Aero-engine test paddle table stabilizing equipment
By designing the protective cover, bearing plate and hydraulic rod system in the aero engine test equipment, the problem of displacement prone to existing equipment during long-term detection tests is solved, and the stable fixation and thrust absorption of the powertrain is achieved, which improves the Overall stability of the equipment.
Patent Information
- Application Number
- CN202421031990.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-05-13
- Publication Date
- 2025-01-07
- Estimated Expiration
- 2034-05-13
AI Technical Summary
Existing aero engine testing equipment is inconvenient to fixed positioning of the powertrain during use, resulting in easy displacement during long-term testing.
A test paddle table stabilization equipment for aircraft engines is designed, including protective cover, load-bearing plate, electro-hydraulic rod, spring and limit arc plate. Through the coordination of electro-hydraulic rod and spring, the extrusion limit and clamping of aircraft engines is achieved. Hold the stationary, and use the damper and tracheal system to absorb and weaken instantaneous thrust to ensure the stability of the equipment.
It effectively prevents jumping and offsetting of the aircraft engine during the test, improves the stability and fixation of the equipment, reduces the impact of instantaneous thrust on the equipment, and ensures the stable positioning of the powertrain during long-term inspection tests.
Smart Images
Figure CN222318459U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the technical field of aviation engine testing equipment, in particular to aviation engine testing propeller platform stabilization equipment. Background Art
[0002] An aircraft engine is a highly complex and sophisticated thermal machine. As the heart of an aircraft, it is not only the driving force for the aircraft to fly, but also an important driving force for the development of the aviation industry. Every important change in human aviation history is closely related to the technological progress of aircraft engines.
[0003] In the prior art, it is not convenient to fix and position the power assembly during the use of aircraft engine testing equipment, which may cause displacement during long-term testing. Utility Model Content
[0004] The utility model provides an aero-engine test propeller stabilization device, aiming to solve the problem in the prior art that the aero-engine test device is not convenient for fixing and positioning the power assembly during use, thus causing displacement during long-term detection and testing.
[0005] The utility model is implemented as follows: an aircraft engine test propeller platform stabilization device comprises a protective cover, an inner wall of the protective cover is slidably connected with a bearing plate, and a base is arranged on the lower surface of the protective cover, a first electric hydraulic rod is fixedly connected to the upper surface of the top end of the protective cover, and a first spring is fixedly connected to the telescopic end of the first electric hydraulic rod, a first limiting arc plate is fixedly connected to the lower surface of the first spring, and a second electric hydraulic rod is fixedly connected to the inner wall of the protective cover, a second spring is fixedly connected to the telescopic end of the second electric hydraulic rod, and a second limiting arc plate is fixedly connected to the outer wall of the second spring, a device pipe is fixedly connected to the left outer wall of the protective cover, and an air pipe is connected to the outer wall of the device pipe, a piston plate is movably connected to the inner wall of the device pipe, and the outer wall of the piston plate is fixedly connected to the first assembly plate, the outer wall of the first assembly plate is fixedly connected to the first damper, and the outer wall of the first damper is sleeved with a third spring, and the outer wall of the first damper is fixedly connected to the second assembly plate.
[0006] Preferably, rollers are provided on the lower surface of the carrying plate.
[0007] Preferably, a second damper is fixedly connected to the lower surface of the protective cover, and the second damper is located between the protective cover and the base, and a fourth spring is sleeved on the outer wall of the second damper.
[0008] Preferably, the outer wall of the protective cover is provided with glass.
[0009] Preferably, a rubber pad is fixedly connected to the outer wall of the first spring.
