CN115258143A

CN115258143A - Wing tip jet-propelled rotation rotor wing composite power system

Info

Publication number: CN115258143A
Application number: CN202211051834.6A
Authority: CN
Inventors: 王云; 王亚超; 吴宪举; 吴锦武; 杨蓓; 吴逸飞
Original assignee: Taizhou University; Nanchang Hangkong University
Current assignee: Taizhou University; Nanchang Hangkong University
Priority date: 2022-08-31
Filing date: 2022-08-31
Publication date: 2022-11-01

Abstract

The wing tip jet autorotation rotor wing composite power system has the characteristics of high power-weight ratio and low oil consumption, and comprises a wing tip jet rotor wing, a fuel gas generator, an engine, a variable pitch propeller, a centrifugal supercharger, a centrifugal clutch and a fuel tank. The hybrid power system is realized by two paths of power in the vertical take-off and landing stage and the front flying stage, the engine can work at full load in the whole process, and the power is fully utilized: when the aircraft vertically rises and falls, the engine drives the centrifugal supercharger to work under the transmission of the centrifugal clutch to generate compressed gas, meanwhile, boosting fuel injected into the fuel tank and high-temperature tail gas of the engine are assisted to be mixed and reacted in the fuel gas generator to generate fuel gas for wing tip injection, and the rotor is driven to rotate to generate larger lift force required by rising and falling; when flying forward, the engine drives the variable pitch propeller to work to propel the aircraft to fly, and meanwhile, the rotor wing rotates at low speed to maintain lift force, so that the power of the engine is not consumed, the problem of limitation of the flying speed of the traditional helicopter is solved, and higher flying speed can be realized.

Description

Wing tip jet rotation rotor wing composite power system

Technical Field

The invention relates to the technical field of vertical take-off and landing aircraft power systems, in particular to a wing tip air injection autorotation rotor wing composite power system.

Background

The rotor is the main lift device of present VTOL aircraft, but traditional shaft drive rotor can not avoid having fuselage counter moment balance, flight safety nature is poor and flight speed scheduling problem not high. The wing tip jet autorotation rotor wing can be driven to rotate by means of wing tip jet to generate lift force when being hovered in a rising, landing and hovering mode, is not in hard connection with any power machinery, and can safely slowly descend by means of autorotation of the rotor wing even if no wing tip jet exists when the power machinery fails; because the tip jet autorotation rotor wing has no counter moment of a hard drive rotor wing, a tail rotor system and a long tail body can be omitted; the rotor can rotate at low speed to generate lift force during high-speed flight, and the problem that the flight speed is restricted by forward wing sharp shock waves, backward side airflow separation and the like of the rotor is avoided.

Although the wingtip jet autogyro has the above-identified benefits, unfortunately, although the wingtip jet autogyro has been developed and developed for over half a century, and has various embodiments, the overall effect is not satisfactory, and there are still many problems in terms of compact power, high efficiency and reliability, and thus a solution is urgently needed. At present, the bottleneck and the technical key of the wingtip jet-rotation rotor wing composite helicopter are in a power system, and the power system needs to meet the following requirements: when VTOL and hover, can effectively drive the rotor, when flying before high-speed, can release the rotor rotation, have higher efficiency simultaneously. However, any single power system such as wingtip jet, gas generator, internal combustion engine and electric motor can not be sufficient at present. Therefore, a novel wingtip jet rotation rotor wing composite power system is developed to solve a series of key technologies, and has positive significance for vertical take-off and landing aircrafts such as ship-borne helicopters, unmanned planes and the like.

