Rotor arrangement for an aircraft starter generator and aircraft starter generator

Abstract

The application relates to the technical field of aviation electric machines, in particular to a rotor device for an aviation starting generator and the aviation starting generator. The rotor device comprises a first wheel body, a second wheel body, a third wheel body, an impeller and a magnetic component. The first wheel body is provided with a central hole used for connecting a central shaft of the aviation starting generator. The second wheel body is located on the outer side of the first wheel body and is spaced apart from the first wheel body along the radial direction of the rotor device. The third wheel body is located on the outer side of the second wheel body and is spaced apart from the second wheel body along the radial direction. The impeller is located between the first wheel body and the second wheel body and is provided with a ventilation hole. The magnetic component is connected to the third wheel body. According to the rotor device, the third wheel body drives the first wheel body to rotate, thereby driving the central shaft to rotate. The impeller is also provided with the ventilation hole to enable air flow, thereby greatly reducing the influence on the main shaft of the aviation engine.

Description

Technical Field

[0001] This application relates to the field of aviation electrical technology, and in particular to a rotor device for an aircraft starter generator and an aircraft starter generator. Background Technology

[0002] In aviation flight systems, starter generators not only serve as starting devices, providing necessary power to the engine during ground startup, but also function as generators to supply electricity to the aircraft during flight. Currently, the rotor assembly of aviation starter generators has a significant impact on the main shaft of the aero-engine due to its rotation, unreasonable layout, harsh working environment, and unsuitability for installation, disassembly, and maintenance. Utility Model Content

[0003] The summary of this application introduces a series of simplified concepts, which will be further explained in detail in the detailed description section. This summary is not intended to limit the key features and essential technical features of the claimed technical solution, nor is it intended to determine the scope of protection of the claimed technical solution.

[0004] This application provides a rotor assembly for an aircraft starter generator, the rotor assembly comprising:

[0005] A first wheel body, the first wheel body being provided with a central hole, the central hole being used to connect to the central shaft of the aircraft starter generator;

[0006] The second wheel is located outside the first wheel and is spaced apart from the first wheel in the radial direction of the rotor device;

[0007] A third wheel body is located outside the second wheel body and is spaced apart from the second wheel body along the radial direction;

[0008] An impeller, located between the first wheel body and the second wheel body, is provided with vent holes; and

[0009] A magnetic component, which is connected to the third wheel.

[0010] According to the present application, a rotor device for an aircraft starter generator includes a first wheel body, a second wheel body, a third wheel body, an impeller, and a magnetic component. The first wheel body has a central hole for connecting to the central shaft of the aircraft starter generator. The second wheel body is located outside the first wheel body and is spaced apart from the first wheel body in the radial direction of the rotor device. The third wheel body is located outside the second wheel body and is spaced apart from the second wheel body in the radial direction. The impeller is located between the first wheel body and the second wheel body and has a vent hole. The magnetic component is connected to the third wheel body. In this way, the rotor device of this application can simultaneously serve as an aircraft starter generator rotor and a ventilation component, thereby fulfilling the functions of engine starting, power generation, and ventilation. The rotation of the third wheel body drives the rotation of the first wheel body, which in turn drives the rotation of the central shaft. The central shaft drives the main shaft of the aircraft engine to rotate, causing the engine piston to move. The impeller is also equipped with ventilation holes to allow air to flow. The rotation of the main shaft of the aircraft engine can drive the rotation of the central shaft, which in turn drives the rotation of the impeller, allowing air to flow into the aircraft engine. The magnetic component rotates with the third wheel body, allowing the coil to cut the magnetic field generated by the magnetic component, thereby generating electricity. This significantly reduces the impact on the main shaft of the aircraft engine, has a reasonable layout, a good working environment, and is convenient for installation, disassembly, and maintenance.

[0011] Optionally, the impeller is provided with a first port, the third impeller body is provided with a second port, and the vent hole connects the first port and the second port.

[0012] Optionally, the third wheel body includes a first wheel portion, a second wheel portion, and a third wheel portion, with the second wheel portion located between the first wheel portion and the third wheel portion, the first wheel portion being connected to the magnetic component, and the third wheel portion being provided with a second opening.

[0013] Optionally, the second wheel portion protrudes from the first wheel portion in the radial direction, and / or the second wheel portion protrudes from the third wheel portion in the radial direction.

[0014] Optionally, the rotor device further includes a slot located between the second wheel body and the third wheel body.

[0015] Optionally, the second wheel body includes an outer wall, the third wheel body includes an inner wall, and the rotor device further includes a spacer wall, the two ends of which are respectively connected to the outer wall and the inner wall, and the outer wall, the inner wall and the spacer wall together form the groove.

[0016] Optionally, the rotor device includes at least two slots, which are spaced apart along the circumferential direction of the rotor device.

[0017] This application also provides an aircraft starter generator, which includes the rotor device described above.

[0018] According to the present application, the aircraft starter generator includes the aforementioned rotor assembly. The rotor assembly includes a first wheel body, a second wheel body, a third wheel body, an impeller, and a magnetic component. The first wheel body has a central hole for connecting to the central shaft of the aircraft starter generator. The second wheel body is located outside the first wheel body and is spaced apart from the first wheel body in the radial direction of the rotor assembly. The third wheel body is located outside the second wheel body and is spaced apart from the second wheel body in the radial direction. The impeller is located between the first wheel body and the second wheel body and has a vent hole. The magnetic component is connected to the third wheel body. In this way, the rotor device can function as a starter, a generator, and a ventilator. The rotation of the third wheel drives the rotation of the first wheel, which in turn drives the central shaft. The central shaft drives the main shaft of the aero-engine, causing the engine piston to move. The impeller is also equipped with vents to allow air to flow. The rotation of the aero-engine main shaft drives the rotation of the central shaft, which in turn drives the impeller to rotate, allowing air to flow into the aero-engine. The magnetic components rotate with the third wheel, allowing the coil to cut the magnetic field generated by the magnetic components, thereby generating electricity. This does not affect the main shaft of the aero-engine. The layout is reasonable, the working environment is good, and installation, disassembly, and maintenance are convenient.

