CN114992220A - Generators and Aircraft - Google Patents

Abstract

Embodiments of the present invention provide a generator and an aircraft, and relate to the technical field of generators. The generator includes a generator flexible shaft and a flexible ring. The generator flexible shaft includes a flexible shaft body, a shoulder and an external spline. The outer wall of the flexible shaft body is protruded with a shoulder, and the outer wall of the flexible shaft body is provided with an external spline. The key, the external spline and the shoulder are spaced apart. The flexible ring is sleeved on the flexible shaft body and is located on the side of the shoulder close to the external spline. When the engine and the generator are assembled, the end of the internal spline of the engine is fitted on the outside. On the splines, since the flexible ring is sleeved on the flexible shaft body, the end of the internal spline shaft of the engine will not directly hit the shoulder of the flexible shaft of the generator. The vibration of the flexible shaft of the generator is reduced, and the shoulder of the flexible shaft of the generator is also protected, so as to avoid the damage of the flexible shaft of the generator.

Description

Generators and Aircraft

technical field

The present invention relates to the technical field of generators, and in particular, to a generator and an aircraft.

Background technique

Generators used in aircraft are divided into two categories: DC and AC, and the working principle is the same as that of industrial motors. The main features of aircraft generators are: working in harsh environmental conditions such as high altitude, high speed, impact, etc.; driven by aero-engines with a wide range of speed changes, and adopting more effective cooling systems and high-quality materials to reduce the weight-to-power ratio , Due to the safety requirements of the aircraft, the operation reliability of the generator flexible shaft of the aircraft must be guaranteed.

In the prior art, when the generator and the engine are assembled, the inner spline shaft end of the engine will collide with the shoulder of the generator, which will easily damage the flexible shaft of the generator, cause the generator to fail, and affect the power supply system of the aircraft.

SUMMARY OF THE INVENTION

The present invention provides a generator and an aircraft, which can avoid damage to the flexible shaft of the generator.

Embodiments of the present invention can be implemented as follows:

Embodiments of the present invention provide a generator comprising:

The flexible shaft of the generator, the flexible shaft of the generator includes a flexible shaft body, a shoulder and an external spline, the outer wall of the flexible shaft body is protruded with a shoulder, and the outer wall of the flexible shaft body is provided with the outer spline. Splines, the external splines and the shoulder are spaced apart; and

A flexible ring is sleeved on the flexible shaft body and located on the side of the shoulder close to the external spline.

Optionally, the outer wall of the flexible shaft body is provided with an annular groove along the circumferential direction, and the flexible ring is sleeved on the annular groove.

Optionally, the outer wall of the shoulder and the outer wall of the flexible shaft body together define an annular groove.

Optionally, the generator further includes a first guard ring, the first guard ring is provided with a first gap, the first guard ring is sleeved in the annular groove, and is away from the flexible ring. The shoulder of the flexible shaft of the generator.

Optionally, the generator further includes a second guard ring, the second guard ring is provided with a second gap, the second guard ring is sleeved in the annular groove, and is located between the flexible ring and the between the shoulders of the generator flexible shaft.

Optionally, both the first guard ring and the second guard ring are gaskets.

Optionally, the flexible ring is elastically sleeved on the annular groove.

Optionally, the length of the external spline in the axial direction of the flexible shaft body is greater than the length of the annular groove along the axial direction of the flexible shaft body.

Optionally, the flexible ring is a rubber ring.

Embodiments of the present invention also provide an aircraft including the above generator.

The beneficial effects of the generator and the aircraft according to the embodiments of the present invention include, for example:

An embodiment of the present invention provides a generator, which includes a generator flexible shaft and a flexible ring, the generator flexible shaft includes a flexible shaft body, a shoulder and an external spline, and a shoulder is protruded on the outer wall of the flexible shaft body, The outer wall of the flexible shaft body is provided with external splines, and the external splines and the shoulder are spaced apart. The flexible ring is sleeved on the flexible shaft body and is located on the side of the shoulder close to the external splines. When the engine and generator are assembled , the inner spline shaft end of the engine is matched with the outer spline. Since the flexible ring is sleeved on the flexible shaft body, the inner spline shaft end of the engine will not directly hit the shoulder of the generator flexible shaft. The ring can also buffer the inner spline shaft end of the engine, reduce the vibration of the flexible shaft of the generator, and also protect the shoulder of the flexible shaft of the generator to avoid the damage of the flexible shaft of the generator.