Disclosure of Invention

The invention aims to provide a wing tip jet rotation rotor wing composite power system which is used for overcoming the problems in the prior art. The wing tip air injection autorotation rotor wing composite power system is ingenious in structural design and has the characteristics of large power-weight ratio and low oil consumption; the vertical take-off and landing stage and the front flying stage are realized by two paths of power, the engine can work at full load in the whole process, and the power is fully utilized: during vertical lifting, the engine drives the centrifugal supercharger to work under the transmission of the centrifugal clutch to generate compressed gas, meanwhile, boosting fuel injected into the fuel tank and high-temperature tail gas of the engine are assisted to be mixed and reacted in the fuel gas generator to generate fuel gas for wing tip injection, and the rotor wing is driven to rotate to generate larger lifting force required during lifting; when flying forward, the engine drives the variable pitch propeller to work, the aircraft is propelled to fly, meanwhile, the rotor wing rotates at low speed to maintain lift force, the power of the engine is not consumed, the problem of limitation of the flying speed of the traditional helicopter is solved, and higher flying speed can be realized.

The technical scheme of the invention is as follows: the wing tip jet autorotation rotor wing composite power system comprises a wing tip jet rotor wing, a fuel gas generator, an engine, a variable pitch propeller and a centrifugal supercharger; the air outlet of the fuel gas generator is communicated with the hollow main shaft of the wing tip jet rotor wing; the air inlet of the fuel gas generator is communicated with a tail gas pipe of the engine; the injection port of the gas generator is communicated with the fuel tank; the variable-pitch propeller is connected with an output shaft of the engine; a centrifugal clutch is arranged on the output shaft; the centrifugal clutch comprises a driving part, a driven part and a centrifugal block; the driving part is arranged on the output shaft; the driven part is in transmission connection with a driving shaft of the centrifugal supercharger through an accelerating mechanism; the engine is connected with the oil tank.

Compared with the prior art, the wing tip jet rotation rotor wing composite power system has the following advantages:

(1) The composite power system is provided with the wingtip jet rotor, the fuel gas generator, the engine, the variable pitch propeller and the centrifugal supercharger, all components have synergistic effect, the wingtip jet can be used for driving the rotor to rotate to generate lift force when the wing vertically takes off and lands, no counter moment exists, and a tail rotor system does not need to be balanced, so that the structure of the aircraft can be simplified; when flying forwards, the variable-pitch propeller rotates to generate thrust, and simultaneously, the rotor rotates at low speed to maintain lift force, so that the power of an engine is not consumed by the rotor, the problem of limitation of the flight speed of the traditional helicopter can be solved, and higher flight speed can be realized; in addition, the wingtip jet rotor wing is not directly connected with the engine, and can automatically rotate and fall when a power system fails, so that the safety is good;

(2) The centrifugal supercharger, the tail gas pipe of the engine and the fuel tank are communicated with the fuel gas generator, when the vertical takeoff needs high power, high-temperature tail gas of the engine, compressed air generated by the centrifugal supercharger and boosting fuel in the fuel tank enter the fuel gas generator together to be mixed, and fuel gas is generated and used for wing tip jet to drive the rotor wing to generate lift force;

(3) The boosting fuel can be directly heated and reacted by using the high-temperature tail gas of the engine without an additional ignition or catalytic device, so that a complex catalytic reaction control system is avoided;

(4) The composite power system is realized by two paths of power in the vertical take-off and landing stage and the front flying stage through ingenious structural design, so that the engine can work at full load (namely in the maximum power state of the engine) in the whole process, the power is fully utilized, and the problem that partial power is idle and wasted in the vertical take-off and landing stage and the front flying stage of the conventional aircraft power system is solved; during vertical take-off and landing, the engine drives the centrifugal supercharger to work under the transmission of the centrifugal clutch to generate compressed air, meanwhile, boosting fuel injected into the fuel tank and high-temperature tail gas of the engine are assisted to be mixed and reacted in the fuel gas generator to generate fuel gas for wing tip injection, the rotor wing is driven to rotate to generate large lifting force required during lifting, when the aircraft flies forwards, the centrifugal supercharger stops working, meanwhile, the boosting fuel is stopped being injected, only the engine drives the variable-pitch propeller to work, the aircraft is propelled to fly, and the high power-weight ratio and low oil consumption are favorably realized.

