CN212429040U

CN212429040U - Double-fan engine

Info

Publication number: CN212429040U
Application number: CN202021286031.5U
Authority: CN
Inventors: 梁锦云
Original assignee: Individual
Current assignee: Individual
Priority date: 2020-07-03
Filing date: 2020-07-03
Publication date: 2021-01-29
Anticipated expiration: 2030-07-03

Abstract

The utility model discloses a double-fan engine, which comprises a support component, a fan, a gearbox and an engine main unit, wherein the support component is provided with a flow guide cover and an air inlet and is used for being connected with an aircraft; the fans are arranged at the air inlet and are provided with a plurality of air inlets, and the fans are connected with the main shaft; the gearbox is rotationally connected with the main shaft and is arranged in the support component; the engine host computer is connected with the supporting component and is equipped with the pivot, and the pivot rotates with the gearbox and is connected. The utility model provides a pair of two fan engines, the setting up of a plurality of fans has reduced the traction force of fan to the engine host computer when having increased the duct ratio, and can not cause extra pressure to the spare part. The utility model discloses effectively solve and lead to part wearing and tearing to accelerate, engine life shortens and for increaseing the torque moment that the duct ratio leads to the engine reduces, problem that slows down with higher speed for overcoming the traction force of fan or thick liquid.

Description

Double-fan engine

Technical Field

The utility model relates to an aircraft power technical field, in particular to, a two-fan engine.

Background

The development history of aircraft engines started from the earliest propeller, the automobile needs to be driven by wheels, and engines such as turbofan engines and turboprop engines need front propeller or fan to drive the aircraft to move ahead more effectively.

At present, in the development of an aeroengine, some problems of comparatively contradictory selectivity exist, for example, the effect is not ideal when a turboprop engine runs at a high speed, and the effect is not ideal when a turbofan engine runs at a low speed. Most designers therefore desire to increase the bypass ratio of turbofan engines to better economy and low speed maneuverability of the engines. In addition, the fan or the propeller of the existing engine generates considerable traction force on the engine in the flying process, and in order to overcome the traction force of the fan or the propeller, the thrust bearing is arranged in the main shaft of the engine to counteract the traction force, so that the thrust bearing becomes the part with the largest stress in the airplane and is also the part with the fastest abrasion, and the whole service life of the engine is influenced finally. In addition, the diameter of the fan is increased to increase the air flow rate of the turbofan engine, and the torque of the engine is reduced by the fan with the increased diameter, so that the acceleration is slowed down, and the like.

In view of the above problems, it is desirable to design an engine that solves the problems of the prior art, such as accelerated wear of parts, shortened service life of the engine, and reduced torque and accelerated speed of the engine caused by increased bypass ratio.

SUMMERY OF THE UTILITY MODEL

To the above defect, the utility model provides a technical problem lies in, provides a two fan engines to solve the traction force that prior art exists for overcoming fan or thick liquid and lead to part wearing and tearing to accelerate, engine life shortens and for increaseing the torque moment that the bypass ratio leads to the engine reduce, accelerate the problem that slows down.

The utility model provides a two-fan engine includes:

the supporting assembly is provided with a flow guide cover and an air inlet and is used for being connected with the aircraft;

the fans are arranged on the air inlets, and a main shaft is connected to the fans;

the gearbox is rotationally connected with the main shaft and is arranged in the support assembly;

the engine host computer, with supporting component connects, and is equipped with the pivot, the pivot with the gearbox rotates to be connected.

Preferably, the support assembly further comprises:

the outer shell is integrally formed with the air guide sleeve, and the air inlet is formed in the outer shell;

the flow guide cone is integrally formed with the outer shell and is arranged at one end of the outer shell;

the engine bracket is connected with the other end of the outer shell;

the gearbox bracket is respectively connected with the diversion cone and the gearbox;

the fixing frame is connected with the outer shell and the aircraft respectively.

