Differential mechanism for aviation transmission device

Abstract

The utility model discloses a differential mechanism for an aviation transmission device, and belongs to the technical field of differential mechanisms, the differential mechanism for the aviation transmission device is characterized by comprising a differential mechanism main body, and a gear structure is arranged in the differential mechanism main body. The lower oil hopper on the bottom side in the differential main body absorbs lubricating oil, then the lubricating oil in the differential main body is slowly conveyed into the filtering structure, meanwhile, it is guaranteed that normal use of the inner lubricating oil is not interfered, the filtering structure can accurately intercept metal impurities and other pollutants generated by abrasion of the gear structure, secondary abrasion is avoided, and the service life of the gear structure is prolonged. When filtered lubricating oil flows into the guide pipe, the cooling structure on the outer side of the guide pipe quickly takes away heat according to the heat exchange principle, so that the oil temperature is reduced to a proper interval, the lubricating performance is recovered, and it is ensured that the lubricating oil forms an effective lubricating film on the surface of the gear structure under high temperature and high load.

Description

TECHNICAL FIELD

[0001] The utility model relates to differential mechanism technical field, especially relates to a differential mechanism for aviation transmission device. BACKGROUND

[0002] Differential mechanism is a kind of mechanical device, usually used in transmission system, differential mechanism is usually composed of ring gear, steel plate, friction plate and hydraulic controller etc., in aviation transmission system, the performance of differential mechanism is directly related to the safety and stability of flight.

[0003] Due to the existence of multiple ring gears in differential mechanism, differential mechanism is usually filled with special gear oil liquid, for lubricating and cooling each moving part in differential mechanism, the long-time transmission use between multiple ring gears inevitably causes impurities in oil liquid, too much impurities affect transmission, and when replacing oil liquid, it needs to be replaced regularly according to mileage or years, needs to replace all oil, increases replacement cost and replacement frequency simultaneously;

[0004] The existing patent (announcement number: CN219673220U) discloses a differential mechanism assembly, the utility model discloses a differential mechanism is self-cleaning collection when using, keeps the cleanness of oil liquid between ring gears, to ensure the stability of transmission.

[0005] For the above problems, the existing patent provides a solution, but the existing aviation transmission device generates a lot of heat during operation, especially under high-speed and high-load working conditions, the temperature in differential mechanism rises sharply, and although the lubricating oil in differential mechanism plays a certain cooling and lubrication, it is still easy to oxidize and deteriorate under high temperature, thereby causing the decline of lubricating performance, aggravating the gear wear in differential mechanism, at the same time, the gear wear will fall off metal impurities, too much impurities will affect gear transmission use.

[0006] Therefore, a differential mechanism for aviation transmission device is provided. UTILITY MODEL CONTENTS

[0007] The utility model aims at providing a differential mechanism for aviation transmission device, which can solve the problem that the existing aviation transmission device generates a lot of heat during operation, especially under high-speed and high-load working conditions, the temperature in differential mechanism rises sharply, and although the lubricating oil in differential mechanism plays a certain cooling and lubrication, it is still easy to oxidize and deteriorate under high temperature, thereby causing the decline of lubricating performance, aggravating the gear wear in differential mechanism, at the same time, the gear wear will fall off metal impurities, too much impurities will affect gear transmission use.

[0008] In order to achieve the above object, the utility model provides the following technical scheme: a differential mechanism for aviation transmission device, including differential mechanism main part, the inside of differential mechanism main part is provided with gear structure, the right side of differential mechanism main part is provided with circulation processing mechanism,

[0009] The circulation processing mechanism includes an oil tank embedded in the interior of the differential mechanism main body, the right side of the oil tank penetrates the interior of the differential mechanism main body, the right side of the differential mechanism main body is bolted with a filter structure, the left side of the filter structure is in communication with the right side of the oil tank, the right side of the filter structure is communicated with a conduit, the outer side of the conduit is provided with a cooling structure, the right side of the differential mechanism main body is bolted with a peristaltic pump, the absorption end of the peristaltic pump is in communication with the top of the conduit, the output end of the peristaltic pump is communicated with a return pipe, the return pipe is communicated at the back side of the differential mechanism main body, the right side of the differential mechanism main body is provided with a temperature monitoring structure, and the temperature monitoring structure is electrically connected with the cooling structure.