[0019] Optionally, the aircraft starter generator further includes a central shaft connected to the central bore, the central shaft being used to connect to the main shaft of the aircraft engine.

[0020] Optionally, the aircraft starter generator further includes a stator assembly and coils disposed on the stator assembly, the stator assembly being spaced apart from the rotor assembly, the rotor assembly rotating to cause the coils to generate electrical charge.

[0021] Optionally, the aircraft starter generator also includes a power supply unit.

[0022] The power supply device is energized to drive the central shaft to rotate, thereby causing the rotor device and the main shaft to rotate.

[0023] The main shaft rotates to drive air through the rotor assembly into the aircraft engine.

[0024] The main shaft rotates to drive the rotor device to rotate, thereby causing the coil to generate electrical charge. Attached Figure Description

[0025] The following figures are included as part of this application for understanding the application. The figures illustrate embodiments of the application and their descriptions, explaining the apparatus and principles of the application. In the figures,

[0026] Figure 1 This is a front view schematic diagram of a rotor device according to a preferred embodiment of this application;

[0027] Figure 2 for Figure 1 A schematic cross-sectional view of the rotor assembly shown;

[0028] Figure 3 for Figure 1 Another cross-sectional schematic diagram of the rotor device shown;

[0029] Figure 4 This is a cross-sectional schematic diagram of an aircraft starter generator according to a preferred embodiment of this application.

[0030] Explanation of reference numerals in the attached figures:

[0031] 1: Rotor assembly; 2: Central shaft; 3: Main shaft; 4: Coupling; 5: Stator assembly; 6: Coil; 7: Second air intake device;

[0032] 10: First wheel body; 11: Central hole;

[0033] 20: Second round body;

[0034] 221: Outer wall

[0035] 30: Third wheel body; 31: Second mouth;

[0036] 321: First wheel section; 322: Second wheel section; 323: Third wheel section; 324: Inner wall;

[0037] 40: Impeller; 41: Vent hole; 42: First inlet;

[0038] 50: Magnetic components;

[0039] 60: slot;

[0040] 70: partition wall;

[0041] 721: First partition wall; 722: Second partition wall. Detailed Implementation

[0042] The following description provides numerous specific details to offer a more thorough understanding of this application. However, it will be apparent to those skilled in the art that this application can be practiced without one or more of these details. In other instances, certain technical features well-known in the art have not been described to avoid confusion with this application.

[0043] To fully understand this application, detailed portions will be set forth in the following description in order to illustrate it. Obviously, implementation of this application is not limited to the specific details familiar to those skilled in the art. Preferred embodiments of this application are described in detail below; however, other embodiments may exist besides these detailed descriptions, and should not be construed as being limited to the embodiments set forth herein.

[0044] It should be understood that the terminology used herein is intended only to describe particular embodiments and is not intended to limit the scope of this application. The singular forms “a,” “an,” and “the” are also intended to include the plural forms unless the context clearly indicates otherwise. When the terms “comprising” and / or “including” are used in this specification, they indicate the presence of the stated features, integrals, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components, and / or combinations thereof. The terms “upper,” “lower,” “front,” “rear,” “left,” “right,” and similar expressions used in this application are for illustrative purposes only and are not intended to be limiting.

[0045] The ordinal numbers such as "first" and "second" used in this application are merely identifiers and have no other meaning, such as a specific order. In this application, unless otherwise expressly specified and limited, "above" or "below" a second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of a second feature includes the first feature directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" of a second feature includes the first feature directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0046] The specific embodiments of this application will be described in more detail below with reference to the accompanying drawings, which illustrate representative embodiments of this application and are not intended to limit this application.

[0047] An aircraft starter generator is installed on the auxiliary power unit of an aircraft engine to start the engine and provide power. During the engine startup process, the starter generator operates in electric mode to start the engine. After the engine has started and entered normal operating condition, the starter generator operates in generator mode, providing direct current (DC) power to the aircraft's electrical grid.

[0048] The aircraft starter generator described in this application is a flange-type starter generator. It is particularly suitable for applications in hybrid electric vehicles. Figures 1 to 3As shown, this application provides a rotor assembly 1 for an aircraft starter generator, the rotor assembly 1 being rotatable. The rotor assembly 1 includes a first wheel body 10, a second wheel body 20, and a third wheel body 30, the first wheel body 10 and the second wheel body 20 being spaced apart, and the second wheel body 20 and the third wheel body 30 being spaced apart. The first wheel body 10 is constructed in a generally annular structure. The second wheel body 20 is constructed in a generally annular structure. The third wheel body 30 is constructed in a generally annular structure. The second wheel body 20 is located outside the first wheel body 10. The second wheel body 20 is located outside the first wheel body 10 along the radial direction of the rotor assembly 1. The first wheel body 10 and the second wheel body 20 are spaced apart along the radial direction of the rotor assembly 1. The third wheel body 30 is located outside the second wheel body 20. The third wheel body 30 is located outside the second wheel body 20 along the radial direction of the rotor assembly 1. The second wheel body 20 and the third wheel body 30 are spaced apart along the radial direction of the rotor assembly 1.

