Small turbojet engine thrust vectoring nozzle test bench
By designing a small turbojet engine vector nozzle test stand, the problem of traditional test stands being unable to accurately measure vector nozzle torque was solved, achieving efficient and flexible testing, applicable to various turbojet engine models, and reducing transportation and storage costs.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- BAODING SWIWIN TURBOJET POWER EQUIPENT R&D CO LTD
- Filing Date
- 2025-05-21
- Publication Date
- 2026-05-12
AI Technical Summary
Traditional small turbojet engine test benches cannot comprehensively and accurately test the force and torque characteristics of vector nozzles, resulting in inaccurate test results or inability to draw valid conclusions. Furthermore, existing large-scale equipment is bulky and expensive, making it unsuitable for small turbojet engines.
A small turbojet engine vector nozzle test bench was designed, including a fixed platform, a six-component balance, a working platform, and a fixing mechanism. The six-component balance accurately measures forces and torques, and the fixing mechanism allows for the detachable installation of the turbojet engine. The adjustment components are in contact with the outer wall of the engine for fine-tuning, ensuring installation accuracy and applicability.
It improves the accuracy and reliability of testing, reduces transportation and storage pressure, enables flexible testing of different models of turbojet engines, is suitable for outdoor environments, and enhances the versatility and convenience of the equipment.
Smart Images
Figure CN224231271U_ABST
Abstract
Description
Technical Field
[0001] This utility model relates to the field of turbojet engine testing technology, and in particular to a small turbojet engine vector nozzle test stand. Background Technology
[0002] As a crucial power source for modern aircraft, the performance of small turbojet engines directly impacts flight performance and safety. Vectoring nozzles, a key engine component, significantly enhance aircraft maneuverability and stability by adjusting the direction and force of the jet stream. However, traditional small turbojet engine test benches often cannot comprehensively and accurately test the force and torque characteristics of vectoring nozzles, limiting the improvement and optimization of aero-engine performance.
[0003] Currently, while some testing equipment exists for large aero-engine vector nozzles, this equipment is often bulky and expensive, making it unsuitable for testing small turbojet engines. Furthermore, when testing small turbojet engines, these devices may produce inaccurate results or fail to yield valid conclusions due to size mismatches and insufficient testing precision.
[0004] To address the aforementioned problems, this invention proposes a small turbojet engine vector nozzle test bench to solve these technical issues. Utility Model Content
[0005] The purpose of this invention is to provide a test bench for small turbojet engine vector nozzles, which aims to solve the shortcomings of traditional test benches in testing small turbojet engine vector nozzles and improve the accuracy and reliability of the test.
[0006] To achieve the above objectives, this utility model provides the following solution: This utility model provides a small turbojet engine vector nozzle test stand, comprising:
[0007] A fixed platform, which secures the equipment to a stable platform to withstand thrust;
[0008] A six-component balance, the base of which is detachably mounted on the fixed platform, is used to measure the forces and torques generated by the turbojet engine during testing;
[0009] A working platform, which is fixedly installed at the measuring end of the six-component balance, is used to transmit the force and torque it bears to the six-component balance.
[0010] The fixing mechanism includes a fixing component that is detachably mounted on the working platform, and the turbojet engine to be measured is clamped inside the fixing component; the fixing component is provided with an adjustment component, which is disposed in contact with the outer wall of the turbojet engine.
[0011] Preferably, the bottom end of the fixed platform is detachably connected to a fixing frame, and the fixed platform is fixed to the platform by the fixing frame.
[0012] Preferably, the fixing component includes a fixed base fixedly installed on the working platform, a liftable fixing column fixedly connected to the top of the fixed base, a fixing ring for clamping the turbojet engine fixedly connected to the top of the fixing column, and the adjusting component movably disposed on both sides of the fixing ring.
[0013] Preferably, the fixing column includes a fixing tube fixed to the top of the fixing base, and a movable column is slidably connected to the top of the fixing tube. The top of the movable column extends out of the fixing tube and is fixed to the bottom of the fixing ring.
