Dynamic impact detection device, system and method for blade disc of aero-engine

Abstract

The invention discloses a dynamic impact detection device, system and method for a blade disc of an aero-engine. The detection device comprises a supporting assembly; the at least two groups of testing assemblies are arranged on the supporting assembly, and each testing assembly comprises a moving block, a housing fixed on the moving block and a rotation driving part which is arranged in the housing and is used for fixing and driving a leaf disc to be detected to rotate; the cover shell comprises a fixed part, a transition section and a straight barrel section which are arranged in sequence; the fixed part is used for being fixed on the moving block; the inner diameter of the transition section is gradually increased from one end connected with the fixed part to one end connected with the straight barrel section. By simulating the motion state of the whole bladed disc when the engine runs and realizing the impact test of the whole bladed disc, the accuracy of analyzing the crashworthiness of the bladed disc is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of engine blade disc impact detection, and in particular relates to an aero-engine blade disc dynamic impact detection device system and method. Background Art

[0002] When conventional parts are produced, impact tests are often performed on the parts to detect their impact resistance.

[0003] In the aerospace field, bird strikes may occur during takeoff or landing of an aircraft. When a bird strikes the blade disk on the engine, it often causes catastrophic damage to the aircraft. Therefore, it is very necessary to perform impact detection on the blade disk in the engine.

[0004] In the existing impact test of the engine blade disk, a single blade on the blade disk is impact tested to judge the impact performance of the entire blade disk. However, the existing detection method has the following problems: since the blade disk is composed of multiple blades, only a single blade is impact tested, and the accuracy of the overall impact resistance test of the blade disk is low. Summary of the invention

[0005] In order to solve the problem of low detection accuracy caused by the existing use of impact detection of a single blade disk to judge the impact performance of the entire blade disk, the present invention proposes an aircraft engine blade disk dynamic impact detection device, system and method, which can effectively improve the detection accuracy.

[0006] The objective of the present invention is achieved through the following technical solutions:

[0007] The first aspect of the present invention discloses a dynamic impact detection device for an aero-engine blade disk, comprising:

[0008] a support assembly;

[0009] At least two groups of test components are arranged on the support component, and the test component includes a moving block, a cover shell fixed on the moving block, and a rotating drive member arranged in the cover shell for fixing and driving the rotation of the blade disk to be tested, and the cover shell includes a fixing part, a gradient section and a straight tube section which are arranged in sequence and are used to be fixed on the moving block, and the inner diameter of the gradient section gradually increases from one end connected to the fixing part to the other end connected to the straight tube section.

[0010] The second aspect of the present invention discloses an aircraft engine blade disk dynamic impact detection system, comprising:

[0011] An aircraft engine blade disk dynamic impact detection device as described in the first aspect;

[0012] a birdshot launching assembly, the birdshot launching assembly being used to launch birdshot into the housing;

[0013] A mobile driver, the mobile driver is used to drive all test components to move synchronously toward or away from the birdshot launch component;

[0014] A video acquisition device, the video acquisition device is used to collect video data of a process in which the birdshot launched by the birdshot launching assembly hits the blade disk to be detected;

[0015] An analysis instrument is signal-connected to the video acquisition device to perform a collision resistance analysis on the blade disk to be inspected according to the video data output by the video acquisition device.

[0016] The third aspect of the present invention discloses a method for dynamic impact detection of an aero-engine blade disk, the method adopts the aero-engine blade disk dynamic impact detection system described in the second aspect, and the detection method comprises the following steps: at least two blade disks to be detected with the same structure are respectively mounted on at least two groups of test assemblies;

[0017] Starting the rotating drive member and the moving drive member to control the blade disc to rotate and move toward one end of the birdshot launching assembly at the same time, and each rotating drive member has a different rotation speed;

[0018] The birdshot launching assembly is started to launch the birdshot into the housing, and at the same time, a video acquisition device is started to capture the process of the birdshot launched by the birdshot launching assembly hitting the blade disk to be inspected;

[0019] The analyzing instrument performs collision resistance analysis on the blade disk to be inspected according to the video data output by the video acquisition device.

