Aero-engine detection device

Abstract

The utility model discloses an aero-engine detection device, which relates to the technical field of aviation instruments, and comprises a detection body, a binding surface and a measuring surface are respectively formed at two opposite ends of the detection body, the binding surface is suitable for abutting against a bottom surface, and the detection body is also provided with a channel penetrating along the axial direction. The central axis of the channel is perpendicular to the binding face. The detection body is provided with a binding surface, a measuring surface and a channel penetrating through the binding surface and the measuring surface, the actuating rod is arranged in the channel of the aero-engine detection device in a penetrating mode, the binding surface abuts against the bottom face of a valve body of the vacuum diaphragm capsule valve, and at the moment, the relative position between the center of the actuating rod and the center of the measuring surface is compared; therefore, whether the actuating rod is eccentric or not can be judged. According to the arrangement, the offset condition of the actuating rod can be clearly observed through the measuring surface, a maintainer accurately judges the specific state of the actuating rod, and in the subsequent calibration process, the aero-engine detection device can also accurately provide reference so as to solve the problem of diaphragm eccentric wear.

Description

TECHNICAL FIELD

[0001] The utility model relates to aviation instrument technology field especially, relates to an aero-engine detection device. BACKGROUND

[0002] In the use process of the aviation piston engine, the engine feeds back signals to the electronic control unit (ECU) through the air intake pressure sensor, then actuates the BPA assembly, and the BPA assembly changes the speed of the turbocharger to control the air intake pressure through the air pressure control exhaust valve controller.

[0003] The existing vacuum diaphragm valve of the exhaust valve controller has a gas leakage failure, and the main reason is that the movement process of the actuating rod is eccentric, which causes the rubber diaphragm of the vacuum diaphragm valve to wear on one side. After the rubber diaphragm wears and leaks, the exhaust valve controller cannot actuate, the turbocharger exhaust valve cannot open, and the engine air intake pressure is out of limit. This will reduce the service life of the exhaust valve controller, and even may increase the risk of aviation work.

[0004] However, in the narrow engine, it is difficult for maintenance personnel to find out whether the actuating rod is eccentric, and the maintenance personnel cannot accurately calibrate the actuating rod, which will cause the rubber diaphragm to wear and tear. UTILITY MODEL CONTENTS

[0005] In view of the shortcomings of the above related technologies, the present application provides an aero-engine detection device to solve the above technical problems.

[0006] The present application provides an aero-engine detection device for detecting a vacuum diaphragm valve, the vacuum diaphragm valve comprising a valve body and an actuating rod connected to each other, the valve body having a bottom surface, the bottom surface being provided with an opening, the actuating rod extending out of the opening, the aero-engine detection device comprising a detection body, opposite ends of the detection body being formed with a fitting surface and a measuring surface respectively, the fitting surface being adapted to abut against the bottom surface, the detection body further having a channel penetrating in the axial direction, the central axis of the channel being perpendicular to the fitting surface, the channel being adapted to pass through the actuating rod, and the measuring surface being used to measure the eccentricity of the actuating rod relative to the axis of the opening.

[0007] In an embodiment of the present application, the detection body is provided with a through groove, the through groove penetrating the side wall of the detection body in the radial direction and being communicated with the channel, and the through groove extending from the fitting surface to the measuring surface.

[0008] In an embodiment of the present application, the detection body comprises a first detection member and a second detection member, the first detection member and the second detection member being detachably connected, and the channel being formed between the first detection member and the second detection member.

[0009] The first detection piece has a first fitting surface and a first measuring surface, and the second detection piece has a second fitting surface and a second measuring surface; when the first detection piece and the second detection piece are detachably connected, the first fitting surface and the second fitting surface are connected with each other to form a fitting surface, and the first measuring surface and the second measuring surface are connected with each other to form a measuring surface.

[0010] In an embodiment of the present application, the detection body comprises a fitting part and a measuring part, one end of the measuring part is connected to the fitting part, the other end extends away from the fitting part, the central axis of the measuring part and the central axis of the channel overlap each other, and the outer diameter of the fitting part is greater than the outer diameter of the measuring part; the channel penetrates through the fitting part and the measuring part; the fitting surface is the surface of the fitting part away from the measuring part; and the measuring surface is the surface of the measuring part away from the fitting part.

