Locking ventilation cooling structure and method

Abstract

This invention relates to the field of aircraft generator cooling technology, specifically to a locking-type ventilation cooling structure and method, comprising: an air outlet, a ventilation housing assembly, an air outlet duct, and multiple air ducts. The air ducts are used to transport heat from the exciter stator, main generator stator, and permanent magnet stator cores and windings of the aircraft generator; the exciter rotor and main generator rotor cores and windings; the magnets of the permanent magnet rotor; and the rectifier diodes and resistors on the exciter bracket. During aircraft flight, the oncoming airflow enters from the air inlet duct outlet, is diverted through multiple air ducts, and exits from the air outlet through a ring channel and the air outlet duct, discharging the heat from the heat-generating components inside the aircraft generator outside the engine. This invention reduces the temperature rise of various heat-generating components of the aircraft generator, prevents insulation aging of these components, and ensures reliability and service life.

Description

Technical Field

[0001] This invention relates to the field of aircraft generator cooling technology, specifically to a locking-type ventilation cooling structure and method. Background Technology

[0002] With the development of aircraft technology and changes in power supply systems and electrical equipment, high-power aircraft generators have become the main power source for aircraft. Aircraft generators are small in size, lightweight, and high-power. Operating under harsh environmental conditions such as high altitude, high speed, and impact, they generate a large amount of heat. An effective cooling system is crucial to ensuring the normal operation of the generator, directly affecting its operating efficiency and reliability. Better cooling conditions result in lower stable temperature rise, lower generator operating temperature, higher reliability, and longer service life.

[0003] Forced ventilation utilizes the dynamic pressure generated during aircraft flight to direct oncoming airflow through ventilation ducts into the generator for cooling. This method offers superior cooling compared to self-cooling and self-ventilation, significantly improving generator heat dissipation. Currently, most aircraft generators employ forced ventilation, with air intake at one end and exhaust at the other. The ventilation duct is typically a casting or sheet metal component, installed on the end cap assembly stop at the non-drive end of the aircraft generator. Cooling air enters the ventilation duct under specific pressure and temperature and is exhausted into the engine nacelle through the generator's drive end window. The generator window is usually covered by a protective cover, which affects heat dissipation. Furthermore, the cover has small openings that allow foreign objects to fall into the generator; therefore, care must be taken to prevent foreign objects from entering during assembly or field maintenance. This ventilation duct structure not only increases the axial length of the aircraft generator but also forces hot air into the engine nacelle, impacting aircraft safety.

[0004] Therefore, there is a need to provide a locking ventilation and cooling structure and method to solve the above problems. Summary of the Invention

[0005] To address the problem that ventilation duct structures not only increase the axial length of aircraft generators but also exhaust hot air into the engine compartment, affecting aircraft safety, this invention provides a locking ventilation and cooling structure and method. The exhaust duct is mounted on the outer ring of the stator assembly via a ventilation shell assembly. The air inlet of the aircraft generator is directly connected to the air duct on the aircraft. Cooling air passes through the aircraft generator and is directly exhausted outside the engine hood through the exhaust duct, thus solving the existing problems.

[0006] The first aspect of this invention provides a locking-type ventilation and cooling structure, which adopts the following technical solution, including: The air outlet is located on the housing of the stator assembly of the aircraft generator, and the air outlet is located on the housing of the stator assembly corresponding to the radial direction of the fan assembly of the aircraft generator. A ventilation housing assembly is detachably connected to the housing of the stator assembly, forming an annular channel between the ventilation housing assembly and the housing of the stator assembly, and the annular channel is connected to the air outlet. An air outlet duct is located on the outer ring of the ventilation housing assembly and is connected to the annular channel; Multiple air ducts are installed inside the aircraft generator, with one end of the air duct connected to the air outlet and the other end of the air duct passing through the end cover assembly of the aircraft generator and connected to the outlet of the air inlet pipe of the aircraft generator. The air ducts are used to transport the iron cores and windings of the exciter stator, main generator stator, and permanent magnet stator of the aircraft generator, the iron cores and windings of the exciter rotor and main generator rotor, the magnets of the permanent magnet rotor, and the heat dissipated by the rectifier diodes and resistors on the exciter bracket. During flight, the oncoming airflow enters through the outlet of the air intake duct, is diverted through multiple air ducts, and then passes through the air outlet in sequence through the annular channel and the air outlet duct to expel the heat from the heat-generating components inside the aircraft engine.

