Locking type ventilation cooling structure and method
By installing a ventilation shell assembly on the outer ring of the stator assembly housing of the aircraft generator, and using the aircraft's dynamic pressure to introduce airflow, the heat inside the generator is efficiently discharged. This solves the problems of increased axial length and safety of the ventilation duct, and improves the reliability and service life of the generator.
Patent Information
- Application Number
- CN202511137953.7
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-08-14
- Publication Date
- 2025-11-07
AI Technical Summary
The ventilation duct structure of existing aircraft generators increases the axial length of the generator and exhausts hot air into the engine compartment, affecting aircraft safety.
The system adopts a locking ventilation and cooling structure. By setting a ventilation shell assembly on the outer ring of the stator assembly housing, the oncoming airflow is introduced into the generator using the aircraft dynamic pressure. After being split by multiple air ducts, the airflow is discharged outside the engine through the exhaust pipe, thus preventing hot air from entering the engine compartment.
It effectively shortens the axial length of the generator, prevents hot air from entering the engine compartment, improves safety, reduces the temperature rise of heat-generating components, and extends service life.
Smart Images
Figure CN120915044A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the field of aero-generator cooling technology, in particular to a locking type ventilation cooling structure and method. BACKGROUND
[0002] With the development of aircraft technology, the change of power supply system and electrical equipment, high-power aero-generator becomes the main power supply of aircraft. The aero-generator is small in size, light in weight and high in power, and generates a large amount of heat under the harsh environmental conditions of high altitude, high speed and impact. An effective cooling system is the key to ensure the normal operation of the generator and directly affects the operating efficiency and reliability of the generator. The better the cooling condition is, the lower the stable temperature rise is, and the lower the working temperature of the generator is, the higher the reliability is and the longer the service life is.
[0003] Forced ventilation is to use the dynamic pressure generated by the aircraft in flight to introduce the airflow of the aircraft into the generator through the ventilation pipe for cooling. The cooling effect is better than that of self-cooling and self-ventilation cooling, and the heat dissipation condition of the generator is significantly improved. At present, the aero-generator mostly uses forced ventilation, and the air enters from one end of the ventilation pipe and exits from the other end of the generator. The ventilation pipe is generally a cast or sheet metal part, which is installed on the end cover assembly of the non-driving end of the aero-generator. The cooling air enters the ventilation pipe at a certain pressure and temperature, and is discharged to the engine compartment through the window of the driving end of the generator. The generator window is generally provided with a protective cover, which affects the heat dissipation effect. In addition, the protective cover is provided with a small window, and foreign matters can fall into the generator, so it is necessary to prevent foreign matters from falling into the generator during assembly or field use and maintenance. The structure of the ventilation pipe not only increases the axial length of the aero-generator, but also discharges hot air into the engine compartment, which affects the safety of the aircraft.
[0004] Therefore, it is necessary to provide a locking type ventilation cooling structure and method to solve the above problems. SUMMARY
[0005] In order to solve the problem that the structure of the ventilation pipe not only increases the axial length of the aero-generator, but also discharges hot air into the engine compartment, which affects the safety of the aircraft, the present application provides a locking type ventilation cooling structure and method. The air outlet pipe is arranged on the outer circle of the stator assembly shell through the ventilation shell assembly, the air inlet of the aero-generator is directly connected with the air pipe on the aircraft, the cooling air passes through the aero-generator and is directly discharged outside the engine cover through the air outlet pipe, so as to solve the existing problems.
[0006] The first aspect of the present application provides a locking type ventilation cooling structure, which adopts the following technical scheme, comprising: An air outlet is arranged on the shell of the stator assembly of the aero-generator, and the air outlet is located on the radial corresponding stator assembly shell of the fan assembly of the aero-generator; The ventilation shell assembly is detachably connected to the shell of the stator assembly, and an annular channel is formed between the ventilation shell assembly and the shell of the stator assembly, and the annular channel is communicated with the air outlet; An air outlet pipe is arranged at the outer ring of the ventilation shell assembly and communicated with the annular channel. A plurality of air ducts are arranged in the aero-generator, one end of the air duct is communicated with the air outlet, and the other end of the air duct is communicated with the outlet of the air inlet pipe of the aero-generator through the end cover assembly of the aero-generator; the air duct is used for conveying the heat generated by the corresponding core and winding of the exciter stator, the main generator stator and the permanent magnet stator, the corresponding core and winding of the exciter rotor and the main generator rotor, the magnetic steel of the permanent magnet rotor, and the rectifier diode and resistor on the exciter support. During the flight of the aircraft, the head-on airflow enters from the outlet of the air inlet pipe, is distributed into the plurality of air ducts, and is sequentially discharged from the air outlet through the annular channel and the air outlet pipe, so that the heat of the heating components inside the aero-generator is discharged outside the aero-generator.
