CN117780861A - Aeroengine gearbox with external equipment driving mechanism - Google Patents
Aeroengine gearbox with external equipment driving mechanism Download PDFInfo
- Publication number
- CN117780861A CN117780861A CN202311577833.XA CN202311577833A CN117780861A CN 117780861 A CN117780861 A CN 117780861A CN 202311577833 A CN202311577833 A CN 202311577833A CN 117780861 A CN117780861 A CN 117780861A
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- Prior art keywords
- gear
- gearbox
- aeroengine
- housing
- compressor
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- 230000005540 biological transmission Effects 0.000 claims abstract description 27
- 238000007789 sealing Methods 0.000 claims description 6
- 238000010276 construction Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 6
- 230000002411 adverse Effects 0.000 abstract 1
- 230000000694 effects Effects 0.000 abstract 1
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 230000010354 integration Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000001816 cooling Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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- Applications Or Details Of Rotary Compressors (AREA)
Abstract
The invention belongs to the technical field of aeroengines, and relates to an aeroengine gearbox with an external equipment driving mechanism. The aeroengine gearbox comprises a gearbox shell, a propeller shaft and a driving mechanism, wherein the driving mechanism comprises a driving gear, a gear shaft, a connecting block and a spline housing. The driving mechanism transmits the output power of the engine to the compressor crankshaft, realizes the integral installation of the compressor and the direct-drive transmission of gears, meets the requirement of the operation of the same rotation speed of the engine crankshaft and the rotation speed of external equipment, realizes the integral arrangement of the driving mechanism, and avoids the adverse effect on the propeller output shaft and the engine. According to the invention, the mounting position of the air compressor is transferred from the free end of the crankshaft of the aeroengine to the crankshaft end of the gearbox of the aeroengine, so that the problem of mounting space of the air compressor is solved, the direct power transmission between the engine and the air compressor is realized, the safety and the reliability are improved, and the requirement of the aeroengine on the high rotating speed of the air compressor during working is met.
Description
Technical Field
The invention belongs to the technical field of aeroengines, and relates to an aeroengine gearbox with an external equipment driving mechanism.
Background
At present, a vacuum pump transmission gear and an output shaft can be arranged at the position of the transmission of the aero-engine, and a crankshaft of the transmission drives a vacuum pump to work, but the volume of the vacuum pump is larger, so that the requirement of compact design of the aero-engine cannot be met. Meanwhile, the transmission ratio between the transmission gear of the vacuum pump and the driving gear of the transmission gear box of the aeroengine is small, so that the rated rotation speed of the vacuum pump is low, the requirement of high rotation speed of the aeroengine cannot be met, and the working efficiency of the aeroengine is reduced. The output shaft of the vacuum pump of the aeroengine gearbox is connected with the transmission gear through a key, compared with the transmission shaft formed integrally, the transmission shaft is complex to install and high in production cost through the key connection, and hidden danger exists in stability of the transmission shaft when the aeroengine works under high load, so that the working reliability is reduced.
When the compressor is used for replacing a vacuum pump as external equipment, the problem that the vacuum pump is large in volume and cannot meet the compact design of the aero-engine structure can be solved. However, the conventional compressor mounting position is arranged at the free end of the engine crankshaft, which conflicts with the placement position of the aero-engine generator. The space of the free end of the crankshaft of the aeroengine is narrow, which is not beneficial to the installation of the air compressor, and when the air compressor works under high load, the air compressor can generate higher temperature, and when the air compressor is in a working environment with narrow space, the air compressor is not beneficial to the cooling treatment of the air compressor. And when the installation position of the compressor is arranged at the free end of the engine crankshaft at present, the transmission mode is belt transmission, compared with gear transmission, the belt can have abrasion after long-time working, the replacement is troublesome, the working stability is poor when in high-load working, the maintenance is troublesome, and the production cost is higher.
Therefore, a brand new mechanism matched with the aeroengine for driving external equipment is necessary to be designed, the problems in the prior art are solved, the mounting position of the air compressor can be transferred from the free end of the crankshaft of the aeroengine to the crankshaft end of the gearbox of the aeroengine, the problem that the mounting space of the air compressor is limited is solved, meanwhile, the direct power transmission between the engine and the air compressor can be realized, the safety and the reliability of the aeroengine are improved, and meanwhile, the requirement of the aeroengine on high rotation speed of the air compressor during operation is met.