Preferably, in the wing tip jet-rotation rotor wing compound power system, the driven member is in transmission connection with a driving shaft of a centrifugal supercharger through a vertical shaft gear accelerating mechanism. The vertical shaft gear accelerating mechanism is adopted to realize the transmission connection between the driven part and the driving shaft, and has the advantages of small volume, high transmission efficiency, stable performance and the like. Furthermore, the vertical shaft gear accelerating mechanism comprises a large bevel gear arranged at the end part of the driven part and a small bevel gear arranged at the end part of the driving shaft; the big bevel gear and the small bevel gear are meshed with each other. At the moment, the structure is simple, the occupied space is small, and the assembly is convenient. Further, the large bevel gear and the driven part are integrally formed; the bevel pinion and the driving shaft are integrally formed. At this time, the manufacturing is convenient, and the cost is favorably controlled.

Preferably, in the composite power system of the wingtip jet autorotation rotor wing, the centrifugal supercharger comprises a shell, a centrifugal impeller, an annular diffuser and a rectifying bracket; the annular diffuser is connected with the centrifugal impeller; the centrifugal impeller is sleeved on the driving shaft; the rectifying bracket is fixed on the shell; the driving shaft is rotatably connected with the rectifying support. After the centrifugal supercharger adopts the structure, the centrifugal supercharger has the advantages of less parts, simple structure, small axial size and high working stability. Further, the driving shaft is connected with the rectifying support through a rolling bearing. Therefore, the friction coefficient of the driving shaft in the rotating process can be reduced, and the rotating precision and the normal working position during rotation of the driving shaft are ensured.

Preferably, in the wing tip jet autorotation rotor wing compound power system, the hollow main shaft is connected with the fuel gas generator through a rotary joint. At this time, the assembly is convenient. Further, the rotary joint comprises a driven part and a driving part which are connected in a rotating mode; the driven part is sleeved outside the hollow main shaft; the active part is provided with a corrugated pipe which is sleeved outside the fuel gas generator. The corrugated pipe can adapt to the expansion with heat and contraction with cold of the gas generator; after the corrugated pipe is arranged on the rotary joint, the corrugated pipe can be used for compensating thermal deformation and coaxial errors, and the normal work of the rotary joint is ensured. Furthermore, the hollow main shaft and the driven part are welded and fixed, so that the connection firmness of the hollow main shaft and the rotary joint is ensured. Further, the driven part is rotatably connected with the driving part through a bearing, and a sealing element is arranged between the driven part and the driving part. Thereby, the rotation accuracy and the sealing performance between the driven portion and the driving portion are ensured.

As an optimization, in the wing tip air injection autorotation rotor wing composite power system, 2 to 4 blades can be arranged on the hollow main shaft; the fuel tank can be filled with hydrogen peroxide or fuel oil or a mixture thereof.

Drawings

FIG. 1 is a schematic structural view of a wingtip jet autorotation rotor hybrid power system of the present invention;

FIG. 2 is a cross-sectional view of the wingtip jet autorotation rotor hybrid power system of the present invention;

FIG. 3 is a schematic view of the centrifugal clutch of the present invention;

FIG. 4 is a schematic view of the assembly of the centrifugal booster and gas generator of the present invention;

fig. 5 is a sectional view of a rotary joint in the present invention.

The symbols in the drawings are: 1-rotor, 101-hollow main shaft, 102-blade; 2-a gas generator; 3-engine, 301-output shaft, 302-tail gas pipe; 4-a variable pitch propeller; 5-centrifugal supercharger, 501-driving shaft, 502-housing, 503-centrifugal impeller, 504-annular diffuser, 505-rectifying bracket and 506-rolling bearing; 6-centrifugal clutch, 601-driving part, 602-centrifugal block, 603-driven part, 604-bearing, 605-end cover; 7-vertical axis gear acceleration mechanism; 8-a fuel tank; 9-an oil tank; 10-swivel joint, 1001-driven part, 1002-driving part, 1003-seal, 1004-bearing, 1005-bellows.