[0011] In an embodiment of the present application, the fitting part is provided with a groove, the fitting surface is the end surface of the groove wall forming the groove, and the channel is arranged in the groove bottom; the groove is used for avoiding the boss of the bottom surface.

[0012] In an embodiment of the present application, the aviation engine detection device is further provided with an insertion part, the insertion part is protruded in the groove, the groove is formed between the insertion part and the fitting surface, and the channel penetrates through the insertion part; the insertion part is suitable for being inserted into the opening.

[0013] In an embodiment of the present application, the end of the insertion part away from the measuring part is provided with a chamfer.

[0014] In an embodiment of the present application, the length of the measuring part is 1-3 times of the inner diameter of the channel.

[0015] In an embodiment of the present application, the fitting surface and the measuring surface are parallel to each other.

[0016] In an embodiment of the present application, the measuring surface is provided with a plurality of marks, and the marks are used for showing the position of the center of the measuring surface.

[0017] The technical scheme adopted by the utility model can achieve the following beneficial effects: the aviation engine detection device comprises a detection body, the detection body has a fitting surface and a measuring surface and a channel penetrating between the fitting surface and the measuring surface, the actuating rod is arranged in the channel of the aviation engine detection device, and the fitting surface is abutted to the bottom surface of the valve body of the vacuum diaphragm valve; at this time, the relative position between the actuating rod and the center of the measuring surface can be compared, so that it can be judged whether the actuating rod is eccentric. If the actuating rod is offset, the axis of the actuating rod will deviate from the center of the actuating rod. The setting can clearly observe the offset of the actuating rod through the measuring surface, the specific state of the actuating rod can be accurately judged by the maintenance personnel, and in the subsequent calibration process, the aviation engine detection device can also accurately provide a reference, so that the maintenance personnel can accurately calibrate the actuating rod, thereby solving the problem of diaphragm eccentric wear. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.

[0019] Figure 1 is a structural schematic diagram of a vacuum diaphragm valve shown by an exemplary embodiment of the present application;

[0020] Figure 2 is a structural schematic diagram of another vacuum diaphragm valve shown by an exemplary embodiment of the present application;

[0021] Figure 3 is a structural schematic diagram of an aero-engine detection device shown by an exemplary embodiment of the present application;

[0022] Figure 4 is a structural schematic diagram of the aero-engine detection device from another perspective shown by an exemplary embodiment of the present application;

[0023] Figure 5 is a structural schematic diagram of another aero-engine detection device shown by an exemplary embodiment of the present application;

[0024] Figure 6 is an exploded schematic diagram of still another aero-engine detection device shown by an exemplary embodiment of the present application;

[0025] Figure 7 is a structural schematic diagram of the aero-engine detection device from still another perspective shown by an exemplary embodiment of the present application.

[0026] In the drawings: 1, aero-engine detection device; 100, detection body; 11, fitting surface; 111, first fitting surface; 112, second fitting surface; 12, measurement surface; 121, first measurement surface; 122, second measurement surface; 123, mark; 13, passage; 14, first detection piece; 15, second detection piece; 16, fitting part; 161, groove; 17, measurement part; 18, insertion part; 19, through slot; 2, vacuum diaphragm valve; 21, valve body; 22, actuating rod; 23, diaphragm; 24, opening; 25, bottom surface. DETAILED DESCRIPTION

[0027] Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work belong to the scope of protection of the present application.

[0028] The terms "first", "second", and the like in the specification and claims of the present application are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances, so that the embodiments of the present application can be implemented in an order other than those illustrated or described herein, and the objects distinguished by "first", "second", etc. are generally a class, not limited to the number of objects, for example, the first object can be one or more. In addition, "and / or" in the specification and claims indicates at least one of the connected objects, and the character " / ", generally indicates that the front and rear associated objects are in an "or" relationship.

[0029] Please refer to Figure 1 The vacuum diaphragm valve 2 comprises a valve body 21 and an actuating rod 22 connected with each other, the valve body 21 has a bottom surface 25 provided with an opening 24, and the actuating rod 22 extends out of the opening 24. Exemplarily, the valve body 21 has a diaphragm 23 inside, the valve body 21 inhales or exhales air, the internal pressure of the valve body 21 changes, and the pressure can act on the diaphragm 23 to cause the diaphragm 23 to deform. At the same time, the diaphragm 23 pushes the actuating rod 22 to move, so as to change the opening degree of the subsequent valve body 21.

