Motor assembly for aero-engine

Abstract

The utility model discloses a motor assembly for an aero-engine, which comprises a magnetor, a starting motor and a support, and the magnetor and the starting motor are mounted on the same support. The support is provided with a positioning claw matched with a magneto, a first positioning hole used for being matched with a cartridge receiver and a second positioning hole matched with a starting motor, and the magneto is connected with the starting motor through a gear transmission mechanism. According to the scheme, the problem that the light weight effect of a motor assembly in the prior art is insufficient is solved.

Description

Technical Field

[0001] This utility model relates to auxiliary equipment for aircraft engines, specifically an electric motor assembly for aircraft engines. Background Technology

[0002] The motor assembly for aero engines is a collective term for the magneto and starter motor of the aero engine. The magneto generates electricity when the engine is running, while the starter motor provides starting drive force when the engine starts. In the present technology, the magneto and starter motor need to be installed and fixed to the aero engine separately. The specific method of installation and fixing is generally to use their respective designed mounting brackets for connection and fixation. Moreover, the vibration generated when the aero engine is running is relatively strong. In order to enhance the stability of the magneto and starter motor in the vibration environment, the entire aero engine motor assembly requires a large number and variety of mounting brackets, and correspondingly, a large number of fasteners for connection. With the increasing requirements for lightweight aero engines, existing technologies have emerged to improve the generator bracket to achieve a higher level of lightweight aero engines.

[0003] Chinese patent document CN109139244A discloses a generator bracket structure, including a bracket body. The bracket body is connected to an engine body via bolts passing through bolt holes. The lower end of the bracket body is connected to a suspension bracket via a lower connecting bolt. The generator is fixedly connected to the bracket body via an upper connecting bolt and a fixing bolt. The suspension bracket is connected to an aircraft truss and connected to a suspension fixing point on the aircraft truss. The bracket body is constructed of magnesium alloy. The advantages of this prior art are: integrating a fixing point of the generator bracket structure's bracket body with a suspension bracket of the engine allows the suspension bracket to both fix the engine and integrate with the generator bracket, thus achieving both engine connection and ensuring reliable and stable generator installation. This reduces the number of fixing points and brackets on the engine, does not affect the normal operation of the generator, reduces the weight of the generator bracket structure and the engine, and improves engine performance. The generator bracket structure described in this invention is simple in structure and low in manufacturing cost. With only simple structural improvements, it can effectively ensure the reliable connection performance of the generator while reducing the number of generator fixing brackets, lowering the cost of the generator bracket structure, and reducing the overall weight of the generator bracket structure, thereby increasing the ratio of the engine's maximum output power to its weight.

[0004] While the aforementioned existing technologies reduce the weight of the generator mount in aero engines to some extent, thus contributing to the lightweighting of aero engines, they do not address the installation of the starter motor. Therefore, in terms of achieving overall lightweighting of the aero engine's motor assembly, the effects of these existing technologies are quite limited. Utility Model Content

[0005] The purpose of this invention is to provide an electric motor assembly for aero engines to solve the problem of insufficient lightweighting effect of existing electric motor assemblies.

[0006] To achieve the above objectives, the basic solution of this utility model provides an electric motor assembly for an aircraft engine, including a magneto, a starter motor, and a bracket. The magneto and the starter motor are mounted on the same bracket. The bracket is provided with a positioning claw that cooperates with the magneto, a first positioning hole for cooperating with the casing, and a second positioning hole for cooperating with the starter motor. The magneto and the starter motor are connected by a gear transmission mechanism.

[0007] The beneficial effects of this basic solution are as follows: By mounting the magneto and starter motor on the same bracket, and providing positioning claws, a first positioning hole, and a second positioning hole on the bracket, and enabling the magneto and starter motor to drive each other, the magneto and starter motor can share a single bracket for mounting on the aircraft engine. Furthermore, the positioning claws, first positioning hole, and second positioning hole improve the stability of the magneto and starter motor under vibration environments, reducing the need for additional support and fixing structures. Compared to the prior art where the magneto and starter motor are mounted and fixed separately, this significantly reduces the number, types, material usage, and fastener usage of brackets, thereby improving the lightweight effect of the motor assembly. Simultaneously, the positioning claws, first positioning hole, and second positioning hole enhance the stability of the relative position between the magneto and starter motor under vibration environments, thus contributing to improved reliability of the motor assembly.