[0049] like Figure 2 As shown, the aircraft starter generator also includes a central shaft 2, which is used to connect to the rotor assembly 1. The central shaft 2 can be connected to the rotor assembly 1 via bearings. The central shaft 2 can also be connected to the rotor assembly 1 via bolts or other connecting parts. Rotation of the central shaft 2 can drive the rotor assembly 1 to rotate. Rotation of the rotor assembly 1 can drive the central shaft 2 to rotate.

[0050] Specifically, such as Figure 3 As shown, the first wheel body 10 is provided with a central hole 11. The central hole 11 passes through the first wheel body 10. The central hole 11 can be located at the center of the first wheel body 10. The axial direction of the central hole 11 is parallel to the axial direction of the rotor device 1. A central shaft 2 is used to pass through the central hole 11. The central shaft 2 is connected to the first wheel body 10. Rotation of the central shaft 2 can drive the first wheel body 10 to rotate. Rotation of the first wheel body 10 can drive the central shaft 2 to rotate.

[0051] Now return Figure 1 The rotor assembly 1 also includes an impeller 40, which is located between the first wheel body 10 and the second wheel body 20. The impeller 40 includes an inner end and an outer end, which are located at opposite ends of the impeller 40 along the radial direction of the rotor assembly 1. The impeller 40 is connected to the first wheel body 10. The inner end of the impeller 40 is connected to the first wheel body 10. For example, the impeller 40 and the first wheel body 10 can be integrally formed. The impeller 40 is also connected to the second wheel body 20. The outer end of the impeller 40 is connected to the second wheel body 20. For example, the impeller 40 and the second wheel body 20 can be integrally formed. Thus, the impeller 40 and the wheel body are integrally formed, making the rotor assembly 1 integrated and structurally strong.

[0052] The impeller 40 is provided with a vent 41. The vent 41 is used to allow air to pass through. The impeller 40 includes at least two blades, which are spaced apart along the circumferential direction of the rotor device. Vents 41 are formed between adjacent blades. Air from outside the impeller 40 can enter the vents 41. The blades can be constructed as arc-shaped blades. The vent 41 can be constructed as an arc-shaped channel. An arc-shaped channel can be formed between adjacent arc-shaped blades. The impeller 40 rotates, which can increase the air pressure. Air flows in the rotor device 1 in a direction away from the center of the rotor device 1. Air enters the rotor device 1 along the axial direction of the rotor device 1. The impeller 40 rotates. The rotation of the impeller 40 does work on the airflow, causing the airflow to accelerate. Under the action of the rotating impeller 40, the air flows along the radial direction of the rotor device 1 to the outer edge of the rotor device 1. In this embodiment, the "outer edge of the rotor device 1" refers to the edge of the outer surface of the rotor device 1 in the radial direction. The outer edge of the rotor device 1 faces the outside of the rotor device 1 along the radial direction of the rotor device 1. The air then flows to the aircraft engine through the air duct. The air is thrown from the center of the rotor device 1 to the outer edge of the rotor device 1 by centrifugal force, and the pressure gradually increases, eventually being output to the aircraft engine in a stable high-pressure state.

[0053] For example, air flows radially from the rotor assembly 1 to the outside of the third wheel body 30. Air flows radially from the rotor assembly 1 to the outer edge of the third wheel body 30. In this embodiment, the "outer edge of the third wheel body 30" refers to the edge of the outer surface of the third wheel body 30 in the radial direction. The outer edge of the third wheel body 30 faces outwards along the radial direction of the third wheel body 30. Alternatively, air outside the third wheel body 30 can flow radially from the rotor assembly 1 to the center of the end of the rotor assembly 1.

[0054] Combination Figure 2 As shown, the rotor assembly 1 also includes a magnetic component 50, which is connected to the third wheel 30. The magnetic component 50 can be constructed as a permanent magnet. Rotation of the third wheel 30 can drive the magnetic component 50 to rotate. When the key is turned or the start button is pressed, the entire circuit is connected. The power supply device (such as a battery) supplies power to the coil (such as the excitation winding) of the aircraft starter generator, generating a magnetic field. At this time, the aircraft starter generator is in motor mode, ready to drive the aircraft engine. After the coil (such as the excitation winding) is energized, the rotor assembly 1 begins to rotate under the action of the magnetic field.

[0055] The central shaft 2 is connected to the main shaft 3 of the aero-engine, transmitting rotational power to the main shaft 3. For example, the central shaft 2 and the main shaft 3 can be connected together via a coupling 4. The rotation of the central shaft 2 drives the main shaft 3 of the aero-engine to rotate, causing the piston of the aero-engine to begin reciprocating motion, completing processes such as intake, compression, and fuel injection (or ignition). When the aero-engine reaches idle speed and can operate autonomously (such as fuel injection combustion in a diesel engine or spark plug ignition in a gasoline engine), the starting process ends.

[0056] After the aero-engine starts, its speed increases. The main shaft 3 drives the central shaft 2 to rotate, which in turn drives the impeller 40 of the rotor assembly 1 to rotate, thereby driving airflow. Under the action of the rotating impeller 40, the air flows radially along the rotor assembly 1 to the outer edge of the rotor assembly 1. The air then flows through the air passage to the aero-engine for combustion.

[0057] After the aircraft engine starts, its speed increases. The main shaft 3 drives the central shaft 2 to rotate, which in turn drives the rotor assembly 1 to rotate. When the rotor rotates, the magnetic field generated by its magnetic component 50 cuts into the coil (such as the excitation winding). According to the principle of electromagnetic induction, an alternating electromotive force (AC) is generated in the coil.

