CN213279414U - Double-generator structure of aircraft engine - Google Patents
Double-generator structure of aircraft engine Download PDFInfo
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- CN213279414U CN213279414U CN202022621513.8U CN202022621513U CN213279414U CN 213279414 U CN213279414 U CN 213279414U CN 202022621513 U CN202022621513 U CN 202022621513U CN 213279414 U CN213279414 U CN 213279414U
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- crankshaft
- rotor
- aircraft engine
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Abstract
The utility model discloses an aeroengine's two generator structures, its characterized in that: the generator comprises a crankshaft and two generators connected in series, and comprises a first generator and a second generator, wherein the first generator is an inner stator outer rotor generator, the second generator is an inner rotor outer stator generator, the first generator is rigidly connected with the crankshaft, and the second generator is directly or indirectly connected with the crankshaft or the outer rotor of the first generator. Adopt the utility model discloses a two generator structures have improved the generated energy and have improved the security performance again promptly.
Description
Technical Field
The utility model relates to an aeroengine especially relates to aeroengine's two generator structures.
Background
The aeroengine has higher requirements on space and weight, and especially for the unmanned aerial vehicle, the overall dimension and the weight have very serious influence on the unmanned aerial vehicle. In order to achieve higher power generation, the customer generally uses the following methods: first, a high-power generator is replaced, but the size of the engine is increased; second, two generators are used, which can increase the power generation within a size allowable range.
Generally, a generator of an existing aircraft engine is fixedly sleeved on a crankshaft, and a rotor of the generator is driven to rotate by the rotation of the crankshaft to generate electricity. If the two generators are arranged on the crankshaft of the engine, the requirement on the axial size of the crankshaft of the engine is increased, and the mold opening design needs to be carried out again on the basis of the existing engine. In addition, the existing design directly and rigidly connects the crankshaft with the rotor of the generator to drive the rotor of the generator to rotate for power generation, so that the defects that the center of gravity of the rear-end generator is far away from the engine, the rotational inertia is large, the rotation speed fluctuation of a shafting is large, resonance and shaft breakage are easy to occur, and the service life requirement of the generator cannot be met.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a big and small aeroengine's of generated energy double generator structure.
In order to achieve the above object, the present invention is realized as follows: the utility model provides an aeroengine's two generator structures which characterized in that: the generator comprises a crankshaft and two generators connected in series, and comprises a first generator and a second generator, wherein the first generator is an inner stator outer rotor generator, the second generator is an inner rotor outer stator generator, the first generator is rigidly connected with the crankshaft, and the second generator is directly or indirectly connected with the crankshaft or the outer rotor of the first generator. The double generators serially arranged in the mode can improve the generating capacity, reduce the size and have compact axial size.
Preferably, the stator of the first generator is fixedly connected with the crankcase body, and the outer rotor of the first generator is sleeved on the crankshaft and is in transmission connection with the crankshaft.
In order to further realize reliable transmission connection, the outer rotor of the first generator is connected with the crankshaft in a key mode, and a limiting piece for limiting the outer rotor of the first generator is arranged on the end face of the crankshaft.
In order to further improve the service life and reduce the abrasion to a connecting key, the outer rotor of the first generator is in conical surface fit with the crankshaft, the tail end of the crankshaft is provided with inward taper, an inner conical surface matched with the tail end of the crankshaft is arranged in an inner hole of the outer rotor of the first generator, a gasket is arranged on the end face of the crankshaft, a screw penetrates through the gasket and is in threaded connection with the inner hole of the crankshaft, and the screw limits the outer rotor of the first generator.
Preferably, the crankshaft is in transmission connection with a coaxial connecting shaft, and an inner rotor of the second generator is in transmission connection with the connecting shaft.
In order to further improve the safety performance of the crankshaft, reduce the axial volume and avoid the fracture of the crankshaft, 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 inner rotor of the second generator is in transmission connection with the connecting shaft.
Preferably, a shaft shoulder is arranged at one end, facing the crankshaft, of the connecting shaft, an inner rotor of the second generator is fixedly sleeved on the connecting shaft, one end of the inner rotor of the second generator is limited through the shaft shoulder, and the other end of the inner rotor of the second generator is limited through a screw and a gasket.
Preferably, the outer stator of the second generator is fixedly connected with the crankcase body.
Furthermore, an enclosure is sleeved outside the second generator, a stator of the second generator is fixedly mounted on the enclosure, and the enclosure is fixedly connected with the crankcase body.
In order to further improve the heat dissipation effect, the housing is provided with a vent hole.
