Exhaust funnel cooling device for light airplane

Abstract

The utility model relates to the field of aviation science and technology, in particular to an exhaust funnel cooling device for a light airplane, which comprises an exhaust funnel, a cooling sleeve, a water tank, a water delivery pipe, a water pump, a drainage pipe, a cooling component and the like. The bottom of the water tank is connected with a water conveying pipe, the top of the water tank is connected with a drainage pipe, the water conveying pipe and the drainage pipe are communicated with the annular water tank, and a water pump is installed in the middle of the water conveying pipe. Water circularly flows through the water pump, heat emitted by the exhaust funnel is continuously absorbed, the maintenance waiting time is shortened, rapid cooling and cyclic utilization of cooling water are achieved through the dual effects of the refrigeration pieces and the stirring blades, the cooling effect is further optimized, and the service life of the aircraft exhaust system is effectively prolonged.

Description

Technical Field

[0001] The utility model relates to the field of aviation technology, in particular to an exhaust pipe cooling device for light aircraft. Background Art

[0002] With the continuous advancement and popularization of aviation technology, light aircraft, as a flexible and efficient means of air transportation, have shown broad application prospects in a variety of fields, including private flights, agricultural spraying, aerial photography, and emergency rescue. Light aircraft are highly favored by users for their low operating costs, convenient takeoff and landing conditions, and excellent maneuverability. In the power system of light aircraft, the exhaust pipe, as a key component of engine exhaust emissions, not only bears the heavy responsibility of directing high-temperature and high-pressure exhaust gases to the outside world, but is also directly related to the aircraft's operating efficiency and safety. The design of the exhaust pipe must fully consider multiple factors such as exhaust efficiency, noise control, and thermal protection.

[0003] Currently, most light aircraft exhaust pipes on the market are made of high-temperature resistant alloys to withstand the high-temperature airflow generated by engine exhaust. A compact and sophisticated design for a light sport aircraft, published as CN213627730U, aims to minimize the impact on flight performance and reduce noise emissions. However, while pursuing efficient exhaust and low noise, a common problem is that most light aircraft exhaust pipes lack dedicated cooling devices. This means that after long or high-load flights, a large amount of heat energy accumulates in the exhaust pipe and surrounding area, creating a high-temperature environment.

[0004] After the flight, the surface temperature of the exhaust pipe is much higher than the ambient temperature. For maintenance or troubleshooting personnel of light aircraft, burn accidents are very likely to occur. Post-flight inspection requires a long wait, affecting work efficiency. This situation poses a considerable safety hazard. Moreover, the service life of the exhaust pipe that is in a high temperature state for a long time is seriously shortened. Utility Model Content

[0005] In order to overcome the shortcomings of inconvenience in maintenance and shortened service life caused by high temperature, the utility model provides an exhaust pipe auxiliary cooling device for light aircraft.

[0006] Disclosed is an exhaust pipe cooling device for a light aircraft, comprising an exhaust pipe, a cooling sleeve, a water tank, a tank cover, a water pipe, a water pump, a drain pipe and a cooling assembly. The exhaust pipe is provided with a cooling sleeve, a threaded annular water trough is provided in the cooling sleeve, one side of the cooling sleeve is connected to the water tank, the bottom of the water tank is connected to a water pipe, the other end of the water pipe is connected to the cooling sleeve, the top of the water tank is connected to a drain pipe, the other end of the drain pipe is connected to the cooling sleeve, and both the water pipe and the drain pipe are in communication with the annular water trough. A water pump is installed in the middle of the water pipe, a tank cover is threadedly connected to the water tank, and a cooling assembly is provided in the water tank for accelerating the cooling of the liquid in the water tank.

[0007] Optionally, the cooling assembly includes an inclined plate, a refrigeration fin, a driver, a rotating shaft and blades. The inclined plate is laid in the water tank, and the thinner part of the inclined plate is located at the connection between the water pipe and the water tank. The refrigeration fin is laid on the inclined plate. A driver is installed on the outside of the water tank. The driver is electrically connected to the refrigeration fin. A rotating shaft is connected in the water tank, and blades are connected to the rotating shaft. The driver provides power for the rotation of the rotating shaft.

[0008] Optionally, a sealing ring is further included, and a sealing ring is sleeved on the connection between the rotating shaft and the water tank.

[0009] Optionally, a hanging rope is further included, the tank cover is connected to the hanging rope, and the other end of the hanging rope is connected to the water tank.

[0010] Optionally, a stabilizing frame is further included. The cooling sleeve is connected to the stabilizing frame, and the stabilizing frame is respectively connected to the water pipe and the drainage pipe to support them.

[0011] Optionally, an observation window is further included, and a transparent observation window is opened on the water tank.