[0008] Preferably, the bracket is fixed with at least three positioning claws for connecting the magneto, and the bracket has weight-reducing holes in the area surrounded by all the positioning claws, with the positioning claws evenly distributed along the edges of the weight-reducing holes. This arrangement uses the positioning claws to support and position the magneto, thereby further improving the magneto's stability in vibration environments, and consequently enhancing the reliability of the motor assembly.

[0009] Preferably, the stator of the magneto is annular, and the positioning claw has a stepped positioning portion that fits against the inner surface and end face of the magneto stator. This arrangement utilizes the positioning portion of the positioning claw to provide axial and radial positioning support for the magneto stator, thereby improving the installation accuracy of the magneto stator, reducing the need for additional support structures, further enhancing the lightweight effect of the motor assembly, and simultaneously improving the reliability of the magneto in vibration environments.

[0010] Preferably, the rotor of the magneto is sleeved on the outside of the stator, and a transmission gear is coaxially fixedly connected to the rotor in the circumferential direction. A mounting portion for connecting the engine is provided on the side of the rotor. This arrangement fully utilizes the magneto rotor to support the transmission gear for power transmission, thereby reducing the number of transmission components between the starter motor and the engine, simplifying the structure, and further improving the lightweight effect of the motor assembly.

[0011] Preferably, the transmission gear and the mounting part are integrally formed. This arrangement creates a gear-like structure after the transmission gear and mounting part are integrally formed, which improves structural stability. Furthermore, the transmission gear and the mounting part can share a connecting piece for connection to the magneto, reducing the number of connecting pieces used and further simplifying the structure and improving the lightweight effect of the motor assembly.

[0012] Preferably, the first positioning hole and the weight-reducing hole are coaxially arranged, and the diameter of the first positioning hole is larger than the diameter of the weight-reducing hole. This arrangement allows for accurate positioning and support of the engine casing via the first positioning hole when the bracket is connected to it, while the weight-reducing hole provides auxiliary support, thus facilitating the installation process.

[0013] Preferably, the edge of the bracket is provided with multiple wire clamp mounting seats. This arrangement facilitates the installation of wire clamps on the bracket, thereby making it easier to secure the wire harness.

[0014] This utility model has the following beneficial effects:

[0015] By adopting this solution, the magneto and the starter motor are mounted on the same bracket, and the two motors and the casing are accurately positioned by the positioning claw, the first positioning hole and the second positioning hole. Moreover, the two motors are connected by a gear transmission mechanism, thereby achieving a significant improvement in the lightweight effect of the motor assembly and improving the reliability of the motor assembly in the vibration environment generated by the aero-engine. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of an embodiment of the electric motor assembly for an aircraft engine according to the present invention;

[0017] Figure 2 for Figure 1 A schematic diagram of the midline support;

[0018] Figure 3 for Figure 2 A schematic diagram of the support structure from another perspective. Detailed Implementation

[0019] The following detailed description illustrates the specific implementation method:

[0020] As is known to those skilled in the art, the casing is an important component of an aircraft engine. It is usually located outside the engine and surrounds and protects the engine's internal components, such as the fan, shaft, blades, combustion chamber, and turbine.

[0021] The reference numerals in the accompanying drawings include: 1. starter motor, 2. bracket, 3. transmission gear, 4. magneto, 5. mounting part, 6. second positioning hole, 7. weight reduction hole, 8. positioning claw, and 9. first positioning hole.

[0022] The basic implementation examples are as follows: Figure 1 , Figure 2 and Figure 3 As shown: An electric motor assembly for an aircraft engine includes a magneto 4, a starter motor 1, and a bracket 2. The magneto 4 and the starter motor 1 are mounted on the same bracket 2. In this embodiment, the bracket 2 is generally plate-shaped, and reinforcing ribs are integrally formed on its surface. The bracket 2 is provided with a positioning claw 8 that cooperates with the magneto 4, a first positioning hole 9 that cooperates with the housing, and a second positioning hole 6 that cooperates with the starter motor 1. The magneto 4 and the starter motor 1 are connected by a gear transmission mechanism.

[0023] In this embodiment, one end of the starter motor 1 is inserted into the second positioning hole 6, thereby enabling the second positioning hole 6 to accurately position the starter motor 1. The bracket 2 has connection holes around the second positioning hole 6 for connecting bolts to the starter motor 1, thus fixing the starter motor 1 to the bracket 2 with bolts.

