WO2022100655A1

WO2022100655A1 - Dual-generator structure of aero-engine

Info

Publication number: WO2022100655A1
Application number: PCT/CN2021/130018
Authority: WO
Inventors: 周丹; 翟少兵; 罗刚; 韩龙章
Original assignee: 重庆宗申航空发动机制造有限公司
Priority date: 2020-11-13
Filing date: 2021-11-11
Publication date: 2022-05-19
Also published as: CN112436675B; CN112436675A

Abstract

Disclosed in the present invention is a dual-generator structure of an aero-engine, comprising a crankshaft and two generators connected in series, including a first generator and a second generator, wherein the first generator and the second generator are both internal-stator and external-rotor generators, the external rotor of the first generator is in transmission connection with the crankshaft, the internal stator of the first generator is fixedly connected to a crankcase body, the internal stator of the second generator is fixedly connected to the crankcase body, and the external rotor of the second generator is flexibly connected to the crankshaft or the external rotor of the first generator. With the dual-generator structure of the present invention, the strength is improved and the vibration and breaking of a shaft are avoided.

Description

A dual-generator structure of an aero-engine

technical field

The present invention relates to an aeroengine, in particular to a double generator structure of the aeroengine.

Background technique

Aero-engines have high requirements on space and weight, especially for UAVs, the size and weight have a very serious impact on UAVs. In order to achieve higher power generation, customers can generally use the following methods: first, replace the high-power generator, but the size of the engine will be increased; second, use two generators, so that the Increase the power generation within the range allowed by the size.

Generally speaking, the generator of the existing aero-engine is fixedly sleeved on the crankshaft, and the rotation of the crankshaft drives the rotor of the generator to rotate to generate electricity. If the two generators are installed on the engine crankshaft, the axial dimension of the engine crankshaft is required to be increased, and the mold design needs to be re-opened on the basis of the existing engine. In addition, the existing design is rigidly connected to the rotor of the generator directly through the crankshaft to drive the rotor of the generator to rotate and generate electricity. The back-end generator center of gravity is far away from the engine and the moment of inertia is large, resulting in large fluctuations in the shafting speed, prone to resonance, and broken shafts. And other shortcomings, can not meet the generator life requirements.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a double generator structure of an aero-engine with high safety performance and large power generation.

In order to achieve the above object, the present invention is achieved as follows: an aero-engine dual-generator structure, including a crankshaft, and two series-connected generators, including a first generator and a second generator, the first generator The generator and the second generator are both inner stator and outer rotor generators, the outer rotor of the first generator is connected to the crankshaft in a drive, the inner stator of the first generator is fixedly connected to the crankcase, and the second generator is connected to the crankcase. The inner stator of the generator is fixedly connected to the crankcase, and the outer rotor of the second generator is flexibly connected to the crankshaft or the outer rotor of the first generator. The double generator structure arranged in the above manner adopts the rigid connection + flexible connection method, which can avoid the danger of shaft breakage and the like, and improve the safety performance of the engine. And the use of dual generators is higher, which can increase the power generation of the aero-engine.

Preferably, the outer rotor of the second generator is drivingly connected to the crankshaft or the outer rotor of the first generator through a flexible coupling.

Preferably, a coaxial connecting shaft is drivingly connected to the crankshaft, and the outer rotor of the second generator is sleeved on the connecting shaft through a bearing and connected to the connecting shaft through a flexible coupling.

In order to further improve reliability and safety, the outer rotor of the first generator is fixedly connected with a connecting shaft, and the connecting shaft is arranged coaxially with the crankshaft, and the outer rotor of the second generator is sleeved at the place through a bearing. on the connecting shaft and connected with the connecting shaft through a flexible coupling.

In order to further improve reliability and safety, the end of the connecting shaft facing the crankshaft is provided with a flange, and the flange is fixedly connected to the end face of the outer rotor of the first generator through screws.

In order to further shorten the axial distance, one end of the connecting shaft facing the crankshaft is provided with a shaft shoulder, and the inner stator of the second generator is sleeved on the connecting shaft through a ball bearing, and one end of the ball bearing is limited by the shaft shoulder. The other end is limited by the stepped surface of the inner stator of the second generator, and the inner stator of the second generator is fixedly connected to the crankcase through the bracket.