[0010] Preferably, the filter structure includes a filter box bolted to the right side of the differential mechanism main body, and the left side of the filter box is in communication with the right side of the oil tank.

[0011] Preferably, the top of the filter box is bolted with a cover, and the left side of the top of the cover is bolted with a magnet filter screen.

[0012] Preferably, the right side of the top of the cover is bolted with a foreign matter filter screen, and the bottom of the magnet filter screen and the foreign matter filter screen is bolted with a bottom plate.

[0013] Preferably, the cooling structure includes a cooling coil provided on the outer side of the conduit, the left side of the cooling coil is communicated with a water outlet valve, and the water outlet valve is located on the left side of the conduit.

[0014] Preferably, the right side of the cooling coil is communicated with a water inlet valve, and the water inlet valve is located on the right side of the conduit.

[0015] Preferably, the temperature monitoring structure includes a self-controller bolted to the right side of the differential mechanism main body, and the self-controller is electrically connected with the water outlet valve and the water inlet valve respectively.

[0016] Preferably, the right side of the differential mechanism main body is bolted with a temperature sensor, the sensing end of the temperature sensor is located in the interior of the differential mechanism main body, and the temperature sensor is electrically connected with the self-controller.

[0017] Compared with the prior art, the utility model has the advantages that:

[0018] 1、The application sets up the circulating processing mechanism, through starting the peristaltic pump to suck the catheter, so that the oil tank on the bottom side of the differential main body absorbs the lubricating oil, then the lubricating oil in the differential main body is slowly transported to the filter structure, while ensuring that the internal lubricating oil is not disturbed, the filter structure can accurately intercept the metal impurities and other pollutants generated by the gear structure wear, avoid secondary wear, prolong the gear life, ensure stable transmission, when the filtered lubricating oil flows into the catheter, the cooling structure outside the catheter quickly takes away the heat according to the heat exchange principle, so that the oil temperature is reduced to the appropriate interval, the lubricating performance is restored, the effective lubricating film of the lubricating oil is formed on the surface of the gear structure under high temperature and high load, the friction is reduced, the temperature of the differential main body is reduced, the transmission efficiency is improved, then the lubricating oil is transported to the return pipe by the peristaltic pump, the return pipe accurately returns the cooled and filtered oil to the inside of the differential main body, realizes the closed loop circulation, keeps the differential main body in good lubrication and heat dissipation state, reduces the risk of failure, and lays the foundation for safe operation of the aviation transmission device;

[0019] 2、The application sets up the temperature monitoring structure, which can accurately perceive the temperature change of the lubricating oil in the differential main body, when the temperature rises sharply under high speed and high load and approaches or exceeds the tolerance limit of the lubricating oil, the cooling structure is signaled immediately, the cooling structure cools the lubricating oil circulating in the catheter, ensures that the oil temperature is in the best range, avoids high temperature oxidation of the lubricating oil, maintains the chemical stability, ensures the lubrication is reliable and durable, indirectly protects the gear structure, reduces the temperature fluctuation risk, improves the reliability and durability of the aviation transmission device, and protects the safe flight of the aircraft. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 It is the overall structure diagram of the differential mechanism for aviation transmission device of the utility model;

[0021] Figure 2 It is the structure diagram of the circulating processing mechanism of the utility model;

[0022] Figure 3 It is the structure diagram of the filter structure of the utility model;

[0023] Figure 4 It is the structure diagram of the cooling structure of the utility model;

[0024] Figure 5 It is the structure diagram of the temperature monitoring structure of the utility model.

