Fuel oil test device for unmanned aerial vehicle aeroengine main shaft bearing

Abstract

The invention discloses a fuel oil test device for an aircraft engine main shaft bearing of an unmanned aerial vehicle. The fuel oil test device comprises a test platform, a test base, an axial loading device, a radial loading device and a rotation driving device. The test base is fixed on the test platform, the radial loading device and the rotation driving device are respectively arranged at two sides of the test base, and the axial loading device is arranged above the test base. A test cavity is arranged in the test base, a to-be-tested bearing is arranged in the test cavity, and an aviation kerosene through hole is formed in the cavity; a rotating shaft of the rotation driving device extends into the test cavity and is sleeved with the bearing. A heating sleeve is embedded in the test cavity corresponding to the position of the bearing and sleeves the outer ring of the bearing; and the test cavity is provided with a gas inlet and a gas outlet for inputting and discharging flame-retardant gas. The device can simulate the working state of a bearing fuel oil environment, guarantees safety through temperature control of the heating sleeve and introduction of flame-retardant gas, and is compact in structure and accurate and reliable in test result.

Description

Technical Field

[0001] This invention relates to the field of aero-engine bearing testing technology, and more specifically to a fuel testing device for the main shaft bearing of an unmanned aerial vehicle (UAV) engine. Background Technology

[0002] Aero engines are the power units of various aircraft, and their performance directly affects the performance and safety of the aircraft. As a critical component of the engine, the main shaft bearing of the aero engine can cause the engine to malfunction and lead to a major accident if a problem occurs. Therefore, various performance tests must be carried out after the bearing is manufactured.

[0003] In aero engines used in fields such as heavy-duty drones, aviation fuel is used to lubricate bearings to reduce weight. However, the lubrication effect of aviation fuel is not ideal. This device was designed to verify whether the bearings can meet the requirements under these conditions. The outer ring of the main shaft bearing near the combustion chamber experiences very high temperatures, while the inner ring remains relatively cool due to airflow. Furthermore, testing with aviation fuel at high temperatures poses significant risks. However, without testing, it is impossible to determine whether the bearing performance meets the standards.

[0004] Aviation fuel is highly volatile, and high-temperature heating is required to better simulate operating conditions, making testing risky. The industry lacks dedicated equipment for verifying bearing performance under extreme conditions. Once this equipment is put into use, it can rapidly conduct verification and accelerate the development of miniaturized and lightweight aero-engines.

[0005] When a bearing fails during a test, it seizes instantly, generating extremely high-temperature sparks. Since the lubricating oil is fuel oil, the temperature at this time is sufficient to ignite the fuel oil, causing combustion or explosion, which can harm the equipment and personnel. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the present invention aims to provide a fuel testing device for the main shaft bearing of UAV engines. By setting up a test chamber with a heating jacket and a flame-retardant gas circulation system, the safety risks of high-temperature fuel testing are solved, and the performance of the bearing is verified under extreme operating conditions.

[0007] To achieve the above objectives, the present invention provides the following technical solution: a fuel testing device for a main shaft bearing of an unmanned aerial vehicle (UAV) engine, comprising a test platform, a test base, an axial loading device, a radial loading device, and a rotary drive device. The test base is fixedly installed on the test platform. The radial loading device and the rotary drive device are arranged opposite each other on both sides of the test base. The axial loading device is arranged above the test base. A test cavity is provided inside the test base. The bearing to be tested is placed inside the test cavity. A through hole for aviation kerosene is opened on the test cavity. The rotating shaft of the rotary drive device extends into the test cavity. The bearing to be tested is sleeved on the rotating shaft of the rotary drive device. A heating sleeve is embedded in the test cavity at a position relative to the bearing to be tested. The heating sleeve is sleeved on the outer ring of the bearing to be tested. An air inlet and an air outlet are provided on the test cavity to input flame-retardant gas through the air inlet and to output the input flame-retardant gas through the air outlet.

[0008] As a further improvement of the present invention, the heating jacket is a hollow cylinder with an air inlet and an air outlet on its end face. The heating jacket has multiple heat dissipation channels inside, which are connected to the air inlet and the air outlet. An external air compressor inputs heated gas into the multiple heat dissipation channels through the air inlet to heat the heating jacket, and then cooled gas is output from the air outlet.

[0009] As a further improvement of the present invention, it also includes a mixing chamber, which is connected to the outlet of the heating jacket and also to the inlet port to receive the cooled gas output by the heating jacket, mix it with the flame-retardant gas, and then send it into the inlet port.

[0010] As a further improvement of the present invention, the mixing chamber is provided with a cooling chamber and a mixing chamber. The cooling chamber is connected to the outlet of the heating jacket, and the mixing chamber is connected to the inlet. The cooled gas first enters the cooling chamber to cool down, and then enters the mixing chamber to mix with the flame-retardant gas before being input into the inlet.