[0030] However, the movement process of the actuating rod 22 is eccentric, which causes the diaphragm 23 of the vacuum diaphragm valve 2 to be easily worn on one side. More specifically, as shown in Figure 1 and Figure 2 The actuating rod 22 has an initial position and a limit position. Figure 1 A structural schematic view when the actuating rod 22 is in the initial position is shown, Figure 2 A structural schematic view when the actuating rod 22 is in the limit position is shown. Please refer to Figure 2 When the actuating rod 22 is in the limit position, the deformation amount and the load of the diaphragm 23 increase to the maximum. However, the movement process of the actuating rod 22 is eccentric, that is, there is an included angle between the central axis of the actuating rod 22 in the initial position and the central axis of the actuating rod 22 in the limit position. Due to the existence of the included angle, the actuating rod 22 will force the diaphragm 23 to tilt during the movement. Therefore, when the actuating rod 22 is in the limit position, the load of the diaphragm 23 is the maximum, and the tilting angle of the diaphragm 23 is the maximum, which causes the force on one side of the diaphragm 23 to be unbalanced, resulting in rapid wear.

[0031] The application provides an aero-engine detection device 1, please refer to Figure 3 The aero-engine detection device 1 is used for detecting a vacuum diaphragm valve 2.

[0032] Please continue to refer to Figure 3 and Figure 4 The aero-engine detection device 1 can comprise a detection body 100, the detection body 100 can be a cylinder or a circular table structure, and the embodiment is not limited. The opposite ends of the detection body 100 are formed with a fitting surface 11 and a measuring surface 12, respectively, and the sizes of the fitting surface 11 and the measuring surface 12 can be the same or different. Further, the fitting surface 11 and the measuring surface 12 can be parallel to each other, and the measuring surface 12 is also parallel to the bottom surface 25, which can enable the maintenance personnel to more clearly observe the condition of the actuating rod 22 through the measuring surface 12. Exemplarily, the detection body 100 is a cylinder, and the fitting surface 11 and the measuring surface 12 can both be configured as circular surfaces.

[0033] Please refer to Figure 2 and Figure 3 The fitting surface 11 is adapted to abut against the bottom surface 25, at which time the fitting surface 11 and the bottom surface 25 are in the same plane. The detection body 100 also has a channel 13 penetrating in the axial direction, the central axis of the channel 13 is perpendicular to the fitting surface 11, and the channel 13 is adapted to pass through the actuating rod 22. Since there is a perpendicular relationship between the central axis of the channel 13 and the fitting surface 11, the central axis of the channel 13 is perpendicular to the bottom surface 25. The actuating rod 22 is arranged in the channel 13. The central axis of the actuating rod 22 with eccentricity phenomenon is not perpendicular to the bottom surface 25, and thus the direction of the central axis of the actuating rod 22 deviates from the central axis of the channel 13. Therefore, there is an included angle between the central axis of the actuating rod 22 and the central axis of the opening 24, and whether the central axis of the actuating rod 22 coincides with the central axis of the channel 13 can be used as a basis for the maintenance personnel to determine whether the actuating rod 22 has eccentricity phenomenon at this time.

[0034] The measuring surface 12 is used for measuring the eccentricity of the actuating rod 22 relative to the central axis of the opening 24. In the case of a certain included angle, as the distance between the actuating rod 22 and the opening 24 increases, the distance between the central axis of the actuating rod 22 and the central axis of the channel 13 also increases. At the measuring surface 12, the maintenance personnel can clearly observe whether the central axis of the actuating rod 22 passes through the center of the measuring surface 12. If the central axis of the actuating rod 22 does not pass through the center of the measuring surface 12, it is determined that the actuating rod 22 at the current position has eccentricity phenomenon. The setting can clearly observe the offset of the actuating rod 22 through the measuring surface 12, and the maintenance personnel can accurately determine the specific state of the actuating rod 22. And in the subsequent calibration process, the aero-engine detection device 1 can also accurately provide a reference to ensure that the maintenance personnel can accurately calibrate the actuating rod 22 to solve the problem of eccentric wear of the diaphragm 23.