[0058] When the electrical load is low (such as during idling), the electrical energy generated by the coil can also charge the battery. When the electrical load is high (such as when the refrigeration unit or lighting unit is turned on), the battery and the aircraft starter generator work together to power the electrical appliances, ensuring stable system operation.

[0059] According to the present application, a rotor device 1 for an aircraft starter generator includes a first wheel body 10, a second wheel body 20, a third wheel body 30, an impeller 40, and a magnetic component 50. The first wheel body 10 is provided with a central hole 11 for connecting the central shaft 2 of the aircraft starter generator. The second wheel body 20 is located outside the first wheel body 10 and is spaced apart from the first wheel body 10 in the radial direction of the rotor device 1. The third wheel body 30 is located outside the second wheel body 20 and is spaced apart from the second wheel body 20 in the radial direction. The impeller 40 is located between the first wheel body 10 and the second wheel body 20 and is provided with a vent hole 41. The magnetic component 50 is connected to the third wheel body 30. Thus, the rotor device 1 of this application can simultaneously serve as an aircraft starter generator rotor and a ventilation component, thereby fulfilling the functions of engine starting, power generation, and ventilation. The rotation of the third wheel 30 drives the rotation of the first wheel 10, which in turn drives the rotation of the central shaft 2. The central shaft 2 drives the rotation of the main shaft 3 of the aircraft engine, causing the piston of the engine to move. The impeller 40 is also provided with a ventilation hole 41 to allow air to flow. The rotation of the main shaft 3 of the aircraft engine can drive the rotation of the central shaft 2, which in turn drives the rotation of the impeller 40, allowing air to flow into the aircraft engine. The magnetic component 50 rotates with the third wheel 30, allowing the coil to cut the magnetic field generated by the magnetic component 50, thereby generating electricity. This significantly reduces the impact on the main shaft 3 of the aircraft engine. The mechanical structure is simple, the layout is reasonable, the working environment is good, and the installation, disassembly, and maintenance are convenient.

[0060] like Figure 3 As shown, the impeller 40 is provided with a first port 42, and the third impeller body 30 is provided with a second port 31. The vent 41 connects the first port 42 and the second port 31. The vent 41 is constructed as a bent hole.

[0061] As an optional implementation, this technology employs a centrifugal compressor and motor rotor coupling scheme to achieve an integrated design of the aircraft starter generator and engine. The rotor device of this application can simultaneously serve as both the aircraft starter generator rotor and compressor component, thereby fulfilling the functions of engine starting, power generation, and pressurization. The rotor device can be made of materials such as titanium and aluminum alloy. The control system can control the power supply device to be in a discharging state to start the aircraft engine. Specifically, the discharge of the aircraft starter generator's battery energizes the coil 6 on the stator device 5. The current interacts with the magnetic field generated by the magnetic component 50, thereby driving the magnetic component 50 and the third wheel 30 to rotate. The third wheel 30 drives the impeller 40 to rotate, which in turn drives the central shaft 2 to rotate. The central shaft 2 drives the main shaft 3 of the aircraft engine to rotate, causing the piston of the aircraft engine to move, thus drawing in air. Of course, the number and structure of the impeller 40 in the rotor device 1 of this application can also be adjusted according to different pressure ratios, and this application does not limit this. Different coupling methods between the rotor device 1 and the central shaft 2 of this application will not affect the coupling between the rotor device 1 and the main shaft 3 of the aircraft engine.

[0062] After the aircraft engine starts, the main shaft 3 of the aircraft engine drives the central shaft 2 to rotate. The rotation of the central shaft 2 drives the first wheel 10 to rotate, which in turn drives the third wheel 30 to rotate. The rotation of the third wheel 30 causes the magnetic component 50 to rotate, thereby enabling the coil 6 on the stator device 5 to cut the magnetic field generated by the magnetic component 50, thus causing the coil 6 to generate electricity, thereby generating electricity. The control system can control the power supply device to be in a charging state. The electricity generated by the coil 6 can charge the power supply device.

[0063] When the aircraft starter generator generates electricity, it can also drive airflow. After the aircraft engine starts, the main shaft 3 of the aircraft engine drives the central shaft 2 to rotate. The rotation of the central shaft 2 drives the first wheel body 10 to rotate, which in turn drives the impeller 40 to rotate. The rotation of the impeller 40 causes airflow, for example, air can flow towards the edge of the impeller 40, so that the air is compressed and then delivered to the aircraft engine.

[0064] Air can flow through the impeller 40 to the edge of the rotor device 1. The airflow in the rotor device 1 flows from a small radius to a large radius. Air can enter the vent 41 through the first opening 42. The first opening 42 opens towards the outside of the rotor device 1 along the axial direction. Preferably, the first opening 42 is provided on the end face of the impeller 40. The end face of the impeller 40 faces towards the outside of the rotor device 1 along the axial direction. The end face of the impeller 40 is approximately parallel to the radial direction of the rotor device 1. The axial direction of the first opening 42 is approximately parallel to the axial direction of the central hole 11.

[0065] Air in the vent 41 is discharged through the second port 31. The second port 31 opens towards the outside of the rotor device 1 along the radial direction of the rotor device 1. Preferably, the second port 31 is provided on the outer annular surface of the third wheel body 30. In this embodiment, the "outer annular surface of the third wheel body 30" refers to the annular surface of the third wheel body 30 facing the outside of the rotor device 1 along the radial direction of the rotor device 1. The outer annular surface of the third wheel body 30 is approximately perpendicular to the radial direction of the rotor device 1. The outer annular surface of the third wheel body 30 faces the outside of the rotor device 1 along the radial direction of the rotor device 1. The axial direction of the second port 31 is approximately perpendicular to the axial direction of the central hole 11.