[0007] In a further technical solution of the present application, the plurality of air ducts include: A first air duct is arranged on the inner wall of the stator assembly shell, one end of the first air duct is communicated with the air outlet, and the other end of the first air duct is communicated with the outlet of the air inlet pipe through the end cover assembly. A second air duct includes the gap between the exciter rotor and the exciter stator of the exciter assembly, the gap between the main generator rotor and the main generator stator of the main generator assembly, and the second air duct formed by the communication of the two gaps, one end of the second air duct is communicated with the air outlet, and the other end of the second air duct is communicated with the outlet of the air inlet pipe through the end cover assembly. A mixed channel is arranged between the hollow shaft and the main generator assembly. A third air duct includes a first channel and a mixed channel formed between the exciter support and the outer periphery of the permanent magnet assembly, the first channel and the mixed channel are communicated to form the third air duct, one end of the third air duct is communicated with the air outlet, and the other end of the third air duct is communicated with the outlet of the air inlet pipe through the end cover assembly. A fourth air duct includes a second channel, the second channel and the mixed channel are communicated to form the fourth air duct, one end of the fourth air duct is communicated with the air outlet, and the other end of the fourth air duct is communicated with the outlet of the air inlet pipe through the permanent magnet shell, the end cover assembly and the air inlet pipe in sequence.
[0008] In a further technical solution of the present application, a plurality of convex strips are uniformly arranged on the inner wall of the stator assembly shell, a first air duct is formed between every two convex strips in the axial direction, a plurality of air inlet grooves are formed on the end cover assembly, and the end portion of the stator assembly shell is provided with a first ventilation hole communicated with the first air duct and the air inlet grooves of the end cover assembly.
[0009] The further technical scheme of the application is that a plurality of second ventilation holes are formed on the permanent magnet casing, the third air duct is communicated through the air inlet groove on the end cover assembly and the outlet of the air inlet pipe, and the fourth air duct is communicated through the second ventilation holes of the permanent magnet casing, the air inlet groove of the end cover assembly and the outlet of the air inlet pipe in sequence.
[0010] The further technical scheme of the application is that the end surface of the exciter support is provided with a third ventilation hole, wherein the first channel and the second channel are both communicated through the third ventilation hole on the end surface of the exciter support and the mixing channel.
[0011] The further technical scheme of the application is that a plurality of support ribs are uniformly arranged 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, wherein the support ribs are connected with the main generator assembly through the key grooves arranged thereon and the main generator rotor keys.
[0012] The further technical scheme of the application is that the total cooling air duct of the communication air outlet, the first air duct, the second air duct, the third air duct and the fourth air duct is formed between the end surface of the fan assembly and the main generator assembly of the aero-generator.
[0013] The further technical scheme of the application is that the ventilation shell assembly comprises: The upper arc-shaped casing and the lower arc-shaped casing are detachably connected between the end portions to form an annular structure, an annular cavity is formed in the inner ring of the annular structure, and the annular cavity is communicated with the air outlet; and a connecting casing, the inner ring of which is an arc surface, the inner ring of the connecting casing is connected with the outer arc surface of the upper arc-shaped casing, the cavity of the connecting casing and the upper arc-shaped casing is communicated, and the air outlet pipe is connected to the side of the arc surface of the connecting casing away from the upper arc-shaped casing.
[0014] The further technical scheme of the application is that the cavity of the side of the arc surface of the connecting casing away from the upper arc-shaped casing is gradually reduced, and the outlet of the cavity reduction section is communicated with the air outlet pipe.