[0014] Preferably, the side wall of the fixed tube is provided with a locking bolt, the end of which extends into the inner cavity of the fixed tube and abuts against and locks against the outer wall of the movable column.
[0015] Preferably, the fixing ring includes a first half-ring fixed to the top of the movable column, a second half-ring hinged to one side of the first half-ring, and the free end of the second half-ring locked by a locking buckle; the turbojet engine clamp is located between the first half-ring and the second half-ring.
[0016] Preferably, the first half-ring and the second half-ring are provided with a plurality of heat dissipation holes for heat dissipation.
[0017] Preferably, the adjustment assembly includes a plurality of adjusting screws threadedly connected to the first half-ring and the second half-ring, the adjusting screws extending into the inner cavity of the first half-ring and the second half-ring and rotatably connected to adjusting blocks, the adjusting blocks abutting against the outer wall of the turbojet engine.
[0018] Preferably, a flexible contact pad is fixed to the side of the adjusting block away from the adjusting screw, and the contact pad abuts against the outer wall of the turbojet engine.
[0019] Preferably, the inner walls of the first half-ring and the second half-ring are provided with a plurality of clearance grooves corresponding to the adjusting block, the adjusting screw passes through the clearance grooves, and the adjusting block is telescopically disposed in the clearance grooves.
[0020] Compared with existing technologies, this utility model has the following advantages and technical effects: This utility model discloses a small turbojet engine vector nozzle test stand. The fixed platform is used to stabilize the equipment and bear the thrust, providing a stable foundation for the entire test stand, reducing the impact of external interference on the test results, and ensuring the reliability of the test data. The six-component balance is detachably installed on the fixed platform and is the core component for measuring the forces and torques generated by the turbojet engine. It can accurately measure the forces and torques generated by the turbojet engine during the test. These data are of great significance for evaluating engine performance, analyzing its working state, and conducting subsequent optimization design. Its measurement data is crucial for evaluating engine performance. The working platform is connected to the six-component balance. The flat measuring end transmits force and torque, ensuring measurement accuracy. The fixing mechanism includes a detachable mounting component on the work platform, which securely clamps the turbojet engine, facilitating its installation and removal and improving the test bench's versatility and convenience. Simultaneously, the adjustable component abuts against the engine's outer wall, allowing for fine-tuning of the engine's position to ensure installation precision. This adjustment component ensures the engine is in the optimal testing position, further improving measurement accuracy. Furthermore, the adjustable component allows for testing different models of turbojet engines without replacing the fixing mechanism, enhancing the equipment's applicability and reducing transportation and storage burdens.
[0021] This utility model has a compact structure, is easy to use, and can be flexibly disassembled and assembled, making it convenient for use in outdoor environments. At the same time, it can be used to test different models of turbojet engines, achieving multiple uses in one machine, improving the applicability of the test bench, reducing the pressure of storage and transportation, and facilitating large-scale promotion. Attached Figure Description
[0022] The accompanying drawings, which form part of this application, are used to provide a further understanding of this application. The illustrative embodiments and descriptions of this application are used to explain this application and do not constitute an undue limitation of this application. In the drawings:
[0023] Figure 1 This is an axial view of the test bench for the vector nozzle of the small turbojet engine of this utility model;
[0024] Figure 2 This is a side view of the fixing ring structure of this utility model;
[0025] Figure 3 This is a schematic diagram of the fixed column connection structure of this utility model;
[0026] In the diagram: 1. Fixed platform; 2. Six-component balance; 3. Working platform; 4. Fixing mechanism; 5. Turbojet engine; 6. Fixing frame; 7. Fixed base; 8. Fixing column; 9. Fixing ring; 10. Fixing tube; 11. Movable column; 12. Locking bolt; 13. First half ring; 14. Second half ring; 15. Locking buckle; 16. Heat dissipation hole; 17. Adjusting screw; 18. Adjusting block; 19. Contact pad; 20. Leaving groove. Detailed Implementation
[0027] 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.