[0007] A further technical solution of the present invention includes multiple air ducts comprising: The first air duct is located on the inner wall of the stator assembly housing, with one end connected to the air outlet and the other end of the first air duct passing through the end cover assembly and the outlet of the air inlet pipe. The second air duct includes the gap between the excitation rotor and the excitation stator of the exciter assembly, and the gap between the main generator rotor and the main generator stator of the main generator assembly. The two gaps are connected to form the second air duct, and one end of the second air duct is connected to the air outlet, and the other end of the second air duct passes through the end cover assembly and the outlet of the air inlet pipe. A mixing channel is located between the hollow shaft and the main generator assembly; The third air duct includes a first channel and a mixed channel formed between the outer periphery of the exciter bracket and the permanent magnet assembly. The first channel and the mixed channel are connected to form the third air duct. One end of the third air duct is connected to the air outlet, and the other end of the third air duct passes through the end cover assembly and is connected to the outlet of the air inlet pipe. And a fourth air duct, which includes a second channel, the second channel and the mixing channel are connected to form a fourth air duct, one end of the fourth air duct is connected to the air outlet, and the other end of the fourth air duct passes through the permanent magnet housing and the end cover assembly in sequence and is connected to the outlet of the air inlet pipe.

[0008] In a further technical solution of the present invention, the inner wall of the stator assembly housing is provided with a plurality of protrusions evenly distributed, and a first air duct is formed between every two protrusions along the axial direction. The end cover assembly is provided with a plurality of air inlet slots, and the end of the stator assembly housing is provided with a first ventilation hole that connects the first ventilation duct and the air inlet slot of the end cover assembly.

[0009] In a further technical solution of the present invention, a plurality of second ventilation holes are provided on the permanent magnet housing, a third air duct is connected to the air inlet groove on the end cover assembly and the air inlet pipe outlet, and a fourth air duct is connected sequentially through the second ventilation holes of the permanent magnet housing, the air inlet groove of the end cover assembly and the air inlet pipe outlet.

[0010] In a further technical solution of the present invention, a third ventilation hole is provided on the end face of the exciter bracket, wherein the first channel and the second channel are connected through the third ventilation hole and the mixing channel on the end face of the exciter bracket.

[0011] In a further technical solution of the present invention, a plurality of support ribs are evenly distributed on the outer circumferential surface of the hollow shaft. The support ribs are arranged along the axial direction of the hollow shaft, and a mixing channel is formed between every two support ribs. The support ribs are connected to the main generator rotor key of the main generator assembly through keyways provided thereon.

[0012] A further technical solution of the present invention is that a total cooling air duct is formed between the end faces of the fan assembly and the main generator assembly of the aircraft generator, which connects the air outlet and the first air duct, the second air duct, the third air duct and the fourth air duct.

[0013] A further technical solution of the present invention includes a ventilation housing assembly comprising: The upper arc-shaped shell and the lower arc-shaped shell are detachably connected at their ends to form a ring structure. The inner ring of the ring structure forms a ring cavity, which is connected to the air outlet. And a connecting shell, the inner ring of which is an arc-shaped surface, the inner ring of which is connected to the outer arc surface of the upper arc-shaped shell, and the connecting shell and the cavity of the upper arc-shaped shell are connected. The air outlet pipe is connected to the side of the connecting shell that is away from the arc-shaped surface of the upper arc-shaped shell.

[0014] In a further technical solution of the present invention, the cavity on the side of the connecting shell away from the arc-shaped surface of the upper arc-shaped shell gradually shrinks, and the outlet of the shrinking section of the cavity is connected to the air outlet pipe.

[0015] The second aspect of this invention provides a method for cooling an aircraft generator, which employs a locking-type ventilation cooling structure provided in the first aspect of this invention to cool the aircraft generator. The cooling steps are as follows: The aircraft generator operates by using an engine to drive the rotor of the generator. Utilizing the dynamic pressure generated by the aircraft during flight, the oncoming airflow is introduced from the outlet of the air intake duct on the aircraft through the air intake slot of the end cover assembly, and then splits into the main cooling air duct after passing through the first air duct, the second air duct, the third air duct, and the fourth air duct. The fan assembly directs the hot airflow into the main cooling duct to the air outlet, and through the annular channel of the ventilation housing assembly, the heat inside the aircraft generator is discharged from the aircraft generator through the air outlet, thus completing the cooling of the aircraft generator.