[0015] The second aspect of the application provides an aero-generator cooling method, which uses the locking type ventilation cooling structure provided in the first aspect of the application to cool the aero-generator, and the cooling steps are as follows: The rotor of the aero-generator is rotated by the engine to drive the aero-generator to operate; The dynamic pressure generated by the airplane in flight is used to introduce the oncoming airflow from the outlet of the air inlet pipe on the airplane into the end cover assembly through the air inlet groove, and the airflow is divided into the total cooling air duct through the first air duct, the second air duct, the third air duct and the fourth air duct; The hot airflow in the total cooling air duct is sent to the air outlet under the action of the fan assembly, and the heat in the aero-generator is discharged from the air outlet pipe to the outside of the aero-generator through the annular channel of the ventilation shell assembly, so that the cooling of the aero-generator is completed.
[0016] The beneficial effects of the present application are: 1、The present application utilizes the dynamic pressure generated by the airplane in flight to introduce the oncoming airflow from the outlet of the air inlet pipe on the airplane into the air inlet groove of the end cover assembly, and then through the air ducts, the air outlet, and the annular channel of the ventilation shell assembly to discharge the heat inside the aviation generator outside the aviation generator, and then discharge the hot air outside the engine compartment, thereby completing the cooling of the aviation generator. From the perspective of safety, it is necessary to directly discharge the hot air from the generator outside the cabin to prevent the air entering the engine compartment from the generator from causing a fire; wherein the air duct is used to transport the heat generated by the corresponding cores and windings of the exciter stator, main generator stator, and permanent magnet stator, the corresponding cores and windings of the exciter rotor and main generator rotor, the magnetic steel of the permanent magnet rotor, and the rectifier diode and resistor on the exciter support; the fan assembly rotates at high speed to form an airflow channel, so that the heat generated by the corresponding cores and windings of the exciter stator, main generator stator, and permanent magnet stator, the corresponding cores and windings of the exciter rotor and main generator rotor, and the magnetic steel of the permanent magnet rotor, and the rectifier diode and resistor on the exciter support are sequentially discharged outside the aviation generator through the air outlet, annular channel, and air outlet pipe, thereby reducing the temperature rise of each heat generating component of the aviation generator, preventing the insulation of each component from aging, and ensuring reliability and service life. The ventilation shell assembly is installed on the outer ring of the stator assembly, thereby shortening the axial length of the generator.
[0017] 2、Secondly, when the aviation generator is working abnormally, only the ventilation shell assembly needs to be disassembled to determine the internal condition of the aviation generator and preliminarily judge the fault, without the need to disassemble the aviation generator, thereby reducing the maintenance workload and quickly determining the fault, and improving the maintainability. BRIEF DESCRIPTION OF DRAWINGS
[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained from these drawings without creative labor.
[0019] Figure 1 is a schematic view of the overall structure of an embodiment of the locking type ventilation cooling structure of the present application; Figure 2 is Figure 1 a structure diagram of the ventilation shell assembly in the present application; Figure 3 is Figure 1 a structure diagram of the end cover assembly in the present application; Figure 4 is Figure 1 a structure diagram of the end cover assembly in the present application; Figure 5is Figure 1 Structure diagram of the permanent magnet machine shell; Figure 6 is Figure 1 Structure diagram of the exciter machine support; Figure 7 is Figure 1 Structure diagram of the hollow shaft; Figure 8 is Figure 1 Structure diagram of the fan assembly; Figure 9 is Figure 2 Structure diagram of the upper arc-shaped shell assembly; Figure 10 is Figure 2 Structure diagram of the lower arc-shaped shell assembly; Figure 11 is Figure 2 Structure diagram of the connection between the shell and the air outlet pipe.