Embodiments of the present invention also provide an aircraft, including the above-mentioned generator, which can avoid damage to the flexible shaft of the generator, ensure the normal operation of the generator, and avoid affecting the power supply system of the aircraft.

Description of drawings

In order to illustrate the technical solutions of the embodiments of the present invention more clearly, the following briefly introduces the accompanying drawings used in the embodiments. It should be understood that the following drawings only show some embodiments of the present invention, and therefore do not It should be regarded as a limitation of the scope. For those skilled in the art, other related drawings can also be obtained according to these drawings without any creative effort.

Fig. 1 is the partial schematic diagram of the generator flexible shaft provided in the embodiment of the present invention;

FIG. 2 is a schematic diagram of a first guard ring provided in an embodiment of the present invention.

Icon: 100-generator flexible shaft; 110-flexible shaft body; 111-annular groove; 120-shoulder; 130-external spline; 200-flexible ring; 300-first protection ring; 310-first notch; 400 - Second guard ring.

Detailed ways

In order to make the purposes, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments These are some embodiments of the present invention, but not all embodiments. The components of the embodiments of the invention generally described and illustrated in the drawings herein may be arranged and designed in a variety of different configurations.

Thus, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

It should be noted that like numerals and letters refer to like items in the following figures, so once an item is defined in one figure, it does not require further definition and explanation in subsequent figures.

In the description of the present invention, it should be noted that, if the terms "upper", "lower", "inner", "outer", etc. appear, the orientation or positional relationship indicated is based on the orientation or positional relationship shown in the drawings, or It is the orientation or positional relationship that the product of the invention is usually placed in use, only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation , so it should not be construed as a limitation of the present invention.

In addition, where the terms "first", "second" and the like appear, they are only used to differentiate the description, and should not be construed as indicating or implying relative importance.

It should be noted that the features in the embodiments of the present invention may be combined with each other without conflict.

An aircraft is a heavier-than-air aircraft that flies in the upper, middle, and lower atmospheres by means of a power unit with one or more engines that generates forward thrust or pulling force, and the fixed wings of the fuselage generate lift. There are two categories of military aircraft and civilian aircraft. Military aircraft refers to aircraft used in various military fields, while civil aircraft generally refers to all non-military aircraft (such as passenger aircraft, cargo aircraft, agricultural aircraft, sports aircraft, ambulance aircraft, and experimental research aircraft, etc.).

Among them, the aircraft power generation system refers to the system that continuously generates electric energy on the aircraft, including the main power supply, emergency power supply and secondary power supply. It consists of generator, battery (or auxiliary power generator), bus bar and its control and protection device (voltage regulator, control and protection device), etc. During the flight, the system or device used to supply power to the important electrical equipment when the main power supply fails during the flight is called the "main power supply". "Emergency power supply", a device that converts part of the electrical energy of the main power supply into another electrical energy of voltage, current or frequency to supply a few special electrical equipment is called "secondary power supply".

The generators used in aircraft are divided into two categories: DC and AC, and the working principle is the same as that of industrial motors. The main features of aircraft generators are: working in harsh environmental conditions such as high altitude, high speed, impact, etc.; driven by aero-engines with a wide range of speed changes, and adopting more effective cooling systems and high-quality materials to reduce the weight-to-power ratio , Due to the safety requirements of the aircraft, the operation reliability of the generator flexible shaft of the aircraft must be guaranteed.

In the prior art, when the generator and the engine are assembled, the inner spline shaft end of the engine will collide with the shoulder of the generator, resulting in easy damage to the flexible shaft of the generator. For example, after the generator and the engine are assembled, especially When the generator is running, the axial movement of the engine and the generator are superimposed on each other, which will have a great impact on the shoulder of the flexible shaft, affect the life of the flexible shaft, and may damage the flexible shaft and cause the generator. If it fails, it will affect the power supply system of the aircraft and cause great potential safety hazards.

