阅读说明：本技术 一种航空发动机用高速飞轮储存减排装置 (High-speed flywheel storage emission reduction device for aero-engine ) 是由 胡灿 于 2019-11-18 设计创作，主要内容包括：本发明涉及航空发动机储能技术领域,且公开了一种航空发动机用高速飞轮储存减排装置,包括机体,所述机体的内部活动连接有转轴,转轴的表面套接有叶片,叶片的背部且位于转轴的表面活动连接有齿轮,齿轮的表面开设有导向槽,导向槽的表面通过滚轮活动连接有挡持板,所述转轴的内部固定连接有支撑架,支撑架的内部固定连接有磁块。叶片受到的风力变大并做逆时针旋转运动,叶片反转使之前存储的电能释放出来,并单独驱动叶片做逆时针旋转运动,叶片产生的风力方向与飞机的运动方向相反,从而达到了辅助刹车系统进行刹车工作的效果；当飞机停止时,储存的电能未释放完,剩余的电量可用于下次起飞阶梯使用,起到降低能耗的作用。(The invention relates to the technical field of energy storage of aero-engines, and discloses a high-speed flywheel storage and emission reduction device for an aero-engine, which comprises an engine body, wherein a rotating shaft is movably connected inside the engine body, blades are sleeved on the surface of the rotating shaft, a gear is movably connected to the back of each blade and the surface of the rotating shaft, a guide groove is formed in the surface of the gear, a retaining plate is movably connected to the surface of the guide groove through a roller, a support frame is fixedly connected inside the rotating shaft, and a magnetic block is fixedly connected inside the support frame. The wind power received by the blades is increased and the blades rotate anticlockwise, the blades rotate reversely to release the stored electric energy and independently drive the blades to rotate anticlockwise, and the direction of the wind power generated by the blades is opposite to the movement direction of the airplane, so that the effect of braking by the auxiliary braking system is achieved; when the airplane stops, the stored electric energy is not released, and the rest electric energy can be used for the next takeoff ladder, so that the effect of reducing energy consumption is achieved.)

1. The utility model provides an aeroengine stores emission reduction device with high-speed flywheel, includes organism (1), its characterized in that: a rotating shaft (2) is movably connected inside the machine body (1), a blade (3) is sleeved on the surface of the rotating shaft (2), a gear (4) is movably connected to the back of the blade (3) and the surface of the rotating shaft (2), a guide groove (5) is formed in the surface of the gear (4), and a retaining plate (7) is movably connected to the surface of the guide groove (5) through a roller (6); the wind power generation device is characterized in that a support frame (8) is fixedly connected to the inside of the rotating shaft (2), a magnetic block (9) is fixedly connected to the inside of the support frame (8), a surface metal rod (10) of the magnetic block (9), and a wind direction plate (11) is movably connected to the surface of the support frame (8).

2. The high-speed flywheel storage emission reduction device for the aircraft engine according to claim 1, characterized in that: the blades (3) are movably connected with the rotating shaft (2) through shaft sleeves (12).

3. The high-speed flywheel storage emission reduction device for the aircraft engine according to claim 1, characterized in that: both sides of the baffle plate (7) are movably connected with ventilation openings (13).

4. The high-speed flywheel storage emission reduction device for the aircraft engine according to claim 1, characterized in that: the inner part of the shaft sleeve (12) is movably connected with a ratchet wheel (14), and the surface of the ratchet wheel (14) is hinged with a pawl (15).

5. The high-speed flywheel storage emission reduction device for the aircraft engine according to claim 1, characterized in that: the inner part of the shaft sleeve (12) is fixedly connected with a rectangular groove (16).

6. The high-speed flywheel storage emission reduction device for the aircraft engine according to claim 1, characterized in that: and a component sleeve (17) is fixedly connected to the surface of the gear (4) in the shell (1).

7. The high-speed flywheel storage emission reduction device for the aircraft engine according to claim 1, characterized in that: the number of the magnetic blocks (9) is two, and the magnetism of the two magnetic blocks (9) is opposite.

8. The high-speed flywheel storage emission reduction device for the aircraft engine according to claim 1, characterized in that: the rectangular groove (16) is placed along the clockwise direction.

Technical Field

The invention relates to the technical field of energy storage of aero-engines, in particular to a high-speed flywheel storage and emission reduction device for an aero-engine.

Background

The aircraft engine is a highly complex and precise thermal machine, is used as the heart of an aircraft, is not only the power of the aircraft flight, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aircraft engine.

