Armature winding cooling device and method for aviation internally cooled generator

Abstract

The embodiment of the present invention discloses an armature winding cooling device and method for an aviation internal cooling generator, and relates to the technical field of aviation three-stage generators. In the present invention, the stator armature winding adopts a hollow conductor, and oil can be directly cooled inside; the hollow conductors between different stator slots are welded together through an oil-electric separation joint to achieve the circuit connection between the conductors of different stator slots; the cooling oil in the hollow conductor is led out by an oil guide hose through the oil-electric separation joint, and the oil inlet plate and the oil return plate are connected to achieve the connection on the oil circuit; during normal operation, the lubricating oil flows from the oil inlet plate under the action of external pressure, passes through the hollow conductor, and then flows out from the oil return plate, thereby taking away the heat generated by the armature winding. The present invention realizes a complete hollow conductor oil circuit structure, and the cooling medium is in direct contact with the armature winding, which can realize the efficient heat dissipation of the stator armature winding, which is beneficial to improving the power density of the motor.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation three-stage generators, and in particular to an armature winding cooling device and method for aviation internally cooled generators. Background Art

[0002] As the main power source of aircraft, aviation three-stage generators have been widely used in the aviation field. Their basic structure includes: main motor, exciter, permanent magnet exciter, and rotating rectifier. The main part of the aviation three-stage generator is the main motor, which is an electrically excited synchronous motor used to output power to the outside. In order to reduce weight and increase power density, aircraft generators have the characteristics of high electrical load and high magnetic load, so their loss and heating problems are very prominent, and they must have a good cooling system.

[0003] For aircraft generators with lower power, air cooling can be used, including: self-ventilation cooling, forced ventilation cooling, and a combination of self-ventilation and forced ventilation cooling. For high-power generators, air cooling can no longer meet the heat dissipation requirements, and oil cooling is usually used. Oil-cooled motors are designed with a special oil circuit, in which aircraft cooling oil is passed, and the heat from the heating parts of the motor is taken away by the cooling oil. Generally, a combination of stator circulating oil + rotor oil injection is used for cooling. A spiral oil channel is designed in the stator housing, and the rotor shaft is a hollow shaft with oil injection holes opened along the circumferential direction.

[0004] However, with the development of hybrid electric propulsion aircraft, the onboard power consumption has increased significantly, requiring more powerful and higher power density aircraft generators, and therefore more efficient cooling methods. Among them, how to improve the cooling method suitable for high power density aircraft internal cooling generators has become a topic that needs in-depth research. Summary of the invention

[0005] The embodiments of the present invention provide an armature winding cooling device and method for an aviation internally cooled generator, which can achieve a highly efficient cooling effect while improving power density.

[0006] To achieve the above object, the embodiments of the present invention adopt the following technical solutions:

[0007] In a first aspect, an embodiment of the present invention provides an armature winding cooling device for an aircraft internally cooled generator, comprising:

[0008] The armature winding cooling device is integrated in the aviation internal cooling type generator, and comprises: a stator core (1), a hollow conductor (2), an oil-electricity separation joint (3), an oil guide hose (4), an oil inlet tray (6) and an oil return tray (7); the oil inlet tray (6) and the oil return tray (7) are respectively installed on both sides of the stator core (1), and the oil inlet tray (6) and the oil return tray (7) respectively correspond to the oil-electricity separation joint (3) on one side; the oil inlet tray (6) is connected to the oil-electricity separation joint (3) corresponding to the oil inlet tray (6) through the oil guide hose (4) on one side of the oil inlet tray (6); The oil-electricity separation joint (3) corresponding to the oil return plate (7) is connected to the oil inlet end of the hollow wire (2); the oil outlet end of the hollow wire (2) is connected to the oil-electricity separation joint (3) corresponding to the oil return plate (7); the oil-electricity separation joint (3) corresponding to the oil return plate (7) is connected to the oil return plate (7) through an oil guide hose (4) on one side of the oil return plate (7); the oil inlet plate (6) and the oil return plate (7) both adopt a disk-shaped structure with an internal cavity; the oil inlet plate (6) is provided with an oil inlet port (61), and the oil return plate (7) is provided with an oil return port (71); the oil inlet port (61) and the oil return port (71) differ by 180 degrees in the circumferential direction.

