Aerospace engine micro-armor thermocouple impact buffering device

Abstract

The utility model belongs to aero -engine technical field, and disclose a kind of aero -engine micro armor thermocouple impact resistance buffer device, including two bottom plate, the top of bottom plate is equipped with upper movable plate, the upper side of upper movable plate is equipped with engine body, and the both sides of engine body are symmetrically fixed with support rod, the lower surface of support rod is fixedly connected with upper movable plate, the lower end of upper movable plate is fixedly equipped with four support blocks, the opposite face one end of support block corresponding to two positions is rotatably equipped with sleeve, the inner end of sleeve is movably inserted with telescopic column, the opposite face one end of telescopic column corresponding to two positions is rotatably equipped with connecting block. By the above scheme, by multiple spring and telescopic structure cooperation, impact vibration is effectively buffered to protect equipment;The ring is connected with upper movable plate by bolt, easy to disassemble and maintain, overall structure is reasonable, guarantee buffering effect and reliability.

Description

Technical Field

[0001] This utility model belongs to the field of aero-engine technology, specifically a micro-armored thermocouple shock-resistant buffer device for aero-engines. Background Technology

[0002] An aircraft engine is a highly complex and precise thermodynamic machine. As the heart of an aircraft, it not only powers the aircraft's flight but also serves as a vital driving force for the development of the aviation industry. It needs to possess powerful thrust capable of propelling an aircraft that is more than ten times its own weight; its internal rotation speed is extremely high, reaching up to 40,000 revolutions per minute.

[0003] However, the following problems were found in the implementation of the relevant technologies:

[0004] First, existing technologies for aero-engine thermocouples mostly employ a single rigid connection or a simple spring structure, lacking a coordinated design of multiple springs and telescopic structures. For example, semi-rigid cables have poor shock resistance and are prone to breakage under high vibration conditions due to excessive tensile force; the solder joints rely solely on sintering for fixation, making them prone to detachment under vibration and tension, and lack a graded buffering mechanism of sleeves and telescopic columns, failing to effectively disperse impact energy. This results in vibration being directly transmitted to the thermocouple components, causing failures such as lead wire breakage and thermocouple wire deformation.

[0005] Furthermore, traditional thermocouple protection components (such as retaining rings and slip rings) are mostly fixed by flanges, clamps, or welding, requiring cumbersome operations for disassembly and assembly. The connection between the slip ring and the thermocouple even requires the removal of multiple nuts and connecting plates, which seriously affects maintenance efficiency. At the same time, the loose fit between components (such as the gap fit between the thermocouple and the housing) can easily cause relative shaking in a vibration environment, exacerbating the risks of glass breakage, solder fatigue, etc., making it difficult to guarantee the overall structural reliability. Utility Model Content

[0006] To address the problems mentioned in the background section, this invention provides a micro-armored thermocouple shock-resistant buffer device for aero-engines, which boasts advantages such as strong shock resistance, convenient maintenance, and reliable structure. This invention solves the problem of component damage caused by impact vibration in existing technologies through the coordinated design of multiple springs and telescopic structures, along with auxiliary telescopic rods and anti-slip pads. Furthermore, the bolted connection between the retaining ring and the upper movable plate, along with the overall tight fit, overcomes the problems of cumbersome disassembly and assembly and insufficient reliability in traditional devices.

[0007] To achieve the above objectives, this utility model provides the following technical solution: a micro-armored thermocouple shock-resistant buffer device for an aero-engine, comprising two base plates, an upper movable plate above the base plates, an engine body on the upper side of the upper movable plate, and support rods symmetrically fixed on both sides of the engine body. The lower surface of the support rods is fixedly connected to the upper movable plate. Four support blocks are fixedly provided at the lower end of the upper movable plate. A sleeve is rotatably provided at one end of the opposite face of two corresponding support blocks. A telescopic column is movably inserted at the inner end of the sleeve. A connecting block is rotatably provided at one end of the opposite face of two corresponding telescopic columns. A lower column is fixedly provided at the lower end of the connecting block and is connected through the base plate. A first spring is fixedly connected to the upper end of the connecting block and the upper end of the base plate. A contact column is fixedly provided at the upper end of the connecting block, and the upper end of the contact column is movably fitted with the lower end of the upper movable plate.