[0035] It can be understood that, on the premise of knowing the length value of the channel 13, the maintenance personnel measures the distance between the actuating rod 22 and the center of the measuring surface 12 in the direction of the vertical channel 13, and calculates the included angle between the central axis of the actuating rod 22 and the central axis of the opening 24 through the relationship between the distance and the length value. Thus, the relative size of the eccentricity of the actuating rod 22 is derived, so as to facilitate the maintenance personnel to calibrate and record.

[0036] Referring to Figure 5 The detection body 100 of the embodiment is provided with a through groove 19 which penetrates the side wall of the detection body 100 in the radial direction and which is communicated with the channel 13. In other words, the through groove 19 penetrates the side wall of the detection body 100, and the channel 13 is formed at the groove bottom of the through groove 19. The groove width of the through groove 19 can be greater than the outer diameter of the actuating rod 22, so that the actuating rod 22 can pass through the through groove 19 and be installed in the channel 13. The through groove 19 extends from the abutting surface 11 to the measuring surface 12, and the actuating rod 22 can be accurately installed in the channel 13 through the through groove 19. This arrangement can enable the detection body 100 to perform detection work in a narrow engine compartment without disassembling the vacuum diaphragm valve 2, that is, the work of detecting the eccentricity is completed, and the detection efficiency of the aero-engine detection device 1 is improved.

[0037] Preferably, the groove width of the through groove 19 is less than or equal to the diameter of the channel 13. This arrangement can make the through groove 19 smaller in size, and the small-volume through groove 19 can ensure the detection effect of the aero-engine detection device 1.

[0038] In another embodiment, referring to Figure 6 The detection body 100 can include a first detection piece 14 and a second detection piece 15, and the sizes and shapes of the first detection piece 14 and the second detection piece 15 can be the same or different. For example, the sizes and shapes of the first detection piece 14 and the second detection piece 15 are the same, and the first detection piece 14 and the second detection piece 15 are symmetrically arranged in the radial direction of the channel 13.

[0039] In the narrow engine compartment, the maintenance personnel cannot install the aero-engine detection device 1 into the vacuum diaphragm valve 2. However, the first detection piece 14 and the second detection piece 15 of the embodiment can be detachably connected, and the channel 13 is formed between the first detection piece 14 and the second detection piece 15. In other words, the channel 13 is surrounded by the first detection piece 14 and the second detection piece 15. When it is needed to pass the actuating rod 22 in the channel 13, the first detection piece 14 and the second detection piece 15 are installed on the side of the actuating rod 22 in different directions, and the first detection piece 14 and the second detection piece 15 are detachably connected. The detachable arrangement of the first detection piece 14 and the second detection piece 15 can assemble the first detection piece 14 and the second detection piece 15 in batches, which can reduce the installation difficulty of the aero-engine detection device 1, and the smaller first detection piece 14 and second detection piece 15 can smoothly enter the narrow engine compartment. This arrangement can also complete the detection of eccentricity without disassembling the vacuum diaphragm valve 2, which improves the detection efficiency of the aero-engine detection device 1. Such installation method not only reduces the installation difficulty, but also significantly improves the installation efficiency.

[0040] Further, please continue to refer to Figure 6 , the first detection piece 14 has a first fitting surface 111 and a first measurement surface 121, and the second detection piece 15 has a second fitting surface 112 and a second measurement surface 122. When the first detection piece 14 and the second detection piece 15 are detachably connected, the first fitting surface 111 and the second fitting surface 112 are connected with each other to form the fitting surface 11, and the first measurement surface 121 and the second measurement surface 122 are connected with each other to form the measurement surface 12. The detection body 100 formed by the combination of the first detection piece 14 and the second detection piece 15 can complete the detection of the actuating rod 22, which will not be described in detail here. In addition, after one of the first detection piece 14 and the second detection piece 15 is damaged, only one of them can be replaced, and the remaining one can still be used, which reduces the maintenance cost.

[0041] In the embodiment, please refer to Figure 3 , the detection body 100 can include a fitting part 16 and a measurement part 17. One end of the measurement part 17 is connected to the fitting part 16, and the other end extends away from the fitting part 16. The central axis of the measurement part 17 overlaps with the central axis of the channel 13. The channel 13 penetrates through the fitting part 16 and the measurement part 17. The fitting surface 11 is the surface of the fitting part 16 away from the measurement part 17, and the measurement surface 12 is the surface of the measurement part 17 away from the fitting part 16. The channel 13 can pass through the actuating rod 22 to detect or calibrate the actuating rod 22.

