Miniature turbojet engine test fixing device

Abstract

The utility model discloses a miniature turbojet engine test fixing device, which relates to the field of turbojet engine test and comprises a first supporting mechanism, a second supporting mechanism and a third supporting mechanism. The hoop mechanism is mounted on the first supporting mechanism and used for clamping the turbojet engine on the first supporting mechanism; the first supporting mechanism is provided with a first containing groove used for containing the turbojet engine, one end of the hoop mechanism is hinged to one side of the first containing groove, and the other end of the hoop mechanism is movably connected with the other side of the first containing groove. A first locking part is arranged at the movable connecting end of the hoop mechanism and the first containing groove, and a second locking part is arranged on the movable connecting side of the first containing groove and the hoop mechanism. According to the utility model, the first supporting mechanism is provided with the first placement groove, and the first placement groove is matched with the hoop mechanism to stably lock the turbojet engine on the first supporting mechanism, so that the purpose of stably fixing the turbojet engine in testing and verification processes is achieved.

Description

Technical Field

[0001] The utility model relates to the field of turbojet engine testing, in particular to a micro turbojet engine testing fixture. Background Art

[0002] A turbojet engine is an aircraft engine that generates thrust by using air that enters the engine, undergoes compression, combustion, and expansion to generate a high-speed airflow that is discharged from the tail nozzle. Its working principle follows the principle of work done by a heat engine: input energy at high pressure and release energy at low pressure. The basic structure of a turbojet engine includes an air inlet, a compressor, a combustion chamber, a turbine, and a tail nozzle. During flight, air first enters the engine through the air inlet, and is then compressed by the compressor to increase pressure and temperature. The compressed air enters the combustion chamber, where it mixes with the fuel and burns to generate high-temperature and high-pressure gas. These gases then flow through the turbine, which converts part of the energy into mechanical energy to drive the compressor. Finally, the high-temperature gas is discharged through the tail nozzle to generate thrust.

[0003] As a strategic emerging industry, the general aviation industry is an important part of the low-altitude economy. Micro turbojet engines, as power devices for micro-UAVs, cruise missiles and other types of micro-aircraft, have the advantages of light weight, high power and high energy density, and have broad application prospects in the military and civilian markets.

[0004] During the production and assembly process, turbojet engines need to go through multiple testing and verification processes, such as compressor testing, electronic control circuit testing, etc. A simple, low-cost and easy-to-operate device is needed to fix the turbojet engine horizontally, so that the staff can carry out a series of testing and verification work. Utility Model Content

[0005] The purpose of the utility model is to provide a micro-turbojet engine test fixture, in which a first mounting groove is arranged on a first supporting mechanism, and cooperates with a clamp mechanism to stably lock the turbojet engine on the first supporting mechanism, so as to solve the problem of difficulty in fixing in the turbojet engine test and verification process in the prior art.

[0006] The utility model embodiment is implemented by the following technical scheme: The utility model embodiment provides a micro turbojet engine test fixture, comprising:

[0007] A first supporting mechanism, used for supporting the turbojet engine;

[0008] A clamp mechanism, mounted on the first supporting mechanism, and used for clamping the turbojet engine on the first supporting mechanism;

[0009] The first supporting mechanism is provided with a first placement groove for placing the turbojet engine, one end of the clamp mechanism is hinged to one side of the first placement groove, and the other end is movably connected to the other side of the first placement groove;

[0010] A first locking component is provided at the movable connection end between the clamp mechanism and the first placement groove, and a second locking component is provided at the movable connection side between the first placement groove and the clamp mechanism. The first locking component and the second locking component can be locked with each other.

[0011] Preferably, the fixing device further comprises a second supporting mechanism, and the second supporting mechanism is provided with a second placement groove for placing the turbojet engine;

[0012] When one side of the turbojet engine is clamped in the first mounting groove by the clamping mechanism, the second mounting groove can support the other side of the turbojet engine.