[0010] Compared with the prior art, the embodiments of the present application have the following beneficial effects:
[0011] The aircraft engine is placed on a load-bearing plate, and the load-bearing plate is pushed into the protective cover. The telescopic end of the first electric hydraulic rod and the telescopic end of the second electric hydraulic rod are extended, so that the first limit arc plate is lowered to squeeze and limit the upper end of the aircraft engine to prevent the aircraft engine from jumping. The two second limit arc plates are brought close to each other, so that the two second limit arc plates clamp and fix the aircraft engine to prevent the aircraft engine from deflecting. Thrust is generated during the aircraft engine test. The first damper and the third spring are used to absorb and weaken the instantaneous thrust generated when the aircraft engine starts to test, and the aircraft engine starts to test. The instantaneous thrust generated will cause the piston plate to penetrate into the trachea. The piston plate compresses the air in the trachea to weaken the instantaneous thrust, thereby reducing the impact of the instantaneous thrust on the protective cover and improving the stability of the equipment. The thrust generated by the aircraft engine test will cause the load-bearing plate to move forward, thereby causing the first spring and the second spring to twist. The trachea is connected to the boost pump. Through the operation of the boost pump, the air pressure in the trachea increases, thereby pushing the piston plate to move right, causing the aircraft engine to return to its initial position, preventing the first spring and the second spring from twisting, and ensuring the stability of the first limit arc plate and the second limit arc plate in clamping the aircraft engine. BRIEF DESCRIPTION OF THE DRAWINGS
[0012] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;
[0013] Figure 2 It is a front cross-sectional structural schematic diagram of the utility model;
[0014] Figure 3 It is a side sectional structural schematic diagram of the utility model;
[0015] In the figure: 1, protective cover; 2, bearing plate; 3, roller; 4, base; 5, first electric hydraulic rod; 6, first spring; 7, first limit arc plate; 8, second electric hydraulic rod; 9, second spring; 10, second limit arc plate; 11, equipment pipe; 12, air pipe; 13, piston plate; 14, first assembly plate; 15, first damper; 16, second assembly plate; 17, glass; 18, second damper. DETAILED DESCRIPTION
[0016] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by technicians in the technical field of this application; the terms used in the specification of the application herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" and any variations thereof in the specification and claims of this application and the above-mentioned drawings are intended to cover non-exclusive inclusions. The terms "first", "second", etc. in the specification and claims of this application or the above-mentioned drawings are used to distinguish different objects, not to describe a specific order.
[0017] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.
[0018] The utility model provides an aero-engine test propeller stabilization device, such as Figure 1-3 As shown, it includes a protective cover 1, the inner wall of which is slidably connected to a bearing plate 2, and a base 4 is provided on the lower surface of the protective cover 1, a first electric hydraulic rod 5 is fixedly connected to the upper surface of the top of the protective cover 1, and the telescopic end of the first electric hydraulic rod 5 is fixedly connected to a first spring 6, and the lower surface of the first spring 6 is fixedly connected to a first limiting arc plate 7, and the inner wall of the protective cover 1 is fixedly connected to a second electric hydraulic rod 8, the telescopic end of the second electric hydraulic rod 8 is fixedly connected to a second spring 9, and the outer wall of the second spring 9 is fixedly connected to a second limiting arc plate 10, the left outer wall of the protective cover 1 is fixedly connected to an equipment pipe 11, and the outer wall of the equipment pipe 11 is connected to an air pipe 12, the inner wall of the equipment pipe 11 is movably connected to a piston plate 13, and the outer wall of the piston plate 13 is fixedly connected to a first assembly plate 14, the outer wall of the first assembly plate 14 is fixedly connected to a first damper 15, and the outer wall of the first damper 15 is sleeved with a third spring, and the outer wall of the first damper 15 is fixedly connected to a second assembly plate 16.
[0019] It should be noted that, since it is not convenient to fix the power assembly during use of the aircraft engine test equipment in the prior art, which leads to displacement during long-term detection and testing, therefore, in order to solve the problem that it is not convenient to fix the power assembly during use of the aircraft engine test equipment in the prior art, which leads to displacement during long-term detection and testing, this solution places the aircraft engine on the load-bearing plate 2, pushes the load-bearing plate 2 into the protective cover 1, and extends the telescopic end of the first electric hydraulic rod 5 and the telescopic end of the second electric hydraulic rod 8 to make the first limiting arc plate 7 descend to squeeze and limit the upper end of the aircraft engine to prevent the aircraft engine from jumping, and the two second limiting arc plates 10 are brought close to each other, so that the two second limiting arc plates 10 clamp and fix the aircraft engine to prevent the aircraft engine from deflecting. , thrust is generated during the aircraft engine test. The first damper 15 and the third spring absorb and weaken the instantaneous thrust generated when the aircraft engine starts to be tested. The instantaneous thrust generated when the aircraft engine starts to be tested will cause the piston plate 13 to penetrate into the trachea 12. The piston plate 13 compresses the air in the trachea 12 to weaken the instantaneous thrust, thereby reducing the impact of the instantaneous thrust on the protective cover 1 and improving the stability of the equipment. The thrust generated by the aircraft engine test will cause the bearing plate 2 to move forward, thereby causing the first spring 6 and the second spring 9 to twist. The trachea 12 is connected to the boost pump. Through the operation of the boost pump, the air pressure in the trachea 12 is increased, thereby pushing the piston plate 13 to move right, causing the aircraft engine to return to its initial position, preventing the first spring 6 and the second spring 9 from twisting, and ensuring the stability of the first limit arc plate 7 and the second limit arc plate 10 in clamping the aircraft engine.