In order to further improve safety and stability, the outer rotor of the second generator is sleeved on the connecting shaft through needle bearings, and the outer end of the outer rotor of the second generator is sleeved on the connecting shaft through the shaft. The sleeve is limited, the outer sleeve of the sleeve is provided with a flexible coupling, the radial direction of the flexible coupling is fixedly connected to the shaft sleeve and the connecting shaft through screws, and the axial direction of the flexible coupling is connected to the second shaft through screws. The outer rotor of the generator is fixedly connected.

Preferably, the outer rotor of the first generator is keyed to the crankshaft, and a limiter for limiting the position of the outer rotor of the first generator is provided on the end face of the crankshaft.

In order to further improve the service life, the outer rotor of the first generator is matched with the crankshaft by a conical surface, the rear end of the crankshaft has an inward taper, and the inner hole of the outer rotor of the first generator is provided with the The end surface of the crankshaft is matched with the inner cone surface, the end surface of the crankshaft is provided with a gasket, and a screw passes through the gasket and is screwed with the inner hole of the crankshaft, and the screw limits the outer rotor of the first generator.

In order to further improve the structural reliability, a casing is provided on the outer casing of the second generator, and the casing is fixedly connected with the crankcase or the bracket.

In order to further improve the heat dissipation performance, ventilation holes are provided on the crankcase body, and ventilation holes are provided on the casing and the bracket.

In order to further improve the heat dissipation performance, the outer rotor of the first generator and the inner ring of the outer rotor of the second generator are provided with fan-shaped guide fins.

Beneficial effects:

The aero-engine dual-generator of the present invention adopts a series rigid connection + flexible connection scheme, which can avoid damage to the crankshaft caused by the large inertia of the engine during rotation. In addition, on the basis of the original transmission shaft system of the aero-engine, the connection of the dual generators is matched to meet the heat dissipation requirements, which can avoid the problems of the rigid connection scheme.

At the same time, the generator is easy to use and maintain. The front end is an outer rotor inner stator generator, which directly drives the outer rotor of the front end generator through the rigid connection of the crankshaft, and the crankcase body fixes the generator stator. The rear end is an outer rotor and inner stator generator. The outer rotor of the front end generator is connected to a coaxial generator connection shaft with the crankshaft. The generator connection shaft and the outer rotor of the rear end generator are connected by flexible parts, and the flexible connection parts can realize the circumferential direction. Vibration reduction and axial/radial deflection are satisfied by the needle roller bearing between the outer rotor and the connecting shaft, so that the double generator will not be offset and the operation is more reliable. Moreover, the generator bracket is connected through the crankcase, the generator bracket fixes the inner stator of the rear generator, and the inner stator is designed with rolling bearings to support the generator connecting shaft, so as to ensure the stable operation of the rear generator.

In addition, the present invention adopts the method of crankshaft (rigidly connected with the first generator) + connecting shaft (flexibly connected with the second generator) to avoid the large vibration and resonance of the end caused by the excessively long shaft, and improve the reliability of the shaft to avoid the risk of fracture of the crankshaft. And it can reduce the vibration intensity and ensure the reliability of the work.

Description of drawings

Fig. 1 is the front view of the double generator structure of the aero-engine in the embodiment;

Fig. 2 is the A-A sectional view of Fig. 1;

Figure 3 is an axonometric view of the connection between the cover and the bracket.

DESCRIPTION OF SYMBOLS: 1 crankshaft, 2 first generator, 21 inner stator of first generator, 22 outer rotor of first generator, 3 second generator, 31 inner stator of second generator, 32 second generator outer rotor, 4 crankcase, 5 bracket, 51 connecting lug, 52 stator connecting hole, 53 box connecting hole, 54 casing connecting hole, 6 connecting shaft, 61 connecting shaft flange, 62 connecting shaft shoulder, 7 connecting keys, 8 washers, 9 screws, 10 ball bearings, 11 needle bearings, 12 bushings, 13 flexible couplings, 14 housings, 15 ventilation holes.

Detailed ways

The specific embodiments of the present invention will be described in further detail below in conjunction with the accompanying drawings, but the present invention is not limited to these embodiments, and any improvement or substitution in the basic spirit of the present embodiment still belongs to the protection of the claims of the present invention. scope.

Embodiment: As shown in Figures 1-3, this embodiment provides a dual-generator structure of an aero-engine, which is especially suitable for unmanned aerial vehicles. Including a crankshaft 1, and two series-connected generators, namely a first generator 2 and a second generator 3, the first generator in this embodiment is an inner stator outer rotor generator, and the second generator is also It is an inner stator outer rotor generator. The "series connection" mentioned in this embodiment means that the axes of the two generators are the same straight line.