At present, civil aircraft mainly rely on the traction of own aeroengine or ground trailer to provide advancing power during the ground taxiing, and this kind of mode that has been used for decades is easy and simple to handle, but with the development of technology and the standard that energy saving and emission reduction is becoming stricter, and reuse has not been advocated to this kind of mode.

In addition, when the airplane brakes in a ground sliding mode, the airplane needs to be braked by a brake system of the airplane, and although the brake system can effectively brake, the brake distance is long, so that the landing of the airplane is limited by a place.

Disclosure of Invention

In order to achieve the purpose of generating electric energy by utilizing the characteristics of the brake pad and using the electric energy for driving or braking, the invention provides the following technical scheme: the utility model provides an emission reduction device is stored to high-speed flywheel for aeroengine, includes the organism, the inside swing joint of organism has the pivot, and the blade has been cup jointed on the surface of pivot, and the back of blade and the surperficial swing joint that is located the pivot have a gear, and the guide way has been seted up on the surface of gear, and the surface of guide way has the fender through gyro wheel swing joint and holds the board, the inside fixedly connected with support frame of pivot, the inside fixedly connected with magnetic path of support frame, the surperficial metal pole of magnetic path, the surperficial swing joint of.

The invention has the beneficial effects that:

1. the aircraft body is connected with the driving blade of the aircraft, the aircraft starts the driving part to generate driving force, the rotating shaft is driven to rotate clockwise to enable the blade to generate driving force, the ratchet wheel inside the shaft sleeve is driven to rotate, the pawl is meshed with the rectangular groove, the metal rod is driven to move perpendicular to the magnetic induction line generated by the magnetic plate, a magnetic electricity generation phenomenon is generated, magnetic force generated by the metal rod is transmitted to the inside of the part sleeve to be stably stored, and therefore the effect of generating electric energy by utilizing the characteristics of the aircraft body is achieved.

2. The magnetic induction lines are cut by the metal rods to generate electric energy, when an airplane lands and lands on the ground, the driving power supply is closed and the airplane starts to brake, the rotating shaft loses power and does not rotate any more, the wind direction plate in the rotating shaft can push the baffle plate to drive the rollers to gradually keep away from the surface of the ventilation opening under the clamping of the guide grooves under the action of wind force, the ventilation opening is opened, the wind force borne by the blades is increased and rotates anticlockwise, the blades rotate reversely to release the stored electric energy, the blades are driven to rotate anticlockwise independently, and the direction of the wind force generated by the blades is opposite to the direction of the movement of the airplane, so that the effect of assisting the brake system in braking is achieved; when the airplane stops, the stored electric energy is not released, and the rest electric energy can be used for the next takeoff ladder, so that the effect of reducing energy consumption is achieved.

Preferably, the blades are movably connected with the rotating shaft through a shaft sleeve, so that the blades can be driven to rotate independently.

Preferably, both sides of the retaining plate are movably connected with ventilation openings, and when the ventilation openings are opened, the blades can be blown to move in the direction opposite to the rotating shaft.

Preferably, the inside of the shaft sleeve is movably connected with a ratchet wheel, the surface of the ratchet wheel is hinged with a pawl, and the pawl and the ratchet wheel can be meshed only when the ratchet wheel rotates clockwise.

Preferably, a rectangular groove is fixedly connected to the inside of the shaft sleeve.

Preferably, a component sleeve is fixedly connected to the surface of the gear inside the shell.

Preferably, the number of the magnetic blocks is two, the magnetism of the two magnetic blocks is opposite, and a magnetic induction line generated by the two magnetic blocks is perpendicular to the metal rod.

Preferably, the rectangular slot is placed clockwise to limit the direction of engagement with the pawl.

Drawings

FIG. 1 is a top view of the body structure of the present invention;

FIG. 2 is a top sectional view of the housing structure of the present invention;

FIG. 3 is a cross-sectional view of the sleeve construction of the present invention;

FIG. 4 is an enlarged view of a portion A of FIG. 3;

fig. 5 is a sectional view of the structure of the bushing of the present invention.