Preferably, the gearbox comprises:

the box body is connected with the gearbox bracket;

the driving bevel gear is connected with the rotating shaft;

a driven bevel gear connected with the main shaft and engaged with the drive bevel gear;

and the bearing is respectively connected with the main shaft, the box body and the rotating shaft.

Preferably, a connecting frame is arranged on the engine main machine and connected with the gearbox.

Preferably, the fan comprises a plurality of blades, and the angle between the normal vector of the surface of each blade and the main shaft is less than 90 degrees.

Preferably, an air outlet is formed between the engine bracket and the outer housing.

Preferably, the end of the outer housing connected to the engine bracket is the rear end of the outer housing, and the cross-sectional area of the rear end of the outer housing is the smallest.

Preferably, the main shaft is provided with one piece and penetrates through the gearbox, and the driven bevel gear is arranged on the main shaft.

Preferably, the fans are arranged in two groups and symmetrically arranged at two ends of the main shaft.

Preferably, the air inlet corresponds to the fan, and the air guide sleeve is arranged at a position corresponding to the air inlet.

According to the scheme, the double-fan engine provided by the utility model has the advantages that the outer duct of the engine is formed between the inner cavity of the supporting component and the engine main engine and the gear box, the bypass ratio of the double-fan engine is increased by arranging a plurality of fans, the diameter of each fan is maintained at a proper size, the problems of torque reduction and acceleration slowing of the engine caused by overlarge diameter of each fan are avoided, meanwhile, the arrangement that the fans are connected with the main shaft and then connected with the gearbox enables the force borne by the fans to directly act on the gearbox, the gearbox is mutually restrained by various acting forces, the stress is balanced, the traction force of the fans to the engine host is reduced, and can not cause extra pressure to the part, effectively guaranteed the life of this kind of double fan engine, the gearbox conducts the moment of torsion of pivot to the main shaft with high efficiency, has guaranteed the effective conduction of the moment of torsion that the engine host computer provided, and generator efficiency is higher. The utility model discloses effectively solve for the traction force of overcoming fan or thick liquid lead to part wearing and tearing to accelerate, engine life shortens and for increaseing the torque moment that the duct ratio leads to the engine reduce, problem that slows down with higher speed, and simple structure is suitable for extensive popularization.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is a schematic rear view structure diagram of a two-fan engine according to an embodiment of the present invention;

FIG. 2 is a sectional view taken along line A-A of FIG. 1;

FIG. 3 is a sectional view taken along line B-B of FIG. 1;

FIG. 4 is a schematic illustration of the direction of air flow during operation of the dual fan engine of FIG. 2;

FIG. 5 is a schematic view of the fan and main shaft forces during operation of the dual fan engine shown in FIG. 1;

fig. 6 is a schematic structural diagram of another two-fan engine according to an embodiment of the present invention.

In FIGS. 1-6:

1. a support assembly; 2. a fan; 3. a gearbox; 4. an engine main unit; 5. a main shaft; 6. an outer duct; 11. a pod; 12. an outer housing; 13. a flow guide cone; 14. an engine mount; 15. a gearbox bracket; 16. a fixed mount; 17. an air outlet; 31. a box body; 32. a drive bevel gear; 33. a driven bevel gear; 34. a bearing; 41. a rotating shaft; 42. and a connecting frame.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Example 1

Referring to fig. 1 to 5, a description will now be given of an embodiment of a two-fan engine according to the present invention. The double-fan engine comprises a support component 1, a fan 2, a gearbox 3 and an engine host 4, wherein the support component 1 is provided with a flow guide cover 11 and an air inlet, and the support component 1 is used for being connected with an aircraft; the fans 2 are arranged at the air inlet and are provided with a plurality of air inlets, and the main shaft 5 is connected to the fans 2; the gearbox 3 is rotationally connected with the main shaft 5 and is arranged in the support component 1; the engine main machine 4 is connected with the supporting component 1 and is provided with a rotating shaft 41, and the rotating shaft 41 is rotatably connected with the gearbox 3.