[0011] As a further improvement of the present invention, a first partition plate and a second partition plate are provided in the mixing chamber. The first partition plate and the second partition plate are arranged alternately in the mixing chamber to form an S-shaped flow channel structure in the mixing chamber. The lower half of the S-shaped flow channel structure serves as a cooling chamber, and the upper half of the S-shaped flow channel structure serves as a mixing chamber. A plurality of dry ice are provided on the first partition plate so that the dry ice on the first partition plate vaporizes when the gas passes below the first partition plate.

[0012] The beneficial effects of this invention are as follows: by setting a heating jacket inside the test chamber, the high-temperature environment of the bearing outer ring can be accurately simulated, while the inner ring is kept at a low temperature through airflow, realizing the simulation of the temperature gradient under real working conditions; the flame-retardant gas input through the air intake interface can effectively suppress the flammable environment formed by fuel volatilization, solving the combustion and explosion risks of high-temperature fuel tests. The multi-layer flow channel design of the heating jacket ensures uniform heating of the bearing outer ring, and the S-shaped flow channel of the mixing chamber combined with dry ice cooling realizes gas recycling, which reduces energy consumption and improves temperature control accuracy, providing a dedicated device for extreme working condition verification of UAV engine main shaft bearings. Attached Figure Description

[0013] Figure 1 This is a schematic diagram of the fuel testing device for the main shaft bearing of an unmanned aerial vehicle (UAV) engine according to the present invention. Figure 2 for Figure 1 Schematic diagram of the structure of the heating jacket; Figure 3 This is a schematic diagram of the mixing tank. Detailed Implementation

[0014] The present invention will now be described in further detail with reference to the embodiments shown in the accompanying drawings.

[0015] Reference Figure 1As shown, the fuel testing device for the main shaft bearing of a UAV engine in this embodiment includes a test platform 1, a test base 2, an axial loading device 3, a radial loading device 4, and a rotary drive device 5. The test base 2 is fixedly installed on the test platform 1. The radial loading device 4 and the rotary drive device 5 are arranged opposite each other on both sides of the test base 2. The axial loading device 3 is arranged above the test base 2. The test base 2 has a test cavity 6. The bearing to be tested is placed in the test cavity 6. The test cavity 6 has a through hole for aviation kerosene. The rotating shaft of the rotary drive device 5 extends into the test cavity 6. The bearing to be tested is fitted onto the rotating shaft of the rotary drive device 5. A heating sleeve 7 is embedded in the test cavity 6 at a position relative to the bearing to be tested. The heating sleeve 7 is fitted onto the outer ring of the bearing to be tested. The test cavity 6 has an air inlet and an air outlet to input flame-retardant gas through the air inlet and to output the input flame-retardant gas through the air outlet. During operation, the bearing to be tested is installed in the test chamber 6. The rotary drive device 5 drives the bearing to rotate, and the axial loading device 3 and radial loading device 4 apply a preset load. Aviation kerosene enters the test chamber 6 through the through hole for lubrication. The heating sleeve 7 heats the outer ring of the bearing to a set temperature, while flame-retardant gas is continuously introduced into the test chamber 6 to create an inert environment. This solves the problem of easy combustion and explosion of high-temperature fuel in the background technology and realizes safe and reliable bearing performance testing. In this embodiment, in order to ensure the success of the test, only one set of bearings is heated as the test bearing. The high-temperature gas heating fixture 7 is used to simulate the high temperature of the combustion chamber of an aero-engine. In order to prevent the high-temperature gas from entering the test chamber and igniting the fuel, the heating fixture 7 is a high-sealing component.

[0016] Reference Figure 2 As shown, the heating jacket 7 is further shaped as a hollow cylinder. The end face of the heating jacket 7 is provided with an air inlet 71 and an air outlet 72. The heating jacket 7 has multiple layers of heat dissipation channels connected to the air inlet 71 and the air outlet 72. An external air compressor inputs heated gas through the air inlet 71 into the multiple layers of heat dissipation channels to heat the heating jacket 7. The cooled gas is then output from the air outlet 72. This multi-layered channel design ensures a uniform temperature distribution on the inner wall of the heating jacket 7, preventing localized overheating of the bearing outer ring and accurately simulating the temperature field near the combustion chamber. Simultaneously, the high-temperature gas cools naturally after flowing through the channels, creating conditions for subsequent gas recycling.

[0017] Reference Figure 3 As shown, furthermore, a mixing chamber 8 is included. The mixing chamber 8 is connected to the outlet 72 of the heating jacket 7 and also to the inlet port to receive the cooled gas output from the heating jacket 7, mix it with the flame-retardant gas, and then send it into the inlet port. This design realizes gas recycling, reduces the consumption of flame-retardant gas, and maintains the inert atmosphere concentration in the test chamber 6 by mixing new flame-retardant gas.

[0018] Reference Figure 3As shown, the mixing chamber 8 further includes a cooling chamber 81 and a mixing chamber 82. The cooling chamber 81 is connected to the outlet 72 of the heating jacket 7, and the mixing chamber 82 is connected to the inlet port. The cooled gas first enters the cooling chamber 81 for further cooling, and then enters the mixing chamber 82 to mix with the flame-retardant gas before being input into the inlet port. The secondary cooling in the cooling chamber 81 ensures the stability of the gas temperature entering the test chamber 6, preventing high-temperature gas from affecting the accuracy of the bearing inner ring temperature field simulation.