[0012] Compared with the prior art, the beneficial effects of the present invention are:

[0013] The water is circulated by the water pump, continuously absorbing the heat emitted by the exhaust pipe, shortening the waiting time for maintenance. Through the dual functions of the refrigeration plate and the stirring blade, the cooling water is quickly cooled and recycled, further optimizing the cooling effect and effectively extending the service life of the aircraft exhaust system. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the overall structure of the utility model.

[0015] Figure 2 This is a three-dimensional structural sectional view of the cooling jacket and water tank of the utility model.

[0016] Figure 3 This is a schematic diagram of the connection structure of the rotating shaft, blades and sealing ring of the utility model.

[0017] In the above figures: 1: exhaust pipe, 2: cooling sleeve, 3: annular water tank, 4: water tank, 5: inclined plate, 6: cooling plate, 7: tank cover, 8: water pipe, 9: water pump, 10: drain pipe, 11: drive, 12: rotating shaft, 13: blade, 14: hanging rope, 15: sealing ring, 16: stabilizing frame, 17: observation window. DETAILED DESCRIPTION

[0018] Reference herein to an embodiment means that a particular feature, structure, or characteristic described in connection with the embodiment may be included in at least one embodiment of the present invention. The appearance of such a phrase in various places in the specification does not necessarily refer to the same embodiment, nor does it constitute an independent or alternative embodiment that is mutually exclusive of other embodiments. It is understood, both explicitly and implicitly, by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0019] Example: An exhaust pipe cooling device for a light aircraft, such as Figure 1-Figure 3 As shown, it includes an exhaust pipe 1, a cooling sleeve 2, a water tank 4, a tank cover 7, a water pipe 8, a water pump 9, a drain pipe 10 and a cooling assembly. The exhaust pipe 1 is provided with a cooling sleeve 2, and a threaded annular water trough 3 is opened in the cooling sleeve 2. One side of the cooling sleeve 2 is connected to the water tank 4, and the bottom of the water tank 4 is connected to the water pipe 8. The other end of the water pipe 8 is connected to the cooling sleeve 2. The top of the water tank 4 is connected to the drain pipe 10, and the other end of the drain pipe 10 is connected to the cooling sleeve 2. The water pipe 8 and the drain pipe 10 are both connected to the annular water trough 3. A water pump 9 is installed in the middle of the water pipe 8. The tank 4 is threadedly connected to the tank cover 7. A cooling assembly is provided in the water tank 4 to accelerate the cooling of the liquid in the water tank 4.

[0020] like Figure 1-Figure 3 As shown, the cooling assembly includes an inclined plate 5, a refrigeration fin 6, a driver 11, a rotating shaft 12 and blades 13. The inclined plate 5 is laid in the water tank 4. The thinner part of the inclined plate 5 is located at the connection between the water pipe 8 and the water tank 4. The refrigeration fin 6 is laid on the inclined plate 5. A driver 11 is installed on the outside of the water tank 4. The driver 11 is electrically connected to the refrigeration fin 6. A rotating shaft 12 is connected to the water tank 4 for rotation. The blades 13 are connected to the rotating shaft 12. The driver 11 provides power for the rotation of the rotating shaft 12.

[0021] When the aircraft is in use, the exhaust pipe 1 continuously emits heat. The water pump 9 and the driver 11 are connected to the aircraft's power system. The water pump 9 extracts water from the water tank 4, which flows along the water pipe 8 to the cooling jacket 2, along the annular water trough 3 to the drain pipe 10, and finally flows back into the water tank 4. The driver 11 provides energy to the cooling fins 6, which continuously cool the water in the water tank 4. At the same time, the driver 11 drives the rotating shaft 12 and the blades 13 to rotate, stirring the water in the water tank 4, thereby accelerating the cooling of the water. The water will gradually be consumed during the circulation process, and the tank cover 7 needs to be opened regularly for replenishment.

[0022] like Figure 3 As shown, a sealing ring 15 is also included. The sealing ring 15 is sleeved at the connection between the rotating shaft 12 and the water tank 4. The sealing ring 15 optimizes the sealing performance of the connection between the rotating shaft 12 and the water tank 4, reducing the extra consumption of water.

[0023] like Figure 3 As shown, it also includes a hanging rope 14, which is connected to the box cover 7, and the other end of the hanging rope 14 is connected to the water tank 4. Through the hanging rope 14, when the box cover 7 is unscrewed, the box cover 7 will not be lost, which facilitates the smooth progress of water-adding related steps.

[0024] like Figure 1 As shown, it also includes a stabilizing frame 16. The cooling jacket 2 is connected to the stabilizing frame 16. The stabilizing frame 16 is respectively connected to the water pipe 8 and the drainage pipe 10 to support them. Through the stabilizing frame 16, the aircraft is optimized in the process of moving the water flow during the transportation process.

