An aircraft generator with self-stabilizing function

Abstract

This invention discloses an aircraft generator with self-stabilizing function, relating to the field of aircraft generator technology. It includes a housing, a drive unit, a cooling unit, and a heat spreader. The housing serves as the main load-bearing structure, used to mount other components. The drive unit is mounted through a drive chamber and converts externally input torque into electrical energy for storage. The cooling unit cools the entire unit. The heat spreader assists in regulating the oil temperature. Based on the oil temperature rise under different operating conditions, the proportion of oil being cooled is adjusted to regulate the final oil temperature, ensuring that the temperature of the oil re-entering circulation tends to stabilize.

Description

Technical Field

[0001] This invention relates to the field of aircraft generator technology, specifically an aircraft generator with self-stabilizing function. Background Technology

[0002] In recent years, with the continuous development of various aircraft, the requirements for the operational stability of aircraft generators have become increasingly stringent, and one of the decisive factors for the stable operation of generators is temperature control.

[0003] However, under different operating conditions, the oil temperature and flow rate of a generator are unstable, making it prone to thermal runaway. Directly cooling the entire generator with oil can reduce the risk of thermal failure to some extent. However, due to the complex distribution of power components inside the generator, the oil temperature is prone to significant fluctuations after cooling by the existing external circulation system. Excessive temperature reduction can lead to increased oil viscosity, affecting power generation efficiency; while insufficient temperature reduction can result in incomplete cooling, localized heat accumulation in power components, affecting their service life and jeopardizing the overall operational stability of the generator. Summary of the Invention

[0004] The purpose of this invention is to provide an aircraft generator with a self-stabilizing function to solve the problems raised in the prior art.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] An aircraft generator includes a housing, a drive unit, a cooling unit, and a heat exchanger. The housing has a drive chamber, and the drive unit is placed inside the drive chamber. The cooling unit is connected to the housing by pipes and is used to cool the oil. The heat exchanger is connected to the cooling unit and is used to adjust the cooling ratio of the oil.

[0007] The housing serves as the main load-bearing structure, used to install other devices. The drive unit is installed through the drive chamber, which converts the externally input torque into electrical energy for storage. The cooling device cools the entire machine, and the heat dissipation device assists in regulating the temperature of the oil. The proportion of oil being cooled is adjusted according to the oil temperature rise under different operating conditions, thereby regulating the final oil temperature and making the temperature of the oil re-entering the circulation tend to be stable.

[0008] Furthermore, the drive unit includes a stator winding and a hollow rotor shaft. The stator winding is fastened to the drive cavity wall. The hollow rotor shaft is provided with rotor bearings at both ends, and the two rotor bearings are respectively engaged with the two shaft ends of the drive cavity.

[0009] The outer rings of two rotor bearings are installed in the drive cavity, and the inner rings of the rotor bearings are fitted onto the outer rings of the hollow rotor shaft to provide double-end rotational support for the hollow rotor shaft. The stator windings are installed on the wall of the drive cavity. When the input torque drives the hollow rotor shaft to rotate, the coils on the stator windings cut the magnetic field of the permanent magnets on the hollow rotor shaft to generate electricity to power navigation.

[0010] Furthermore, the hollow rotor shaft is provided with oil passages, and several oil injection holes are provided along the circumference of the oil passages. The distance between adjacent oil injection holes decreases sequentially from the vertical center of the hollow rotor shaft in the radial direction to both ends.

[0011] Oil channels are installed on the hollow rotor shaft to guide the oil flow. As the hollow rotor shaft rotates, the oil is thrown out along the injection holes under centrifugal force, improving the cooling effect on the excitation winding through oil immersion cooling. Simultaneously, by adjusting the distribution density of the injection holes, the density is maximized near the rotor bearings at both ends, improving the cooling effect on mechanically contacting components and enhancing lubrication, preventing localized wear from affecting the overall operational stability of the machine.

[0012] Furthermore, the housing is provided with an oil inlet, the cooling device includes a circulating pump, the outlet of the circulating pump is connected to the oil inlet pipe, the end of the oil inlet is connected to the oil passage pipe, and a return oil port is provided on one side of the drive chamber, which is connected to the circulating pump pipe.