Has the advantages that:
the utility model discloses a mode of two generator series connection of aeroengine on the former transmission shafting basis of aeroengine, matches two generator and connects, satisfies the electricity generation demand. Meanwhile, the generator is convenient to use and maintain. The front end is an outer rotor inner stator generator which is rigidly connected with a crankshaft to directly drive the outer rotor of the front end generator and a crankshaft box body to fix a generator stator. The rear end is the outer stator generator of inner rotor, connect one through the front end generator external rotor and with the coaxial connecting axle of bent axle, the connecting axle directly links firmly the inner rotor of second generator with the rear end to it is spacing through both ends axial, the outer stator of second generator is fixed on the housing and is linked firmly housing and bent axle box, so, can shorten the axial length of two generators greatly, and can guarantee the reliability and the security of bent axle, avoid the bent axle because of resonance or the fracture that tip vibration intensity is big and lead to. The reliability of the shaft is improved, and the danger of breakage of the crankshaft is avoided. And the vibration intensity can be reduced, and the working reliability is ensured. The stable work of the double generators is ensured.
Drawings
FIG. 1 is a front view of a dual generator configuration of an aircraft engine in an embodiment;
FIG. 2 is a cross-sectional view of FIG. 1;
fig. 3 is an isometric view of the housing.
Description of reference numerals: 1 crankshaft, 2 first generators, 21 inner stator of the first generators, 22 outer rotor of the first generators, 3 second generators, 31 outer stator of the second generators, 32 inner rotor of the second generators, 4, gasket, 5 screw, 6 connecting shaft, 61 connecting shaft flange, 62 connecting shaft shoulder, second gasket 7, second nut 8, 9 encloser, 91 support lug, 92 box connecting hole, 93 vent hole and 10 crankcase body.
Detailed Description
The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings, but the present invention is not limited to these embodiments, and any modifications or replacements within the basic spirit of the embodiments still fall within the scope of the present invention claimed in the claims.
Example (b): as shown in fig. 1-3, the present embodiment provides a dual generator structure of an aircraft engine, which is particularly suitable for an unmanned aerial vehicle. The generator comprises a crankshaft 1 and two generators connected in series, namely a first generator 2 and a second generator 3, wherein the first generator is an inner stator and outer rotor generator, and the second generator is an inner rotor and outer stator generator. In this embodiment, the term "in series" means that the axes of the two generators are the same straight line.
In the embodiment, the inner stator 21 of the first generator is fixedly connected with the crankcase body 10 by using a screw, and the outer rotor 22 of the first generator is in transmission connection with the crankshaft. Specifically, the method comprises the following steps: 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. And a connecting key 7 is also arranged 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 in key connection and are limited in a taper fit mode. In addition, the end face of the crankshaft is provided with a gasket 4, a screw 5 penetrates through the gasket and is in threaded connection with the inner hole of the crankshaft, and the screw limits the outer rotor of the first generator in the other direction. By adopting the mode, the service life of the key in the key connection can be ensured, and abrasion is avoided.
The outer stator 31 of the second generator is directly or indirectly fixedly connected with the crankcase body, and the inner rotor 32 of the second generator can be directly or indirectly connected with the crankshaft and also can be directly or indirectly connected with the outer rotor of the first generator. In this embodiment, the outer circumference of the outer stator of the first generator is fixed to a cover, and the cover is fixedly connected to the crankcase by screws. The inner rotor of the second generator is connected with the outer rotor of the first generator in an indirect mode.
Specifically, the crankshaft connecting structure further comprises a connecting shaft 6, and the connecting shaft and the crankshaft are arranged coaxially. One end of the connecting shaft is provided with a flange plate 61, and the connecting shaft is fixedly connected with the outer rotor of the first generator through the flange plate, and is fixedly connected with the outer rotor of the first generator through screws. A shaft shoulder 62 is arranged on the outer wall of one end, facing the crankshaft, of the connecting shaft, the inner rotor of the second generator is sleeved on the connecting shaft in a transmission mode, one end face of the inner rotor of the second generator is limited through the shaft shoulder, and the other end of the inner rotor of the second generator is axially limited through a second gasket 7 and a second nut 8 which are sleeved on the connecting shaft. In another embodiment of this embodiment, a stepped surface is provided at an end of the connecting shaft away from the crankshaft, a section of the connecting shaft away from an extreme end of the crankshaft is a section of the connecting shaft having a smallest diameter, and the spacer and the nut are sleeved on the small-diameter section.
As another embodiment in this embodiment, the inner rotor of the second generator is in key connection with the connecting shaft to realize transmission, but may also be in key connection with the connecting shaft to realize transmission.
Wherein, the housing 9 is bowl dress and wraps up the second generator, the open end of housing is provided with three lugs 91 that outwards stretch out, seted up box connecting hole 92 on the lug, adopt the screw to pass box connecting hole on the lug with crankcase fixed connection.