In the present embodiment, the engine main unit 4 may be a turbine engine. The fan 2 and the main shaft 5 can be connected by screw threads or welding, and the engine main machine 4 and the support assembly 1 can be connected by welding or bolts. An engine outer duct 6 is formed between the inner cavity of the support component 1 and the engine main machine 4 and the gearbox 3. One end of the outer duct 6 is communicated with the air inlet, and the other end is communicated with the air outlet 17 of the supporting component 1. The fans 2 are connected through the main shaft 5, each fan 2 can be independently connected with one main shaft 2, each main shaft 2 is connected with the gearbox 3, the stability of the mode of connecting the two fans 2 through one main shaft 2 is better, and all components are stressed more uniformly. It is within the scope of the present document to achieve the performance-related effects of the gearbox 3.

The engine host machine 4 operates, the torque generated by the rotation of the rotating shaft 41 is transmitted to the main shaft 5 through the action of the gearbox 3, the main shaft 5 rotates to drive the fan 2 to rotate, the fan 2 rotates to guide the air gathered in the air guide sleeve 11 into the supporting component 1, the air is compressed to a certain degree through the outer duct 6, the compressed air is discharged through the air outlet 17, and the driving force is generated to drive the aircraft to move.

Guide the air through setting up a plurality of fans 2 and kuppe 11 and gathering, increase the bypass ratio of this kind of two-fan engine, fan 2 diameter is maintained and has been avoided the too big moment of torsion that causes the engine of fan 2 diameter at suitable size and reduce, problem with higher speed and slow down, a plurality of fans 2 connect through main shaft 5 and hold down each other simultaneously, the atress is balanced, the traction force of fan 2 to engine host 4 has been reduced, and can not cause extra pressure to all the other relevant parts, the life of this kind of two-fan engine has effectively been guaranteed, gearbox 3 conducts the high-efficient conduction of moment of torsion of pivot 41 to main shaft 5, the effective conduction of the moment of torsion that has guaranteed engine host 4 and has made this kind of two-fan generator efficiency higher.

Simultaneously, in this embodiment, the air intake sets up in supporting component 1 side, 2 axis directions of fan are perpendicular with the aircraft direction of motion promptly, can withdraw a bit toward the middle part fan 2 even, including the effect of sheltering from of kuppe 11, very big reduction radar openly shines fan 2, and then acquire the characteristic information that its blade clearance was constantly changed because rotatory when fan 2 was moved, the aircraft includes that this kind of two fan engine surface can use stealthy coating, can not obtain the fan 2 motion information and increase the stealthy effect of the aircraft of using this kind of two fan engine through the radar exposure to the sector like this.

Example 2

As a specific implementation manner of the embodiment of the present invention, please refer to fig. 1 to 5 together, the structure of the two-fan engine provided in this embodiment is basically the same as that of embodiment 1, and the difference lies in that the support assembly 1 further includes an outer housing 12, a guide cone 13, an engine support 14, a transmission support 15 and a fixing frame 16, wherein the outer housing 12 and the guide cover 11 are integrally formed, the air inlet is disposed on the outer housing 12, the air inlet is a through hole penetrating through the outer housing 12, and the fan 2 is disposed on the through hole, so as to blow air inside the support assembly 1; the diversion cone 13 is integrally formed with the outer shell 12 and is arranged at one end of the outer shell 12; the engine bracket 14 is connected with the other end of the outer shell 12; the gearbox bracket 15 is respectively connected with the diversion cone 13 and the gearbox 3; the fixed mount 16 is disposed on the top of the outer shell 12 and is connected to the outer shell 12 and the aircraft, respectively. The engine support 14 may be a cross-shaped metal frame for fixing the engine, an air outlet 17 is formed between the engine support 14 and the outer casing 12, and the air outlet 17 is used for flowing out of the gas in the support assembly 1. The air inlet corresponds to the fan 2, and the air guide sleeve 11 is arranged at a position corresponding to the air inlet. The gearbox bracket 15 is connected with the gearbox 3 through a fixing screw. The transmission case bracket 15 may be a bracket made of a metal plate, which is simple in structure and convenient to use, and is used to effectively fix the transmission case 3.