[0042] Please refer to Figure 4, the outer diameter d1 of the fitting portion 16 is greater than the outer diameter d2 of the measuring portion 17. Compared with the measuring surface 12, this can make the fitting portion 16 have a larger area of the fitting surface 11, which can have a larger contact area with the bottom surface 25, improving the detection accuracy of the aero-engine detection device 1. In contrast, the small size of the measuring portion 17 can reduce the distance between the measuring surface 12 and the actuating rod 22, making it easier to compare the positional relationship between the center of the actuating rod 22 and the measuring surface 12. At the same time, the small size of the measuring portion 17 can reduce the volume of the detection body 100, so that the detection body 100 can enter a smaller space.

[0043] In other cases, the outer diameter of the fitting portion 16 can be equal to the outer diameter of the measuring portion 17, i.e. the size of the fitting portion 16 and the measuring portion 17 is the same, and the structure is simple and reliable, which will not be described here.

[0044] In actual application, there are protrusions around the opening 24 of the vacuum diaphragm valve 2, which can be caused by the internal structure of the valve body 21 extending out, and can also provide a stable path for the actuating rod 22. However, the protrusions can hinder the fitting surface 11, causing the fitting surface 11 to be unable to abut against the bottom surface 25. In the present embodiment, please refer to Figure 3 , the fitting portion 16 is provided with a groove 161, the fitting surface 11 is an end surface of the groove wall of the groove 161, and the channel 13 is provided in the groove bottom of the groove 161. Further, the groove 161 can be arranged around the channel 13. The groove 161 is used to avoid the boss of the bottom surface 25, to ensure that the fitting surface 11 and the bottom surface 25 abut against each other, solving the interference problem caused by the boss of the bottom surface 25. In addition, the groove 161 can also avoid other structures on the bottom surface 25, which will not be listed here.

[0045] Please continue to refer to Figure 3The aero-engine detection device 1 is further provided with an insertion portion 18, which is protruded in a groove 161 formed between the insertion portion 18 and the abutting surface 11, and the channel 13 penetrates through the insertion portion 18. In the insertion portion 18, the channel 13 provides an insertion path for the actuating rod 22, so that the actuating rod 22 can be inserted into the part of the channel 13 in the insertion portion 18. The insertion portion 18 is adapted to be inserted into the opening 24, and there is an active gap between the insertion portion 18 and the opening 24, for example, and the insertion portion 18 can be inserted into the active gap. At this time, the outer wall of the insertion portion 18 can be in close contact with the inner wall of the opening 24, which not only stabilizes the position of the aero-engine detection device 1 in the opening 24, but also effectively prevents detection errors caused by shaking or misplacement. The setting can make the insertion portion 18 play a positioning role, which ensures that the aero-engine detection device 1 can be accurately positioned at the predetermined position of the opening 24. The aero-engine detection device 1 can detect the actuating rod 22 according to two reference factors of the bottom surface 25 and the opening 24 at the same time, which can significantly improve the accuracy and reliability of the detection.

[0046] In an embodiment, referring to Figure 4 The end of the insertion portion 18 away from the measurement portion 17 is provided with a chamfer. The chamfer can be a rounded chamfer or an inclined chamfer, and the present embodiment is not limited thereto. The insertion portion 18 can enter the opening 24 along a more stable path. This smooth transition reduces friction and collision between the insertion portion 18 and the valve body 21, reduces the risk of damage to the valve body 21, and improves the accuracy and efficiency of the operation.

[0047] Preferably, referring to Figure 4 The length d3 of the measurement portion 17 is 1-3 times, such as 1 times, 2.5 times or 3 times, of the inner diameter d4 of the channel 13, and the present embodiment is not limited thereto. The ratio should not be set too large or too small. When the ratio is set too large, the length of the measurement portion 17 is large. At this time, even if the actuating rod 22 has a small eccentricity problem, the distance between the axis of the actuating rod 22 and the center of the measurement surface 12 is large enough to cause the channel 13 to be unable to completely accommodate the actuating rod 22, resulting in failure of the aero-engine detection device 1. When the ratio is set too small, the distance between the axis of the actuating rod 22 and the axis of the channel 13 on the measurement surface 12 is not obvious, and it is difficult for maintenance personnel to judge whether the actuating rod 22 is eccentric. The setting of the appropriate ratio can quickly and accurately install the aero-engine detection device 1, and the maintenance personnel can quickly observe the specific situation of the actuating rod 22, thereby improving the detection efficiency of the aero-engine detection device 1.