[0019] Reference Figure 3 As shown, the mixing chamber 8 further includes a first partition plate 83 and a second partition plate 84, which are staggered vertically within the mixing chamber 8 to form an S-shaped flow channel structure. The lower half of this S-shaped flow channel structure serves as a cooling chamber 81, and the upper half serves as a mixing chamber 82. Several dry ice crystals 85 are placed on the first partition plate 83 so that the dry ice crystals 85 on the first partition plate 83 vaporize when the gas passes below it. The S-shaped flow channel prolongs the gas residence time, and the vaporization of the dry ice crystals 85 absorbs heat to achieve rapid cooling. Simultaneously, the vaporized carbon dioxide can be used as a supplement for flame-retardant gas, improving the system's safety and environmental friendliness. That is, the high-temperature gas after passing through the heating jacket 7 still retains residual heat and pressure. Direct discharge is also wasteful; to better utilize the remaining gas, it is introduced into a stainless steel housing 8, such as... Figure 3 As shown, the cooling chamber 81 cools naturally, while the mixing chamber 82 contains slowly vaporizing dry carbon dioxide ice for further cooling. Simultaneously, the vaporizing dry ice produces a large amount of carbon dioxide. Ultimately, this forms low-temperature carbon dioxide gas, similar to a carbon dioxide fire extinguisher.

[0020] This invention achieves safe testing of UAV engine main shaft bearings under high-temperature fuel conditions by constructing an integrated testing device comprising a test chamber 6, a heating jacket 7, and a mixing chamber 8. The heating jacket 7 simulates the high-temperature environment of the outer ring, the flame-retardant gas circulation system mitigates the risk of fuel explosion, and the S-shaped flow channel and dry ice 85 cooling design of the mixing chamber 8 improve temperature control accuracy and gas utilization efficiency. This effectively verifies the bearing's performance under extreme conditions and provides a key testing method for the lightweight development of aero-engines.

[0021] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A fuel testing device for the main shaft bearing of an unmanned aerial vehicle (UAV) engine, comprising a test platform (1), a test base (2), an axial loading device (3), a radial loading device (4), and a rotary drive device (5), wherein the test base (2) is fixedly mounted on the test platform (1), the radial loading device (4) and the rotary drive device (5) are arranged opposite to each other on both sides of the test base (2), and the axial loading device (3) is arranged above the test base (2), characterized in that: The test base (2) is provided with a test chamber (6), the bearing to be tested is placed in the test chamber (6), the test chamber (6) is provided with a through hole for aviation kerosene, the rotating shaft of the rotary drive device (5) extends into the test chamber (6), the bearing to be tested is sleeved on the rotating shaft of the rotary drive device (5), a heating sleeve (7) is embedded in the test chamber (6) at a position relative to the bearing to be tested, the heating sleeve (7) is sleeved on the outer ring of the bearing to be tested, the test chamber (6) is provided with an air inlet and an air outlet, so that flame-retardant gas is input through the air inlet and the input flame-retardant gas is sent out through the air outlet.

2. The fuel testing device for UAV engine main shaft bearings according to claim 1, characterized in that: The heating jacket (7) is a hollow cylinder. The end face of the heating jacket (7) is provided with an air inlet (71) and an air outlet (72). The heating jacket (7) has multiple heat dissipation channels inside. The multiple heat dissipation channels are connected to the air inlet (71) and the air outlet (72). An external air compressor inputs heated gas into the multiple heat dissipation channels through the air inlet (71) to heat the heating jacket (7). Then the cooled gas is output from the air outlet (72).

3. The fuel testing device for UAV engine main shaft bearings according to claim 2, characterized in that: It also includes a mixing chamber (8), which is connected to the outlet (72) of the heating jacket (7) and also to the inlet port to receive the cooled gas output by the heating jacket (7), mix it with the flame-retardant gas, and then send it into the inlet port.

4. The fuel testing device for UAV engine main shaft bearings according to claim 3, characterized in that: The mixing chamber (8) is provided with a cooling chamber (81) and a mixing chamber (82). The cooling chamber (81) is connected to the air outlet (72) of the heating jacket (7). The mixing chamber (82) is connected to the air inlet. The cooled gas first enters the cooling chamber (81) to cool down, and then enters the mixing chamber (82) to mix with the flame-retardant gas before being input into the air inlet.

5. The fuel testing device for UAV engine main shaft bearings according to claim 4, characterized in that: The mixing chamber (8) is provided with a first partition plate (83) and a second partition plate (84). The first partition plate (83) and the second partition plate (84) are arranged alternately in the mixing chamber (8) to form an S-shaped flow channel structure in the mixing chamber (8). The lower half of the S-shaped flow channel structure serves as a cooling chamber (81), and the upper half of the S-shaped flow channel structure serves as a mixing chamber (82). The first partition plate (83) is provided with a number of dry ice (85) so that when the gas passes under the first partition plate (83), the dry ice (85) on the first partition plate (83) vaporizes.

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