[0025] like Figure 1 As shown, an observation window 17 is also included. A transparent observation window 17 is opened on the water tank 4. During the maintenance process, the water consumption in the water tank 4 can be directly observed through the observation window 17, and the water quality can be observed at the same time to decide whether it needs to be replenished or replaced.

[0026] During the operation of the aircraft, the heat generated by the exhaust pipe 1 is effectively captured by the cooling jacket 2 and initially dissipated through the threaded annular water tank 3 inside it. The water pump 9 is connected to the power system of the aircraft, continuously extracting cooling water from the water tank 4 and transporting it to the annular water tank 3 of the cooling jacket 2 through the water pipe 8. After the water circulates in the tank, it flows back to the water tank 4 through the drain pipe 10, forming a closed-loop cooling system. At the same time, the cooling component built into the water tank 4 further accelerates the cooling. The inclined plate 5 guides the water flow so that the water flow is quickly cooled under the cover of the cooling plate 6. The driver 11 not only drives the shaft 12 and the blades 13 to rotate to stir the water body to enhance the heat exchange efficiency, but also provides energy to the cooling plate 6 to continuously circulate the water body. Low temperature treatment is carried out. In addition, the sealing ring 15 ensures the sealing of the connection between the rotating shaft 12 and the water tank 4 to reduce water evaporation. The hanging rope 14 is designed to facilitate the management of the box cover 7 to prevent loss. The stabilizing frame 16 enhances the stability of water flow delivery to ensure the reliable operation of the cooling system during high-speed flight. Through the transparent observation window 17, the operator can intuitively monitor the water volume and water quality in the water tank 4, replenish or replace it in time to ensure the continuous and effective operation of the cooling components. When the aircraft stops running, the water pump 9 and the driver 11 connected to the power system will stop working. At this time, the water pump 9 no longer extracts cooling water from the water tank 4, the water flow in the water pipe 8 stops flowing, and the water in the annular water tank 3 in the cooling jacket 2 gradually tends to be still.

[0027] Although the present invention has been described in detail with reference to the above embodiments, it will be apparent to those skilled in the art from this disclosure that various changes or modifications may be made to the present invention without departing from the principles and spirit of the present invention as defined in the claims. Therefore, the detailed description of the disclosed embodiments is intended to illustrate rather than limit the present invention, which shall be defined by the claims.

Claims

1. An exhaust pipe cooling device for a light aircraft, characterized by: The invention comprises an exhaust pipe (1), a cooling sleeve (2), a water tank (4), a tank cover (7), a water pipe (8), a water pump (9), a drain pipe (10) and a cooling assembly. The exhaust pipe (1) is provided with a cooling sleeve (2), a threaded annular water trough (3) is provided in the cooling sleeve (2), one side of the cooling sleeve (2) is connected to the water tank (4), the bottom of the water tank (4) is connected to a water pipe (8), the other end of the water pipe (8) is connected to the cooling sleeve (2), the top of the water tank (4) is connected to a drain pipe (10), the other end of the drain pipe (10) is connected to the cooling sleeve (2), and both the water pipe (8) and the drain pipe (10) are in communication with the annular water trough (3), a water pump (9) is installed in the middle of the water pipe (8), the tank cover (7) is threadedly connected to the water tank (4), and a cooling assembly is provided in the water tank (4) for accelerating the cooling of the liquid in the water tank (4).

2. The exhaust stack cooling device for a light aircraft according to claim 1, characterized in that: The cooling assembly comprises an inclined plate (5), a refrigeration fin (6), a driver (11), a rotating shaft (12) and blades (13). The inclined plate (5) is laid in the water tank (4). The thinner part of the inclined plate (5) is located at the connection between the water pipe (8) and the water tank (4). The refrigeration fin (6) is laid on the inclined plate (5). The driver (11) is installed outside the water tank (4). The driver (11) is electrically connected to the refrigeration fin (6). A rotating shaft (12) is rotatably connected in the water tank (4). The blades (13) are connected to the rotating shaft (12). The driver (11) provides power for the rotation of the rotating shaft (12).

3. The exhaust stack cooling device for a light aircraft according to claim 2, characterized in that: It also includes a sealing ring (15), and the sealing ring (15) is sleeved on the connection between the rotating shaft (12) and the water tank (4).

4. The exhaust stack cooling device for a light aircraft according to claim 3, characterized in that: The utility model also comprises a hanging rope (14), the box cover (7) is connected with the hanging rope (14), and the other end of the hanging rope (14) is connected to the water tank (4).

5. The exhaust stack cooling device for a light aircraft according to claim 4, characterized in that: It also includes a stabilizing frame (16), which is connected to the cooling sleeve (2) and is respectively connected to the water pipe (8) and the drainage pipe (10) to support them.

6. The exhaust stack cooling device for a light aircraft according to claim 5, characterized in that: The utility model also comprises an observation window (17), and a transparent observation window (17) is opened on the water tank (4).

Images