[0028] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the utility model will be further described in detail below with reference to the accompanying drawings and specific embodiments.
[0029] Reference Figure 1-3 As shown, this embodiment provides a small turbojet engine vector nozzle test stand, including:
[0030] Fixed platform 1, which fixes the equipment on a stable platform to withstand the thrust;
[0031] The six-component balance 2 has a base that can be detachably mounted on the fixed platform 1, and is used to measure the forces and torques generated by the turbojet engine 5 during the test.
[0032] The working platform 3 is fixedly installed at the measuring end of the six-component balance 2 and is used to transmit the force and torque it bears to the six-component balance 2.
[0033] The fixing mechanism 4 includes a fixing component that can be detachably installed on the working platform 3. The turbojet engine 5 to be measured is clamped inside the fixing component. An adjustment component is provided on the fixing component, and the adjustment component is set to abut against the outer wall of the turbojet engine 5.
[0034] This utility model discloses a small turbojet engine 5 vector nozzle test stand. The fixed platform 1 stabilizes the equipment and bears the thrust, providing a stable foundation for the entire test stand, reducing the impact of external interference on the test results, and ensuring the reliability of the test data. The six-component balance 2 is detachably mounted on the fixed platform 1 and is the core component for measuring the forces and torques generated by the turbojet engine 5. It can accurately measure the forces and torques generated by the turbojet engine 5 during the test. These data are of great significance for evaluating engine performance, analyzing its operating status, and conducting subsequent optimization design. The measurement data is crucial for evaluating engine performance. The working platform 3 connects to the measuring end of the six-component balance 2, serving to transmit force. The torque and force ensure measurement accuracy; the fixing mechanism 4 includes a fixing component that can be detachably installed on the working platform 3, which can firmly clamp the turbojet engine 5, facilitating the installation and removal of the turbojet engine 5, and improving the versatility and convenience of the test bench; at the same time, the adjustment component abuts against the outer wall of the engine, which can fine-tune the position of the engine to ensure the installation accuracy; the adjustment component abuts against the outer wall of the engine, which can fine-tune the position of the engine to ensure that the engine is in the optimal test position, further improving the measurement accuracy; at the same time, the adjustment component can test different models of turbojet engines 5 without replacing the fixing mechanism 4, improving the applicability of the equipment and reducing the pressure of transportation and storage. This utility model has a compact structure, is easy to use, and can be flexibly disassembled and assembled, making it convenient for use in outdoor environments; at the same time, it can test different models of turbojet engines 5, realizing multiple uses in one machine, improving the applicability of the test bench, reducing the pressure of storage and transportation, and facilitating large-scale promotion.
[0035] In one embodiment of this utility model,
[0036] The design is further optimized by detachably connecting a mounting bracket 6 to the bottom of the fixed platform 1, which then secures the fixed platform 1 to the platform. The detachable mounting bracket 6 at the bottom of the fixed platform 1 allows for securing the platform 1 to other platforms, enhancing the installation flexibility of the fixed platform 1 and facilitating the selection of appropriate fixing methods based on different testing sites and requirements, thereby improving the versatility of the testing station.
[0037] The design is further optimized. The fixing component includes a fixed base 7 fixedly mounted on the working platform 3. A liftable fixing column 8 is fixedly connected to the top of the fixed base 7. A fixing ring 9 for clamping the turbojet engine 5 is fixedly connected to the top of the fixing column 8. Adjustment components are movably arranged on both sides of the fixing ring 9. The fixing component consists of a fixed base 7, a liftable fixing column 8, and a fixing ring 9. The adjustment components are located on both sides of the fixing ring 9. The liftable fixing column 8 can be adjusted according to the different heights of the turbojet engine 5, so that the fixing ring 9 can better clamp the engine, improving the adaptability and stability of the fixing. At the same time, the height adjustment of the fixing ring 9 can simulate the injection of different vector nozzles, improving practicality and avoiding the burning damage of the vector nozzle to the platform.