[0013] Preferably, a limited position locking mechanism is provided on the first mounting groove.

[0014] Preferably, a limited position locking mechanism is provided on the second mounting groove.

[0015] Preferably, the fixing device further comprises a mounting plate, one end of the mounting plate is connected to the first supporting mechanism, and the other end of the mounting plate is connected to the second supporting mechanism, and the first supporting mechanism and the second supporting mechanism are arranged in parallel.

[0016] Preferably, the projection of the first mounting groove on the second supporting mechanism coincides with the second mounting groove.

[0017] Preferably, a plurality of screw holes are provided on the mounting plate.

[0018] Preferably, both the first supporting mechanism and the second supporting mechanism are plate-shaped structures, and there is a gap between the first supporting mechanism and the second supporting mechanism.

[0019] Preferably, the first supporting mechanism is arranged perpendicular to the mounting plate.

[0020] Preferably, the first locking component is a through groove, and the second locking component is a screw groove, and the through groove and the screw groove can be locked by bolts.

[0021] Compared with the prior art, the embodiments of the present invention have the following advantages and beneficial effects:

[0022] 1. A micro-turbojet engine test fixture provided by an embodiment of the utility model is provided, wherein a first supporting mechanism is provided, and a first mounting groove is provided on the first supporting mechanism, so that the turbojet engine in the test or verification process can be placed in the first mounting groove, so that the first supporting mechanism can stably support the turbojet engine, and a clamping mechanism is provided on the outside of the first mounting groove, one end of the clamping mechanism is hinged to one side of the first mounting groove, and the other end is movably connected to the other side of the first mounting groove, so that the clamping mechanism can be rotated with the hinged end as a base point, thereby controlling the opening and closing and the opening and closing size of the movable connection end, when the turbojet engine needs to be installed, the clamping mechanism is rotated to separate the movable connection end from the first supporting mechanism, and after the turbojet engine is placed in the first mounting groove, the clamping mechanism is rotated to connect its movable connection end to the first supporting mechanism, and then the clamping mechanism locks the turbojet engine on the first supporting mechanism through the cooperation of the first locking component and the second locking component, so as to achieve the purpose of stably supporting the turbojet engine, and the structure is simple and easy to operate.

[0023] 2. The embodiment of the utility model also provides a second supporting mechanism, and a second mounting groove is provided on the second supporting mechanism. Through the cooperation of the first supporting mechanism and the second supporting mechanism, the turbojet engine is jointly supported. The supporting surface and supporting area of ​​the turbojet engine improve the supporting stability of the entire fixing device.

[0024] 3. Setting a mounting plate can connect the first supporting mechanism and the second supporting mechanism to improve the stability of the entire device. The key is that the mounting plate is used for installation, which can improve the use of the entire device. In the actual production process, the first supporting mechanism, the second supporting mechanism and the mounting plate can be pre-installed as one or stably connected to avoid temporary installation at the operation site and improve work efficiency.

[0025] In general, an embodiment of the utility model provides a micro-turbojet engine test fixture, in which a first mounting groove is arranged on a first support mechanism, and cooperates with a clamp mechanism to stably lock the turbojet engine on the first support mechanism, so as to achieve the purpose of stably fixing the turbojet engine during the testing and verification process. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the utility model and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without paying creative work.

[0027] Figure 1 A schematic diagram of the structure of a fixing device provided in an embodiment of the utility model;

[0028] Figure 2 A cross-sectional view of a first supporting mechanism provided in an embodiment of the utility model;

[0029] Figure 3 A schematic diagram of the structure of the mounting plate provided in the embodiment of the utility model;

[0030] Figure 4 This is a side structural diagram of the clamp mechanism provided in an embodiment of the utility model.