[0025] In the figure, 1, differential main body; 2, gear structure; 3, circulating processing mechanism; 301, lower oil tank; 302, filter structure; 3021, filter box; 3022, cover; 3023, magnet filter screen; 3024, impurity filter screen; 3025, bottom plate; 303, conduit; 304, cooling structure; 3041, cooling coil; 3042, water outlet valve; 3043, water inlet valve; 305, peristaltic pump; 306, back feeding pipe; 307, temperature monitoring structure; 3071, automatic controller; 3072, temperature sensor. DETAILED DESCRIPTION

[0026] The technical solutions in the embodiments of the utility model will be clearly and completely described below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the protection scope of the utility model.

[0027] Please refer to Figures 1-5 The utility model provides technical schemes:

[0028] A differential for an aviation transmission device, comprising a differential main body 1, the inside of the differential main body 1 is provided with a gear structure 2, the right side of the differential main body 1 is provided with a circulating processing mechanism 3;

[0029] The circulating processing mechanism 3 includes a lower oil tank 301 embedded in the inside of the differential main body 1, the right side of the lower oil tank 301 penetrates the inside of the differential main body 1, the right side of the differential main body 1 is bolted with a filter structure 302, the left side of the filter structure 302 is communicated with the right side of the lower oil tank 301, the right side of the filter structure 302 is communicated with a conduit 303, the outside of the conduit 303 is provided with a cooling structure 304, the right side of the differential main body 1 is bolted with a peristaltic pump 305, the absorption end of the peristaltic pump 305 is communicated with the top of the conduit 303, the output end of the peristaltic pump 305 is communicated with a back feeding pipe 306, the back feeding pipe 306 is communicated at the back side of the differential main body 1, the right side of the differential main body 1 is provided with a temperature monitoring structure 307, and the temperature monitoring structure 307 is electrically connected with the cooling structure 304.

[0030] In this embodiment: by setting the circulation processing mechanism 3, when the gear structure 2 inside the differential main body 1 is running at high speed and high load, the lubricating oil plays a lubricating role while the temperature gradually rises, and in this process, the peristaltic pump 305 is started to suck the conduit 303, so that part of the lubricating oil flows to the bottom of the embedded oil tank 301 under the action of gravity, the right side of the oil tank 301 penetrates the differential main body 1, so that the accumulated lubricating oil flows into the filter structure 302 in communication, this filter structure 302 accurately intercepts the metal impurities and other small pollutants generated by the wear of the gear structure 2, ensures that only pure lubricating oil can continue to move forward, effectively avoids secondary wear of the gear structure 2 caused by impurities, and provides protection for the long-term operation of the gear structure 2. After filtration, the lubricating oil flows into the conduit 303, at this time, according to the temperature monitoring structure 307, the actual temperature of the lubricating oil inside the differential main body 1 is monitored, when the temperature of the lubricating oil inside the differential main body 1 rises close to the tolerance limit of the lubricating oil, an electrical signal is immediately sent to the cooling structure 304, the cooling structure 304 outside the conduit 303 is immediately started, and heat exchange is carried out with the lubricating oil in the conduit 303. Quickly take away the heat in the lubricating oil, make its temperature fall rapidly to the appropriate working interval, the cooled lubricating oil restores good lubricating performance, can form a stable lubricating film on the surface of the gear structure 2, greatly reduce the friction coefficient, reduce power loss, improve the transmission efficiency of the differential main body 1. Finally, the lubricating oil is returned to the differential main body 1 through the return pipe 306 connected to the output end of the peristaltic pump 305, and a complete cycle is completed, so that the lubricating oil inside the differential main body 1 is always in good lubrication and heat dissipation state, effectively reducing the risk of failure caused by poor lubrication or overheating, and providing solid protection for the continuous and safe operation of the aviation transmission device.

[0031] Specifically, as shown in Figure 3 , the filter structure 302 includes a filter box 3021 bolted to the right side of the differential main body 1, and the left side of the filter box 3021 is in communication with the right side of the oil tank 301.

[0032] Specifically, as shown in Figure 3 , the top of the filter box 3021 is bolted with a cover 3022, and the left side of the top of the cover 3022 is bolted with a magnet filter screen 3023.