In view of this, please refer to FIG. 1 and FIG. 2 , the generator and the aircraft provided in the embodiments of the present invention can solve this problem, which will be described in detail below.

An embodiment of the present invention provides an aircraft (not shown in the figure), which may be a fixed-wing aircraft or a rotary-wing unmanned aerial vehicle. The aircraft includes an aircraft body, an engine, and a generator. The engine and the generator are installed on the aircraft body, and the engine Connected with the generator, the generator can avoid the damage of the generator flexible shaft 100, ensure the normal operation of the generator, and avoid affecting the power supply system of the aircraft.

Specifically, the generator includes a generator flexible shaft 100 and a flexible ring 200. The generator flexible shaft 100 includes a flexible shaft body 110, a shoulder 120 and an external spline 130. The outer wall of the flexible shaft body 110 is protruded with a shoulder 120, the outer wall of the flexible shaft body 110 is provided with external splines 130, and the external splines 130 and the shoulder 120 are spaced apart. On the one hand, it should be noted that FIG. 1 is only a partial schematic diagram of the generator flexible shaft 100 , specifically the end of the generator flexible shaft 100 provided with the external splines 130 .

When the engine and the generator are assembled, the inner spline shaft end of the engine is fitted on the outer spline 130. It should be noted that the inner spline shaft end here refers to the rotating shaft with the inner spline on the engine rotor shaft. At the end, since the flexible ring 200 is sleeved on the flexible shaft body 110, the inner spline shaft end of the engine will not directly hit the shoulder 120 of the generator flexible shaft 100. The inner spline shaft end is buffered, the vibration of the generator flexible shaft 100 is reduced, and at the same time, the shoulder 120 of the generator flexible shaft 100 is protected, the damage of the generator flexible shaft 100 is avoided, and the generator failure can be avoided at the same time. Affect the power supply system of the aircraft.

In this embodiment, the flexible ring 200 is sleeved on the outer wall of the flexible shaft body 110 between the external splines 130 and the shoulder 120 , and the flexible ring 200 is a rubber ring. Specifically, the flexible ring 200 can be made of aviation rubber. , the structure of the flexible ring 200 is a ring shape, and the cross-sectional shape is a circle. Of course, in other embodiments, the structure of the flexible ring 200 can also be an oval shape, in order to avoid the flexible ring 200 from the flexible shaft body 110 The inner diameter of the flexible ring 200 is smaller than the outer diameter of the flexible shaft body 110 , so that the flexible ring 200 can be elastically sleeved on the outer diameter of the flexible shaft body 110 .

Of course, in order to further limit the position of the flexible ring 200, the outer wall of the flexible shaft body 110 is provided with an annular groove 111 along the circumferential direction, that is, the circumferential outer wall of the flexible shaft body 110 is provided with an annular groove 111, and the flexible ring 200 is sleeved on the annular groove The groove 111 , specifically, the outer wall of the shoulder 120 and the outer wall of the flexible shaft body 110 together define the annular groove 111 .

At the same time, in order not to affect the cooperation between the internal splines and the external splines 130 of the engine and ensure the matching strength of the internal splines and the external splines 130, the length of the external splines 130 in the axial direction of the flexible shaft body 110 is greater than that of the annular groove 111 along the length of the flexible shaft body 110 in the axial direction.

In addition, in order to strengthen the buffering of the internal spline shaft end of the engine, the generator further includes a first guard ring 300 . The first guard ring 300 is provided with a first gap 310 , and the first guard ring 300 is sleeved on the annular groove 111 . , and is away from the shoulder 120 of the flexible shaft relative to the flexible ring 200 .

Specifically, the first guard ring 300 is a circular ring with a rectangular cross section, and the extending direction of the first notch 310 and the annular end surface of the first guard ring 300 form an acute angle, that is, the first notch 310 is obliquely opened in the first guard ring 300 In this way, the first guard ring 300 can buffer the inner spline shaft end of the engine when it moves to the shoulder 120 . Preferably, the first guard ring 300 can be a washer made of fluoroplastic.