Detailed Description

The present application is further described with reference to the following drawings and examples, but the present application is not limited thereto.

Referring to fig. 1 to 5, the composite power system of the wingtip jet autorotation rotor wing of the present application comprises a wingtip jet rotor wing 1, a fuel gas generator 2, an engine 3, a variable pitch propeller 4 and a centrifugal supercharger 5; the air outlet of the fuel gas generator 2 is communicated with a hollow main shaft 101 of the wingtip jet rotor wing 1; the air inlet of the gas generator 2 is communicated with an exhaust pipe 302 of the engine 3; the injection port of the gas generator 2 is communicated with a fuel tank 8 through a fuel pipe, and an electric valve is arranged on the fuel pipe; the fuel tank 8 is filled with hydrogen peroxide boosting fuel; the variable pitch propeller 4 is connected with an output shaft 301 of the engine 5; a centrifugal clutch 6 is arranged on the output shaft 301; the centrifugal clutch 6 comprises a driving piece 601, a driven piece 603 and a centrifugal block 602; the centrifugal block 602 is slidably mounted on the driving part 601; the driving part 601 is arranged on the output shaft 301; the driven member 603 is in transmission connection with the driving shaft 501 of the centrifugal supercharger 5 through an accelerating mechanism; the engine 3 is connected with the oil tank 9 through an oil delivery pipe.

When the engine is vertically lifted, the engine 3 rotates at a high speed, the variable pitch propeller 4 feathers, and rotates the blade angle to a state without generating thrust, no work is consumed, the rotating speed of the engine output shaft 301 is increased, and after a certain rotating speed is reached, the centrifugal block 602 of the centrifugal clutch 6 overcomes the elastic force of the spring (namely, the centrifugal force is greater than the elastic force of the spring) and is thrown outwards under the action of the centrifugal force to be in contact with the driven piece 603; under the action of friction between the centrifugal block 602 and the driven member 603, the centrifugal block 602 can drive the driven member 603 to synchronously rotate until the driven member rotates at a constant speed, when the driven member 603 rotates, the driving shaft 501 of the centrifugal supercharger 5 can be driven by an accelerating mechanism to rotate, the centrifugal supercharger 5 is driven to work to generate compressed air, the compressed air enters the gas generator 2, meanwhile, high-temperature tail gas of the engine 3 and boosting fuel in the fuel tank 8 also enter the gas generator 2, the high-temperature tail gas directly heats the boosting fuel to decompose and release heat, the compressed air is heated to form high-temperature and high-pressure fuel gas, the fuel gas enters the wingtip jet rotor wing 1 from the gas outlet of the gas generator 2 and is sent to the wingtip to be jetted to drive the rotor wing tip to rotate the rotor wing rotor, and lift force required by the aircraft is generated (at this time, the inner rotor wing has inner and outer flow fields, wherein the inner flow field is used for sending the fuel gas in the gas generator 2 to the wingtip to be jetted to provide drive torque for the rotor wing rotor, and the outer flow field is used for generating lift force required by the rotation of the rotor wing; during forward flight, the variable pitch propeller 4 changes the blade angle to generate torque and consume power, so that the rotating speed of the engine output shaft 301 is reduced, the centrifugal force of the centrifugal block 602 cannot overcome the elastic force of the spring (namely, the centrifugal force is smaller than the elastic force of the spring), the centrifugal block 602 is separated from the driven part 603, when the driving part 601 rotates, the driven part 603 does not rotate any more, the centrifugal supercharger 5 stops working, and meanwhile, boosting fuel is stopped being injected, the wingtip jet rotor 1 rotates at low speed (the rotor rotates under the blowing of airflow, and the rotating speed is low due to no power driving), so that the lift force is maintained, the variable pitch propeller 4 rotates under the driving of the engine output shaft 301, and the aircraft is propelled to fly (when forward flight, the high-temperature tail gas waste of the engine 3 is utilized, enters the fuel gas generator 2 and is sent to the wingtip to be sprayed to assist in generating the lift force).