[0031] Marks and corresponding parts names in the attached drawings:

[0032] 1-first supporting mechanism, 2-hooping mechanism, 3-first mounting groove, 4-first locking component, 5-second locking component, 6-second supporting mechanism, 7-second mounting groove, 8-limiting engaging mechanism, 9-mounting plate, 10-screw hole, 11-gap, 12-bolt. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solution and advantages of the embodiment of the utility model clearer, the technical solution in the embodiment of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiment of the utility model. Obviously, the described embodiment is a part of the embodiment of the utility model, not all of the embodiments. The components of the embodiment of the utility model described and shown in the drawings here can be arranged and designed in various different configurations.

[0034] 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 present invention to be protected, 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.

[0035] 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.

[0036] In the description of the present utility model, it should be noted that the terms "first", "second", "third", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0037] Example

[0038] like Figure 1 As shown, the embodiment of the utility model provides a micro turbojet engine test fixture, comprising: a first support mechanism 1, such as Figure 2As shown, it is used to support the weight of the turbojet engine and maintain the position of the turbojet engine; the hoop mechanism 2, as shown Figure 1 and Figure 4 As shown, it is installed on the first support mechanism 1, and is used to clamp the turbojet engine on the first support mechanism 1 to prevent the turbojet engine from sliding or moving; the first support mechanism 1 is provided with a first placement groove 3 for placing the turbojet engine, and the first placement groove 3 can be a groove or a specific space, and the shape and size are preferably matched with the turbojet engine. One end of the clamp mechanism 2 is hinged to one side of the first placement groove 3, allowing the clamp mechanism 2 to rotate, and the other end is movably connected to the other side of the first placement groove 3, and the movably connected method can be clamping, bonding, etc., which is not limited here; the movably connected end of the clamp mechanism 2 and the first placement groove 3 is provided with a first locking component 4, and the movably connected side of the first placement groove 3 and the clamp mechanism 2 is provided with a second locking component 5, and the first locking component 4 and the second locking component 5 can be mutually locked. The first locking component 4 and the second locking component 5 can cooperate with each other to ensure that the turbojet engine is firmly fixed on the first support mechanism 1. Specifically, when in use, the fixing device of the embodiment of the utility model can be first fixed and installed, and then the turbojet engine can be installed on the fixing device. For example, the movable connection end of the clamp mechanism 2 is first separated from the first support mechanism 1 and rotated around its hinged end, and the turbojet engine is placed into the first mounting groove 3 from the opening between the clamp mechanism 2 and the first mounting groove 3, and then the position of the jet engine in the first mounting groove 3 is adjusted. After the position is determined, the clamp mechanism 2 is rotated so that the first locking component 4 at its free end cooperates with the second locking component 5 on the first support mechanism 1, so as to clamp the turbojet engine on the first support mechanism 1, thereby providing stable support and fixation for the testing and verification process.

[0039] In order to improve the support stability of the fixing device to the turbojet engine, the fixing device of the embodiment of the utility model further includes a second supporting mechanism 6, on which a second placement groove 7 for placing the turbojet engine is provided, the second supporting mechanism 6 corresponds to the first supporting mechanism 1, and the second placement groove 7 corresponds to the first placement groove 3, and is used to place the other side of the turbojet engine; when one side of the turbojet engine is clamped in the first placement groove 3 by the clamping mechanism 2, the second placement groove 7 can support the other side of the turbojet engine. That is, the structure of the utility model enables the turbojet engine to be supported and fixed in both directions, thereby improving the stability of the detection. Of course, in other embodiments, a third supporting mechanism, a fourth supporting mechanism, etc. can also be provided to jointly support the turbojet engine. The number of specific supporting mechanisms is not limited here, and can be provided according to actual stability requirements. When one side of the turbojet engine has been fixed by the first supporting mechanism 1, the second placement groove 7 on the second supporting mechanism 6 can provide support for the other side of the engine. This double-support design can ensure that the turbojet engine remains stable in both directions, reducing the risk of displacement or tipping during operation.