[0038] The design is further optimized. The fixed column 8 includes a fixed tube 10 fixed to the top of the fixed base 7. A movable column 11 is slidably connected to the top of the fixed tube 10. The top of the movable column 11 extends out of the fixed tube 10 and is fixed to the bottom of the fixed ring 9. A locking bolt 12 is provided on the side wall of the fixed tube 10. The end of the locking bolt 12 extends into the inner cavity of the fixed tube 10 and abuts against the outer wall of the movable column 11 for locking. The fixed column 8 is composed of a fixed tube 10 and a movable column 11. The movable column 11 slides inside the fixed tube 10 and is connected to the fixed ring 9. This optimizes the lifting function of the fixed column 8, making the height adjustment of the fixed ring 9 more flexible and precise, and adapting to the testing requirements of turbojet engines 5 of different sizes. The locking bolt 12 on the side wall of the fixed tube 10 locks the movable column 11 by abutting against the outer wall of the movable column 11. This ensures that the movable column 11 is securely locked after the fixed ring 9 is adjusted to a suitable height, preventing displacement during testing and ensuring the reliability of engine fixation.
[0039] Further optimizing the design, the fixing ring 9 includes a first half-ring 13 fixed to the top of the movable column 11, with a second half-ring 14 hinged to one side of the first half-ring 13. The free end of the second half-ring 14 is locked in place by a locking buckle 15. The turbojet engine 5 is clamped between the first half-ring 13 and the second half-ring 14. The fixing ring 9 is designed to be composed of the first half-ring 13 and the second half-ring 14 hinged together and connected by the locking buckle 15. The turbojet engine 5 is clamped between the two, which facilitates the installation and removal of the turbojet engine 5, improves testing efficiency, and ensures the fastening effect of the fixing ring 9 on the engine.
[0040] Further optimization of the design involves providing several heat dissipation holes 16 through the first half-ring 13 and the second half-ring 14. These heat dissipation holes 16 on the first half-ring 13 and the second half-ring 14 help dissipate heat from the turbojet engine 5 during testing, preventing overheating of the engine caused by the first half-ring 13 and the second half-ring 14 from affecting performance, thus ensuring the accuracy of the test and the safety of the engine.
[0041] Further optimization of the scheme involves an adjustment assembly comprising several adjusting screws 17 threadedly connected to the first half-ring 13 and the second half-ring 14. Each adjusting screw 17 extends into the inner cavity of the first half-ring 13 and the second half-ring 14 and is rotatably connected to an adjusting block 18, which abuts against the outer wall of the turbojet engine 5. The adjustment assembly utilizes adjusting screws 17 and adjusting blocks 18. The adjusting screws 17 are threadedly connected to the half-rings, and the adjusting blocks 18 are rotatably connected to the screws. Rotating the adjusting screws 17 allows for precise adjustment of the position of the adjusting blocks 18. The adjusting blocks 18 abut against the outer wall of the engine, thereby fine-tuning the engine's position, improving the accuracy of fixation, and ensuring the reliability of the test results.
[0042] In a further optimized design, a flexible contact pad 19 is fixed to the side of the adjusting block 18 away from the adjusting screw 17, and the contact pad 19 abuts against the outer wall of the turbojet engine 5. The flexible contact pad 19 can protect the outer wall of the engine from scratches, while increasing the friction of the contact, making the adjustment and fixation of the engine by the adjusting block 18 more stable.
[0043] In a further optimized design, the inner walls of the first semi-ring 13 and the second semi-ring 14 are provided with several clearance grooves 20 corresponding to the adjusting block 18. The adjusting screw 17 passes through the clearance grooves 20, and the adjusting block 18 is telescopically positioned within the clearance grooves 20. The clearance grooves 20 provide storage space for the adjusting block 18, making its telescopic movement smoother and preventing it from shifting during adjustment, thus improving the accuracy of the adjustment.