In the figure: 1-machine body, 2-rotating shaft, 3-blade, 4-gear, 5-guide groove, 6-roller, 7-retaining plate, 8-supporting frame, 9-magnetic plate, 10-metal rod, 11-wind direction plate, 12-shaft sleeve, 13-ventilation opening, 14-ratchet wheel, 15-pawl, 16-rectangular groove and 17-component sleeve.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring to fig. 1-5, a high-speed flywheel storage emission reduction device for an aircraft engine comprises an engine body 1, a rotating shaft 2 is movably connected inside the engine body 1, a blade 3 is sleeved on the surface of the rotating shaft 2, the blade 3 is movably connected with the rotating shaft 2 through a shaft sleeve 12, a ratchet 14 is movably connected inside the shaft sleeve 12, a pawl 15 is hinged on the surface of the ratchet 14, the pawl 15 and the ratchet 14 are only engaged when the ratchet 14 rotates clockwise, a rectangular groove 16 is fixedly connected inside the shaft sleeve 12 and is convenient for driving the blade 3 to rotate independently, the rectangular groove 16 is placed clockwise to limit the direction of being clamped with the pawl 15, a gear 4 is movably connected on the back of the blade 3 and on the surface of the rotating shaft 2, a component sleeve 17 is fixedly connected inside the housing 1 and on the surface of the gear 4, a guide groove 5 is formed on the surface of the gear 4, a retaining plate 7 is movably connected on the surface of, both sides of the retaining plate 7 are movably connected with vent holes 13, when the vent holes 13 are opened, the blades 3 can be blown to move in a direction opposite to that of the rotating shaft 2, if the rotating shaft 2 loses power and does not rotate any more, the wind direction plate 11 in the rotating shaft 2 is acted by wind force and can reversely push the retaining plate 7 to drive the roller 6 to gradually keep away from the surface of the vent holes 13 under the clamping of the guide groove 5, the vent holes 13 are opened, the wind force borne by the blades 3 is increased and rotates anticlockwise, the blades 3 are reversely rotated to release the previously stored electric energy and independently drive the blades 3 to rotate anticlockwise, the direction of the wind force generated by the blades 3 is opposite to the moving direction of an airplane, the effect of assisting a braking system in braking is achieved, the supporting frame 8 is fixedly connected inside the rotating shaft 2, the magnetic blocks 9 are fixedly connected inside the supporting frame 8, the number of the magnetic blocks 9 is two, the magnetic induction lines generated by the magnetic block and the magnetic block are vertical to the metal rod 10, the metal rod 10 on the surface of the magnetic block 9 and the rotating shaft 2 rotate clockwise to enable the blade 3 to generate driving force and drive the ratchet wheel 14 inside the shaft sleeve 12 to rotate, the pawl 15 is meshed with the rectangular groove 16, the metal rod 10 is driven to do cutting motion vertical to the magnetic induction lines generated by the magnetic plate 9, and a magnetoeletricity phenomenon is generated, and is discovered by England scientists Faraday. The principle is that when a part of conductors of a closed circuit do cutting magnetic induction line movement, a phenomenon that current is generated on the conductors is called an electromagnetic induction phenomenon, and the generated current is called induction current. The generator is manufactured according to the principle; the surface of the supporting frame 8 is movably connected with a wind vane 11.

When the aircraft is used, the aircraft body 1 is connected with the driving blade 3 of the aircraft, the aircraft starts the driving part to generate driving force, the rotating shaft 2 is driven to rotate clockwise to enable the blade 3 to generate driving force, the ratchet wheel 14 in the shaft sleeve 12 is driven to rotate, the pawl 15 is meshed with the rectangular groove 16, the metal rod 10 is driven to perform cutting motion perpendicular to a magnetic induction line generated by the magnetic plate 9, namely, a magnetic electricity generation phenomenon is generated, magnetic force generated by the metal rod 10 is transmitted to the inside of the part sleeve 17 to be stored in a stable voltage mode, and the effect of generating electric energy by utilizing the characteristics of the aircraft is achieved; the metal rod 10 cuts the magnetic induction line to generate electric energy, when an airplane lands and lands on the ground, the driving power supply is turned off and the airplane starts to brake, the rotating shaft 2 loses power and does not rotate any more, the wind direction plate 11 in the rotating shaft 2 can reversely push the retaining plate 7 to drive the roller 6 to be clamped by the guide groove 5 and gradually keep away from the surface of the ventilation opening 13 due to the action of wind force, the ventilation opening 13 is opened, the wind force borne by the blades 3 is increased and rotates anticlockwise, the blades 3 reversely rotate to release the previously stored electric energy and independently drive the blades 3 to rotate anticlockwise, the direction of the wind force generated by the blades 3 is opposite to the moving direction of the airplane, and the effect of assisting a brake system in braking is achieved; when the airplane stops, the stored electric energy is not released, and the rest electric energy can be used for the next takeoff ladder, so that the effect of reducing energy consumption is achieved.

The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be able to cover the technical scope of the present invention and the equivalent alternatives or modifications according to the technical solution and the inventive concept of the present invention within the technical scope of the present invention.