[0016] The beneficial effects of this invention are: 1. When the rotor of the aircraft generator is rotated by the engine, the present invention utilizes the dynamic pressure generated by the aircraft during flight to introduce the oncoming airflow from the outlet of the air intake pipe through the air intake slot of the end cover assembly. After being split by various air ducts, the airflow passes through the air outlet and the annular channel of the ventilation shell assembly to exhaust the heat inside the aircraft generator from the air outlet pipe to the outside of the aircraft generator, and exhaust the hot air to the outside of the engine compartment, thus completing the cooling of the aircraft generator. For safety reasons, it is necessary to directly exhaust hot air from the generator to the outside of the engine compartment to prevent fires caused by air entering the engine compartment from the generator. The air duct is used to transport heat from the exciter stator, main generator stator, and permanent magnet generator stator cores and windings, the exciter rotor and main generator rotor cores and windings, the permanent magnet generator rotor magnets, and the rectifier diodes and resistors on the exciter bracket. The high-speed rotation of the fan assembly creates an airflow channel, allowing the heat from the exciter stator, main generator stator, and permanent magnet generator stator cores and windings, the exciter rotor, main generator rotor, permanent magnet generator rotor, and the rectifier diodes and resistors on the exciter bracket to be expelled from the generator sequentially through the air outlet, annular channel, and exhaust duct. This reduces the temperature rise of the various heat-generating components of the generator, prevents insulation aging, and ensures reliability and service life. The ventilation housing assembly is mounted on the outer ring of the stator assembly, shortening the axial length of the generator.

[0017] 2. Secondly, when the aircraft generator malfunctions, only the ventilation housing assembly needs to be disassembled to check the internal condition of the aircraft generator and make a preliminary judgment on the fault. There is no need to disassemble the aircraft generator, thereby reducing the workload of maintenance, quickly identifying the fault, and improving maintainability. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the overall structure of an embodiment of a locking ventilation and cooling structure according to the present invention; Figure 2 yes Figure 1 Structural diagram of the central ventilation shell assembly; Figure 3 yes Figure 1 Shell structure diagram of the middle stator assembly; Figure 4 yes Figure 1 Structural diagram of the middle end cap assembly; Figure 5yes Figure 1 Structural diagram of the housing of the permanent magnet generator; Figure 6 yes Figure 1 Structural diagram of the central exciter support; Figure 7 yes Figure 1 Structural diagram of a hollow mandrel; Figure 8 yes Figure 1 Structural diagram of the middle fan assembly; Figure 9 for Figure 2 Schematic diagram of the upper and middle arc-shaped shell assembly; Figure 10 for Figure 2 Schematic diagram of the lower arc-shaped shell assembly; Figure 11 for Figure 2 A schematic diagram of the structure connecting the shell and the air outlet duct.

[0020] In the diagram: 1. Fan assembly; 2. Ventilation housing assembly; 3. Stator assembly; 4. Main generator stator; 5. Exciter stator; 6. Exciter rotor; 7. End cover assembly; 8. Permanent magnet generator housing; 9. Permanent magnet generator rotor; 10. Permanent magnet generator stator; 11. Exciter bracket; 12. Hollow shaft; 13. Main generator rotor; 14. First lower arc-shaped housing; 15. Second lower arc-shaped housing; 16. First upper arc-shaped housing; 17. Second upper arc-shaped housing; 18. Air outlet duct; 19. Locking strap; 20. Pin; 21. Bolt; 22. First air duct; 23. First ventilation hole; 24. First connecting rib; 25. Air inlet slot; 26. Second connecting rib; 27. Second ventilation hole; 28. Third connecting rib; 29. ​​Third ventilation hole; 30. Reinforcing rib; 31. Mixing channel; 32. Keyway; 33. Fan blade; 34. Annular balance groove; 35. Window; 36. Connecting shell. Detailed Implementation

[0021] 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.