In this embodiment, the inner stator 21 of the first generator is fixedly connected to the crankcase 4 by means of screws, and the outer rotor 22 of the first generator is drive-connected to the crankshaft. Specifically: the end of the crankshaft has an inward (axial) taper, and the inner ring of the outer rotor of the first generator has a taper matched with the crankshaft. A connecting key 7 is also provided between the crankshaft and the inner ring of the outer rotor of the first generator. Therefore, the crankshaft and the outer rotor of the first generator are connected by a key and are limited by a taper fit. In addition, the end face of the crankshaft is provided with a washer 8, and a screw 9 passes through the washer and is screwed into the inner hole of the crankshaft, and the screw restricts the outer rotor of the first generator in another direction. In this way, the service life of the key in the key connection can be ensured and wear and tear can be avoided.

The inner stator 31 of the second generator is directly or indirectly fixedly connected to the crankcase, and the outer rotor 32 of the second generator can be directly or indirectly connected to the crankshaft, or directly or indirectly to the first engine. The outer rotor is connected. In this embodiment, the inner stator of the first generator is fixedly connected to the crankcase through a bracket, and the outer rotor of the second generator is indirectly connected to the outer rotor of the first generator. .

Specifically, a connecting shaft 6 is also included, and the connecting shaft is arranged coaxially with the crankshaft. One end of the connecting shaft is provided with a flange 61, and the connecting shaft is fixedly connected to the outer rotor of the first generator through the flange, and a screw is used for fixed connection here. The outer wall of the end of the connecting shaft facing the crankshaft is provided with a shaft shoulder 62, and the inner stator of the second generator is sleeved on the connecting shaft through a ball bearing 19, and one end of the ball bearing is limited by the shaft shoulder, The other end is limited by the stepped surface of the inner stator of the second generator. The inner stator of the second generator is fixedly connected to the crankcase through the bracket 5 . The outer rotor of the second generator is sleeved on the connecting shaft through the needle roller bearing 11, and the outer end of the outer rotor of the second generator is limited by the shaft sleeve 12 sleeved on the connecting shaft, so The outer sleeve of the shaft sleeve is provided with a flexible coupling 13, and the end of the shaft sleeve is provided with a step for limiting the position of the flexible coupling. The radial direction of the flexible coupling is fixedly connected with the shaft sleeve and the connecting shaft through screws, and the axial direction of the flexible coupling is fixedly connected with the outer rotor of the second generator through screws. In this way, the installation of the first generator and the second generator is completed.

In this embodiment, the bracket used to connect the inner stator of the second generator and the crankcase is umbrella-shaped, the small end of which has an inner ring and the inner ring is provided with an axial stator connection hole 52, A screw is used to pass through the stator connection hole to connect with the inner stator of the second generator, and its large end face is provided with an axial case connection hole 53, and a screw is used to pass through the case connection hole to the crankshaft. Box connection.

As another implementation in this embodiment, a casing 14 is provided on the second generator casing, and the casing is fixedly connected to the crankcase or the bracket. In this embodiment, the large end of the bracket has a connecting lug 51 protruding outward, the lug is provided with a casing connecting hole 54, and a screw is used to pass through the casing connecting hole 54 to connect the The connecting lugs are fixedly connected with the housing. In this embodiment, the number of the connecting lugs is 4, and they are generally evenly distributed in the circumferential direction.

As another implementation in this embodiment, a ventilation hole 15 is provided on the crankcase body, and a ventilation hole is provided on the casing and the bracket.

As another implementation in this embodiment, the outer rotor of the first generator and the inner ring of the outer rotor of the second generator are provided with fan-shaped guide vanes.

The aero-engine dual-generator in this embodiment adopts the first generator rigid connection + the second generator flexible connection scheme. On the basis of the original transmission shaft of the aero-engine, the dual-generator connection is matched to meet the heat dissipation requirements, and the rigid connection scheme can be avoided. problems that arise. At the same time, the generator is easy to use and maintain. The front end is an outer rotor inner stator generator, which directly drives the outer rotor of the front end generator through the rigid connection of the crankshaft, and the crankcase body fixes the generator stator. The rear end is an outer rotor and inner stator generator. The outer rotor of the front end generator is connected to a coaxial generator connection shaft with the crankshaft. The generator connection shaft and the outer rotor of the rear end generator are connected by flexible parts, and the flexible connection parts can realize the circumferential direction. Vibration damping and axial/radial deflection are met by needle roller bearings between the outer rotor and the connecting shaft. The generator bracket is connected through the crankcase, the generator bracket fixes the inner stator of the rear generator, and the inner stator is designed with rolling bearings to support the generator connecting shaft to ensure the stable operation of the rear generator.