Disclosure of Invention
The technical scheme adopted by the invention is as follows:
an aeroengine gearbox with an external device driving mechanism comprises a gearbox housing 1, a compressor crankshaft 7, a compressor housing 8, a propeller shaft 12 and a driving mechanism; the driving mechanism comprises a driving gear 2, a gear shaft 3, a bearing 4, a spline housing 5 and a connecting block 6;
a driving gear 2 is connected to the shaft outer side of the propeller shaft 12; one end of the gear shaft 3 is provided with a gear structure, and the other end of the gear shaft is provided with a first spline groove; the driving gear 2 is meshed with a gear on the gear shaft 3, and the propeller shaft 12 transmits the power of the propeller shaft 12 to the gear shaft 3 through the meshing of the driving gear 2 and the gear on the gear shaft 3; the first spline groove at the other end of the gear shaft 3 is meshed with one side of the spline housing 5, and the other side of the spline housing 5 is meshed with a second spline groove arranged on the compressor crankshaft 7, so that the power of the gear shaft 3 is transmitted to the compressor crankshaft 7;
the driving gear 2, the gear shaft 3, the bearing 4 and the propeller shaft 12 are positioned inside the gearbox housing 1; the compressor crankshaft 7 is positioned in the compressor housing 8;
a connecting block 6 is arranged between the gearbox housing 1 and the compressor housing 8, the housing connecting structure penetrates through a connecting hole in the connecting block 6 to connect the gearbox housing 1 and the compressor housing 8 together, and the inner side surface of the connecting block 6 is in contact with the outer side surface of the middle part of the spline housing 5.
Preferably, bearings 4 are arranged at the left end and the right end of the gear shaft 3 outside the inner side of the gear structure and the first spline groove, and oil seals 9 are arranged between the bearings 4 at the left end and the right end of the gear shaft 3; the outer side surface of the bearing 4 is contacted with the outer side surface of the oil seal 9 and the inner side surface of the gearbox housing 1.
Preferably, a first sealing ring 10 is arranged on the connecting side between the gearbox housing 1 and the connecting block 6, and a second sealing ring 11 is arranged on the connecting side between the connecting block 6 and the compressor housing 8.
Preferably, the propeller shaft 12 is connected to the driving gear 2 by means of splines.
Preferably, the shell connecting structure is a screw, and the connecting hole on the connecting block 6 is a screw hole.
Preferably, the driving gear 2 and the gear shaft 3 are of a high transmission ratio structure.
Further, the transmission ratio of the driving gear 2 to the gear shaft 3 is 2-3.
The invention has the beneficial effects that:
the invention designs an external equipment driving mechanism matched with the aeroengine gearbox, which connects the aeroengine gearbox with external equipment, can better match with the external equipment applicable to the engine, improves the system integration level, and ensures that the whole structure of the engine is more compact and efficient;
the traditional compressor mounting position is too narrow and small, is unfavorable for compressor heat dissipation, and the installation is too complicated. The transmission mechanism is positioned between the gearbox shell and the air compressor, the installation space is not limited, the heat dissipation problem of the air compressor can be effectively solved, and the working efficiency and the safety and the reliability are improved;
compared with the traditional compressor belt transmission mode, the driving mechanism with the gear shaft is provided, so that the technical requirements of high reliability, high integration level and high power-to-weight ratio of an aeroengine can be better met, and the belt abrasion condition of long-time working of the belt transmission is avoided;
compared with the traditional hydraulic variable pitch (vacuum pump) output shaft of the aeroengine gearbox, which is meshed with a transmission gear by a key, the invention provides an integrated design of the output shaft and the transmission gear, which has simple installation, low production cost and high reliability.
Drawings
Fig. 1 is a schematic cross-sectional view of an aeroengine gearbox with an external device driving mechanism according to the present invention.
Detailed Description
The present invention will be further described in detail with reference to the following examples in order to make the objects, technical solutions and advantages of the present invention more apparent. It should be noted that the present invention is not limited to the following examples.
The working principle of the invention is that the engine power is transmitted to the gear shaft through the meshing of the driving gear and the gear on the gear shaft to drive the gear shaft to rotate, and the gear shaft is connected with the crankshaft of the compressor through the spline housing to transmit the power to the compressor to drive the compressor to work.
Example 1
As shown in fig. 1, an aeroengine gearbox with an external device driving mechanism comprises a gearbox housing 1, a compressor crankshaft 7, a compressor housing 8, a propeller shaft 12 and a driving mechanism; the driving mechanism comprises a driving gear 2, a gear shaft 3, a bearing 4, a spline housing 5 and a connecting block 6;
the outside of the propeller shaft 12 is connected with a driving gear 2 through a spline; one end of the gear shaft 3 is provided with a gear structure, and the other end of the gear shaft is provided with a first spline groove; the driving gear 2 is meshed with a gear on the gear shaft 3, and the propeller shaft 12 transmits the power of the propeller shaft 12 to the gear shaft 3 through the meshing of the driving gear 2 and the gear on the gear shaft 3; the first spline groove at the other end of the gear shaft 3 is meshed with one side of the spline housing 5, and the other side of the spline housing 5 is meshed with a second spline groove arranged on the compressor crankshaft 7, so that the power of the gear shaft 3 is transmitted to the compressor crankshaft 7;
the driving gear 2, the gear shaft 3, the bearing 4 and the propeller shaft 12 are positioned inside the gearbox housing 1; the compressor crankshaft 7 is positioned in the compressor housing 8;
a connecting block 6 is arranged between the gearbox housing 1 and the compressor housing 8, a screw penetrates through a screw hole on the connecting block 6 to connect the gearbox housing 1 and the compressor housing 8 together, and the inner side surface of the connecting block 6 is contacted with the outer side surface of the middle part of the spline housing 5;
bearings 4 are arranged at the left end and the right end of the gear shaft 3 outside the inner side of the gear structure and the first spline groove, and an oil seal 9 is arranged between the bearings 4 at the left end and the right end of the gear shaft 3; the outer side surface of the bearing 4 is contacted with the outer side surface of the oil seal 9 and the inner side surface of the gearbox housing 1;
the side face of the connection between the gearbox housing 1 and the connecting block 6 is provided with a first sealing ring 10, and the side face of the connection between the connecting block 6 and the compressor housing 8 is provided with a second sealing ring 11.