[0022] An embodiment of the locking ventilation cooling structure of the present invention, such as... Figure 1As shown, it includes: an air outlet, a ventilation housing assembly 2, an air outlet duct 18, and multiple air ducts. The air outlet is located on the housing of the stator assembly 3 of the aircraft generator (i.e., on the housing of the transmission end of the aircraft generator), and the air outlet is located on the housing of the stator assembly 3 corresponding to the fan assembly 1 of the aircraft generator in the radial direction; the ventilation housing assembly 2 is detachably connected to the housing of the stator assembly 3, and an annular channel is formed between the ventilation housing assembly 2 and the housing of the stator assembly 3, and the annular channel is connected to the air outlet; the air outlet 18 is set on the outer ring of the ventilation housing assembly 2, and the air outlet 18 is connected to the annular channel; multiple air ducts are set inside the aircraft generator, and one end of the air duct is connected to the air outlet, and the other end of the air duct passes through the end cover assembly 7 of the aircraft generator and is connected to the outlet of the air inlet pipe; the air ducts are used to transport the iron cores and windings corresponding to the exciter stator 5, the main generator stator 4, and the permanent magnet stator 10 of the aircraft generator, the iron cores and windings corresponding to the exciter rotor 6 and the main generator rotor 13 of the aircraft generator, the magnets of the permanent magnet rotor 9, and the heat dissipated by the rectifier diodes and resistors on the exciter bracket 11. During flight, the oncoming airflow enters through the outlet of the air intake duct, is diverted through multiple air ducts, and then passes through the air outlet in sequence through the annular channel and the air outlet duct 18 to expel the heat from the heat-generating components inside the aircraft generator outside the aircraft engine, thus completing the cooling of the aircraft generator.

[0023] For example, such as Figure 1As shown, in one specific embodiment, the multiple air ducts include: a first air duct 22, a second air duct, a mixing channel 31, a third air duct, and a fourth air duct. The first air duct 22 is disposed on the inner wall of the stator assembly 3 housing. One end of the first air duct 22 is connected to the air outlet, and the other end of the first air duct 22 passes through the end cover assembly 7 and is connected to the outlet of the air inlet pipe. The second air duct includes the gap between the excitation rotor 6 and the excitation stator 5 of the exciter assembly, and the gap between the main generator rotor 13 and the main generator stator 4 of the main generator assembly. The two gaps form the fourth air duct. The system has two air ducts, one end of which is connected to the air outlet, and the other end of which passes through the end cover assembly 7 and connects to the outlet of the air inlet pipe; a mixing channel 31 is located between the hollow shaft and the main generator assembly; a third air duct includes a first channel formed between the exciter bracket 11 and the outer periphery of the permanent magnet assembly, the first channel and the mixing channel 31 forming the third air duct, one end of which is connected to the air outlet, and the other end of which passes through the end cover assembly 7 and connects to the outlet of the air inlet pipe; a fourth air duct includes the permanent magnet rotor 9 and the permanent magnet stator 1. The gap between 0 forms a second channel, which connects with the mixing channel 31 to form a fourth air duct. One end of the fourth air duct is connected to the air outlet, and the other end of the fourth air duct passes through the permanent magnet housing 8 and the end cover assembly 7 in sequence before connecting to the outlet of the air inlet pipe. Specifically, in this embodiment, the first air duct 22 is used to transport the heat dissipated from the iron core and winding outer ring of the exciter stator 5 and main generator stator 4 of the aero-generator, and the second air duct is used to transport the heat dissipated from the iron core and winding inner ring of the exciter stator 5 and main generator stator 4 of the aero-generator. The third air duct is used to transport the heat dissipated from the iron core and outer winding of the permanent magnet stator 10 of the aircraft generator, the iron core and inner winding of the exciter rotor 6, and the rectifier diodes and resistors on the exciter bracket 11. The fourth air duct is used to transport the heat dissipated from the iron core and inner winding of the permanent magnet stator 10 of the aircraft generator, the magnet outer ring of the permanent magnet rotor 9, and the rectifier diodes and resistors on the exciter bracket 11.