In addition, the housing is provided with a vent hole 93. In this embodiment, a plurality of axially disposed vent holes are formed along the circumference of the housing.
The mode that the two generators of aeroengine of this embodiment establish ties matches two generator and connects on the basis of the original transmission shafting of aeroengine, satisfies the heat dissipation demand. Meanwhile, the generator is convenient to use and maintain. The front end is an outer rotor inner stator generator which is rigidly connected with a crankshaft to directly drive the outer rotor of the front end generator and a crankshaft box body to fix a generator stator. The rear end is the outer stator generator of inner rotor, connect one through the front end generator external rotor and with the coaxial connecting axle of bent axle, the connecting axle directly links firmly the inner rotor of second generator with the rear end to it is spacing through both ends axial, the outer stator of second generator is fixed on the housing and is linked firmly housing and bent axle box, so, can shorten the axial length of two generators greatly, and can guarantee the reliability and the security of bent axle, avoid the bent axle to respond to resonance or the tip vibration intensity is big and the fracture that leads to. The reliability of the shaft is improved, and the danger of breakage of the crankshaft is avoided. And the vibration intensity can be reduced, and the working reliability is ensured. The stable work of the double generators is ensured.
Claims (10)
1. The utility model provides an aeroengine's two generator structures which characterized in that: the generator comprises a crankshaft and two generators connected in series, and comprises a first generator and a second generator, wherein the first generator is an inner stator outer rotor generator, the second generator is an inner rotor outer stator generator, the first generator is rigidly connected with the crankshaft, and the second generator is directly or indirectly connected with the crankshaft or the outer rotor of the first generator.
2. A dual generator configuration for an aircraft engine as defined in claim 1, wherein: the stator of the first generator is fixedly connected with the crankcase body, and the outer rotor of the first generator is sleeved on the crankshaft and is in transmission connection with the crankshaft.
3. A dual generator configuration for an aircraft engine as defined in claim 2, wherein: the outer rotor of the first generator is connected with the crankshaft key, and a limiting piece for limiting the outer rotor of the first generator is arranged on the end face of the crankshaft.
4. A dual generator configuration for an aircraft engine as defined in claim 3, wherein: the outer rotor of the first generator is in conical surface fit with the crankshaft, the tail end of the crankshaft is provided with inward taper, an inner conical surface matched with the tail end of the crankshaft is arranged in an inner hole of the outer rotor of the first generator, a gasket is arranged on the end face of the crankshaft, a screw penetrates through the gasket and is in threaded connection with the inner hole of the crankshaft, and the screw limits the outer rotor of the first generator.
5. A dual generator arrangement for an aircraft engine as claimed in claim 1, 2, 3 or 4, wherein: the crankshaft is in transmission connection with a coaxial connecting shaft, and an inner rotor of the second generator is in transmission connection with the connecting shaft.
6. A dual generator arrangement for an aircraft engine as claimed in claim 1, 2, 3 or 4, wherein: 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 inner rotor of the second generator is in transmission connection with the connecting shaft.
7. A dual generator configuration for an aircraft engine as defined in claim 5, wherein: the connecting shaft is provided with a shaft shoulder towards one end of the crankshaft, an inner rotor of the second generator is fixedly sleeved on the connecting shaft, one end of the inner rotor of the second generator is limited through the shaft shoulder, and the other end of the inner rotor of the second generator is limited through a screw and a gasket.
8. A dual generator configuration for an aircraft engine as defined in claim 7, wherein: and the outer stator of the second generator is fixedly connected with the crankcase body.
9. A dual generator configuration for an aircraft engine as defined in claim 8, wherein: an outer cover of the second generator is sleeved with the housing, a stator of the second generator is fixedly installed on the outer cover, and the housing is fixedly connected with the crankcase body.
10. A dual generator configuration for an aircraft engine as defined in claim 9, wherein: the housing is provided with a vent hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022621513.8U CN213279414U (en) | 2020-11-13 | 2020-11-13 | Double-generator structure of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022621513.8U CN213279414U (en) | 2020-11-13 | 2020-11-13 | Double-generator structure of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213279414U true CN213279414U (en) | 2021-05-25 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022621513.8U Active CN213279414U (en) | 2020-11-13 | 2020-11-13 | Double-generator structure of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213279414U (en) |
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2020
- 2020-11-13 CN CN202022621513.8U patent/CN213279414U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: Building 14, No. 126, Yunan Avenue, Banan District, Chongqing Patentee after: Chongqing Zongshen Aviation Engine Manufacturing Co.,Ltd. Address before: Building 14, No. 126, Yunan Avenue, Banan District, Chongqing Patentee before: CHONGQING ZONGSHEN AIRCRAFT ENGINE MANUFACTURING CO.,LTD. |
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| CP01 | Change in the name or title of a patent holder |