[0013] Oil is pumped by a circulating pump, which sends the oil into the oil passage through the inlet. The inlet of the oil passage can be annular. The pressurized oil flows out from the oil passage along the injection hole to cool the internal electrical components. After cooling, the heated oil flows out from the drive chamber through the return port and is guided to the circulating pump for continuous cooling.

[0014] Furthermore, the cooling device also includes a flow divider and heat sinks. The oil return port is connected to the circulation pump pipe through the flow divider. The flow divider is provided with a flow divider groove. The oil return port is connected to the flow divider groove pipe. The end of the flow divider groove is provided with a cooling flow channel and a constant temperature flow channel respectively. The end of the cooling flow channel and the constant temperature flow channel is provided with a mixing flow channel. The outlet of the mixing flow channel is connected to the inlet of the circulation pump. There are several heat sinks. One end of each heat sink is inserted into the cooling flow channel.

[0015] The distributor, with its multi-channel design, introduces oil from the return port into the circulation pump. The oil flowing out of the return port enters the distribution channel. Due to the varying power output of the generator under different operating conditions, the temperature of the circulating oil fluctuates significantly. The distribution channel directs the oil into the cooling channel and the constant temperature channel. The oil entering the cooling channel is cooled by heat sinks to ensure cooling performance, while the oil entering the constant temperature channel is kept warm. This regulates the ratio of the oil entering the cooling and constant temperature channels. When the oil enters the mixing channel, it is remixed, limiting the temperature of the circulating oil to prevent excessively high temperatures from affecting cooling performance and excessively low temperatures from increasing viscous resistance and affecting power generation efficiency.

[0016] Furthermore, the heat equalization device includes an adjustment component and a mounting base. The adjustment component includes a first deformable plate, a second deformable plate, and a lever. The mounting base is fastened to the wall of the distribution channel. One side of the mounting base is fastened to the first deformable plate and the second deformable plate respectively. The first deformable plate and the second deformable plate are fastened together. A sliding groove is provided at the connection between the distribution channel and the cooling channel and the constant temperature channel. The lever is slidably connected to the sliding groove. The lever is provided with a cooling groove, a lever groove, and a constant temperature groove in sequence. The ends of the first deformable plate and the second deformable plate are inserted into the lever groove.

[0017] When the temperature exceeds the limit: the fins move toward the cooling channel, and the overlapping area of ​​the cooling tank and the cooling channel increases.

[0018] The first and second deformation plates are fixed on one side by the mounting bracket. After the oil enters the distribution groove, it contacts and exchanges heat with the first and second deformation plates respectively. After heating and deformation, the two materials with different coefficients of thermal expansion are used to deform the ends of the first and second deformation plates inserted into the actuating groove to one side. During the deformation process, the actuating plate is pushed to slide along the sliding groove. The cooling groove corresponds to the cooling flow channel, and the constant temperature groove corresponds to the constant temperature flow channel. By sliding the actuating plate, the overlap area of ​​the two sets of flow channels can be adjusted. For example, when the temperature is too high, the actuating plate is pushed to move towards the cooling flow channel, the overlap area of ​​the cooling groove and the cooling flow channel increases, and the overlap area of ​​the constant temperature groove and the constant temperature flow channel decreases, so that the amount of oil entering the cooling groove increases, ensuring that the temperature of the oil entering the circulation pump is reduced to the standard value, which facilitates circulation cooling.

[0019] Furthermore, the coefficient of thermal expansion of the first deformation plate is smaller than that of the second deformation plate.

[0020] By setting the difference in thermal expansion coefficients, the deformation of the first deformation piece is smaller than that of the second deformation piece. For example, when the temperature is high, the second deformation piece has a larger deformation and the first deformation piece has a smaller deformation, causing the second deformation piece to bend towards the first deformation piece and push the lever to slide towards the side of the first deformation piece.