[0024] In this embodiment, such as Figure 3 As shown, the inner wall of the stator assembly 3 housing is evenly provided with multiple protrusions, and a first air duct 22 is formed between every two protrusions along the axial direction, such as... Figure 4 As shown, the end cap assembly 7 has multiple air inlet slots 25, and a first connecting rib 24 is formed between two adjacent air inlet slots 25. The end of the stator assembly 3 housing is provided with a first ventilation hole 23 connecting the first ventilation channel 22 and the end cap assembly; in this embodiment, the stator assembly 3 housing is a casting, such as Figure 3As shown, the stator assembly 3 has 12 ribs cast inside its housing, which press-fit the main generator stator 4 and the exciter stator 5 respectively, forming 12 axially connected first air ducts 22 in the middle. Specifically, the flange end of the stator assembly 3 has an air outlet circumferentially opened, which is connected to the inner cavity of the ventilation housing assembly 2. The end cover assembly 7 has a bearing chamber in its center, and multiple first connecting ribs 24 are designed at the connection of the heated bearing chamber. An air inlet groove 25 is formed between two first connecting ribs 24. The air inlet groove 25 is connected to the ventilation pipe on the aircraft, forcing airflow into the aero generator. The end cover assembly 7 is positioned by a stop, and the circumference of the air inlet groove 25 of the end cover assembly 7 is a 30° inclined surface so that the air inlet groove 25 is connected to the first air duct 22 on the inner wall of the housing.

[0025] In this embodiment, such as Figure 5 As shown, the permanent magnet generator housing 8 has multiple second ventilation holes 27, and a second connecting rib 26 is formed between every two second ventilation holes 27. The second ventilation holes 27 and the air inlet slots 25 on the end cover assembly are correspondingly connected. The fourth air duct is connected to the second ventilation holes 27 of the permanent magnet generator housing 8, the air inlet slots 25 of the end cover assembly 7 and the outlet of the air inlet pipe in sequence. It should be noted that the permanent magnet generator housing 8 is used to press the permanent magnet generator stator 10. The end face of the permanent magnet generator housing 8 is designed with multiple second ventilation holes 27, and a second connecting rib 26 is formed between every two second ventilation holes 27. The second ventilation holes 27 and the air inlet slots 25 on the end cover assembly allow cooling air to enter the permanent magnet generator, thereby discharging the heat emitted by the permanent magnet generator through the fourth air duct, the air outlet, the annular channel of the ventilation shell assembly and then through the air outlet pipe 18.

[0026] In this embodiment, such as Figure 6 As shown, the exciter bracket 11 has a third ventilation hole 29 on its end face, and a third connecting rib 28 is formed between every two third ventilation holes 29. The first channel and the second channel are both connected to the mixing channel 31 through the third ventilation hole 29 on the end face of the exciter bracket 11. It should be noted that a reinforcing rib 30 is also provided between the end face and the inner wall of the exciter bracket 11. One end of the reinforcing rib 30 is connected to the third connecting rib 28, and the other end of the reinforcing rib 30 is connected to the inner wall of the exciter bracket 11 to enhance the rigidity of the exciter bracket 11 and ensure reliable operation of the exciter bracket 11 under high-speed rotation. It should also be noted that, in addition to the exciter rotor 6, the outer surface of the exciter bracket 11 is also equipped with rectifier diodes and resistors, such as... Figure 6 As shown, the end face of the exciter bracket 11 has six third ventilation holes 29, which are used for ventilation and heat dissipation inside the permanent magnet.

[0027] In this embodiment, such as Figure 7As shown, multiple support ribs are evenly distributed on the outer circumferential surface of the hollow shaft 12. The support ribs are arranged along the axial direction of the hollow shaft 12, and a mixing channel 31 is formed between every two support ribs. The support ribs are connected to the main generator rotor 13 of the main generator assembly by keyway 32 provided on them to prevent the press-fitted main generator rotor 13 from rotating circumferentially. The exciter bracket 11 is positioned and press-fitted onto the hollow shaft 12 with a long round key to prevent the press-fitted exciter rotor 6 from rotating circumferentially and to position the exciter bracket 11.