[0048] In the present embodiment, referring to Figure 7The measuring surface 12 is provided with a plurality of marks 123, the number of which can be 3, 4 or more, which is not limited herein. The marks 123 are used to show the position of the center of the measuring surface 12. The marks 123 can be triangular or arrow-shaped, which is not limited in the embodiment. For example, the plurality of marks 123 are distributed along the circumference of the measuring surface 12, and are arranged at intervals between adjacent two marks 123. The marks 123 can enable the maintenance personnel to clearly observe the approximate position of the center of the measuring surface 12, that is, to determine that the actuating rod 22 is eccentric. This arrangement can improve the detection accuracy of the aero-engine detection device 1 and improve the use convenience of the aero-engine detection device 1.

[0049] For the convenience of understanding, the use method of the aero-engine detection device 1 is briefly described as follows.

[0050] The actuating rod 22 of the vacuum diaphragm valve 2 is moved to a preset position. The preset position can refer to the farthest position of the actuating rod 22 relative to the valve body 21, that is, the position at which the diaphragm 23 is deformed most. At this position, the diaphragm 23 is unevenly stressed, thereby causing eccentric wear. For example, by introducing gas into the vacuum diaphragm valve 2, the diaphragm 23 in the valve body 21 can drive the actuating rod 22 to move to the preset position.

[0051] The actuating rod 22 is arranged in the channel 13 of the aero-engine detection device 1, and the abutting surface 11 is abutted against the bottom surface 25 of the valve body 21. The relative position between the axis of the actuating rod 22 and the center of the measuring surface 12 is compared to detect the specific eccentricity of the actuating rod 22 relative to the axis of the opening 24. For example, if the axis of the actuating rod 22 does not coincide with the center of the measuring surface 12, it is determined that the actuating rod 22 is eccentric. Thus, the detection of the vacuum diaphragm valve 2 is completed.

[0052] Subsequently, the maintenance personnel can also adjust the actuating rod 22 according to the eccentricity of the actuating rod 22, so that the actuating rod 22 extends along the axis of the opening 24. For example, the maintenance personnel can adjust the position or attitude of the valve body 21 to change the relative position and attitude of the actuating rod 22, so that the central axis of the actuating rod 22 overlaps with the axis of the opening 24, which indicates that the actuating rod 22 is perpendicular to the bottom surface 25 at the preset position. At this time, when the actuating rod is at the preset position (i.e., the limit position), the diaphragm 23 is under the maximum load, and the inclination angle of the diaphragm 23 is 0. This arrangement can ensure that the diaphragm 23 inside the valve body 21 is uniformly stressed at the preset position, thereby improving the service life and safety of the aero-piston engine. Thus, the calibration of the actuating rod 22 at the preset position is completed.

[0053] It can be understood that when the actuating rod 22 is in the limit position, the inclination angle of the diaphragm 23 is 0. Based on the working principle of the actuating rod 22, the actuating rod 22 will still be eccentric in the initial position. The diaphragm 23 will be inclined, but at this time the diaphragm 23 has no other load and will not have the problem of eccentric wear of the diaphragm 23. Further, the setting can compensate for a certain angle by the actuating rod 22 in the initial position, so that the inclination angle of the diaphragm 23 is 0 when the actuating rod 22 is in the limit position, thereby solving the problem of eccentric wear of the diaphragm 23.

[0054] The technical scheme adopted by the utility model can achieve the following beneficial effects: the aero-engine detection device 1 includes a detection body 100, the detection body 100 has a fitting surface 11 and a measuring surface 12 and a channel 13 penetrating between the fitting surface 11 and the measuring surface 12, the actuating rod 22 is arranged in the channel 13 of the aero-engine detection device 1, and the fitting surface 11 is abutted against the bottom surface 25 of the valve body 21 of the vacuum diaphragm valve 2, at this time, the relative position between the actuating rod 22 and the center of the measuring surface 12 can be compared to determine whether the actuating rod 22 is eccentric. If the actuating rod 22 is offset, the axis of the actuating rod 22 will deviate from the center of the actuating rod 22. The setting can clearly observe the offset of the actuating rod 22 through the measuring surface 12, so that the maintenance personnel can accurately determine the specific state of the actuating rod 22, and in the subsequent calibration process, the aero-engine detection device 1 can also accurately provide a reference to ensure that the maintenance personnel can accurately calibrate the actuating rod 22 to solve the problem of diaphragm eccentric wear.