[0020] In a further preferred embodiment of the present invention, Figure 1 As shown, a roller 3 is provided on the lower surface of the carrying plate 2 .
[0021] In this embodiment, the right end of the carrying plate 2 is supported by the roller 3 , so that the movement of the carrying plate 2 is facilitated.
[0022] In a further preferred embodiment of the present invention, Figure 1-3 As shown, a second damper 18 is fixedly connected to the lower surface of the protective cover 1, and the second damper 18 is located between the protective cover 1 and the base 4, and a fourth spring is sleeved on the outer wall of the second damper 18.
[0023] In this embodiment, when the aircraft engine is working, vibration will be generated, and the vibration will be transmitted to the protective cover 1. The vibration is absorbed and weakened by the second damper 18 and the fourth spring, thereby improving the stability of the equipment.
[0024] In a further preferred embodiment of the present invention, Figure 1 As shown, the outer wall of the protective cover 1 is provided with glass 17 .
[0025] In this embodiment, the glass 17 facilitates personnel to observe the inside of the protective cover 1 .
[0026] In a further preferred embodiment of the present invention, Figure 2 As shown, a rubber pad is fixedly connected to the outer wall of the first spring 6 .
[0027] It should be noted that, for the above-mentioned embodiments, for the sake of simplicity, they are all described as a series of action combinations, but those skilled in the art should know that the utility model is not limited by the described action sequence, because according to the utility model, some steps may be performed in other sequences or simultaneously. Secondly, those skilled in the art should also know that the embodiments described in the specification are all preferred embodiments, and the actions and modules involved are not necessarily required by the utility model.
[0028] In the several embodiments provided in the present application, it should be understood that the disclosed devices can be implemented in other ways. For example, the device embodiments described above are merely schematic, such as the division of the above-mentioned units. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or communication connection shown or discussed can be through some interfaces, and the indirect coupling or communication connection between devices or units can be in the form of telecommunication or other forms.
[0029] The units described above as separate components may or may not be physically separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.
[0030] The above embodiments are only used to illustrate the technical solutions of the utility model, rather than to limit the protection scope of the utility model. Obviously, the described embodiments are only some embodiments of the utility model, rather than all embodiments. Based on these embodiments, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the utility model. Although the utility model has been described in detail with reference to the above embodiments, ordinary technicians in this field can still combine, add, delete or make other adjustments to the features in the various embodiments of the utility model according to the circumstances without conflict, without making creative work, so as to obtain different other technical solutions that do not deviate from the concept of the utility model in essence, and these technical solutions also belong to the scope of protection of the utility model.
Claims
1. Aero-engine test propeller platform stabilization equipment, characterized in that: The invention comprises a protective cover (1), wherein the inner wall of the protective cover (1) is slidably connected to a bearing plate (2), and the lower surface of the protective cover (1) is provided with a base (4), the upper surface of the top end of the protective cover (1) is fixedly connected to a first electric hydraulic rod (5), and the telescopic end of the first electric hydraulic rod (5) is fixedly connected to a first spring (6), the lower surface of the first spring (6) is fixedly connected to a first limiting arc plate (7), and the inner wall of the protective cover (1) is fixedly connected to a second electric hydraulic rod (8), and the telescopic end of the second electric hydraulic rod (8) is fixedly connected to a second spring (9), and the second spring ( The outer wall of the protective cover (9) is fixedly connected to a second limiting arc plate (10), the left outer wall of the protective cover (1) is fixedly connected to an equipment pipe (11), and the outer wall of the equipment pipe (11) is connected to an air pipe (12), the inner wall of the equipment pipe (11) is movably connected to a piston plate (13), and the outer wall of the piston plate (13) is fixedly connected to a first assembly plate (14), the outer wall of the first assembly plate (14) is fixedly connected to a first damper (15), and the outer wall of the first damper (15) is sleeved with a third spring, and the outer wall of the first damper (15) is fixedly connected to a second assembly plate (16).
2. The aircraft engine test propeller stabilization device according to claim 1, characterized in that: A roller (3) is provided on the lower surface of the carrying plate (2).
3. The aircraft engine test propeller stabilization device according to claim 1, characterized in that: A second damper (18) is fixedly connected to the lower surface of the protective cover (1), and the second damper (18) is located between the protective cover (1) and the base (4), and a fourth spring is sleeved on the outer wall of the second damper (18).
4. The aircraft engine test propeller stabilization device according to claim 1, characterized in that: The outer wall of the protective cover (1) is provided with glass (17).
5. The aircraft engine test propeller stabilization device according to claim 1, characterized in that: A rubber pad is fixedly connected to the outer wall of the first spring (6).