[0033] Specifically, as shown in Figure 3 , the right side of the top of the cover 3022 is bolted with an impurity filter screen 3024, and the bottom of the magnet filter screen 3023 and the impurity filter screen 3024 is bolted with a bottom plate 3025.

[0034] In the embodiment, the gear structure 2 inside the differential body 1 is in operation, the lubricating oil in the differential body 1 entrains various impurities generated by abrasion and flows to the filter box 3021 through the oil outlet 301. The top cover 3022 plays a key role. The magnet filter 3023 at the bottom left of the cover 3022 accurately captures iron-containing metal impurities by using the principle of magnetic adsorption, preventing these particles with strong abrasion from mixing into the lubricating oil again and causing secondary damage to the gear structure 2. The impurity filter 3024 at the right side of the cover 3022 can filter out non-metallic impurities such as dust and debris through fine pores. The bottom plate 3025 at the bottom of the cover 3022 plays a role in stable support and isolation to avoid backflow of impurities. In this way, the lubricating oil after double filtration flows smoothly into the inside of the conduit 303.

[0035] Specifically, as shown in Figure 4 The cooling structure 304 includes a cooling coil 3041 arranged outside the conduit 303. The left side of the cooling coil 3041 is connected to a water outlet valve 3042, and the water outlet valve 3042 is located at the left side of the conduit 303.

[0036] Specifically, as shown in Figure 4 The right side of the cooling coil 3041 is connected to a water inlet valve 3043, and the water inlet valve 3043 is located at the right side of the conduit 303.

[0037] In the embodiment, by arranging the cooling structure 304, when the high-temperature lubricating oil flows through the conduit 303, the cooling coil 3041 outside the conduit 303 starts to operate, the water inlet valve 3043 is opened, and the low-temperature cooling liquid flows into the cooling coil 3041. According to the heat exchange principle, the cooling liquid circulates in the coil and absorbs the heat of the lubricating oil. At this time, the temperature of the lubricating oil is rapidly reduced to ensure that it maintains good lubrication performance in the appropriate temperature range. The water outlet valve 3042 is used to control the discharge of the cooling liquid to ensure the continuous updating of the cooling liquid and maintain the cooling efficiency.

[0038] Specifically, as shown in Figure 5 The temperature monitoring structure 307 includes an automatic controller 3071 bolted to the right side of the differential body 1, and the automatic controller 3071 is electrically connected with the water outlet valve 3042 and the water inlet valve 3043.

[0039] Specifically, as shown in Figure 5 The right side of the differential body 1 is bolted with a temperature sensor 3072, and the sensing end of the temperature sensor 3072 is located inside the differential body 1. The temperature sensor 3072 is electrically connected with the automatic controller 3071.

[0040] In the embodiment: by setting the temperature monitoring structure 307, the temperature inside the differential body 1 is monitored in real time through the sensing end of the temperature sensor 3072, once the temperature rises close to the tolerance limit of the lubricating oil under high load operation, the temperature sensor 3072 immediately transmits a signal to the controller 3071, the controller 3071 quickly processes the information, and sends instructions to the outlet valve 3042 and the inlet valve 3043 to open and adjust the cooling liquid into the inside of the cooling coil 3041, and the high-temperature lubricating oil in the conduit 303 is cooled and processed, so that the temperature of the lubricating oil is always in the best state.