The embodiment is as follows:

in the present embodiment, the engine 3 is a two-stroke heavy oil engine; four blades 102 are arranged on the hollow main shaft 101 (a gas channel is arranged in the hollow main shaft 101, and the tips of the blades 102 are provided with nozzles).

In this embodiment, the driven member 603 is in transmission connection with the driving shaft 501 of the centrifugal supercharger 5 through a vertical axis gear acceleration mechanism 7, and the vertical axis gear acceleration mechanism 7 includes a large bevel gear arranged at an end of the driven member 603 and a small bevel gear arranged at an end of the driving shaft 501; the big bevel gear and the small bevel gear are meshed with each other. At the moment, the structure is simple, the occupied space is small, and the assembly is convenient. Further, the large bevel gear is integrally formed with the driven member 603; the bevel pinion is formed integrally with the drive shaft 501. At this time, the manufacturing is convenient, and the cost is favorably controlled.

In this embodiment, 2 bearings 604 are disposed between the driving member 601 and the driven member 603, and the bearings 604 are sleeved on the driving member 601; an end cover 605 is arranged on the outer side of the bearing 604 (the end cover 605 is positioned on the side far away from the large bevel gear), and the end cover 605 is fixed on the driven part 603 through bolts.

In this embodiment, the centrifugal supercharger 5 comprises a casing 502 (the casing 502 may be formed integrally with the outer casing of the gas generator 2), a centrifugal impeller 503, an annular diffuser 504 and a rectifying support 505; the annular diffuser 504 is connected with a centrifugal impeller 503; the centrifugal impeller 503 is sleeved on the driving shaft 501; the rectifying support 505 is fixed on the shell 502; the drive shaft 501 is rotatably connected to a fairing support 505. After the centrifugal supercharger 5 adopts the structure, the number of parts is small, the structure is simple, the axial size is small, and the working stability is high. Further, the driving shaft 501 is connected to a rectifying support 505 through a rolling bearing 506 (which may be a double-row ceramic roller bearing). Therefore, the friction coefficient of the driving shaft 501 in the rotation process can be reduced, and the rotation precision and the normal working position in the rotation process can be ensured. Compressed air generated by the operation of the centrifugal supercharger 5 is admitted into the gasifier 2 through an annular diffuser 504.

In this embodiment, the hollow main shaft 101 of the tip jet rotor 1 is connected to the gas generator 2 by means of a rotary joint 10. At this moment, convenient assembling easily carries out. Further, the rotary joint 10 includes a driven portion 1001 and a driving portion 1002 which are rotatably connected; the driven part 1001 is sleeved outside the hollow main shaft 101; the active portion 1002 is provided with a corrugated pipe 1005, and the corrugated pipe 1005 is sleeved outside the gasifier 2. The bellows 1005 may accommodate thermal expansion and contraction of the gasifier 2; after the corrugated tube 1005 is disposed on the rotary joint 10, it can be used to compensate thermal deformation and coaxial error, and ensure the normal operation of the rotary joint 10. Further, the hollow main shaft 101 and the driven part 1001 are welded and fixed, so that the connection firmness of the hollow main shaft 101 and the rotary joint 10 is ensured. Further, the driven part 1001 is rotatably connected to the driving part 1002 through a bearing 1004, and two seals 1003 (specifically, a gas-liquid two-phase brush seal) are disposed between the driven part 1001 and the driving part 1002. Thereby, the rotation accuracy and the sealing performance between the driven portion 1001 and the driving portion 1002 are ensured.