[0024] At least three positioning claws 8 for connecting the magneto 4 are fixed on the bracket 2. In this embodiment, four positioning claws 8 are preferably provided, and the positioning claws 8 are integrally formed with the bracket 2. The positioning claws 8 extend in a direction perpendicular to the surface of the bracket plate, and support the stator of the magneto 4. In this embodiment, the stator of the magneto 4 is annular. The positioning claws 8 have stepped positioning portions that fit against the inner surface and end face of the stator of the magneto 4, so that the positioning claws 8 are positioned and supported by the stator of the magneto 4. The end of the positioning claws 8 is also provided with connecting holes for bolting the stator of the magneto 4. The rotor of the magneto 4 is sleeved on the outside of the stator, and a transmission gear 3 is coaxially fixedly connected to the circumference of the rotor, so that the rotor transmits power to the starter motor 1 through the transmission gear 3. The side of the rotor is provided with a mounting portion 5 for connecting the engine. In this embodiment, the transmission gear 3 and the mounting portion 5 are integrally formed, thus forming a structure similar to a gear disc.

[0025] In this embodiment, a weight-reducing hole 7 is provided on the bracket 2 in the area surrounded by all the positioning claws 8, and the positioning claws 8 are evenly distributed along the edge of the weight-reducing hole 7. In this embodiment, the first positioning hole 9 is coaxially arranged with the weight-reducing hole 7, and the diameter of the first positioning hole 9 is larger than the diameter of the weight-reducing hole 7, thereby facilitating the assembly operation between the first positioning hole 9 and the housing using the weight-reducing hole 7, which helps to reduce the assembly difficulty. Multiple wire clamp mounting seats are provided on the edge of the bracket 2. Multiple bolt mounting holes are also provided on the edge of the bracket 2.

[0026] By adopting this solution, the magneto 4 and the starter motor 1 are mounted on the same bracket 2, and the two motors are accurately positioned by the positioning claw 8, the first positioning hole 9 and the second positioning hole 6. Moreover, the two motors are connected by a gear transmission mechanism, thereby achieving a significant improvement in the lightweight effect of the motor assembly and improving the reliability of the motor assembly in the vibration environment generated by the aero-engine.

[0027] The above description is merely an embodiment of this utility model, and common knowledge such as specific structures and characteristics of the solution is not described in detail here. It should be noted that those skilled in the art can make several modifications and improvements without departing from the structure of this utility model, and these should also be considered within the protection scope of this utility model. These modifications and improvements will not affect the effectiveness of the implementation of this utility model or the practicality of the patent.

Claims

1. An electric machine assembly for an aeroengine comprising a magneto, a starter motor and a support, characterised in that: The magnetic motor and the starting motor are mounted on the same bracket, the bracket is provided with a positioning claw matched with the magnetic motor, a first positioning hole matched with a machine case and a second positioning hole matched with the starting motor, and the magnetic motor and the starting motor are connected through a gear transmission mechanism.

2. The motor assembly for an aero-engine of claim 1, wherein: At least three positioning claws for connecting the magnetic motor are fixed on the bracket, the bracket is provided with a lightening hole at a region surrounded by all the positioning claws, and the positioning claws are uniformly distributed along the edge of the lightening hole.

3. The motor assembly for an aero-engine of claim 2, wherein: The stator of the magnetic motor is in the shape of a ring, and the positioning claw has a stepped positioning part matched with the inner surface and end surface of the stator of the magnetic motor.

4. The motor assembly for an aero-engine of claim 3, wherein: The rotor of the magnetic motor is sleeved outside the stator, a transmission gear is fixedly connected coaxially in the circumferential direction of the rotor, and the side surface of the rotor is provided with a mounting part for connecting the engine.

5. The motor assembly for an aero-engine of claim 4, wherein: The transmission gear is integrally formed with the mounting part.

6. The motor assembly for an aeroengine according to any one of claims 2-5, characterized in that: The first positioning hole is coaxially arranged with the lightening hole, and the hole diameter of the first positioning hole is larger than that of the lightening hole.

7. The motor assembly for an aero-engine of claim 6, wherein: The edge of the bracket is provided with a plurality of wire clamp mounting seats.

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