[0009] The cooling oil enters from the oil inlet (61) under the pressure of the external oil pump, fills the oil inlet tray (6), flows out from the oil through port (62), enters the oil-electricity separation joint (3) through the oil guide hose (4), and then flows into the hollow wire (2). The cooling oil flowing into the hollow wire (2) takes away the heat, flows out from the oil-electricity separation joint (3) and the oil guide hose (4) at the other end, flows into the oil return tray (7) from the oil through port (72), and finally flows out from the oil return port (71). The oil circuits of each hollow wire (2) are connected in parallel.

[0010] Specifically, the oil inlet plate (6) is provided with an oil inlet plate oil port (62), and the oil return plate (7) is provided with an oil inlet plate oil port (72); the circular opening (32) of the oil-electricity separation joint (3), the oil inlet plate oil port (62), and the oil return plate oil port (72) are all threadedly mounted with an oil circuit joint (5); a connecting nut (41) is provided at the end of the oil guide hose (4), and the oil guide hose (4) is connected to the oil circuit joint (5) via the connecting nut (41), thereby realizing the connection of the oil-electricity separation joint (3), the oil inlet plate (6), and the oil return plate (7) on the oil circuit.

[0011] Specifically, the inner wall of the circular opening (32) of the oil-electricity separation joint (3) has threads for connecting the oil-conducting hose (4), so that the cooling oil in the hollow conductor (2) flows into the oil-electricity separation joint (3) from the circular opening (32) and into the oil-conducting hose (4). Both ends of the oil-conducting hose (4) are provided with connecting nuts (41), the connecting nuts (41) are hollow in structure and have threads on the inner wall, and the pipe body (42) in the middle of the oil-conducting hose (4) is made of high-temperature-resistant and corrosion-resistant polytetrafluoroethylene material; the oil circuit joint (5) is a through-hole structure, both ends of the through-hole are engraved with threads, and is connected to other components through the outer threads, and cooling oil can flow through the inside.

[0012] Furthermore, the side wall of the oil inlet plate (6) is provided with an oil inlet port (61), which is circular; an oil through port (62) is provided in the axial direction on one side, the number of which is the same as the number of slots in the stator core (1); the inner wall of each oil through port (62) is threaded. The side wall of the oil return plate (7) is provided with an oil return port (71), which is rectangular; an oil through port (72) is provided in the axial direction on one side, the number of which is the same as the number of slots in the stator core (1); the inner wall of each oil through port (72) is threaded.

[0013] Specifically, the armature winding of the aviation internally cooled generator is a double-layer integer slot winding, wherein the hollow conductor (2) is placed in the conductor slot of the stator core (1), and two upper and lower hollow conductors (2) are placed in each conductor slot. The hollow conductor (2) is a flat wire, and cooling oil flows through the hollow conductor (2).

[0014] The armature winding is a wave winding, and the hollow conductor (2) is twisted at a certain angle at the end. The hollow conductor (2) under one pole crosses the pole pitch and is connected to the corresponding conductor of the next pole through an oil-electricity separation joint (3); the oil-electricity separation joint (3) is made of copper, has conductivity, is hollow inside, and is coated with an insulating layer outside. The oil paths of the hollow conductors (2) are connected in parallel. The oil-electricity separation joint (3) is provided with openings in both axial and radial directions, wherein a circular opening (32) is provided in the radial direction, and two upper and lower rectangular openings (31) are provided in the axial direction, and the size of each rectangular opening (31) matches the hollow conductor (2). The hollow conductor (2) is inserted into the oil-electricity separation joint (3) from the rectangular opening (31), and is fixedly connected to the inner wall of the oil-electricity separation joint (3) by welding. The two hollow conductors (2) can be connected in circuit through the conductive oil-electricity separation joint (3).