[0066] Thus, air can enter the vent 41 through the end face of the impeller 40 and be discharged through the outer ring surface of the third wheel body 30. In this way, the rotor device 1 can draw air located at the end of the rotor device 1 into the rotor device 1 and discharge it through the outer ring of the rotor device 1. The air is thrown from the center of the rotor device 1 to the outer edge of the third wheel body 30 by centrifugal force, and the pressure gradually increases, eventually forming a stable high-pressure state.

[0067] As an alternative implementation, this technology employs a centripetal turbine and motor rotor coupling scheme to achieve an integrated design of the aircraft starter generator and engine. The rotor device of this application can simultaneously serve as both the aircraft starter generator rotor and turbine component, thereby fulfilling the functions of engine starting, power generation, and propulsion. The rotor device can be made of high-temperature resistant alloys such as nickel-based alloys (Inconel 718), chromium-molybdenum-vanadium steel (25Cr2MoV), and martensitic stainless steel. The control system can control the power supply device to be in a discharging state to start the aircraft engine. Specifically, the discharge of the aircraft starter generator's battery energizes the coil 6 on the stator device 5. The current interacts with the magnetic field generated by the magnetic component 50, thereby driving the magnetic component 50 and the third wheel 30 to rotate. The third wheel 30 drives the impeller 40 to rotate, which in turn drives the central shaft 2 to rotate. The central shaft 2 drives the main shaft 3 of the aircraft engine to rotate, causing the piston of the aircraft engine to move, thus drawing in air. The impeller structure and geometry of the rotor device can be adjusted according to different expansion ratios. For example, the impeller thickness, guide vane angle, impeller radius, and axial length can be adjusted according to different expansion ratios.

[0068] After the aircraft engine starts, the main shaft 3 of the aircraft engine drives the central shaft 2 to rotate. The rotation of the central shaft 2 drives the first wheel 10 to rotate, which in turn drives the third wheel 30 to rotate. The rotation of the third wheel 30 causes the magnetic component 50 to rotate, thereby enabling the coil 6 on the stator device 5 to cut the magnetic field generated by the magnetic component 50, thus causing the coil 6 to generate electricity, thereby generating electricity. The control system can control the power supply device to be in a charging state. The electricity generated by the coil 6 can charge the power supply device.

[0069] When the aircraft starter generator generates electricity, it also drives airflow. After the aircraft engine starts, the main shaft 3 of the aircraft engine drives the central shaft 2 to rotate. The rotation of the central shaft 2 drives the first wheel body 10 to rotate, which in turn drives the impeller 40 to rotate. The rotation of the impeller 40 causes airflow. For example, air can flow towards the center of the impeller 40, so that air is delivered to the aircraft engine.

[0070] Air can flow through impeller 40 to the center of rotor assembly 1. The airflow in rotor assembly 1 flows from a large radius to a small radius. To ensure that air can flow through impeller 40 to the center of rotor assembly 1, such as... Figure 4As shown, air can enter the vent 41 through the second port 31. The air in the vent 41 is discharged through the first port 42. Thus, air can enter the vent 41 through the outer annular surface of the impeller 40 and be discharged through the end face of the third wheel body 30. In this way, the rotor device 1 can draw air located in the outer annular part of the rotor device 1 into the rotor device 1 and discharge it through the end of the rotor device 1. The air flows from the outer edge of the rotor device 1 to the center of the third wheel body 30 under the action of centripetal force. Thus, the integrated coupling of the power generation system and the turbine rotor is realized. The turbine power generation system has a relatively simple structure, and the structural strength of the coupling with the motor can be greatly improved by the centripetal turbine structure.

[0071] As an alternative implementation method, such as Figure 3 As shown, the third wheel body 30 includes a first wheel portion 321, a second wheel portion 322, and a third wheel portion 323, with the second wheel portion 322 located between the first wheel portion 321 and the third wheel portion 323. The second wheel portion 322 is located between the first wheel portion 321 and the third wheel portion 323 along the axial direction of the rotor device 1. The first wheel portion 321 is connected to a magnetic member 50. The magnetic member 50 is connected to the outer annular surface of the third wheel body 30. In particular, the magnetic member 50 is connected to the outer annular surface of the first wheel portion 321. The first wheel portion 321 and the magnetic member 50 can be coupled together by means of adhesive, clamping with a pressure ring, or bolts. Preferably, the rotor device 1 includes at least two magnetic members 50, which are spaced apart along the circumferential direction of the rotor device 1. At least two magnetic members 50 are both disposed on the third wheel body 30. At least two magnetic members 50 are both connected to the first wheel portion 321. As an alternative embodiment, the second wheel portion 322 protrudes from the first wheel portion 321 in the radial direction of the rotor device 1. A stepped portion is formed between the first wheel portion 321 and the second wheel portion 322. This facilitates the positioning of the magnetic member 50.

[0072] The third wheel portion 323 is provided with a second opening 31. Air in the vent 41 can be discharged through the third wheel portion 323. As an alternative embodiment, the second wheel portion 322 protrudes from the third wheel portion 323 in the radial direction of the rotor device 1. A step is formed between the second wheel portion 322 and the third wheel portion 323. This facilitates the discharge of air from the second opening 31. The first wheel portion 321 and the third wheel portion 323 are separated by the second wheel portion 322. The magnetic member 50 and the second opening 31 are separated by the second wheel portion 322. This avoids air interference with the operation of the magnetic member 50 and facilitates positioning.