[0008] Preferably, the upper side of the engine body is provided with a guard ring, and the lower surface of the guard ring is symmetrically fixed with side plates. The lower end of the side plate is fixed with a connecting plate, and the connecting plate is connected to the upper movable plate by bolts.

[0009] Preferably, auxiliary telescopic rods are fixedly provided on both sides of the upper end of the base plate, and the upper ends of the two auxiliary telescopic rods are fixedly connected to the upper movable plate.

[0010] Preferably, the upper end of the base plate is provided with a column groove for use with the lower column.

[0011] Preferably, one end of the telescopic column passes through the sleeve and is fixedly connected to a disc, and a second spring is fixedly connected between the disc and the sleeve.

[0012] Preferably, the four support blocks are arranged in a rectangular shape, and the two connecting blocks are arranged in a mirror-symmetric shape.

[0013] Preferably, anti-slip pads are symmetrically fixed on the lower surface of the base plate.

[0014] Preferably, the lower surface of the connecting plate is in contact with the upper surface of the upper movable plate.

[0015] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0016] 1. This utility model, through the cooperation of multiple sets of springs (first spring, second spring) and telescopic structure (sleeve, telescopic column), can effectively absorb and buffer the impact and vibration generated during engine operation, greatly reduce the impact force on the engine body and related components, and protect the normal operation of the equipment.

[0017] 2. The retaining ring of this utility model is connected to the upper movable plate by bolts, which facilitates installation and disassembly and is beneficial for the maintenance and repair of the engine body. The overall structure is reasonably designed, and the components fit together tightly, achieving a good buffering effect while ensuring the reliability and durability of the device. Attached Figure Description

[0018] Figure 1 This is a schematic diagram of the overall structure of this utility model;

[0019] Figure 2 This is an exploded view of the relevant structure of the retaining ring of this utility model;

[0020] Figure 3 This is an exploded view of the structure between the base plate and the upper movable plate of this utility model;

[0021] Figure 4 This is a schematic diagram of the relevant structure of the second spring of this utility model.

[0022] In the diagram: 1. Base plate; 11. Anti-slip mat; 2. Upper movable plate; 21. Support block; 22. Sleeve; 23. Telescopic column; 24. Connecting block; 25. Lower column; 26. First spring; 27. Contact column; 28. Disc; 29. ​​Second spring; 210. Column groove; 211. Auxiliary telescopic rod; 3. Engine body; 31. Support rod; 4. Protective ring; 41. Side plate; 42. Connecting plate. Detailed Implementation

[0023] 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.

[0024] like Figures 1 to 4As shown, this utility model provides a micro-armored thermocouple shock-resistant buffer device for aero-engines, including two base plates 1. An upper movable plate 2 is provided above the base plate 1. An engine body 3 is provided on the upper side of the upper movable plate 2, and support rods 31 are symmetrically fixed on both sides of the engine body 3. The lower surface of the support rods 31 is fixedly connected to the upper movable plate 2. Four support blocks 21 are fixedly provided at the lower end of the upper movable plate 2. A sleeve 22 is rotatably provided at one end of the opposite face of two corresponding support blocks 21. The inner end of the sleeve 22 is movably inserted into... A telescopic column 23 is provided. Two telescopic columns 23 in corresponding positions have a connecting block 24 that rotates together at one end of their opposite faces. Four support blocks 21 are arranged in a rectangular shape, and two connecting blocks 24 are arranged in a mirror image. A lower column 25 is fixedly provided at the lower end of the connecting block 24, and the lower column 25 is connected through the base plate 1. A first spring 26 is fixedly connected to the upper end of the base plate 1 at the lower end of the connecting block 24. A contact column 27 is fixedly provided at the upper end of the connecting block 24, and the upper end of the contact column 27 is movably attached to the lower end of the upper movable plate 2. When the engine body 3 generates impact or vibration during operation, the impact force is transmitted to the upper movable plate 2 through the support rod 31, causing the upper movable plate 2 to have a tendency to move. The movement of the upper movable plate 2 drives the four rectangularly distributed support blocks 21 to move synchronously. The support blocks 21 drive the sleeve 22 to move, and the telescopic column 23 inside the sleeve 22 moves relative to the sleeve 22. At this time, the disc 28 at one end of the telescopic column 23 will compress or stretch the second spring 29. The second spring 29 deforms to buffer part of the impact force. The two mirror-distributed connecting blocks 24 move under the drive of the telescopic column 23. The lower column 25 at the lower end of the connecting block 24 moves up and down along the column groove 210 on the base plate 1. At the same time, the first spring 26 between the lower end of the connecting block 24 and the upper end of the base plate 1 is stretched or compressed to further buffer the impact force. The contact column 27 at the upper end of the connecting block 24 keeps in contact with the lower end of the upper movable plate 2, playing an auxiliary support and force transmission role in the buffering process.