[0021] As an optimization, the first and second deformation plates correspond to the cooling channel and the constant temperature channel, respectively. When the lever slides towards the first deformation plate, i.e. when the temperature is too high, it moves towards the cooling channel, increasing the overlap area between the cooling tank and the cooling channel, thereby increasing the proportion of oil entering the cooling channel.

[0022] As an optimization, the cooling channel and the constant temperature channel are arranged at their ends at an angle. By setting the ends at an angle, the cooled oil and the heated oil are impacted and mixed in the mixing channel, so that the temperature is restored to uniformity.

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows: Oil is introduced into the cooling channel and the constant temperature channel respectively through the diversion channel. The oil entering the cooling channel is cooled by the heat sink to ensure circulating cooling performance, while the oil entering the constant temperature channel is kept warm. This adjusts the ratio of the oil entering the cooling channel and the constant temperature channel. When the oil enters the mixing channel, it is remixed, limiting the temperature of the oil entering the circulation to prevent excessively high temperatures from affecting cooling performance. Simultaneously, it prevents excessively low temperatures from increasing viscous resistance and affecting power generation efficiency. When the temperature is too high, the pusher moves the lever towards the cooling channel, increasing the overlap area between the cooling tank and the cooling channel, and decreasing the overlap area between the constant temperature tank and the constant temperature channel. This increases the amount of oil entering the cooling channel, ensuring that the final oil temperature entering the circulation pump is reduced to the standard value, facilitating circulating cooling. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0025] Figure 2 This is a schematic diagram of the drive device structure of the present invention;

[0026] Figure 3 This is a schematic diagram of the hollow rotor shaft structure of the present invention;

[0027] Figure 4 for Figure 2 A magnified view of a portion of the view;

[0028] Figure 5 This is a schematic diagram of the oil cooling structure of the present invention;

[0029] Figure 6 for Figure 5 A partial zoom-in view (B) of the view;

[0030] Figure 7 This is a schematic diagram of the mixed flow circulation of oil after cooling according to the present invention.

[0031] In the diagram: 1. Housing; 11. Oil inlet; 12. Oil return port; 13. Drive chamber; 2. Drive unit; 21. Stator winding; 22. Hollow rotor shaft; 221. Oil injection hole; 222. Oil passage; 23. Rotor bearing; 3. Cooling device; 31. Circulating pump; 32. Flow divider; 321. Flow divider groove; 322. Slide groove; 323. Cooling flow channel; 324. Constant temperature flow channel; 325. Mixing flow channel; 33. Heat sink; 4. Heat dissipation device; 41. Adjustment component; 411. First deformation plate; 412. Second deformation plate; 413. Paddle; 4131. Cooling groove; 4132. Constant temperature groove; 4133. Paddle groove; 42. Mounting base. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0033] Example: Figures 1-7 As shown, the present invention provides a technical solution for an aircraft generator with self-stabilizing function.

[0034] The aircraft generator includes a housing 1, a drive unit 2, a cooling unit 3, and a heat exchanger 4. The housing 1 is provided with a drive chamber 13, and the drive unit 2 is placed in the drive chamber. The cooling unit 3 is connected to the housing 1 by a pipe and is used to cool the oil. The heat exchanger 4 is connected to the cooling unit 3 and is used to adjust the cooling ratio of the oil.

[0035] The housing 1 serves as the main load-bearing structure, used to install other devices. The drive unit 2 is installed through the drive chamber 13. The drive unit 2 is used to convert the externally input torque into electrical energy for storage. The cooling device 3 cools the entire machine. The heat dissipation device 4 is used to assist in regulating the temperature of the oil. According to the temperature rise of the oil under different working conditions, the proportion of oil being cooled is adjusted to regulate the final oil temperature, so that the temperature of the oil re-entering the circulation tends to be stable.

[0036] Furthermore, the drive device 2 includes a stator winding 21 and a rotor hollow shaft 22. The stator winding 21 is fastened to the wall of the drive cavity 13. The rotor hollow shaft 22 is provided with rotor bearings 23 at both ends, and the two rotor bearings 23 are respectively engaged with the two shaft ends of the drive cavity 13.