[0015] In a second aspect, an embodiment of the present invention provides an armature winding cooling method applied to the armature winding cooling device, comprising:

[0016] When the oil circuit is operating normally, cooling oil is pumped into the oil inlet (61) through external pressure and fills the oil inlet pan (6), wherein the cooling oil can be pumped into the oil inlet (61) through external pressure provided by an externally arranged oil pump and fill the oil inlet pan (6);

[0017] The cooling oil flowing out of the oil passage (62) enters the oil-electricity separation joint (3) through the oil guide hose (4) and then flows into the hollow conductor (2), so that the cooling oil flowing into the hollow conductor (2) can take away the heat;

[0018] The cooling oil flows out through the oil-electricity separation joint (3) at the other end of the hollow conductor (2) through the oil guide hose (4), then flows into the oil return pan (7) from the oil passage (72), and finally flows out from the oil return port (71).

[0019] The armature winding cooling device and method for an aviation internally cooled generator provided in an embodiment of the present invention adopts a hollow conductor as the armature winding, the outer wall of the hollow conductor is copper, the armature current is passed through, the cavity of the hollow conductor is passed through a cooling medium such as cooling oil, the cooling medium is in direct contact with the armature winding, and the cooling oil flows in the oil circuit at a certain speed through a complete hollow conductor cooling oil circuit and a reasonably designed oil pressure, thereby taking away the heat generated by the armature winding, and realizing efficient cooling of the armature winding. Compared with the prior art, the armature winding of the present scheme adopts a special hollow conductor, the cooling oil can be passed into the cavity of the hollow conductor, the armature winding can be in direct contact with the cooling medium, direct heat transfer is realized from the structural level, and the cooling effect is good; and the present scheme adopts an axial oil inlet design, the oil is fed from one end of the motor axis and the oil is returned from the other end, the oil circuits of all hollow conductors are connected in parallel, each oil circuit is short in length, low in flow resistance, low in required oil pressure, and good in cooling effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0021] Figure 1 It is a front view of an aviation internally cooled generator armature winding cooling system provided by an embodiment of the present invention;

[0022] Figure 2 It is a back view of an aviation internally cooled generator armature winding cooling system provided by an embodiment of the present invention;

[0023] Figure 3 is a cross-sectional view of a stator provided by an embodiment of the present invention;

[0024] Figure 4is the placement position of the hollow conductor provided in the embodiment of the present invention in the stator;

[0025] Figure 5 It is a schematic diagram of a connection method of two adjacent turns of hollow conductors provided by an embodiment of the present invention;

[0026] Figure 6 is a structural diagram of an oil-electricity separation joint provided in an embodiment of the present invention;

[0027] Figure 7 is a structural diagram of an oil guide hose provided by an embodiment of the present invention;

[0028] Figure 8 is a structural diagram of an oil circuit joint provided by an embodiment of the present invention;

[0029] Fig. 9 is a front view of an oil inlet tray provided by an embodiment of the present invention;

[0030] Fig.10 is a rear view of the oil inlet tray provided by an embodiment of the present invention;

[0031] Fig.11 is a front view of an oil return plate provided by an embodiment of the present invention;

[0032] Fig.12 It is a rear view of the oil return pan provided in the embodiment of the present invention. DETAILED DESCRIPTION

[0033] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. The embodiments of the present invention will be described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be interpreted as limiting the present invention. It can be understood by those skilled in the art that, unless specifically stated, the singular forms "one", "one", "said" and "the" used herein may also include plural forms. It should be further understood that the term "including" used in the specification of the present invention refers to the presence of the features, integers, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or their groups. It should be understood that when we say that an element is "connected" or "coupled" to another element, it can be directly connected or coupled to other elements, or there may also be intermediate elements. In addition, the "connection" or "coupling" used here may include wireless connection or coupling. The term "and / or" used herein includes any unit and all combinations of one or more associated listed items. It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical terms and scientific terms) used herein have the same meaning as generally understood by those of ordinary skill in the art to which the present invention belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have meanings consistent with the meanings in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as herein.