[0040] As a preferred embodiment of the utility model, a limited clamping mechanism 8 is provided on the first placement groove 3 and / or the second placement groove 7. The limited clamping mechanism 8 can ensure that the turbojet engine is correctly aligned and positioned in the first placement groove 3. At the same time, the clamping mechanism can be set to a structure that matches the outer side of the turbojet engine, which can not only prevent the turbojet engine from sliding, but also increase the fitting area between the side of the turbojet engine and the placement groove, thereby improving the stability of the entire support. It should be noted that the limited clamping mechanism 8 can be a different structure such as a clamping groove, a protrusion, etc. The specific design depends on the size, shape and specific requirements of the fixing device of the turbojet engine, which is not limited here. When the limited clamping mechanism 8 is provided on both limit grooves, the limited clamping mechanism 8 can ensure the precise position of the turbojet engine in the second placement groove 7, and work in conjunction with the limited clamping mechanism 8 in the first placement groove 3 to achieve all-round precise positioning. When the first placement groove 3 has fixed one side of the turbojet engine through the hoop mechanism 2 and the limited clamping mechanism 8, the limited clamping mechanism 8 of the second placement groove 7 provides additional fixation to the other side of the engine, thereby achieving double protection.

[0041] In order to improve the convenience of installation of the fixing device of the embodiment of the utility model, the fixing device of the embodiment of the utility model further includes a mounting plate 9, such as Figure 1 and Figure 3As shown, the mounting plate 9 is used to install the entire fixture and connect with other equipment. One end of the mounting plate 9 is connected to the first support mechanism 1, and the other end is connected to the second support mechanism 6. The first support mechanism 1 and the second support mechanism 6 are arranged in parallel, so that the installation of the mounting plate 9 is the installation of the entire fixture. Specifically, the mounting plate 9, as a structure connecting the two support mechanisms, can provide additional stability and rigidity, reduce vibration and bending during operation, and the first support mechanism 1 and the second support mechanism 6 are arranged in parallel, which helps to maintain the horizontal alignment of the turbojet engine. By using the mounting plate 9 to connect the two support mechanisms, the overall design of the fixture can be simplified, and additional connectors and complexity can be reduced. In other embodiments, the mounting plate 9 also allows the distance between the two support mechanisms to be adjusted to a certain extent to accommodate turbojet engines of different sizes or meet specific installation requirements. At the same time, the mounting plate 9 can help evenly distribute the weight of the turbojet engine and reduce the pressure on a single support point, thereby improving the durability of the fixture.

[0042] Preferably, the projection of the first mounting groove 3 on the second support mechanism 6 coincides with the second mounting groove 7, that is, the two mounting grooves are aligned with each other in spatial layout. This structure simplifies the installation process of the turbojet engine, because only one reference point needs to be aligned to ensure the correct placement of the engine on the two support mechanisms. In order to improve the installation efficiency of the mounting plate 9 and other equipment, a plurality of screw holes 10 can be provided on the mounting plate 9 to facilitate the bolt 12 connection between the mounting plate 9 and other equipment. The other equipment here can refer to equipment used for testing and verification of turbojet engines, etc., which is not limited here and can be installed according to the actual application scenario. Similarly, the number and arrangement of the screw holes 10 are not limited here, and can be set according to the actual installation stability. Generally speaking, the more screw holes 10 there are and the larger the area covered, the stronger the installation stability of the fixture.