[0055] It should be noted that in this document, the terms "comprise", "comprising", or any other variant 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 can also include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without more limitations, an element defined by the statement "comprising a" does not exclude the presence of additional identical elements in the process, method, article, or apparatus that includes the element.

[0056] In addition, it should be noted that the scope of the methods and devices in the embodiments of the present application is not limited to performing functions in the order shown or discussed, but can also include performing functions in a substantially simultaneous manner or in the opposite order, for example, the described method can be performed in an order different from that described, and various steps can also be added, omitted, or combined. In addition, the features described with reference to certain examples can be combined in other examples.

[0057] The above merely describes a specific implementation of the present application, but the protection scope of the present application is not limited thereto, any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application.

Claims

1. An aircraft engine detection device for detecting a vacuum diaphragm valve, the vacuum diaphragm valve including a valve body and an actuating rod connected to each other, the valve body having a bottom surface with an opening formed therein, the actuating rod extending out of the opening, characterized by, The aero-engine detection device comprises a detection body, opposite ends of the detection body form a fitting surface and a measuring surface respectively, the fitting surface is suitable for abutting against the bottom surface, the detection body further has a channel penetrating through in the axial direction, the central axis of the channel is perpendicular to the fitting surface, the channel is suitable for penetrating the actuating rod, and the measuring surface is used for measuring the eccentricity of the actuating rod relative to the opening axis.

2. The aircraft engine detection apparatus of claim 1, wherein, The detection body is provided with a through groove, the through groove penetrates through the side wall of the detection body in the radial direction and is communicated with the channel, and the through groove extends from the fitting surface to the measuring surface.

3. The aircraft engine detection apparatus of claim 1, wherein, The detection body comprises a first detection member and a second detection member, the first detection member and the second detection member are detachably connected, and the channel is formed between the first detection member and the second detection member. The first detection member has a first fitting surface and a first measuring surface, the second detection member has a second fitting surface and a second measuring surface, when the first detection member and the second detection member are detachably connected, the first fitting surface and the second fitting surface are connected with each other to form the fitting surface, and the first measuring surface and the second measuring surface are connected with each other to form the measuring surface.

4. The aircraft engine detection apparatus of any one of claims 1-3, wherein, The detection body comprises a fitting part and a measuring part, one end of the measuring part is connected to the fitting part, the other end extends away from the fitting part, the central axis of the measuring part and the central axis of the channel overlap with each other, the outer diameter of the fitting part is greater than the outer diameter of the measuring part, the channel penetrates through the fitting part and the measuring part, the fitting surface is the surface of the fitting part away from the measuring part, and the measuring surface is the surface of the measuring part away from the fitting part.

5. The aircraft engine detection apparatus of claim 4, wherein, The fitting part is provided with a groove, the fitting surface is the end face of the groove wall of the groove, the channel is arranged in the groove bottom of the groove, and the groove is used for avoiding the boss of the bottom surface.

6. The aircraft engine detection apparatus of claim 5, wherein, The aero-engine detection device is further provided with an insertion part, the insertion part protrudes in the groove, the groove is formed between the insertion part and the fitting surface, the channel penetrates through the insertion part, and the insertion part is suitable for being inserted into the opening.

7. The aircraft engine detection apparatus of claim 6, wherein, The end of the insertion part away from the measuring part is provided with a chamfer.

8. The aircraft engine detection apparatus of claim 4, wherein, The length of the measuring part is 1-3 times of the inner diameter of the channel.

9. The aircraft engine detection apparatus of claim 1, wherein, The fitting surface and the measuring surface are parallel to each other.

10. The aircraft engine detection apparatus of claim 1, wherein, The measuring surface is provided with a plurality of marks, and the marks are used for showing the position where the center of the measuring surface is located.

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