In this embodiment, the front end of the guiding cone 13 is conical, the air first contacts the cone tip, the guiding cone 13 divides the air to two sides, the air flows along the side surface of the guiding cone 13, most of the air is collected into the guiding cover 11, the air in the guiding cover 11 enters the outer duct 6 through the air inlet where the fan 2 is located, and the air flows out of the support assembly 1 through the outer duct 6 and the air outlet 17. It should be understood that the terms "front", "back", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are used for convenience of description of the present invention, but are not intended to limit the present invention since the components of the support assembly 1 must have particular orientations, be constructed and operated in particular orientations, and accordingly.

In the present embodiment, the transmission 3 includes a case 31, a drive bevel gear 32, a driven bevel gear 33, and a bearing 34, wherein the case 31 is connected to the transmission housing 15; the drive bevel gear 32 is connected to the rotating shaft 41; the driven bevel gear 33 is connected with the main shaft 5 and meshed with the drive bevel gear 32; the bearings 34 are connected to the main shaft 5, the case 31, and the rotating shaft 41, respectively. The engine main machine 4 is provided with a connecting frame 42, and the connecting frame 42 is connected with the gearbox 3. The rotating shaft 41 rotates to drive the driving bevel gear 32 connected with the rotating shaft to rotate, the driving bevel gear 32 drives the driven bevel gear 33 meshed with the driving bevel gear to rotate, the driving bevel gear 32 and the driven bevel gear 33 are vertically arranged to conduct torque effectively, the driven bevel gear 33 rotates to drive the main shaft 5 connected with the driven bevel gear to rotate, and then the fan 2 is driven to rotate, so that air flow is achieved. The bearing 34 is arranged between the rotating shaft 41 and the gearbox 3 and between the main shaft 5 and the gearbox 3, so that the main shaft 5 and the rotating shaft 41 can rotate more flexibly, the loss of friction resistance to torque is reduced while the supporting effect is achieved, and the torque is conducted more efficiently.

Example 3

As a specific implementation manner of the embodiment of the present invention, please refer to fig. 1 to 5 together, the structure of the two-fan engine provided in this embodiment is basically the same as that of embodiment 2, the difference is that the main shaft 5 is provided with one and runs through the transmission case 3, the driven bevel gear 33 is disposed on the main shaft 5, and the middle portion of the main shaft 5 is disposed to pass through the transmission case 3, so as to facilitate the power input of the engine main unit 4. The fans 2 are arranged in two groups and symmetrically arranged at two ends of the main shaft 5. The fan 2 comprises a plurality of blades, the normal vector of the blade surface and the main shaft 5 form an included angle of less than 90 degrees. The end of the outer shell 12 connected with the engine support 14 is the rear end of the outer shell 12, and the section area of the rear end of the outer shell 12 is the smallest, so that the state that the air in the outer duct 6 is continuously gathered and compressed at the rear end of the outer shell 12 is formed, and the compressed air with stronger power is favorably generated.

The angle that the blade set up more is favorable to two fans 2 to blow to supporting component 1 is inside, fan 2 receives the effect of the outside traction force along main shaft 5 this moment, because fan 2 symmetry sets up in main shaft 5 both sides, the equal opposite direction of traction force size that receives, main shaft 5 atress is balanced relatively, simultaneously because traction force direction is perpendicular with 41 axis directions of pivot, traction force reduces the influence of engine host computer 4, engine host computer 4 transmission efficiency is higher, whole atress is balanced, each subassembly atress is even, make whole equipment life longer.