[0073] As an optional implementation, the rotor assembly 1 further includes a groove 60 located between the second impeller body 20 and the third impeller body 30. The groove 60 is recessed inward along the axial direction of the rotor assembly 1. The opening direction of the groove 60 is open along the axial direction of the rotor assembly 1. This reduces the weight of the rotor assembly 1. Preferably, the groove 60 also serves for heat dissipation. The groove 60 can reduce the temperature of the second impeller body 20 and the third impeller body 30. Specifically, the second impeller body 20 includes an outer wall 221 that faces away from the impeller 40 along the radial direction of the rotor assembly 1. The outer wall 221 of the second impeller body 20 faces the third impeller body 30. The third impeller body 30 includes an inner wall 324 that faces the second impeller body 20 along the radial direction of the rotor assembly 1. The outer wall 221 of the second impeller body 20 can form a sidewall of the groove 60. The inner wall 324 of the third wheel body 30 can form another side wall of the groove 60. The impeller 40 can form the bottom wall of the groove 60.

[0074] Combination Figure 1 The rotor assembly 1 shown also includes a spacer wall 70 located between the second wheel body 20 and the third wheel body 30. The two ends of the spacer wall 70 are connected to the outer wall 221 and the inner wall 324, respectively. The spacer wall 70 is integrally formed with the second wheel body 20. The inner end of the spacer wall 70 along the radial direction of the rotor assembly 1 is connected to the outer wall 221 of the second wheel body 20. The spacer wall 70 is integrally formed with the third wheel body 30. The outer end of the spacer wall 70 along the radial direction of the rotor assembly 1 is connected to the inner wall 324 of the third wheel body 30. The outer wall 221, the inner wall 324, and the spacer wall 70 together form a groove 60. The temperature of the outer wall 221 of the second wheel body 20 can be dissipated through the hollow groove 60. The temperature of the inner wall 324 of the third wheel body 30 can be dissipated through the hollow groove 60.

[0075] The rotor device 1 includes at least two slots 60, which are spaced apart along the circumferential direction of the rotor device 1. For example, the rotor device 1 includes at least two spacer walls 70, which are spaced apart along the circumferential direction of the rotor device 1. For example, the rotor device 1 includes a first spacer wall 721 and a second spacer wall 722, which are spaced apart along the circumferential direction of the rotor device 1. The outer wall 221, the inner wall 324, the first spacer wall 721, and the second spacer wall 722 can together form the slots 60. Of course, the rotor device 1 can also include a greater number of spacer walls 70, such as three, four, or more, to form more slots 60. Thus, at least two slots 60 can share heat dissipation, improving heat dissipation efficiency and reducing weight.

[0076] The rotor device 1 of this application has an annular surface coupled with a magnetic component 50 to form a starter generator rotor, and is connected to an aero-engine via a central shaft 2. The rotor device 1 of this application can perform centrifugal compression, and the third wheel 323 is also coupled with the magnetic component 50 to form a motor rotor. The rotor device 1 of this application is also coupled with the central shaft 2 to connect to the main shaft 3 of the aero-engine for drive. The rotor device 1 of this application can simultaneously serve as an aero-starter generator rotor and a ventilation component, thereby fulfilling the functions of engine starting, power generation, and ventilation. Of course, the number and structure of the impellers 40 in the rotor device 1 of this application can be adjusted according to different pressure ratios, and this application does not limit this. Different coupling methods between the rotor device 1 and the central shaft 2 of this application will not affect the coupling between the rotor device 1 and the main shaft 3 of the aero-engine.

[0077] This application also provides an aircraft starter generator, which includes the rotor device 1 described above.

[0078] According to the present application, the aircraft starter generator includes the aforementioned rotor assembly 1. The rotor assembly 1 includes a first wheel body 10, a second wheel body 20, a third wheel body 30, an impeller 40, and a magnetic component 50. The first wheel body 10 is provided with a central hole 11 for connecting the central shaft 2 of the aircraft starter generator. The second wheel body 20 is located outside the first wheel body 10 and is spaced apart from the first wheel body 10 in the radial direction of the rotor assembly 1. The third wheel body 30 is located outside the second wheel body 20 and is spaced apart from the second wheel body 20 in the radial direction. The impeller 40 is located between the first wheel body 10 and the second wheel body 20 and is provided with a vent hole 41. The magnetic component 50 is connected to the third wheel body 30. In this way, the rotor device 1 can function as a starter, a generator, and a ventilator. The rotation of the third wheel 30 drives the rotation of the first wheel 10, which in turn drives the rotation of the central shaft 2. The central shaft 2 drives the rotation of the main shaft 3 of the aero-engine, causing the piston of the engine to move. The impeller 40 is also equipped with a vent 41 to allow air to flow. The rotation of the main shaft 3 of the aero-engine can drive the rotation of the central shaft 2, which in turn drives the rotation of the impeller 40, allowing air to flow into the aero-engine. The magnetic component 50 rotates with the third wheel 30, allowing the coil 6 to cut the magnetic field generated by the magnetic component 50, thereby generating electricity. This does not affect the main shaft 3 of the aero-engine. The layout is reasonable, the working environment is good, and the installation, disassembly, and maintenance are convenient.

[0079] The aircraft starter generator of this application can achieve integrated operation; in particular, the aircraft starter generator of this application can integrate the functions of starter, generator and ventilation.