[0020] In the figure: 1, fan assembly; 2, ventilation shell assembly; 3, stator assembly; 4, main generator stator; 5, exciter machine stator; 6, exciter machine rotor; 7, end cover assembly; 8, permanent magnet machine shell; 9, permanent magnet machine rotor; 10, permanent magnet machine stator; 11, exciter machine support; 12, hollow shaft; 13, main generator rotor; 14, first lower arc-shaped shell; 15, second lower arc-shaped shell; 16, first upper arc-shaped shell; 17, second upper arc-shaped shell; 18, air outlet pipe; 19, locking belt; 20, pin column; 21, bolt; 22, first air duct; 23, first ventilation hole; 24, first connecting rib; 25, air inlet groove; 26, second connecting rib; 27, second ventilation hole; 28, third connecting rib; 29, third ventilation hole; 30, reinforcing rib; 31, mixing channel; 32, key groove; 33, fan blade; 34, annular balance groove; 35, window; 36, connecting shell. DETAILED DESCRIPTION
[0021] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the protection scope of the present application.
[0022] An embodiment of the locking type ventilation cooling structure of the present application is as shown in Figure 1As shown, the air-cooled aero-generator comprises: an air outlet, a ventilation shell assembly 2, an air outlet pipe 18 and a plurality of air ducts. The air outlet is arranged on the shell of the stator assembly 3 of the aero-generator (i.e. the shell of the drive end of the aero-generator), and the air outlet is located on the shell of the stator assembly 3 corresponding to the fan assembly 1 of the aero-generator in the radial direction; the ventilation shell assembly 2 is detachably connected to the shell of the stator assembly 3, and an annular channel is formed between the ventilation shell assembly 2 and the shell of the stator assembly 3, and the annular channel and the air outlet are in communication; the air outlet pipe 18 is arranged on the outer ring of the ventilation shell assembly 2, and the air outlet pipe 18 is in communication with the annular channel; a plurality of air ducts are arranged in the aero-generator, one end of the air ducts is in communication with the air outlet, and the other end of the air ducts is in communication with the outlet of the air inlet pipe through the end cover assembly 7 of the aero-generator; the air ducts are used to transport the heat generated by the corresponding cores and windings of the exciter stator 5, the main generator stator 4 and the permanent magnet stator 10, the corresponding cores and windings of the exciter rotor 6 and the main generator rotor 13, the magnetic steel of the permanent magnet rotor 9, and the rectifier diodes and resistors on the exciter support 11. During the flight of the aircraft, the oncoming airflow enters from the outlet of the air inlet pipe, is distributed through the plurality of air ducts, and is sequentially discharged from the air outlet through the annular channel and the air outlet pipe 18 to discharge the heat generated by the heat generating components inside the aero-generator outside the aero-generator, thereby completing the cooling of the aero-generator.
[0023] For example, 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 shell of the stator assembly 3 is cast with 12 ribs, respectively, the main generator stator 4, the exciter stator 5 is pressed, and 12 axial through first air duct 22 is formed in the middle, specifically, the flange end of the shell of the stator assembly 3 is circumferentially provided with an air outlet, and the air outlet is communicated with the inner cavity of the ventilation shell assembly 2; the center of the end cover assembly 7 is provided with a bearing chamber, a plurality of first connecting ribs 24 are designed at the connection of the bearing chamber, an air inlet groove 25 is formed between two first connecting ribs 24, and the air inlet groove 25 is communicated with the ventilation pipe on the airplane, so that forced airflow enters the aero-generator, wherein the end cover assembly 7 is positioned by the stopper, and the air inlet groove 25 of the end cover assembly 7 is a 30° inclined surface, so that the air inlet groove 25 is communicated with the first air duct 22 of the inner wall of the shell.
[0025] In this embodiment, as shown in the drawings, Figure 5 As shown, a plurality of second ventilation holes 27 are formed on the permanent magnet machine shell 8, a second connecting rib 26 is formed between every two second ventilation holes 27, the second ventilation hole 27 is communicated with the air inlet groove 25 on the end cover assembly, and the fourth air duct is communicated in turn through the second ventilation hole 27 of the permanent magnet machine shell 8, the air inlet groove 25 of the end cover assembly 7 and the outlet of the air inlet pipe; it should be noted that the permanent magnet machine shell 8 is used for pressing the permanent magnet machine stator 10, a plurality of second ventilation holes 27 are designed on the end face of the permanent magnet machine shell 8, a second connecting rib 26 is formed between every two second ventilation holes 27, and the second ventilation hole 27 is communicated with the air inlet groove 25 on the end cover assembly, so that the cooling air enters the permanent magnet machine, and the heat emitted by the permanent magnet machine is discharged in turn through the fourth air duct, the air outlet, the annular channel of the ventilation shell assembly and the air outlet pipe 18.