[0034] The embodiment of the present invention provides a method for cooling the armature winding of an aviation internally cooled generator, such as Figure 1 , 2 The entire cooling system comprises: a stator core (1), a hollow conductor (2), an oil-electricity separation joint (3), an oil guide hose (4), an oil line joint (5), an oil inlet pan (6), and an oil return pan (7).

[0035] like Figure 3 The number of slots in the stator core (1) is 48, and the armature winding is a double-layer integer slot winding. The armature winding uses a specially made hollow conductor (2). The hollow conductor is rectangular in shape, and the shape of the internal opening is also rectangular. Two upper and lower hollow conductors (2) are placed in each slot of the stator core (1). Cooling oil is passed through the hollow conductor. The hollow conductor (2) is placed in the stator core (1) slot as follows: Figure 4 .

[0036] The armature winding is a wave winding with a pitch of 6. The end of each conductor is bent at a certain angle and connected to the corresponding wire of the next pole through an oil-electric separation connector (3), such as Figure 4 , 5 .

[0037] like Figure 6 The oil-electricity separation connector (3) is made of copper, has electrical conductivity, is hollow inside, and is coated with an insulating layer outside. The oil-electricity separation connector (3) has openings in both axial and radial directions. Two upper and lower rectangular openings (31) are opened in the axial direction, and the opening size matches the hollow wire (2). The hollow wire (2) is inserted into the oil-electricity separation connector (3) from the rectangular opening (31) and connected to the outer wall of the oil-electricity separation connector (3) by welding. The two hollow wires (2) can be connected in circuit through the oil-electricity separation connector (3).

[0038] like Figure 6 The oil-electricity separation joint (3) is provided with a circular opening (32) in the radial direction, and the inner wall of the circular opening (32) is provided with threads for connecting the oil-conducting hose (4). After the cooling oil in the hollow conductor (2) passes into the oil-electricity separation joint (3), it flows into the oil-conducting hose (4) from the circular opening (32).

[0039] like Figure 7 The two ends of the oil guide hose (4) are provided with connecting nuts (41), the connecting nuts (41) are of a hollow structure and the inner wall has threads, and the pipe body (42) in the middle of the oil guide hose (4) is made of high temperature resistant and corrosion resistant polytetrafluoroethylene.

[0040] like Figure 8 The oil line connector (5) is a through hole with threads engraved on both ends of the hole, and can be connected to other components through the outer threads, while cooling oil can pass through the interior.

[0041] like Figure 1 , 9 10. The oil inlet plate (6) is a plate-shaped structure with an internal cavity, an oil inlet port (61) is formed on the side wall, and oil through ports (62) with the same number as the slots of the stator core (1) are formed in the axial direction on one side, and the inner wall of the oil through port (62) has threads. The oil inlet plate (6) is installed at the end of the stator core (1).

[0042] like Figure 2 , 11 , 12, the oil return plate (7) is installed on the other side of the end of the stator core (1), and its structure is basically the same as that of the oil inlet plate (6), and is provided with an oil return port (71) and an oil through port (72). The position of the oil return port (71) is 180 degrees different from that of the oil inlet port (61) in the circumferential direction, and the shape of the oil return port (71) is rectangular.

[0043] The oil circuit connector (5) is installed on the circular opening (32) of the oil-electricity separation connector (3), the oil passage opening (62) of the oil inlet plate (6), and the oil passage opening (72) of the oil return plate (7) through threads. The oil guide hose (4) is connected to the oil circuit connector (5) through a connecting nut (41) at its end, so as to realize the connection of the oil-electricity separation connector (3), the oil inlet plate (6), and the oil return plate (7) on the oil circuit.