The above general description of the invention and the description of the specific embodiments thereof, as referred to in this application, should not be construed as limiting the technical solutions of the invention. Those skilled in the art can add, subtract or combine the technical features disclosed in the general description and/or the specific embodiments (including the examples) to form other technical solutions within the protection scope of the present application according to the disclosure of the present application without departing from the constituent elements of the invention.

Claims

1. Wing tip jet-propelled rotation rotor hybrid power system, its characterized in that: comprises a wing tip jet rotor (1), a fuel gas generator (2), an engine (3), a variable pitch propeller (4) and a centrifugal booster (5); the air outlet of the fuel gas generator (2) is communicated with a hollow main shaft (101) of the wingtip jet rotor wing (1); the air inlet of the fuel gas generator (2) is communicated with a tail gas pipe (302) of the engine (3); the injection port of the gas generator (2) is communicated with a fuel tank (8); the variable-pitch propeller (4) is connected with an output shaft (301) of the engine (3); a centrifugal clutch (6) is arranged on the output shaft (301); the centrifugal clutch (6) comprises a driving piece (601), a centrifugal block (602) and a driven piece (603); the driving piece (601) is arranged on the output shaft (301); the driven part (603) is in transmission connection with a driving shaft (501) of the centrifugal supercharger (5) through an accelerating mechanism; the engine (3) is connected with the oil tank (9).

2. A wingtip jet autorotation rotor hybrid powertrain as claimed in claim 1 wherein: the driven part (603) is in transmission connection with a driving shaft (501) of the centrifugal supercharger (5) through a vertical shaft gear acceleration mechanism (7).

3. A wingtip jet autorotation rotor hybrid powertrain as claimed in claim 2 wherein: the vertical shaft gear accelerating mechanism (7) comprises a large bevel gear arranged at the end part of the driven part (603) and a small bevel gear arranged at the end part of the driving shaft (501); the big bevel gear and the small bevel gear are meshed with each other.

4. The wingtip jet autorotation rotor hybrid power system according to claim 3 wherein: the large bevel gear and the driven part (603) are integrally formed; the bevel pinion is integrally formed with the drive shaft (501).

5. A wingtip jet autorotation rotor hybrid powertrain as claimed in claim 1 wherein: the centrifugal supercharger (5) comprises a shell (502), a centrifugal impeller (503), an annular diffuser (504) and a rectifying bracket (505); the annular diffuser (504) is connected with a centrifugal impeller (503); the centrifugal impeller (503) is sleeved on the driving shaft (501); the rectifying bracket (505) is fixed on the shell (502); the driving shaft (501) is rotatably connected with the rectifying support (505) through a rolling bearing (506).

6. The wingtip jet autorotation rotor hybrid power system according to claim 1 wherein: the hollow main shaft (101) is connected with the gas generator (3) through a rotary joint (10).

7. A wingtip jet autorotation rotor hybrid powertrain system as claimed in claim 6 wherein: the rotary joint (10) comprises a driven part (1001) and a driving part (1002) which are connected in a rotating mode; the driven part (1001) is sleeved outside the hollow main shaft (101) and is welded and fixed with the hollow main shaft (101); the active part (1002) is provided with a corrugated pipe (1005), and the corrugated pipe (1005) is sleeved on the fuel gas generator (3).

8. A wingtip jet autorotation rotor hybrid powertrain system as claimed in claim 7 wherein: the driven part (1001) is rotationally connected with the driving part (1002) through a bearing (1004); a sealing element (1003) is arranged between the driven part (1001) and the driving part (1002).

9. A wingtip jet autorotation rotor hybrid powertrain system as claimed in claim 6 wherein: 2-4 blades (102) are arranged on the hollow main shaft (101).

10. A wingtip jet autorotation rotor hybrid power system according to any one of claims 1 to 9 wherein: the fuel tank (8) is filled with hydrogen peroxide or fuel oil or a mixture thereof.