[0026] In this embodiment, as shown in the drawings, Figure 6 As shown, the end face of the exciter bracket 11 is provided with a third ventilation hole 29, a third connecting rib 28 is formed between every two third ventilation holes 29, and the first channel and the second channel are communicated through the third ventilation hole 29 and the mixed channel 31 on the end face of the exciter bracket 11; it should be noted that a reinforcing rib 30 is further arranged between the end face of the exciter bracket 11 and the inner wall surface, 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 surface of the exciter bracket 11, so as to enhance the rigidity of the exciter bracket 11 and ensure reliable operation of the exciter bracket 11 under high-speed rotation; it should be noted that the outer surface of the exciter bracket 11 is provided with a rectifier diode and a resistor in addition to the exciter rotor 6, Figure 6 As shown, the end face of the exciter bracket 11 is provided with six third ventilation holes 29, and the third ventilation holes 29 are used for ventilation and heat dissipation in the permanent magnet machine.
[0027] In this embodiment, as shown in the drawings, 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, asFigure 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 first lower arc-shaped shells 14 and the second lower arc-shaped shell 15 are oppositely arranged and welded to form a lower arc-shaped shell body, and an arc-shaped cavity is formed in the inner circle of the lower arc-shaped shell body, as shown in Figure 1 As shown, in order to adapt to the shell shape of the stator assembly 3 and improve the sealing between the lower arc-shaped shell body and the shell of the stator assembly 3, the inner circle of the first lower arc-shaped shell 16 and the second lower arc-shaped shell 17 is shaped to match the shape of the outer circle of the shell of the stator assembly 3 at the air outlet, and a sealing ring is arranged at the contact position of the inner circle of the first lower arc-shaped shell 16 and the second lower arc-shaped shell 17 and the shell of the stator assembly 3.
[0035] An aero-generator cooling method, which adopts the locking type ventilation cooling structure to cool the aero-generator, and the cooling steps are as follows: The engine drags the rotor of the aero-generator to rotate, and the aero-generator operates; The ram air is introduced from the outlet of the air inlet pipe through the air inlet groove of the end cover assembly, and is divided into the total cooling air duct through the first air duct, the second air duct, the third air duct and the fourth air duct; The hot air in the total cooling air duct is sent to the air outlet under the action of the fan assembly, and the heat in the aero-generator is discharged from the air outlet pipe 18 through the annular channel of the ventilation shell assembly, so that the cooling of the aero-generator is completed.
[0036] The above only describes the preferred embodiments of the present application and is not used to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims
1. A lock-type ventilation cooling structure, characterized by, The application relates to an aero-generator, which comprises the following parts: an air outlet arranged on a stator assembly shell of the aero-generator and corresponding to a fan assembly of the aero-generator; a ventilation shell assembly detachably connected to the stator assembly shell and forming an annular channel with the stator assembly shell, wherein the annular channel is communicated with the air outlet; an air outlet pipe arranged on an outer ring of the ventilation shell assembly and communicated with the annular channel; and a plurality of air channels arranged in the aero-generator, one end of each air channel communicated with the air outlet, and the other end of each air channel communicated with an outlet of an air inlet pipe of the aero-generator through an end cover assembly of the aero-generator, wherein the air channels are used for conveying heat generated by corresponding cores and windings of an exciter stator, a main generator stator and a permanent magnet generator stator of the aero-generator, corresponding cores and windings of an exciter rotor and a main generator rotor, magnetic steel of a permanent magnet rotor, and rectifier diodes and resistors on an exciter support. During flight of an airplane, the air current from the outlet of the air inlet pipe enters the air channels and is distributed into the air outlet through the air outlet pipe, the annular channel and the air outlet in sequence, so that the heat generated by the heat generating components in the aero-generator is discharged outside the aero-generator. The plurality of air channels comprises: a first air channel arranged on an inner wall of the stator assembly shell, one end of the first air channel communicated with the air outlet, and the other end of the first air channel communicated with the outlet of the air inlet pipe through the end cover assembly; a second air channel formed