[0044] When the oil circuit works normally, cooling oil enters from the oil inlet (61) under external pressure, fills the oil inlet plate (6), flows out from the oil through port (62), enters the oil-electricity separation joint (3) through the oil guide hose (4), and then flows into the hollow wire (2). The cooling oil flowing into the hollow wire (2) takes away the heat, flows out from the oil-electricity separation joint (3) and the oil guide hose (4) at the other end, flows into the oil return plate (7) from the oil through port (72), and finally flows out from the oil return port (71). The oil circuits of each hollow wire (2) are connected in parallel.

[0045] The armature winding cooling device and method for an aviation internally cooled generator provided in an embodiment of the present invention adopts a hollow conductor as the armature winding. The outer wall of the hollow conductor is copper, and the armature current flows through it. A cooling medium such as cooling oil flows through the cavity of the hollow conductor. The cooling medium is in direct contact with the armature winding. Through a complete hollow conductor cooling oil circuit and a reasonably designed oil pressure, the cooling oil flows at a certain speed in the oil circuit, thereby taking away the heat generated by the armature winding, and realizing efficient cooling of the armature winding. Compared with the prior art, the armature winding of the present invention adopts a special hollow conductor, cooling oil can be passed into the cavity of the hollow conductor, the armature winding can be in direct contact with the cooling medium, direct heat transfer is achieved at the structural level, and the cooling effect is good; in addition, the present invention adopts an axial oil inlet design, with oil entering from one end of the motor axis and returning from the other end, the oil circuits of all hollow conductors are connected in parallel, each oil circuit is short in length, low in flow resistance, low in required oil pressure, and good in cooling effect; at the same time, a special oil-electricity separation connector is improved, which can realize the connection of the oil circuits of parallel hollow conductors, and at the same time realize the connection on different hollow conductor circuits, realize the complete connection of the oil circuit and the circuit at the end of the motor, and at the same time separate the oil circuit and the circuit; the various components of the oil circuit are connected through specially designed oil circuit connectors, which ensures that the oil circuit has good sealing and reduces the risk of cooling oil leakage.

[0046] Each embodiment in this specification is described in a progressive manner, and the same or similar parts between the embodiments can be referred to each other, and each embodiment focuses on the differences from other embodiments. In particular, for the device embodiment, since it is basically similar to the method embodiment, the description is relatively simple, and the relevant parts can be referred to the partial description of the method embodiment. The above is only a specific implementation method of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or replacements that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. An armature winding cooling device for an aviation internally cooled generator, characterized in that: The armature winding cooling device is integrated in the aviation internal cooling type generator, and the armature winding cooling device comprises: a stator core (1), a hollow conductor (2), an oil-electricity separation joint (3), an oil guide hose (4), an oil inlet tray (6) and an oil return tray (7); The oil inlet plate (6) and the oil return plate (7) are respectively installed on both sides of the stator core (1), and the oil inlet plate (6) and the oil return plate (7) respectively correspond to the oil-electricity separation connector (3) on one side; The oil inlet pan (6) is connected to an oil-electricity separation connector (3) corresponding to the oil inlet pan (6) through an oil guide hose (4) on one side of the oil inlet pan (6), and the oil-electricity separation connector (3) corresponding to the oil inlet pan (6) is connected to the oil inlet end of the hollow wire (2); The oil outlet end of the hollow conductor (2) is connected to an oil-electricity separation joint (3) corresponding to the oil return plate (7), and the oil-electricity separation joint (3) corresponding to the oil return plate (7) is connected to the oil return plate (7) via an oil guide hose (4) on one side of the oil return plate (7); The oil inlet plate (6) and the oil return plate (7) both adopt a plate-shaped structure with an internal cavity. The oil inlet plate (6) is provided with an oil inlet port (61), and the oil return plate (7) is provided with an oil return port (71). The oil inlet port (61) and the oil return port (71) are 180° apart in the circumferential direction. The oil inlet plate (6) is also provided with an oil inlet plate oil opening (62), and the oil return plate (7) is also provided with an oil return plate oil opening (72); The circular opening (32) of the oil-electricity separation joint (3), the oil through hole (62) of the oil inlet plate, and the oil through hole (72) of the oil return plate are all threadedly mounted with an oil circuit joint (5); A connecting nut (41) is provided at the end of the oil guide hose (4), and the oil guide hose (4) is connected to the oil circuit joint (5) via the connecting nut (41); The cooling oil enters from the oil inlet (61) under the pressure of an external oil pump, fills the oil inlet plate (6), flows out from the oil through port (62), enters the oil-electricity separation joint (3) through the oil guide hose (4), and then flows into the hollow conductor (2). The cooling oil flowing into the hollow conductor (2) takes away the heat, flows out from the oil-electricity separation joint (3) and the oil guide hose (4) at the other end, flows into the oil return plate (7) from the oil through port (72), and finally flows out from the oil return port (71); the inner wall of the circular opening (32) of the oil-electricity separation joint (3) has a thread for connecting the oil guide hose (4), so that the cooling oil in the hollow conductor (2) flows into the oil-electricity separation joint (3) and then flows into the oil guide hose (4) from the circular opening (32); Both ends of the oil-conducting hose (4) are provided with connecting nuts (41), the connecting nuts (41) are hollow structures and the inner wall thereof has threads, and the tube body (42) in the middle of the oil-conducting hose (4) is made of polytetrafluoroethylene; The oil line joint (5) is a through hole structure, and both ends of the through hole are engraved with threads; The oil-electricity separation joint (3) is provided with openings in both axial and radial directions. A circular opening (32) is opened in the radial direction, and two rectangular openings (31) are opened in the axial direction. The size of each rectangular opening (31) matches the hollow conductor (2). The hollow conductor (2) is inserted into the oil-electricity separation joint (3) through the rectangular opening (31) and is fixedly connected to the inner wall of the oil-electricity separation joint (3) by welding.