[0028] For example, in one specific embodiment, such as Figure 8 As shown, the fan assembly 1 includes a fan blade 33. One end of the fan blade 33 is an annular hub. The axial end face of the annular hub is provided with an annular balance groove 34. The other end of the fan blade 33 is connected to the hub. The end face of the hub is provided with 6 sets of through holes. The through holes are used to pass through connecting screws to fix the hub and the housing of the rotor assembly 3. The annular balance groove 34 is used to perform dynamic balance correction on the rotor assembly at low speed. Then, the counterweight is fixed with screws after being coated with anaerobic adhesive to prevent the counterweight from moving.

[0029] For example, the ventilation housing assembly includes: Figure 1 As shown, a total cooling air duct is formed between the end faces of the fan assembly 1 of the aircraft generator and the main generator assembly, connecting the air outlet and the first air duct, the second air duct, the third air duct, and the fourth air duct.

[0030] It should be noted that, as Figure 1 As shown, the main generator rotor 13 is press-fitted onto the support rib of the hollow shaft 12. The exciter bracket 11 is positioned and press-fitted onto the hollow shaft 12 using a long round key, so that the third ventilation hole 29 on the exciter bracket 11 corresponds one-to-one with the mixing channel 31 on the hollow shaft 12. The exciter bracket 11 is used to press-fit the exciter rotor 6. The fan assembly 1 is fixed to the end face of the support rib of the hollow shaft 12 with screws. The permanent magnet housing 8 is positioned by a stop and fixed to the end cover assembly 7 with screws. The third ventilation hole 29 of the permanent magnet housing 8 corresponds to the second ventilation hole 27 on the end cover assembly 7. The end cover assembly 7 is positioned by a stop and fastened to the housing of the stator assembly 3 with screws. The housing of the stator assembly 3 contains the main generator stator 4 and the exciter stator 5.

[0031] For example, such as Figure 2 As shown, in one specific embodiment, the ventilation housing assembly 2 includes: an upper arc-shaped housing, a lower arc-shaped housing, and a connecting housing 36. The ends of the upper and lower arc-shaped housings are detachably connected to form an annular structure. The inner ring of the annular structure forms an annular cavity, which communicates with the air outlet. The inner ring of the connecting housing 36 is an arc-shaped surface, and the inner ring of the connecting housing 36 is connected to the outer arc surface of the upper arc-shaped housing. The connecting housing 36 communicates with the cavity of the upper arc-shaped housing. The air outlet pipe 18 is connected to the side of the connecting housing 36 facing away from the arc-shaped surface of the upper arc-shaped housing. It should be noted that, as Figure 2 and Figure 11 As shown, the cavity on the side of the connecting shell 36 away from the arc-shaped surface of the upper arc-shaped shell gradually shrinks, and the outlet of the shrinking section of the cavity is connected to the air outlet pipe 18. The air outlet pipe 18 and the connecting shell 36 are welded by argon arc welding. The air outlet pipe 18 is made of aluminum alloy plate in a bent shape, with a circular orifice, an SR spherical bottom, and an elliptical opening on the surface for welding to the connecting shell 36.

[0032] Among them, such as Figure 2 As shown, in one specific embodiment, both the ends of the upper and lower arc-shaped housings are provided with locking bands 19. The locking bands 19 have mounting grooves, and pins 20 are provided in the mounting grooves. One pin 20 has a through hole, and the other pin 20 has a threaded hole. One end of a bolt 21 is connected to a threaded hole on one pin 20, and the other end of the bolt 21 passes through the other pin 20 and is fixed by a nut. Specifically, in this embodiment, the locking bands 19 are made of aluminum alloy plates bent and welded together, with a semi-circular middle section. The pins 20 are located in the mounting groove, and their ends are fixed in the bending gap of the aluminum alloy plates. One end of the locking band 19 is welded to the corresponding ends of the upper and lower arc-shaped housings. During welding, it should be ensured that the pins 20 are locked in the locking bands 19 and do not loosen. The bolt 21 has a safety hole at its head, which is locked with a safety wire to prevent loosening, and an external thread at its bottom connects to the pins 20.