[0037] The outer rings of two rotor bearings 23 are installed in the drive cavity 13, and the inner rings of the rotor bearings 23 are fitted onto the outer rings of the hollow rotor shaft 22 to provide double-end rotational support for the hollow rotor shaft 22. The stator winding 21 is installed on the wall of the drive cavity 13. When the input torque drives the hollow rotor shaft 22 to rotate, the coils on the stator winding 21 cut the magnetic field of the permanent magnet on the hollow rotor shaft 22 to generate electricity for navigation.

[0038] Furthermore, the hollow rotor shaft 22 is provided with an oil passage 222, and a number of oil injection holes 221 are provided along the circumference of the oil passage 222. The distance between adjacent oil injection holes 221 decreases sequentially from the vertical center of the rotor shaft 22 radially towards both ends.

[0039] Oil channels 222 are provided on the hollow rotor shaft 22 to guide the oil flow. As the hollow rotor shaft 22 rotates, the oil is thrown out along the oil injection holes 221 under the action of centrifugal force. Through oil immersion cooling, the cooling effect on the excitation winding is improved. At the same time, by adjusting the distribution density of the oil injection holes 221, the distribution density of the oil injection holes 221 near the rotor bearings 23 at both ends is maximized, which improves the cooling effect on the mechanical contact parts, enhances the lubrication capacity, and prevents local wear from affecting the overall operational stability of the machine.

[0040] Furthermore, the housing 1 is provided with an oil inlet 11, the cooling device 3 includes a circulation pump 31, the outlet of the circulation pump 31 is connected to the oil inlet 11, the end of the oil inlet 11 is connected to the oil passage 222, and a return oil port 12 is provided on one side of the drive chamber 13, the return oil port 12 is connected to the circulation pump 31.

[0041] Oil is pumped by a circulating pump 31, which delivers oil through the inlet 11 into the oil passage 222. The inlet of the oil passage 222 can be annular. The pressurized oil flows out from the oil passage 222 along the injection hole 221 to cool the internal electrical components. After cooling, the heated oil flows out from the drive chamber 13 through the return port 12 and is guided to the circulating pump 31 for continuous cooling.

[0042] Furthermore, the cooling device 3 also includes a flow divider 32 and heat sinks 33. The oil return port 12 is connected to the circulation pump 31 through the flow divider 32. The flow divider 32 is provided with a flow divider groove 321. The oil return port 12 is connected to the flow divider groove 321 through a pipe. The end of the flow divider groove 321 is provided with a cooling flow channel 323 and a constant temperature flow channel 324 respectively. The end of the cooling flow channel 323 and the constant temperature flow channel 324 is provided with a mixing flow channel 325. The outlet of the mixing flow channel 325 is connected to the inlet of the circulation pump 31. Several heat sinks 33 are provided, and one end of each heat sink 33 is inserted into the cooling flow channel 323.

[0043] The distributor 32, with its multi-channel configuration, introduces oil from the return port 12 into the circulation pump 31. The oil flowing out of the return port 12 enters the distributor 321. Due to the varying power of the generator under different operating conditions, the temperature of the circulating oil fluctuates significantly. The distributor 321 directs the oil into the cooling channel 323 and the constant temperature channel 324 respectively. The oil entering the cooling channel 323 is cooled by the heat sink 33 to ensure the cooling performance of the circulation, while the oil entering the constant temperature channel 324 is kept warm, thereby adjusting the ratio of the oil entering the cooling channel 323 and the constant temperature channel 324. When the oil enters the mixing channel 325, it is remixed, limiting the temperature of the oil entering the circulation to prevent excessively high temperatures from affecting the cooling performance. At the same time, it prevents excessively low temperatures from increasing viscous resistance and affecting power generation efficiency.

[0044] Furthermore, the heat equalization device 4 includes an adjustment component 41 and a mounting base 42. The adjustment component 41 includes a first deformation plate 411, a second deformation plate 412, and a lever 413. The mounting base 42 is fastened to the wall of the diversion channel 321. One side of the mounting base 42 is fastened to the first deformation plate 411 and the second deformation plate 412 respectively. The first deformation plate 411 and the second deformation plate 412 are fastened together. A sliding groove 322 is provided at the connection between the diversion channel 321 and the cooling channel 323 and the constant temperature channel 324. The lever 413 is slidably connected to the sliding groove 322. The lever 413 is provided with a cooling groove 4131, a lever groove 4133, and a constant temperature groove 4132 in sequence. The ends of the first deformation plate 411 and the second deformation plate 412 are inserted into the lever groove 4133.