2. The armature winding cooling device for an aircraft internally cooled generator according to claim 1, characterized in that: The side wall of the oil inlet plate (6) is provided with an oil inlet (61), and the oil inlet (61) is circular; An oil through hole (62) is provided in the axial direction of one side, and the number of the oil through holes (62) is the same as the number of slots of the stator core (1); The inner wall of each oil passage (62) is provided with threads.

3. The armature winding cooling device for an aircraft internally cooled generator according to claim 2, characterized in that: The side wall of the oil return plate (7) is provided with an oil return port (71), and the oil return port (71) is rectangular; An oil through hole (72) is provided in the axial direction of one side, and the number of the oil through holes (72) is the same as the number of slots of the stator core (1); The inner wall of each oil passage (72) is provided with threads.

4. The armature winding cooling device for an aircraft internally cooled generator according to claim 1, characterized in that: The armature winding of the aviation internally cooled generator is a double-layer integer slot winding, wherein a hollow conductor (2) is placed in a conductor slot of a stator core (1), two upper and lower hollow conductors (2) are placed in each conductor slot, the hollow conductor (2) is a flat wire, and cooling oil flows through the hollow conductor (2).

5. The armature winding cooling device for an aircraft internally cooled generator according to claim 1, characterized in that: The armature winding is a wave winding, the hollow conductor (2) is twisted at the end, and the hollow conductor (2) under one pole is connected to the corresponding conductor of the next pole across the pole pitch through an oil-electric separation joint (3); The oil paths of the hollow conductors (2) are connected in parallel.

6. The armature winding cooling device for an aircraft internally cooled generator according to any one of claims 1 to 5, characterized in that: An armature winding cooling method applied to the armature winding cooling device comprises: The cooling oil is pumped into the oil inlet (61) by external pressure and fills the oil inlet pan (6); The cooling oil flowing out of the oil passage (62) enters the oil-electricity separation joint (3) through the oil guide hose (4) and then flows into the hollow conductor (2), so that the cooling oil flowing into the hollow conductor (2) can take away the heat; The cooling oil flows out through the oil-electricity separation joint (3) at the other end of the hollow conductor (2) through the oil guide hose (4), then flows into the oil return pan (7) from the oil passage (72), and finally flows out from the oil return port (71).

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