Claims

An aero-engine dual-generator structure is characterized in that it includes a crankshaft and two series-connected generators, including a first generator and a second generator, wherein the first generator and the second generator are both inner stators For an external rotor generator, the first generator is rigidly connected to the crankshaft, and the second generator is directly or indirectly flexibly connected to the crankshaft.
The dual-generator structure of an aero-engine according to claim 1, characterized in that: the outer rotor of the first generator is in driving connection with the crankshaft, and the inner stator of the first generator is fixedly connected with the crankcase. , the inner stator of the second generator is directly or indirectly fixedly connected to the crankcase, and the outer rotor of the second generator is directly or indirectly flexibly connected to the crankshaft or the outer rotor of the first generator.
The dual-generator structure of an aero-engine according to claim 2, wherein the outer rotor of the second generator and the crankshaft or the outer rotor of the first generator are drive-connected through a flexible coupling.
The dual-generator structure of an aero-engine as claimed in claim 3, wherein a coaxial connecting shaft is drivingly connected to the crankshaft, and the outer rotor of the second generator is sleeved on the said crankshaft through a bearing. The connecting shaft is connected with the connecting shaft through a flexible coupling.
The dual-generator structure of an aero-engine according to claim 3, characterized in that: the outer rotor of the first generator is fixedly connected with a connecting shaft, the connecting shaft and the crankshaft are arranged coaxially, and the second generator The outer rotor of the machine is sleeved on the connecting shaft through a bearing and is connected with the connecting shaft through a flexible coupling.
The dual-generator structure of an aero-engine as claimed in claim 5, wherein the end of the connecting shaft facing the crankshaft is provided with a flange, and the flange is connected to the outer rotor of the first generator through screws. End face fixed connection.
The dual-generator structure of an aero-engine according to claim 6, characterized in that: the end of the connecting shaft facing the crankshaft is provided with a shoulder, and the inner stator of the second generator is sleeved on the connecting shaft through a ball bearing. On the shaft, one end of the ball bearing is limited by the shaft shoulder, and the other end is limited by the stepped surface of the inner stator of the second generator, which is fixedly connected to the crankcase through the bracket.
The double generator structure of an aero-engine according to claim 5, 6 or 7, characterized in that: the outer rotor of the second generator is sleeved on the connecting shaft through needle roller bearings, and the second generator is The outer end of the outer rotor is limited by a shaft sleeve sleeved on the connecting shaft, the sleeve sleeve is provided with a flexible coupling, and the radial direction of the flexible coupling is fixedly connected with the shaft sleeve and the connecting shaft through screws, The axial direction of the flexible coupling is fixedly connected with the outer rotor of the second generator through screws.
The dual-generator structure of an aero-engine according to any one of the preceding claims, characterized in that: the outer rotor of the first generator is keyed to the crankshaft, and an end face of the crankshaft is provided with a pair of generators for the first generator. The limiter for limiting the outer rotor of the machine.
The dual-generator structure of an aero-engine according to claim 9, wherein the outer rotor of the first generator and the crankshaft are matched with a conical surface, the rear end of the crankshaft has an inward taper, and the first The inner hole of the outer rotor of the generator is provided with an inner conical surface matched with the rear end of the crankshaft, the end surface of the crankshaft is provided with a gasket, and a screw passes through the gasket and is screwed with the inner hole of the crankshaft, and the screw Limit the outer rotor of the first generator.
The dual-generator structure of an aero-engine according to any one of the preceding claims is characterized in that: a casing is provided on the second generator casing, and the casing is fixedly connected to the crankcase or the bracket.
The dual-generator structure of an aero-engine according to claim 11, wherein the crankcase body is provided with ventilation holes, and the casing and the bracket are provided with ventilation holes.
The dual generator structure of aero-engine according to any one of the preceding claims, characterized in that: the outer rotor of the first generator and the inner ring of the outer rotor of the second generator are provided with fan-shaped guide vanes.