[0020] The beneficial effects of the present invention are:

[0021] The present invention improves the accuracy of the collision resistance analysis of the blade disk by simulating the motion state of the entire blade disk when the engine is running and realizing the collision test of the entire blade disk. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0023] Figure 1 This is a schematic diagram of the structure of the dynamic impact detection device for the aero-engine blade disk of the present invention.

[0024] Figure 2 It is a side view of the dynamic impact detection device of the aircraft engine blade disk of the present invention;

[0025] Figure 3 for Figure 2 AA section view;

[0026] Figure 4 The figure is a schematic diagram of the installation of the aero-engine blade disk dynamic impact detection system of the present invention. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0028] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0029] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features of the embodiments may be combined with each other.

[0030] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0031] In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inside", "outside", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, or the positions or positional relationships in which the product of the invention is usually placed when in use, or the positions or positional relationships commonly understood by those skilled in the art, which 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 orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used to distinguish the description, and cannot be understood as indicating or implying relative importance.

[0032] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it 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 elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] The present invention discloses a dynamic impact detection device, system and method for an aero-engine blade disk. Figures 1 to 4 As shown, the engine blade disk dynamic impact detection system includes an aircraft engine blade disk dynamic impact detection device, a birdshot launch assembly 6, a mobile drive component 4, a video acquisition device 5 and an analysis instrument.

[0034] The dynamic impact detection device for the aero-engine blade disk includes a support assembly and a test assembly. There are at least two test assemblies, both of which are arranged on the support assembly. The test assembly includes a moving block 21, a cover 22 fixed on the moving block 21, and a rotating drive 23 arranged in the cover 22 for fixing and driving the blade disk to be detected to rotate. The cover includes a fixing portion 221, a gradient section 222, and a straight section 223, which are arranged in sequence and are used to be fixed on the moving block. The inner diameter of the gradient section gradually increases from one end connected to the fixing portion to the other end connected to the straight section.

[0035] The birdshot launching assembly is used to launch birdshot into the cover; the mobile driving component is used to drive all test components to move synchronously toward or away from the birdshot launching assembly so as to cause relative collision with the birdshot when moving toward the birdshot launching assembly; the video acquisition device is used to collect video data of the process of the birdshot launched by the birdshot launching assembly hitting the blade disk to be tested; the analysis instrument is connected to the video acquisition device 5 by signal so as to perform collision resistance analysis on the blade disk to be tested according to the video data output by the video acquisition device 5.

[0036] By adopting the above device, the blade disk to be tested is fixed as a whole on the rotating drive member, the blade disk is driven by the rotating drive member, the cover and the mobile drive member to simulate the working state of the blade disk, and the bird bullet launching assembly launches bird bullets at the blade disk in the cover to simulate the bird hitting the blade disk in the working state of the blade disk. The impact conditions of the blade disk at different rotation speeds in all test components are collected by the video acquisition device, so that the analysis instrument can perform the collision resistance analysis of the blade disk according to the video data, thereby improving the accuracy of the collision resistance analysis of the blade disk.

[0037] Based on the above structure, in order to improve the stability of the movement of the test assembly, the support assembly includes a vertical plate 11 and a partition plate 12 arranged on the vertical plate 11, and the partition plate 12 is arranged between two adjacent test assemblies. The partition plate is arranged to effectively support the moving block 21 and improve the movement stability.

[0038] The mobile driving member 4 and the test assembly can be driven one to one. Among them, the mobile driving member 4 is an existing conventional structure. The illustration in this scheme is only an example, and its specific structure is not shown. On the basis of the above structure, in order to reduce the number of mobile driving members 4, reduce the volume of the device, save manufacturing costs, and improve the synchronization of the movement of multiple groups of test assemblies, a hole structure 121 is provided on the isolation plate 12 along the moving direction of the test assembly, and a connecting rod 211 for connecting two adjacent moving blocks 21 is provided in the hole structure 121. One or two hole structures 121 can be provided. In order to improve the stability of movement control, two are preferably provided. A mobile driving member 4 is used to drive multiple test assemblies to move synchronously with the corresponding birdshot, so as to facilitate the synchronous test of multiple groups of control groups.