[0033] Among them, such as Figure 2 and Figure 9 As shown, the upper arc-shaped shell includes: a first upper arc-shaped shell 16 and a second upper arc-shaped shell 17, and the first upper arc-shaped shell 16 and the second upper arc-shaped shell 17 are welded together to form the upper arc-shaped shell, that is, it is formed by bending an aluminum alloy plate. Figure 9 The two upper arc-shaped shells 16 and 17 shown are formed by axially aligning the long sides of two semi-circular arc-shaped plates and welding them together. A window 35 connecting the upper arc-shaped shell 36 is provided within a 120° range of the upper arc-shaped shell. Figure 1 As shown, in order to adapt to the housing shape of stator assembly 3 and improve the sealing between the upper arc-shaped housing and the housing of stator assembly 3, the inner rings of the first upper arc-shaped housing 16 and the second upper arc-shaped housing 17 are matched with the shape of the air outlet of the housing of stator assembly 3. At the same time, a sealing ring is provided at the contact part between the inner rings of the first upper arc-shaped housing 16 and the second upper arc-shaped housing 17 and the housing of stator assembly 3.

[0034] Among them, such as Figure 2 and Figure 10 As shown, the lower arc-shaped shell includes: a first lower arc-shaped shell 14 and a second lower arc-shaped shell 15, and the first lower arc-shaped shell 14 and the second lower arc-shaped shell 15 are welded together to form the lower arc-shaped shell, that is, it is formed by bending an aluminum alloy plate. Figure 10The two lower arc-shaped shells 14 and 15 shown are joined together by welding their long arc edges to form a lower arc-shaped shell, and the inner ring of the lower arc-shaped shell forms an arc-shaped cavity, as shown. Figure 1 As shown, in order to adapt to the housing shape of stator assembly 3 and improve the sealing between the lower arc-shaped housing and the housing of stator assembly 3, the inner rings of the first lower arc-shaped housing 16 and the second lower arc-shaped housing 17 are matched with the shape of the air outlet of the housing of stator assembly 3. At the same time, a sealing ring is provided at the contact part between the inner rings of the first lower arc-shaped housing 16 and the second lower arc-shaped housing 17 and the housing of stator assembly 3.

[0035] A method for cooling an aircraft generator, employing the locking-type ventilation cooling structure of this invention to cool the aircraft generator, comprising the following steps: The aircraft generator operates by using an engine to drive the rotor of the generator. Utilizing the dynamic pressure generated by the aircraft during flight, the oncoming airflow is introduced from the outlet of the air inlet duct through the air inlet slot of the end cover assembly, and then split into the main cooling air duct after passing through the first air duct, the second air duct, the third air duct, and the fourth air duct. The fan assembly directs the hot airflow into the main cooling duct to the air outlet, and through the annular channel of the ventilation housing assembly, the heat inside the aircraft generator is discharged from the aircraft generator through the air outlet duct 18, thus completing the cooling of the aircraft generator.

[0036] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A locking-type ventilation and cooling structure, characterized in that, include: The air outlet is located on the housing of the stator assembly of the aircraft generator, and the air outlet is located on the housing of the stator assembly corresponding to the radial direction of the fan assembly of the aircraft generator. A ventilation housing assembly is detachably connected to the housing of the stator assembly, forming an annular channel between the ventilation housing assembly and the housing of the stator assembly, and the annular channel is connected to the air outlet. An air outlet duct is located on the outer ring of the ventilation housing assembly and is connected to the annular channel; Multiple air ducts are installed inside the aircraft generator, with one end of the air duct connected to the air outlet and the other end of the air duct passing through the end cover assembly of the aircraft generator and connected to the outlet of the air inlet pipe of the aircraft generator. The air ducts are used to transport the iron cores and windings of the exciter stator, main generator stator, and permanent magnet stator of the aircraft generator, the iron cores and windings of the exciter rotor and main generator rotor, the magnets of the permanent magnet rotor, and the heat dissipated by the rectifier diodes and resistors on the exciter bracket. During flight, the oncoming airflow enters through the outlet of the air intake duct, is diverted through multiple air ducts, and then passes through the air outlet in sequence through the annular channel and the air outlet duct to expel the heat from the heat-generating components inside the aircraft generator. Multiple air ducts include: The first air duct is located on the inner wall of the stator assembly housing, with one end connected to the air outlet and the other end of the first air duct passing through the end cover assembly and the outlet of the air inlet pipe. The second air duct includes the gap between the excitation rotor and the excitation stator of the exciter assembly, and the gap between the main generator rotor and the main generator stator of the main generator assembly. The two gaps are connected to form the second air duct, and one end of the second air duct is connected to the air outlet, and the other end of the second air duct passes through the end cover assembly and the outlet of the air inlet pipe. A mixing channel is located between the hollow shaft and the main generator assembly; The third air duct includes a first channel and a mixed channel formed between the outer periphery of the exciter bracket and the permanent magnet assembly. The first channel and the mixed channel are connected to form the third air duct. One end of the third air duct is connected to the air outlet, and the other end of the third air duct passes through the end cover assembly and is connected to the outlet of the air inlet pipe. And a fourth air duct, which includes a second channel formed by the gap between the permanent magnet rotor and the permanent magnet stator, the second channel and the mixing channel are connected to form the fourth air duct, one end of the fourth air duct is connected to the air outlet, and the other end of the fourth air duct passes through the permanent magnet housing and the end cover assembly in sequence and is connected to the outlet of the air inlet pipe.