[0080] The aircraft starter generator also includes a central shaft 2, which is connected to a central hole 11. The central shaft 2 is used to connect to the main shaft 3 of the aircraft engine. The central shaft 2 is also used to connect to the rotor assembly 1. The central shaft 2 can be connected to the rotor assembly 1 via bearings. Alternatively, the central shaft 2 can be connected to the rotor assembly 1 via bolts or other connecting components. Rotation of the central shaft 2 can drive the rotor assembly 1 to rotate. Rotation of the rotor assembly 1 can also drive the central shaft 2 to rotate.

[0081] The first wheel body 10 has a central hole 11. The central hole 11 passes through the first wheel body 10. The central hole 11 can be located at the center of the first wheel body 10. The axial direction of the central hole 11 is parallel to the axial direction of the rotor device 1. A central shaft 2 is inserted through the central hole 11. The central shaft 2 is connected to the first wheel body 10. Rotation of the central shaft 2 can drive the first wheel body 10 to rotate. Rotation of the first wheel body 10 can drive the central shaft 2 to rotate.

[0082] The central shaft 2 is connected to the main shaft 3 of the aero-engine, transmitting rotational power to the main shaft 3. The rotation of the central shaft 2 drives the main shaft 3 of the aero-engine to rotate, causing the piston of the aero-engine to begin reciprocating motion, completing processes such as intake, compression, and fuel injection (or ignition). When the aero-engine reaches idle speed and can run autonomously (such as fuel injection combustion in a diesel engine or spark plug ignition in a gasoline engine), the starting process ends.

[0083] After the aero-engine starts, its speed increases. The main shaft 3 drives the central shaft 2 to rotate, which in turn drives the impeller 40 of the rotor assembly 1 to rotate, thereby driving airflow. Under the action of the rotating impeller 40, the air flows radially along the rotor assembly 1 to the outer edge of the rotor assembly 1. The air then flows through the air passage to the aero-engine for combustion.

[0084] The aircraft starter generator also includes a stator assembly 5 and a coil 6, with the coil 6 disposed on the stator assembly 5. The stator assembly 5 is spaced apart from the rotor assembly 1. The rotor assembly 1 rotates to generate electricity in the coil 6.

[0085] After the aircraft engine starts, its speed increases. The main shaft 3 drives the central shaft 2 to rotate, which in turn drives the rotor assembly 1 to rotate. When the rotor rotates, the magnetic field generated by its magnetic component 50 cuts the coil 6. According to the principle of electromagnetic induction, an alternating electromotive force (AC) is generated in the coil 6.

[0086] When the electrical load is low (such as during idling), the electrical energy generated by coil 6 can also charge the battery. When the electrical load is high (such as when the refrigeration unit or lighting unit is turned on), the battery and the aircraft starter generator work together to power the electrical appliances, ensuring stable system operation.

[0087] The control system can control the power supply device to be in a discharging state to start the aircraft engine. Specifically, the discharge of the battery of the aircraft starter generator energizes the coil 6 on the stator device 5. The current interacts with the magnetic field generated by the magnetic component 50, thereby driving the magnetic component 50 and the third wheel 30 to rotate. The third wheel 30 drives the impeller 40 to rotate, which in turn drives the central shaft 2 to rotate. The central shaft 2 drives the main shaft 3 of the aircraft engine to rotate, causing the piston of the aircraft engine to move, thereby drawing in air.

[0088] After the aircraft engine starts, the main shaft 3 of the aircraft engine drives the central shaft 2 to rotate. The rotation of the central shaft 2 drives the first wheel 10 to rotate, which in turn drives the third wheel 30 to rotate. The rotation of the third wheel 30 causes the magnetic component 50 to rotate, thereby enabling the coil 6 on the stator device 5 to cut the magnetic field generated by the magnetic component 50, thus causing the coil 6 to generate electricity, thereby generating electricity. The control system can control the power supply device to be in a charging state. The electricity generated by the coil 6 can charge the power supply device.

[0089] When the aircraft starter generator generates electricity, it can also drive airflow. After the aircraft engine starts, the main shaft 3 of the aircraft engine drives the central shaft 2 to rotate. The rotation of the central shaft 2 drives the first wheel body 10 to rotate, which in turn drives the impeller 40 to rotate. The rotation of the impeller 40 causes airflow, for example, air can flow towards the edge of the impeller 40, so that the air is compressed and then delivered to the aircraft engine.

[0090] The aircraft starter generator includes multiple rotor units 1, which are spaced apart along the axial direction of the rotor units 1. The rotation of the multiple rotor units 1 can jointly drive airflow, thereby improving the efficiency and pressure of airflow. The rotation of the multiple rotor units 1 can also jointly generate electricity, thereby improving power generation efficiency.

[0091] The rotor device 1 of this application has an annular surface coupled with a magnetic component 50 to form a starter generator rotor, and is connected to an aero-engine via a central shaft 2. The rotor device 1 of this application can perform centrifugal compression, and the third wheel 323 is also coupled with the magnetic component 50 to form a motor rotor. The rotor device 1 of this application is also coupled with the central shaft 2 to connect to the main shaft 3 of the aero-engine for drive. The rotor device 1 of this application can simultaneously serve as an aero-starter generator rotor and a ventilation component, thereby fulfilling the functions of engine starting, power generation, and ventilation.

[0092] In one optional implementation, the aircraft starter generator further includes a first air intake device and a first exhaust device. The first air intake device is connected to a first port 42, and the first exhaust device is connected to a second port 31. Gas from the first air intake device enters the vent 41 through the first port 42. Gas from the vent 41 exits through the second port 31 and enters the first exhaust device.