[0039] On the basis of using the isolation plate 12 to support the test assembly, in order to further reduce the friction between the two and facilitate movement control, a roller structure 212 is provided at the bottom of the moving block 21. The roller structure 212 is slidably connected to the isolation plate 12 to reduce movement friction and facilitate movement control.

[0040] The video acquisition device 5 in the system can be a high-speed camera or a camera with image stability and anti-interference ability that meet the video acquisition requirements. Using the same video acquisition device 5 to record the status of multiple test pieces can achieve the recording of test data at the same time point and the same environmental state.

[0041] The rotation driving member 23 may be a driving motor.

[0042] In order to further improve the moving stability of the test assembly, a slide groove 111 is provided on the vertical plate 11 along the moving direction of the test assembly, and a sliding member 213 is provided on the moving block 21 to be clamped in the slide groove 111. Based on the above system, its installation diagram is as follows: Figure 4As shown, the entire detection system is installed in an open environment, wherein the installation position of the video acquisition device 5 is preferably such that it can simultaneously acquire the video data of all test components, so as to synchronously analyze them in one picture, thereby facilitating the synchronous comparative analysis of the analysis instrument, facilitating the analysis of the states generated at multiple different moments of the control group, and being able to timely observe and analyze different states at the same moment. Multiple test components are placed in a vertical direction to save floor space. The dynamic impact detection method for the aero-engine blade disk includes steps S11 to S14. It should be noted that the step identification in this scheme is only for the convenience of explaining the method, and does not constitute a limitation on the sequence. The sequence of the steps is based on the language description and the sequence of the signals.

[0043] Step S11, respectively installing at least two blade disks to be tested with the same structure on at least two groups of test components.

[0044] Reference Figure 1 The blade disk includes a bearing 31, a limit plate 33 and a blade 32 disposed between the bearing 31 and the limit plate 33. The blade disk can be installed by providing a plug-in portion on the bearing and plugging and fixing the plug-in portion on the output shaft of the rotating drive member 23.

[0045] In order to protect the rotating driving member 23, a blocking piece 34 may be installed on the plug-in portion, and the plug-in portion is rotatably connected to the blocking piece via a rotating ring, and the plug-in portion never separates from the blocking piece.

[0046] The blade disk and the test assembly are connected in a detachable manner by plugging, which facilitates the reuse of the test assembly.

[0047] Step S12, start the rotating drive member 23 and the moving drive member 4, control the blade disk to rotate and move toward one end of the birdshot launching assembly at the same time, and the rotation speed of each rotating drive member 23 is different to determine the influence of the rotation speed on the crashworthiness.

[0048] Step S13, start the birdshot launching assembly to launch the birdshot into the housing, so that the birdshot and the blade disk move relative to each other, and simultaneously start the video acquisition device 5 to capture the process of the birdshot launched by the birdshot launching assembly hitting the blade disk to be detected.

[0049] Step S14: the analyzing instrument performs a crashworthiness analysis on the blade disk to be tested according to the video data output by the video acquisition device 5. The analyzing instrument performs a crashworthiness analysis according to the video data of the blade disks in the multiple test assemblies when and after the impact.

[0050] By adopting the above method, the detection part is set as the entire blade disk, and the detection part is in a dynamic state, simulating the state of the engine controlling the rotation of the entire blade disk during the landing or take-off of the aircraft, reducing the existing impact test. When simulating the movement state of the entire blade disk when the engine is running, the rotation speeds of multiple detection parts are different during the detection, which is convenient for the synchronous test of multiple control groups.

[0051] Using the above method, after multiple tests and comparison with the existing technology, it can be concluded that in the dynamic impact test of aviation parts, the collision resistance of the blades obtained by testing a single blade and a whole blade disk composed of multiple blades is different.