Example 4

As a specific implementation manner of the embodiment of the present invention, please refer to fig. 1 to fig. 6 together, the structure of the two-fan engine provided in this embodiment is basically the same as that of embodiment 3, and the difference lies in that the supporting component 1 includes a wind deflector 11, a wind deflector cone 13, an engine bracket 14, a transmission bracket 15 and a fixing frame 16, wherein the air inlet is disposed between the wind deflector 11 and the wind deflector cone 13, and an area formed between the wind deflector 11, the engine mainframe 4 and the transmission 3 is an outer duct 6. The gearbox 3 comprises a box body 31, a bearing 34, a driving gear and driven gears, wherein the driving gear is connected with the rotating shaft 41 and meshed with the driven gears, the driven gears are connected with a main shaft 5, and two main shafts 5 are respectively connected with the fan 2. The engine host 4 operates, the rotating shaft 41 rotates to drive the driving gear to rotate, the driving gear rotates to drive the driven gear meshed with the driving gear to rotate, the driven gear drives the main shaft 5 to rotate so as to drive the fan 2 to rotate, and the fan 2 blows air into the outer duct 6. It is within the scope of the present disclosure that the transmission 3 may be operated to achieve the performance-related function, such as the driven gear and the driving gear moving through a rack connection or the plurality of gear sets moving in cooperation with each other.

The embodiments are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same or similar parts among the embodiments are referred to each other. Details not described in the embodiments of the present invention belong to the prior art known to those skilled in the art.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A two-fan engine, comprising:

the supporting component (1) is provided with a flow guide cover (11) and an air inlet, and the supporting component (1) is used for being connected with an aircraft;

the fans (2) are arranged in the air inlets, and a main shaft (5) is connected to each fan (2);

the gearbox (3) is rotationally connected with the main shaft (5) and is arranged in the support component (1);

the engine main unit (4) is connected with the supporting component (1) and is provided with a rotating shaft (41), and the rotating shaft (41) is rotatably connected with the gearbox (3).

2. A double fan engine according to claim 1, characterized in that the support assembly (1) further comprises:

the outer shell (12) and the air guide sleeve (11) are integrally formed, and the air inlet is formed in the outer shell (12);

the flow guide cone (13) is integrally formed with the outer shell (12) and is arranged at one end of the outer shell (12);

an engine bracket (14) connected with the other end of the outer shell (12);

the gearbox bracket (15) is respectively connected with the diversion cone (13) and the gearbox (3);

a mounting bracket (16) connected to the outer housing (12) and the aircraft, respectively.

3. A twin-fan engine according to claim 2, characterised in that the gearbox (3) comprises:

a case (31) connected to the transmission case holder (15);

a drive bevel gear (32) connected with the rotating shaft (41);

a driven bevel gear (33) connected to the main shaft (5) and engaged with the driving bevel gear (32);

and the bearing (34) is respectively connected with the main shaft (5), the box body (31) and the rotating shaft (41).

4. A twin fan engine as defined in claim 3 in which the engine main unit (4) is provided with a connecting bracket (42), the connecting bracket (42) being connected to the gearbox (3).

5. A twin-fan engine as defined in claim 4, characterised in that the fan (2) comprises a plurality of blades, the normal vector of the blade surface making an angle of less than 90 ° with the main axis (5).

6. A twin fan engine as claimed in claim 5, characterised in that an air outlet (17) is formed between the engine bracket (14) and the outer casing (12).

7. A twin fan engine as defined in claim 6 in which the end of the outer casing (12) to which the engine mount (14) is attached is the rear end of the outer casing (12), the rear end of the outer casing (12) having the smallest cross-sectional area.

8. A double fan engine as claimed in claim 7, characterised in that the main shaft (5) is provided in one piece and extends through the gearbox (3), the driven bevel gear (33) being provided on the main shaft (5).

9. A twin-fan engine as defined in claim 8, characterised in that the fans (2) are arranged in two groups and symmetrically arranged at both ends of the main shaft (5).

10. A twin-fan engine as defined in claim 9, characterised in that the air inlet corresponds to the fan (2) and the air guide sleeve (11) is arranged in a position corresponding to the air inlet.