2. The locking ventilation and cooling structure according to claim 1, characterized in that, The inner wall of the stator assembly housing is provided with multiple protrusions evenly distributed, and a first air duct is formed between every two protrusions along the axial direction. Multiple air inlet slots are provided on the end cover assembly, and a first ventilation hole is provided at the end of the stator assembly housing that connects the first air duct and the air inlet slot of the end cover assembly.

3. The locking-type ventilation and cooling structure according to claim 1, characterized in that, The permanent magnet housing has multiple second ventilation holes, the third air duct is connected to the air inlet slot on the end cover assembly and the air inlet pipe outlet, and the fourth air duct is connected to the second ventilation holes of the permanent magnet housing, the air inlet slot of the end cover assembly and the air inlet pipe outlet in sequence.

4. The locking ventilation and cooling structure according to claim 1, characterized in that, The exciter bracket has a third ventilation hole on its end face. The first channel and the second channel are connected to the mixing channel through the third ventilation hole on the end face of the exciter bracket.

5. The locking ventilation and cooling structure according to claim 1, characterized in that, Multiple support ribs are evenly distributed on the outer circumferential surface of the hollow shaft. The support ribs are arranged along the axial direction of the hollow shaft, and a mixing channel is formed between every two support ribs. The support ribs are connected to the main generator rotor key of the main generator assembly through the keyway provided on them.

6. The locking ventilation and cooling structure according to claim 1, characterized in that, The end faces of the fan assembly and the main generator assembly of the aircraft generator form a total cooling air duct that connects the air outlet and the first air duct, the second air duct, the third air duct, and the fourth air duct.

7. The locking ventilation and cooling structure according to claim 1, characterized in that, The ventilation housing assembly includes: The upper arc-shaped shell and the lower arc-shaped shell are detachably connected at their ends to form a ring structure. The inner ring of the ring structure forms a ring cavity, which is connected to the air outlet. And a connecting shell, the inner ring of which is an arc-shaped surface, the inner ring of which is connected to the outer arc surface of the upper arc-shaped shell, and the connecting shell and the cavity of the upper arc-shaped shell are connected. The air outlet pipe is connected to the side of the connecting shell that is away from the arc-shaped surface of the upper arc-shaped shell.

8. A locking-type ventilation and cooling structure according to claim 7, characterized in that, The cavity on the side of the connecting shell away from the arc-shaped surface of the upper arc-shaped shell gradually shrinks, and the outlet of the shrinking section of the cavity is connected to the air outlet pipe.

9. A method for cooling an aircraft generator, characterized in that, The aircraft generator is cooled using the locking ventilation cooling structure described in any one of claims 1-8, and the cooling steps are as follows: The aircraft generator operates by using an engine to drive the rotor of the generator. Utilizing the dynamic pressure generated by the aircraft during flight, the oncoming airflow is introduced from the outlet of the air inlet duct through the air inlet slot of the end cover assembly, and then split into the main cooling air duct after passing through the first air duct, the second air duct, the third air duct, and the fourth air duct. The fan assembly directs the hot airflow into the main cooling duct to the air outlet, and through the annular channel of the ventilation housing assembly, the heat inside the aircraft generator is discharged from the aircraft generator through the air outlet, thus completing the cooling of the aircraft generator.

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