[0041] Working principle: during the use of the differential of the aviation transmission device, the gear structure 2 inside the differential body 1 is under high-speed and high-load operation, the lubricating oil is under high temperature, at this time the peristaltic pump 305 is in the starting state, part of the heated lubricating oil flows to the filter box 3021 through the oil tank 301 under the action of gravity, the left magnet filter screen 3023 on the top cover 3022 of the filter box 3021 uses magnetic adsorption to filter out iron impurities, the right impurity filter screen 3024 filters out non-metallic impurities such as dust by virtue of fine pores, the bottom plate 3025 prevents the backflow of impurities, and the purified lubricating oil flows into the conduit 303 after double filtration, the cooling coil 3041 outside the conduit 303 is on standby, when the temperature sensor 3072 in the temperature monitoring structure 307 senses that the temperature of the lubricating oil rises close to the tolerance limit, it immediately sends a signal to the controller 3071, the controller 3071 controls the inlet valve 3043 to open, and low-temperature cooling liquid flows into the cooling coil 3041 through the inlet valve 3043, according to the heat exchange principle, the heat of the lubricating oil in the conduit 303 is taken away, at the same time, the outlet valve 3042 controls the cooling liquid to be discharged to maintain the cooling efficiency, so that the temperature of the lubricating oil falls to the appropriate interval, the good lubricating performance is restored, the stable lubricating film is formed to reduce the friction coefficient and the power loss, the transmission efficiency is improved, finally, the lubricating oil is accurately returned to the inside of the differential body 1 through the peristaltic pump 305 and the return pipe 306, so that the lubricating oil is always in a good lubricating and heat dissipation state, the failure risk is reduced, and a solid foundation is laid for the continuous and safe operation of the aviation transmission device.

[0042] The above is only a preferred embodiment of the present application, and is not intended to limit the present application, and any modification, equivalent replacement and improvement made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A differential for an aircraft transmission system, comprising a differential body (1), characterized in that: The differential body (1) is provided with a gear structure (2) inside, and a circulation processing mechanism (3) is provided on the right side of the differential body (1). The circulation processing mechanism (3) includes a lower oil hopper (301) embedded inside the differential body (1). The right side of the lower oil hopper (301) penetrates the interior of the differential body (1). A filter structure (302) is bolted to the right side of the differential body (1). The left side of the filter structure (302) is connected to the right side of the lower oil hopper (301). A conduit (303) is connected to the right side of the filter structure (302). A cooling structure (3) is provided on the outside of the conduit (303). 04), a peristaltic pump (305) is bolted to the right side of the differential body (1). The absorption end of the peristaltic pump (305) is connected to the top of the conduit (303). The output end of the peristaltic pump (305) is connected to the return pipe (306). The return pipe (306) is connected to the rear side of the differential body (1). A temperature monitoring structure (307) is provided on the right side of the differential body (1). The temperature monitoring structure (307) is electrically connected to the cooling structure (304).

2. A differential for an aircraft transmission system according to claim 1, characterized in that: The filter structure (302) includes a filter box (3021) bolted to the right side of the differential body (1), and the left side of the filter box (3021) is connected to the right side of the lower oil hopper (301).

3. A differential for an aircraft transmission system according to claim 2, characterized in that: The top of the filter box (3021) is bolted with a cover (3022), and a magnetic filter screen (3023) is bolted to the left side of the top of the cover (3022).

4. A differential for an aircraft transmission system according to claim 3, characterized in that: An impurity filter (3024) is bolted to the right side of the top of the cover (3022), and a base plate (3025) is bolted to the bottom of the impurity filter (3024) and the magnetic filter (3023).

5. A differential for an aircraft transmission system according to claim 1, characterized in that: The cooling structure (304) includes a cooling coil (3041) disposed outside the conduit (303), and a water outlet valve (3042) is connected to the left side of the cooling coil (3041), and the water outlet valve (3042) is located on the left side of the conduit (303).

6. A differential for an aircraft transmission system according to claim 5, characterized in that: The cooling coil (3041) is connected to a water inlet valve (3043) on the right side, and the water inlet valve (3043) is located on the right side of the conduit (303).

7. A differential for an aircraft transmission system according to claim 6, characterized in that: The temperature monitoring structure (307) includes an automatic controller (3071) bolted to the right side of the differential body (1), and the automatic controller (3071) is electrically connected to the outlet valve (3042) and the inlet valve (3043) respectively.

8. A differential for an aircraft transmission system according to claim 7, characterized in that: A temperature sensor (3072) is bolted to the right side of the differential body (1). The sensing end of the temperature sensor (3072) is located inside the differential body (1). The temperature sensor (3072) is electrically connected to the automatic controller (3071).

Images