[0044] In the description of this utility model, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.
[0045] The embodiments described above are merely preferred embodiments of the present utility model and are not intended to limit the scope of the present utility model. Various modifications and improvements made to the technical solutions of the present utility model by those skilled in the art without departing from the spirit of the present utility model should fall within the protection scope defined by the claims of the present utility model.
Claims
1. A test stand for a small turbojet engine vector nozzle, characterized in that, include: Fixed platform (1), the fixed platform (1) fixes the equipment on a stable platform and bears the thrust; A six-component balance (2), the base of which is detachably mounted on the fixed platform (1), is used to measure the force and torque generated by the turbojet engine (5) during the test. The working platform (3) is fixedly installed at the measuring end of the six-component balance (2) and is used to transmit the force and torque it bears to the six-component balance (2). The fixing mechanism (4) includes a fixing component that is detachably installed on the working platform (3), and the turbojet engine (5) to be measured is clamped in the fixing component; the fixing component is provided with an adjustment component, which is abutted against the outer wall of the turbojet engine (5).
2. The small turbojet engine vector nozzle test stand according to claim 1, characterized in that: The bottom end of the fixed platform (1) is detachably connected to a fixing frame (6), and the fixed platform (1) is fixed on the platform by the fixing frame (6).
3. The small turbojet engine vector nozzle test stand according to claim 1, characterized in that: The fixing component includes a fixing base (7) fixedly installed on the working platform (3), a liftable fixing column (8) is fixedly connected to the top of the fixing base (7), and a fixing ring (9) for clamping the turbojet engine (5) is fixedly connected to the top of the fixing column (8). The adjusting component is movably arranged on both sides of the fixing ring (9).
4. The small turbojet engine vector nozzle test stand according to claim 3, characterized in that: The fixed column (8) includes a fixed tube (10) fixedly connected to the top of the fixed base (7). The top of the fixed tube (10) is slidably connected to a movable column (11). The top of the movable column (11) extends out of the fixed tube (10) and is fixedly connected to the bottom of the fixed ring (9).
5. The small turbojet engine vector nozzle test stand according to claim 4, characterized in that: The side wall of the fixed tube (10) is provided with a locking bolt (12), the end of which extends into the inner cavity of the fixed tube (10) and abuts against the outer wall of the movable column (11) for locking.
6. The small turbojet engine vector nozzle test stand according to claim 4, characterized in that: The fixed ring (9) includes a first half-ring (13) fixed to the top of the movable column (11), a second half-ring (14) is hinged to one side of the first half-ring (13), and the free end of the second half-ring (14) is locked and connected by a locking buckle (15); the turbojet engine (5) is clamped between the first half-ring (13) and the second half-ring (14).
7. The small turbojet engine vector nozzle test stand according to claim 6, characterized in that: The first half-ring (13) and the second half-ring (14) are provided with a plurality of heat dissipation holes (16) for heat dissipation.
8. The small turbojet engine vector nozzle test stand according to claim 6, characterized in that: The adjustment assembly includes several adjusting screws (17) threadedly connected to the first half-ring (13) and the second half-ring (14). The adjusting screws (17) extend into the inner cavity of the first half-ring (13) and the second half-ring (14) and are rotatably connected to adjusting blocks (18). The adjusting blocks (18) abut against the outer wall of the turbojet engine (5).
9. The small turbojet engine vector nozzle test stand according to claim 8, characterized in that: A flexible contact pad (19) is fixed to the side of the adjusting block (18) away from the adjusting screw (17), and the contact pad (19) abuts against the outer wall of the turbojet engine (5).
10. The small turbojet engine vector nozzle test stand according to claim 8, characterized in that: The inner walls of the first half-ring (13) and the second half-ring (14) are provided with a plurality of relief grooves (20) corresponding to the adjusting block (18). The adjusting screw (17) passes through the relief grooves (20), and the adjusting block (18) is extended and retracted in the relief grooves (20).