In addition, in order to further strengthen the buffering of the inner spline shaft end of the engine and protect the flexible ring 200, the generator further includes a second guard ring 400, and the second guard ring 400 is provided with a second gap. The guard ring 400 is the same as the first guard ring 300, and can also be a gasket made of fluoroplastic. The second guard ring 400 is sleeved on the annular groove 111 and is located between the flexible ring 200 and the shoulder 120 of the flexible shaft.

To sum up, the generator includes a flexible generator shaft 100 and a flexible ring 200. The flexible generator shaft 100 includes a flexible shaft body 110, a shoulder 120 and an external spline 130. The outer wall of the flexible shaft body 110 is protruded with a stopper Shoulder 120, the outer wall of the flexible shaft body 110 is provided with external splines 130, the external splines 130 and the shoulder 120 are spaced apart, and the flexible ring 200 is sleeved on the flexible shaft body 110, and is located on the shoulder 120 close to the external splines 130 When the engine and the generator are assembled, the inner spline shaft end of the engine is matched with the outer spline 130. Since the flexible ring 200 is sleeved on the flexible shaft body 110, the inner spline shaft end of the engine will not directly It hits the shoulder 120 of the generator flexible shaft 100, and at the same time, the flexible ring 200 can also buffer the inner spline shaft end of the engine, the vibration of the generator flexible shaft 100 is reduced, and the generator flexible shaft 100 is also protected. The shoulder 120 prevents damage to the flexible shaft 100 of the generator.

At the same time, in order to further strengthen the buffering of the inner spline shaft end of the engine and protect the flexible ring 200, the generator also includes a first guard ring 300 and a second guard ring 400. The first guard ring 300 and the second guard ring 400 may preferably be The gasket made of fluoroplastic is used. During the operation of the engine and the generator, the end of the internal spline shaft of the engine can be directly pressed against the first guard ring 300, and both the first guard ring 300 and the second guard ring 400 can be lifted. The function of energy absorption is achieved, thereby protecting the flexible shaft 100 of the generator.

The aircraft includes the above generator, which can avoid damage to the flexible shaft 100 of the generator, ensure the normal operation of the generator, and avoid affecting the power supply system of the aircraft.

The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art who is familiar with the technical scope disclosed by the present invention can easily think of changes or substitutions. All should be included 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 (10)

1. An electrical generator, comprising:

the generator flexible shaft (100) comprises a flexible shaft body (110), a retaining shoulder (120) and an external spline (130), the retaining shoulder (120) is convexly arranged on the outer wall of the flexible shaft body (110), the external spline (130) is arranged on the outer wall of the flexible shaft body (110), and the external spline (130) and the retaining shoulder (120) are distributed at intervals; and

the flexible shaft is characterized in that the flexible ring (200) is sleeved on the flexible shaft body (110) and is located on one side, close to the external spline (130), of the retaining shoulder (120).

2. The generator according to claim 1, wherein an annular groove (111) is circumferentially formed in an outer wall of the flexible shaft body (110), and the flexible ring (200) is sleeved in the annular groove (111).

3. The generator according to claim 2, characterized in that the outer wall of the catch (120) and the outer wall of the flexible shaft body (110) together define an annular groove (111).

4. The generator according to claim 2, further comprising a first guard ring (300), wherein a first notch (310) is formed in the first guard ring (300), and the first guard ring (300) is sleeved in the annular groove (111) and is away from a shoulder (120) of the generator flexible shaft relative to the flexible ring (200).

5. The generator according to claim 4, further comprising a second guard ring (400), wherein a second notch is formed in the second guard ring (400), and the second guard ring (400) is sleeved in the annular groove (111) and is located between the flexible ring (200) and a shoulder (120) of the flexible shaft (100) of the generator.

6. The generator according to claim 5, characterized in that the first guard ring (300) and the second guard ring (400) are both washers.

7. The generator according to claim 2, characterized in that said flexible ring (200) is elastically sleeved in said annular groove (111).

8. The generator according to claim 2, characterized in that the length of the external spline (130) in the axial direction of the flexible shaft body (110) is greater than the length of the annular groove (111) in the axial direction of the flexible shaft body (110).

9. Generator according to claim 1, characterized in that the flexible ring (200) is a rubber ring.

10. An aircraft comprising a generator according to any one of claims 1 to 9.

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