[0025] Specifically, a protective ring 4 is provided on the upper side of the engine body 3, and a side plate 41 is symmetrically fixed on the lower surface of the protective ring 4. A connecting plate 42 is fixed at the lower end of the side plate 41, and the connecting plate 42 is connected to the upper movable plate 2 by bolts. The lower surface of the connecting plate 42 is in contact with the upper surface of the upper movable plate 2. The protective ring 4 on the upper side of the engine body 3 is connected to the upper movable plate 2 through the side plate 41 and the connecting plate 42 (the lower surface of the connecting plate 42 is in contact with the upper surface of the upper movable plate 2 and is fixed by bolts), which provides a certain degree of protection for the engine body 3 and reduces the direct impact of external factors on it.

[0026] Furthermore, auxiliary telescopic rods 211 are fixedly provided on both sides of the upper end of the base plate 1, and the upper ends of the two auxiliary telescopic rods 211 are fixedly connected to the upper movable plate 2. The auxiliary telescopic rods 211 on both sides of the upper end of the base plate 1 extend and retract with the movement of the upper movable plate 2, which helps to maintain the stability of the upper movable plate 2 and prevent it from shifting.

[0027] Furthermore, the upper end of the base plate 1 is provided with a column groove 210 for use with the lower column 25, and the lower column 25 at the lower end of the connecting block 24 moves up and down along the column groove 210 on the base plate 1.

[0028] It is worth noting that one end of the telescopic column 23 passes through the sleeve 22 and is fixedly connected to a disc 28. A second spring 29 is fixedly connected between the disc 28 and the sleeve 22. The telescopic column 23 inside the sleeve 22 moves in a telescopic motion relative to the sleeve 22. At this time, the disc 28 at one end of the telescopic column 23 will compress or stretch the second spring 29, and the second spring 29 will deform to buffer part of the impact force.

[0029] It is worth mentioning that anti-slip pads 11 are symmetrically fixed on the lower surface of the base plate 1. The anti-slip pads 11 on the lower surface of the base plate 1 increase the friction between the device and the mounting surface, preventing the device from sliding as a whole.

[0030] The engine body 3 is existing technology and will not be described in detail. Additionally, this utility model also includes a power supply, controller, and switches, which are not the main technical points of this patent and will not be described in detail. The "front, rear, left, and right" views of this device are... Figure 1 The direction shown in the diagram is the reference.

[0031] Working principle: When the engine body 3 generates impact or vibration during operation, the impact force is transmitted to the upper movable plate 2 through the support rod 31, causing the upper movable plate 2 to move. The movement of the upper movable plate 2 drives the four rectangularly distributed support blocks 21 to move synchronously. The support blocks 21 drive the sleeve 22 to move, and the telescopic column 23 inside the sleeve 22 moves relative to the sleeve 22. At this time, the disc 28 at one end of the telescopic column 23 will compress or stretch the second spring 29, and the second spring 29 will deform to buffer part of the impact force.