[0052] The above method solves the problem in the prior art that only a single fixed blade in an integral blade disk is tested, resulting in one-sided blade disk detection. It reduces the error between test impact and real bird strike, improves the accuracy of impact detection, and is beneficial to the development of integral blade disks in aircraft engines.

[0053] Those skilled in the art will appreciate that the embodiments described herein are intended to help readers understand the principles of the present invention, and should be understood that the protection scope of the present invention is not limited to such specific statements and embodiments. Those skilled in the art can make various other specific variations and combinations that do not deviate from the essence of the present invention based on the technical revelations disclosed by the present invention, and these variations and combinations are still within the protection scope of the present invention.

Claims

1. An aircraft engine blade disk dynamic impact detection device, characterized in that: include: a support assembly; At least two groups of test assemblies are arranged on the support assembly, the test assemblies comprising a moving block (21), a cover (22) fixed on the moving block (21), and a rotating drive member arranged in the cover (22) for fixing and driving the rotation of a blade disk to be tested, the cover comprising a fixing portion, a gradient section and a straight tube section arranged in sequence for fixing on the moving block, the inner diameter of the gradient section gradually increasing from an end connected to the fixing portion to an end connected to the straight tube section.

2. The aircraft engine blade dynamic impact detection device according to claim 1, characterized in that: The support assembly comprises a vertical plate (11) and an isolation plate (12) arranged on the vertical plate (11), and the isolation plate (12) is arranged between two adjacent test assemblies.

3. The aircraft engine blade dynamic impact detection device according to claim 2, characterized in that: A hole structure (121) is provided on the isolation plate (12) along the moving direction of the test assembly, and a connecting rod (211) for connecting two adjacent moving blocks (21) is provided in the hole structure (121).

4. The aircraft engine blade dynamic impact detection device according to claim 3, characterized in that: There are two hole structures (121).

5. The aircraft engine blade dynamic impact detection device according to claim 2, characterized in that: A roller structure (212) is provided at the bottom of the moving block (21).

6. The aircraft engine blade dynamic impact detection device according to claim 2, characterized in that: A slide groove (111) is provided on the vertical plate (11) along the moving direction of the test assembly, and a sliding member (213) is provided on the moving block (21) and is clamped in the slide groove (111).

7. An aircraft engine blade dynamic impact detection system, characterized in that: include: An aircraft engine blade disk dynamic impact detection device as described in any one of claims 1 to 6; a birdshot launching assembly, the birdshot launching assembly being used to launch birdshot into the housing; A mobile driving member (4), the mobile driving member being used to drive all the test components to move synchronously towards or away from the birdshot launching component; A video acquisition device (5), the video acquisition device is used to collect video data of the process of the birdshot launched by the birdshot launching assembly hitting the blade disk to be detected; An analysis instrument is signal-connected to the video acquisition device (5) so as to perform a collision resistance analysis on the blade disk to be inspected based on the video data output by the video acquisition device (5).

8. A method for dynamic impact detection of an aircraft engine blade disk, characterized in that: The method adopts an aircraft engine blade disk dynamic impact detection system as claimed in claim 7, and the detection method comprises the following steps: at least two blade disks to be detected with the same structure are respectively mounted on at least two groups of test components; Starting the rotating drive member and the moving drive member (4) to control the blade disc to rotate and move toward one end of the birdshot launching assembly at the same time, and each rotating drive member has a different rotation speed; The birdshot launching assembly is started to launch the birdshot into the housing, and at the same time, a video acquisition device (5) is started to capture the process of the birdshot launched by the birdshot launching assembly hitting the blade disk to be detected; The analysis instrument performs collision resistance analysis on the blade disk to be tested based on the video data output by the video acquisition device (5).

9. The method for dynamic impact detection of an aero-engine blade disk according to claim 8, characterized in that: Before respectively installing at least two blade disks to be tested with the same structure on at least two test assemblies, the method further includes: A blocking piece is installed on the plug-in portion of the bearing of the blade disk to be detected, and the plug-in portion is rotatably connected with the blocking piece through a rotating ring.

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