[0045] When the temperature exceeds the limit: the tweezer 413 moves toward the cooling channel 323, and the overlapping area of ​​the cooling groove 4131 and the cooling channel 323 increases.

[0046] The first deformation plate 411 and the second deformation plate 412 are fixed on one side by the mounting base 42. After the oil enters the diversion groove 321, it contacts and exchanges heat with the first deformation plate 411 and the second deformation plate 412 respectively. After heating and deformation, the use of two materials with different coefficients of thermal expansion causes the ends of the first deformation plate 411 and the second deformation plate 412 inserted into the actuating groove 4133 to deform to one side. During the deformation process, the actuating plate 413 is pushed to slide along the sliding groove 322, where the cooling groove 4131 corresponds to cooling. The constant temperature tank 4132 corresponds to the constant temperature flow channel 324. By sliding the lever 413, the overlapping area of ​​the two sets of flow channels can be adjusted. For example, when the temperature is too high, the lever 413 is pushed to move towards the cooling flow channel 323, the overlapping area of ​​the cooling tank 4131 and the cooling flow channel 323 increases, and the overlapping area of ​​the constant temperature tank 4132 and the constant temperature flow channel 324 decreases, so that the amount of oil entering the cooling tank increases, ensuring that the temperature of the oil entering the circulating pump 31 is reduced to the standard value, which facilitates the circulating cooling.

[0047] Furthermore, the coefficient of thermal expansion of the first deformation plate 411 is less than that of the second deformation plate 412.

[0048] By setting the difference in thermal expansion coefficients, the deformation of the first deformation piece 411 is smaller than that of the second deformation piece 412. For example, when the temperature is high, the second deformation piece 412 has a larger deformation and the first deformation piece 411 has a smaller deformation, causing the second deformation piece 412 to bend toward the first deformation piece 411 and push the lever 413 to slide toward the side of the first deformation piece 411.

[0049] As an optimization, the first deformation plate 411 and the second deformation plate 412 correspond to the cooling channel 323 and the constant temperature channel 324, respectively. When the lever 413 slides towards the first deformation plate 411, that is, when the temperature is too high, it moves towards the cooling channel 323, increasing the overlap area between the cooling groove 4131 and the cooling channel 323, thereby increasing the proportion of oil entering the cooling channel 323.

[0050] As an optimization, the cooling channel 323 and the constant temperature channel 324 are arranged at their ends at an angle. By setting the ends at an angle, the cooled oil and the heated oil are impacted and mixed in the mixing channel 325, so that the temperature is restored to uniformity.

[0051] The working principle of this invention is as follows: Oil is introduced into the cooling channel 323 and the constant temperature channel 324 through the diversion channel 321. The oil entering the cooling channel 323 is cooled by the heat sink 33 to ensure the cooling performance of the circulation. The oil entering the constant temperature channel 324 is kept warm, thereby adjusting the ratio of the oil entering the cooling channel 323 and the constant temperature channel 324. When the oil enters the mixing channel 325, it is mixed again, limiting the temperature of the oil entering the circulation to prevent the temperature from being too high and affecting the cooling performance. At the same time, it prevents the temperature from being too low, which would increase the viscous resistance and affect the power generation efficiency. When the temperature is too high, the pusher 413 moves towards the cooling channel 323, increasing the overlap area of ​​the cooling tank 4131 and the cooling channel 323, and decreasing the overlap area of ​​the constant temperature tank 4132 and the constant temperature channel 324. This increases the amount of oil entering the cooling channel, ensuring that the temperature of the oil entering the circulation pump 31 is reduced to the standard value, which facilitates the circulation cooling.