[0093] The airflow in rotor device 1 flows from a small radius to a large radius. Air from the first intake device can enter the vent 41 through the first port 42. Air from the first intake device can enter through the center of the end face of the rotor device. Air from the first intake device enters the vent 41 through the first port 42. Air in the vent 41 is discharged through the second port 31. The second port 31 is open towards the outside of rotor device 1 in the radial direction. Preferably, the outer annular surface of the third wheel body 30 is provided with the second port 31. Air from the second port 31 can enter the first exhaust device. Thus, air from the first intake device can enter the vent 41 through the center of the end face of the impeller 40 and be discharged to the first exhaust device through the outer annular surface of the third wheel body 30. In this way, rotor device 1 can draw air located at the end of rotor device 1 into rotor device 1 and discharge it through the outer annular portion of rotor device 1, realizing the airflow from a small radius to a large radius.

[0094] As another alternative implementation, such as Figure 4 As shown, the aircraft starter generator also includes a second air intake device 7 and a second exhaust device. The second air intake device 7 is connected to a second port 31, and the second exhaust device is connected to a first port 42. Gas from the second air intake device 7 enters the vent through the second port 31. Gas from the vent exits through the second port 31 and enters the second exhaust device.

[0095] The airflow in the rotor device flows from the larger radius to the smaller radius. Air from the second intake device 7 can enter the vent 41 through the second port 31. Air from the second intake device 7 can enter through the outer annular surface of the rotor device 1. Air from the second intake device 7 enters the vent 41 through the second port 31. Air in the vent 41 is discharged through the first port 42. The first port 42 is open towards the outside of the rotor device 1 along the axial direction. Air from the first port 42 can enter the second exhaust device. Thus, air from the second intake device 7 can enter the vent 41 through the outer annular surface of the impeller 40 and be discharged to the second exhaust device via the end face of the third wheel body 30. In this way, the rotor device 1 can draw air located in the outer annular portion of the rotor device 1 into the rotor device 1 and discharge it through the end of the rotor device 1, realizing the airflow from the larger radius to the smaller radius.

[0096] Unless otherwise defined, the technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used herein is for descriptive purposes only and is not intended to limit the scope of this application. Terms such as “part” or “component” appearing herein can refer to a single part or a combination of multiple parts. Terms such as “installation” or “installation” appearing herein can refer to one component being directly attached to another component or one component being attached to another component via an intermediary. A feature described in one embodiment herein may be applied, alone or in combination with other features, to another embodiment, unless that feature is not applicable in that other embodiment or is otherwise stated.

[0097] This application has been described through the above embodiments; however, it should be understood that the above embodiments are for illustrative purposes only and are not intended to limit this application to the described embodiments. Furthermore, those skilled in the art will understand that this application is not limited to the above embodiments, and many more variations and modifications can be made based on the teachings of this application, all of which fall within the scope of protection claimed in this application. The scope of protection of this application is defined by the appended claims and their equivalents.

Claims

1. A rotor device for an aircraft starter generator, characterized in that, The rotor assembly includes: A first wheel body, the first wheel body being provided with a central hole, the central hole being used to connect to the central shaft of the aircraft starter generator; The second wheel is located outside the first wheel and is spaced apart from the first wheel in the radial direction of the rotor device; A third wheel body is located outside the second wheel body and is spaced apart from the second wheel body along the radial direction; An impeller, located between the first wheel body and the second wheel body, is provided with vent holes; and A magnetic component, which is connected to the third wheel.

2. The rotor device according to claim 1, characterized in that, The impeller is provided with a first port, the third impeller body is provided with a second port, and the vent hole connects the first port and the second port.

3. The rotor device according to claim 2, characterized in that, The third wheel body includes a first wheel portion, a second wheel portion, and a third wheel portion. The second wheel portion is located between the first wheel portion and the third wheel portion. The first wheel portion is connected to the magnetic component. The third wheel portion is provided with a second opening.

4. The rotor device according to claim 3, characterized in that, The second wheel portion protrudes from the first wheel portion in the radial direction, and / or the second wheel portion protrudes from the third wheel portion in the radial direction.

5. The rotor device according to claim 1, characterized in that, The rotor assembly also includes a slot located between the second wheel and the third wheel.

6. The rotor device according to claim 5, characterized in that, The second wheel body includes an outer wall, the third wheel body includes an inner wall, and the rotor device further includes a partition wall. The two ends of the partition wall are respectively connected to the outer wall and the inner wall, and the outer wall, the inner wall and the partition wall together form the groove.

7. The rotor device according to claim 5, characterized in that, The rotor device includes at least two slots, which are spaced apart along the circumferential direction of the rotor device.

8. An aircraft starter generator, characterized in that, The aircraft starter generator includes a rotor assembly according to any one of claims 1-7.

9. The aircraft starter generator according to claim 8, characterized in that, The aircraft starter generator also includes a central shaft connected to the central bore, the central shaft being used to connect to the main shaft of the aircraft engine.

10. The aircraft starter generator according to claim 9, characterized in that, The aircraft starter generator also includes a stator assembly and coils disposed on the stator assembly. The stator assembly is spaced apart from the rotor assembly, and the rotor assembly rotates to cause the coils to generate electrical charge.

11. The aircraft starter generator according to claim 9, characterized in that, The impeller is provided with a first port, the third wheel body is provided with a second port, and the aircraft starter generator also includes a first air intake device and a first exhaust device. The first air intake device is connected to the first port, and the first exhaust device is connected to the second port.

12. The aircraft starter generator according to claim 9, characterized in that, The impeller is provided with a first port, the third wheel body is provided with a second port, and the aircraft starter generator also includes a second air intake device and a second exhaust device. The second air intake device is connected to the second port, and the second exhaust device is connected to the first port.

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