by gaps between an exciter rotor and an exciter stator of an exciter assembly and gaps between a main generator rotor and a main generator stator of a main generator assembly, one end of the second air channel communicated with the air outlet, and the other end of the second air channel communicated with the outlet of the air inlet pipe through the end cover assembly; a mixing channel arranged between a hollow shaft and the main generator assembly; a third air channel formed by a first channel between an exciter support and an outer periphery of a permanent magnet assembly and the mixing channel, one end of the third air channel communicated with the air outlet, and the other end of the third air channel communicated with the outlet of the air inlet pipe through the end cover assembly; and a fourth air channel formed by a second channel and the mixing channel, one end of the fourth air channel communicated with the air outlet, and the other end of the fourth air channel communicated with the outlet of the air inlet pipe through the permanent magnet shell, the end cover assembly and the air inlet pipe in sequence. The inner wall of the stator assembly shell is uniformly provided with a plurality of convex strips, a first air channel is formed between every two convex strips in an axial direction, a plurality of air inlet grooves are arranged on the end cover assembly, and the end of the stator assembly shell is provided with a first air hole communicated with the first air channel and the air inlet grooves of the end cover assembly. A plurality of second air holes are arranged on the permanent magnet shell, the third air channel is communicated with the outlet of the air inlet pipe through the air inlet grooves of the end cover assembly, and the fourth air channel is communicated with the outlet of the air inlet pipe through the second air holes of the permanent magnet shell, the air inlet grooves of the end cover assembly and the outlet of the air inlet pipe in sequence. The end surface of the exciter support is provided with a third air hole, and the first channel and the second channel are communicated with the mixing channel through the third air hole on the end surface of the exciter support.
2. The lock-type ventilation cooling structure according to claim 1, wherein 3. The lock vent cooling structure according to claim 2, wherein 4. The lock vent cooling structure according to claim 2, wherein 5. The lock vent cooling structure according to claim 2, wherein 6. The lock vent cooling structure according to claim 2, wherein The hollow shaft is provided with a plurality of support ribs on the outer circumferential surface, the support ribs are arranged along the axial direction of the hollow shaft, and a mixing channel is formed between every two support ribs, wherein the support ribs are connected with the main rotor of the main generator assembly through the key grooves arranged thereon.
7. The lock vent cooling structure according to claim 1, wherein The end surfaces of the fan assembly and the main generator assembly form a total cooling air duct which communicates with the air outlet and the first, second, third and fourth air ducts.
8. The lock vent cooling structure according to claim 1, wherein The ventilation shell assembly comprises: The upper arc-shaped shell and the lower arc-shaped shell are detachably connected between the end portions to form an annular structure, an annular cavity is formed in the inner ring of the annular structure, and the annular cavity is in communication with the air outlet; The connecting shell has an arc-shaped inner ring, the arc-shaped inner ring of the connecting shell is connected with the outer arc surface of the upper arc-shaped shell, the cavity of the connecting shell and the upper arc-shaped shell are in communication, and the air outlet pipe is connected to one side of the arc-shaped surface of the connecting shell which is away from the upper arc-shaped shell.
9. The lock vent cooling structure according to claim 8, wherein The cavity of the connecting shell which is away from the arc-shaped surface of the upper arc-shaped shell gradually narrows, and the outlet of the narrowed cavity is in communication with the air outlet pipe.
10. An aero-generator cooling method, characterized by, The locking ventilation and cooling structure according to any one of claims 1-9 is used to cool the aero-generator, and the cooling steps are as follows: The aero-generator is driven to rotate by the engine; The dynamic pressure generated by the airplane in flight is used to introduce the oncoming airflow from the outlet of the air inlet pipe into the total cooling air duct through the air inlet groove of the end cover assembly, the first, second, third and fourth air ducts, and the total cooling air duct; The hot airflow in the total cooling air duct is sent to the air outlet by the fan assembly, and the heat in the aero-generator is discharged from the air outlet pipe through the annular channel of the ventilation shell assembly, thereby completing the cooling of the aero-generator.