[0052] It will be apparent to those skilled in the art that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered in all respects as exemplary and non-limiting, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. An aircraft generator with self-stabilizing function, characterized in that: The aircraft generator includes a housing (1), a drive unit (2), a cooling unit (3), and a heat exchanger (4). The housing (1) is provided with a drive chamber (13), and the drive unit (2) is placed in the drive chamber (13). The cooling unit (3) is connected to the housing (1) by a pipe. The cooling unit (3) is used to cool the oil. The heat exchanger (4) is connected to the cooling unit (3) and is used to adjust the cooling ratio of the oil. The cooling device (3) includes a flow divider (32), on which a flow divider groove (321) is provided, and at the end of the flow divider groove (321) a cooling flow channel (323) and a constant temperature flow channel (324) are respectively provided. The heat equalization device (4) includes an adjustment assembly (41) and a mounting base (42). The adjustment assembly (41) includes a first deformation plate (411), a second deformation plate (412), and a lever (413). The mounting base (42) is fastened to the wall of the diversion channel (321). One side of the mounting base (42) is fastened to the first deformation plate (411) and the second deformation plate (412) respectively. The first deformation plate (411) and the second deformation plate (412) are fastened to each other. 12) Fastening connection, the flow channel (321) is provided with a sliding groove (322) at the connection between the flow channel (321) and the cooling channel (323) and the constant temperature channel (324), the lever (413) and the sliding groove (322) are slidably connected, the lever (413) is provided with a cooling groove (4131), a lever groove (4133) and a constant temperature groove (4132) in sequence, and the ends of the first deformation plate (411) and the second deformation plate (412) are inserted into the lever groove (4133); When the temperature exceeds the limit: the tweezer (413) moves toward the cooling channel (323), and the overlapping area of ​​the cooling groove (4131) and the cooling channel (323) increases.

2. An aircraft generator with self-stabilizing function according to claim 1, characterized in that: The drive device (2) includes a stator winding (21) and a hollow rotor shaft (22). The stator winding (21) is fastened to the wall of the drive cavity (13). The two ends of the hollow rotor shaft (22) are respectively provided with rotor bearings (23), and the two rotor bearings (23) are respectively engaged with the two shaft ends of the drive cavity (13).

3. An aircraft generator with self-stabilizing function according to claim 2, characterized in that: The hollow rotor shaft (22) is provided with an oil passage (222), and a plurality of oil injection holes (221) are provided along the circumference of the oil passage (222). The distance between adjacent oil injection holes (221) decreases sequentially from the vertical center of the hollow rotor shaft (22) to both ends.

4. An aircraft generator with self-stabilizing function according to claim 3, characterized in that: The housing (1) is provided with an oil inlet (11), the cooling device (3) includes a circulation pump (31), the outlet of the circulation pump (31) and the oil inlet (11) are connected by a pipe, the end of the oil inlet (11) is connected by an oil passage (222), and a return oil port (12) is provided on one side of the drive chamber (13), the return oil port (12) and the circulation pump (31) are connected by a pipe.

5. An aircraft generator with self-stabilizing function according to claim 4, characterized in that: The cooling device (3) also includes heat sinks (33), the oil return port (12) is connected to the circulation pump (31) through the flow divider (32), the oil return port (12) is connected to the flow divider (321) through the flow divider, the cooling channel (323) and the constant temperature channel (324) are provided with a mixing channel (325) at the end, the outlet of the mixing channel (325) is connected to the inlet of the circulation pump (31), and there are a number of heat sinks (33), one end of the number of heat sinks (33) is inserted into the cooling channel (323).

6. An aircraft generator with self-stabilizing function according to claim 5, characterized in that: The coefficient of thermal expansion of the first deformation plate (411) is less than that of the second deformation plate (412).

7. An aircraft generator with self-stabilizing function according to claim 6, characterized in that: The first deformation plate (411) and the second deformation plate (412) correspond to the cooling channel (323) and the constant temperature channel (324), respectively.

8. An aircraft generator with self-stabilizing function according to claim 7, characterized in that: The ends of the cooling channel (323) and the constant temperature channel (324) are arranged at an angle.

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