The transmission ratio of the driving gear 2 to the gear shaft 3 is 3.
Compared with a driving gear with smaller transmission ratio of a traditional aeroengine gearbox, the driving gear with high transmission ratio is provided, and the requirement of high rotating speed of the aeroengine is met.
The foregoing is merely a preferred embodiment of the present invention, and it should be noted that modifications and variations could be made by those skilled in the art without departing from the technical principles of the present invention, and such modifications and variations should also be regarded as being within the scope of the invention.
Claims (7)
1. An aeroengine gearbox with an external equipment driving mechanism is characterized by comprising a gearbox housing (1), a compressor crankshaft (7), a compressor housing (8), a propeller shaft (12) and a driving mechanism; the driving mechanism comprises a driving gear (2), a gear shaft (3), a bearing (4), a spline housing (5) and a connecting block (6);
a driving gear (2) is connected to the outer side of the propeller shaft (12); one end of the gear shaft (3) is provided with a gear structure, and the other end of the gear shaft is provided with a first spline groove; the driving gear (2) is meshed with a gear on the gear shaft (3), and the propeller shaft (12) transmits power of the propeller shaft (12) to the gear shaft (3) through the meshing of the driving gear (2) and the gear on the gear shaft (3); the first spline groove at the other end of the gear shaft (3) is meshed with one side of the spline sleeve (5), and the other side of the spline sleeve (5) is meshed with a second spline groove arranged on the compressor crankshaft (7) to transmit the power of the gear shaft (3) to the compressor crankshaft (7);
the driving gear (2), the gear shaft (3), the bearing (4) and the propeller shaft (12) are positioned in the gearbox shell (1); the compressor crankshaft (7) is positioned in the compressor shell (8);
a connecting block (6) is arranged between the gearbox housing (1) and the compressor housing (8), the housing connecting structure penetrates through a connecting hole in the connecting block (6) to connect the gearbox housing (1) and the compressor housing (8) together, and the inner side surface of the connecting block (6) is in contact with the outer side surface of the middle part of the spline housing (5).
2. The aeroengine gearbox with the external equipment driving mechanism according to claim 1, wherein bearings (4) are arranged at the left end and the right end of the gear shaft (3) outside the inner side of the gear structure and the first spline groove, and oil seals (9) are arranged between the bearings (4) at the left end and the right end of the gear shaft (3); the outer side surface of the bearing (4) is contacted with the outer side surface of the oil seal (9) and the inner side surface of the gearbox housing (1).
3. Aeroengine gearbox with external equipment driving mechanism according to claim 1, characterized in that the side of the connection between the gearbox housing (1) and the connection block (6) is provided with a first sealing ring (10), and the side of the connection between the connection block (6) and the compressor housing (8) is provided with a second sealing ring (11).
4. Aeroengine gearbox with external equipment drive mechanism according to claim 1, wherein the propeller shaft (12) is connected with the driving gear (2) by means of splines.
5. Aeroengine gearbox with external equipment driving mechanism according to claim 1, wherein the housing connection structure is a screw and the connection holes on the connection block (6) are screw holes.
6. Aeroengine gearbox with external equipment drive mechanism according to claim 1, wherein the driving gear (2) and gear shaft (3) are of high ratio construction.
7. Aeroengine gearbox with external equipment drive according to claim 6, wherein the transmission ratio of the driving gear (2) to the gear shaft (3) is 2-3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311577833.XA CN117780861A (en) | 2023-11-24 | 2023-11-24 | Aeroengine gearbox with external equipment driving mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311577833.XA CN117780861A (en) | 2023-11-24 | 2023-11-24 | Aeroengine gearbox with external equipment driving mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117780861A true CN117780861A (en) | 2024-03-29 |
Family
ID=90393451
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311577833.XA Pending CN117780861A (en) | 2023-11-24 | 2023-11-24 | Aeroengine gearbox with external equipment driving mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117780861A (en) |
-
2023
- 2023-11-24 CN CN202311577833.XA patent/CN117780861A/en active Pending
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