[0032] Two mirror-distributed connecting blocks 24 move under the action of the telescopic column 23. The lower column 25 at the lower end of the connecting block 24 moves up and down along the column groove 210 on the base plate 1. At the same time, the first spring 26 between the lower end of the connecting block 24 and the upper end of the base plate 1 is stretched or compressed to further buffer the impact force. The contact column 27 at the upper end of the connecting block 24 remains in contact with the lower end of the upper movable plate 2, playing a role in auxiliary support and force transmission during the buffering process.

[0033] The auxiliary telescopic rods 211 on both sides of the upper end of the base plate 1 extend and retract with the movement of the upper movable plate 2, helping to maintain the stability of the upper movable plate 2 and preventing it from shifting. The anti-slip pads 11 on the lower surface of the base plate 1 increase the friction between the device and the mounting surface, preventing the device from sliding as a whole. The guard ring 4 on the upper side of the engine body 3 is connected to the upper movable plate 2 through the side plate 41 and the connecting plate 42 (the lower surface of the connecting plate 42 is in contact with the upper surface of the upper movable plate 2 and is fixed by bolts), which provides a certain degree of protection for the engine body 3 and reduces the direct impact of external factors.

[0034] 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.

[0035] 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 micro-armored thermocouple shock-resistant buffer device for aero-engines, comprising two base plates (1), characterized in that: An upper movable plate (2) is provided above the base plate (1). An engine body (3) is provided on the upper side of the upper movable plate (2). Support rods (31) are symmetrically fixed on both sides of the engine body (3). The lower surface of the support rods (31) is fixedly connected to the upper movable plate (2). Four support blocks (21) are fixedly provided at the lower end of the upper movable plate (2). A sleeve (22) is rotatably provided at one end of the opposite face of two corresponding support blocks (21). An extension is movably inserted into the inner end of the sleeve (22). The telescopic column (23) has a connecting block (24) at one end of its opposite face, which rotates together. The lower end of the connecting block (24) is fixedly provided with a lower column (25), and the lower column (25) is connected through the bottom plate (1). The lower end of the connecting block (24) is fixedly connected to the upper end of the bottom plate (1) with a first spring (26). The upper end of the connecting block (24) is fixedly provided with a contact column (27), and the upper end of the contact column (27) is movably attached to the lower end of the upper movable plate (2).

2. The impact-resistant buffer device for aero-engine micro-armored thermocouples according to claim 1, characterized in that: The engine body (3) has a protective ring (4) on its upper side, and a side plate (41) is symmetrically fixed on the lower surface of the protective ring (4). A connecting plate (42) is fixed at the lower end of the side plate (41), and the connecting plate (42) is connected to the upper movable plate (2) by bolts.

3. The impact-resistant buffer device for aero-engine micro-armored thermocouples according to claim 1, characterized in that: The upper sides of the base plate (1) are fixedly provided with auxiliary telescopic rods (211), and the upper ends of the two auxiliary telescopic rods (211) are fixedly connected to the upper movable plate (2).

4. The impact-resistant buffer device for aero-engine micro-armored thermocouples according to claim 1, characterized in that: The upper end of the base plate (1) is provided with a column groove (210) for use with the lower column (25).

5. The impact-resistant buffer device for aero-engine micro-armored thermocouples according to claim 1, characterized in that: One end of the telescopic column (23) passes through the sleeve (22) and is fixedly connected to a disc (28). A second spring (29) is fixedly connected between the disc (28) and the sleeve (22).

6. The impact-resistant buffer device for aero-engine micro-armored thermocouples according to claim 1, characterized in that: The four support blocks (21) are arranged in a rectangular shape, and the two connecting blocks (24) are arranged in a mirror shape.

7. The impact-resistant buffer device for aero-engine micro-armored thermocouples according to claim 1, characterized in that: The lower surface of the base plate (1) is symmetrically fixed with anti-slip pads (11).

8. The impact-resistant buffer device for aero-engine micro-armored thermocouples according to claim 2, characterized in that: The lower surface of the connecting plate (42) is in contact with the upper surface of the upper movable plate (2).

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