" are used only 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 process, method, article, or apparatus.

[0024] 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 multi-dimensional pressure sealing performance testing device for aerospace sealing rings, comprising a fixed base plate (1) and a support frame (2) fixed to the rear side of its top end, characterized in that: The fixed base plate (1) and the support frame (2) are arranged in an L-shape. An electric cylinder (3) is installed on the upper part of the support frame (2). A test mechanism (4) is provided on the front side of the support frame (2). An axial pressure mechanism (5) is provided on the upper part of the test mechanism (4) at the output end of the electric cylinder (3). A radial pressure mechanism (7) is installed on the top of the fixed base plate (1) at the lower part of the test mechanism (4) and is connected to it. The electric cylinder (3) is linked with the radial pressure mechanism (7).

2. The aerospace sealing ring multi-dimensional pressure sealing performance testing device according to claim 1, characterized in that: The testing mechanism (4) includes an L-shaped seat (41) fixedly installed on the front side of the support frame (2) in the vertical direction, and a cylindrical part (42) fixedly installed on the top of the L-shaped seat (41) in the horizontal direction. A transparent scale guard plate (43) is installed on the outer side of the L-shaped seat (41) in the horizontal direction.

3. The aerospace sealing ring multi-dimensional pressure sealing performance testing device according to claim 2, characterized in that: The inner bottom of the cylindrical part (42) is provided with a number of through holes (44) in an annular array far from the axis. The inner side of the cylindrical part (42) is connected to the inner side of the transparent scale guard plate (43) through the number of through holes (44). The sealing ring is placed at the inner bottom of the cylindrical part (42) and covers the number of through holes (44).

4. The aerospace sealing ring multi-dimensional pressure sealing performance testing device according to claim 3, characterized in that: The axial pressure mechanism (5) includes an external threaded sleeve (51) fixedly sleeved on the outside of the output shaft of the electric cylinder (3), and a slide rod (53) that slides through the bottom axis of the external threaded sleeve (51). The bottom end of the slide rod (53) is fixedly installed with a pressure plate (54) for pressing the sealing ring placed inside the cylinder (42).

5. The aerospace sealing ring multi-dimensional pressure sealing performance testing device according to claim 4, characterized in that: A slip ring (55) is slidably mounted on the outside of the slide rod (53), and a pressure spring (56) is sleeved on the outside of the slide rod (53). The two ends of the pressure spring (56) abut against the slip ring (55) and the pressure plate (54) respectively. An internal threaded sleeve (52) is threaded on the outside of the external threaded sleeve (51) to limit the movement of the slip ring (55).

6. The aerospace sealing ring multi-dimensional pressure sealing performance testing device according to claim 4, characterized in that: The radial pressure mechanism (7) includes a connecting plate (71) fixed to the outside of the output shaft of the electric cylinder (3) and an air inlet cylinder (73) symmetrically installed on both sides of the top of the fixed base plate (1). A liquid cylinder (72) is fixedly connected between the two air inlets (73), and an upper liquid pipe (721) connected to the inner side of the liquid cylinder (72) is installed on the inner side of the liquid cylinder (72).

7. The aerospace sealing ring multi-dimensional pressure sealing performance testing device according to claim 6, characterized in that: The lower sides of the inner cavities of the two air inlets (73) are connected to the inner side of the liquid cylinder (72). The bottom ends of the connecting plate (71) are symmetrically equipped with pressure tubes (74) that slide against the inner sides of the two air inlets (73). Two return springs (75) are placed inside the two air inlets (73) respectively. The two ends of the two return springs (75) are respectively held between the bottom end of the inner side of the air inlet (73) and the pressure tubes (74).

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