[0043] Exemplarily, the first supporting mechanism 1 and the second supporting mechanism 6 are both plate-shaped structures, such as Figure 1 and Figure 2 As shown, there is a gap 11 between the first supporting mechanism 1 and the second supporting mechanism 6, the mounting plate 9 is also plate-shaped with a rectangular cross section, and more than two screw holes 10 are provided on the mounting plate 9, as shown in FIG. Figure 1 and Figure 3 As shown, the first support mechanism 1 is arranged vertically with the mounting plate 9, because the vertical arrangement can provide better stability and help to evenly distribute the weight of the turbojet engine. Figure 1As shown, the first locking component 4 is a through groove, and the second locking component 5 is a screw groove. The through groove and the screw groove can be locked by a bolt 12. The through groove is a longitudinal or transverse opening formed on the free connection end of the clamp mechanism 2, allowing the bolt 12 or other locking member to pass through. The screw groove can be a groove with a thread, located on one side of the first placement groove 3, matching the through groove, and used to receive and lock the bolt 12. The bolt 12 passes through the through groove and is then screwed into the thread in the screw groove. By tightening the bolt 12, the locking between the through groove and the screw groove can be achieved, thereby achieving the clamping of the clamp mechanism 2 on the turbojet engine. The locking action of the bolt 12 can provide a strong clamping force to ensure the stability of the turbojet engine in the fixture. The structure allows multiple adjustments and locking, and is suitable for application scenarios that require frequent installation and disassembly.

[0044] The above description is only a preferred embodiment of the utility model and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principles of the utility model should be included in the protection scope of the utility model. It should be noted that the structures or components illustrated in the drawings are not necessarily drawn to scale, and the utility model omits the description of known components and processing technologies and processes to avoid unnecessary limitations on the utility model.

Claims

1. A micro turbojet engine test fixture, characterized in that: include: A first supporting mechanism (1) is used to support the turbojet engine; A clamp mechanism (2) is mounted on the first supporting mechanism (1) and is used to clamp the turbojet engine on the first supporting mechanism (1); The first supporting mechanism (1) is provided with a first placement groove (3) for placing the turbojet engine, one end of the clamp mechanism (2) is hinged to one side of the first placement groove (3), and the other end is movably connected to the other side of the first placement groove (3); A first locking component (4) is provided at the movable connection end between the clamp mechanism (2) and the first placement groove (3), and a second locking component (5) is provided at the movable connection side between the first placement groove (3) and the clamp mechanism (2); the first locking component (4) and the second locking component (5) can be locked with each other.

2. A micro turbojet engine test fixture according to claim 1, characterized in that: The fixing device further comprises a second supporting mechanism (6), and the second supporting mechanism (6) is provided with a second placement groove (7) for placing the turbojet engine; When one side of the turbojet engine is clamped in the first mounting groove (3) by the clamp mechanism (2), the second mounting groove (7) can support the other side of the turbojet engine.

3. A micro turbojet engine test fixture according to claim 2, characterized in that: A limited position locking mechanism (8) is provided on the first placement groove (3).

4. A micro turbojet engine test fixture according to claim 2, characterized in that: A limited position locking mechanism (8) is provided on the second placement groove (7).

5. A micro turbojet engine test fixture according to claim 2, characterized in that: The fixing device further comprises a mounting plate (9), one end of the mounting plate (9) being connected to the first supporting mechanism (1) and the other end of the mounting plate (9) being connected to the second supporting mechanism (6), and the first supporting mechanism (1) and the second supporting mechanism (6) being arranged in parallel.

6. A micro turbojet engine test fixture according to claim 5, characterized in that: The projection of the first mounting groove (3) on the second supporting mechanism (6) coincides with the second mounting groove (7).

7. A micro turbojet engine test fixture according to claim 5, characterized in that: The mounting plate (9) is provided with a plurality of screw holes (10).

8. A micro turbojet engine test fixture according to claim 2, characterized in that: The first supporting mechanism (1) and the second supporting mechanism (6) are both plate-shaped structures, and there is a gap (11) between the first supporting mechanism (1) and the second supporting mechanism (6).

9. A micro-turbojet engine test fixture according to claim 5, characterized in that: The first supporting mechanism (1) and the mounting plate (9) are arranged vertically.

10. A micro turbojet engine test fixture according to claim 1, characterized in that: The first locking component (4) is a through groove, and the second locking component (5) is a screw groove. The through groove and the screw groove can be locked by a bolt (12).

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