CN215830601U

CN215830601U - Turbine electromagnetic engine

Info

Publication number: CN215830601U
Application number: CN202122568790.1U
Authority: CN
Inventors: 李江江
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-10-25
Filing date: 2021-10-25
Publication date: 2022-02-15
Anticipated expiration: 2031-10-25

Abstract

The utility model discloses a turbine electromagnetic engine, which comprises a turbine engine device and a speed control device, wherein the turbine engine device comprises a gas compressor, a combustion chamber, a turbine of the turbine engine and a first rotating shaft, and the gas compressor and the turbine of the turbine engine are arranged on the first rotating shaft; the speed control device comprises a power acquisition turbine, a motor speed control device and a second rotating shaft, the power acquisition turbine and the motor speed control device are arranged on the second rotating shaft, an air inlet is formed in one end of the turbine engine device, and an air outlet is formed in the output end of the power acquisition turbine. According to the turbine electromagnetic engine provided by the utility model, the speed control device is arranged to be a rear structure, and the turbine engine device and the speed control device can exist independently, so that research and development, maintenance and repair are facilitated, and the structure is simple.

Description

Turbine electromagnetic engine

Technical Field

The utility model relates to the technical field of engines, in particular to a turbine electromagnetic engine.

Background

In the prior art, two types of conventional manned aircrafts exist, one type is a glider, such as a civil aviation airliner, a fighter plane, a transport plane and the like. Yet another is a single rotor conventional helicopter.

Multi-rotor unmanned aerial vehicles have been widely used in various industries such as aerial photography and aerial survey, agricultural plant protection, geological exploration, earthquake relief, bridging and threading, fire rescue, traffic patrol and the like on small-sized airplanes in the daytime. The multi-rotor aircraft removes a large amount of mechanical structures, and the multipoint lift structure of the multi-rotor aircraft has the inherent flight stability, so that the structure has the inherent stability advantage.

However, the motor has the extremely short plate, namely the motor capable of accurately controlling the speed must be used as power output, because the torque constant response speed of the motor is extremely high, the multi-rotor unmanned aerial vehicle can adjust the posture in time, the aerial self-stability is achieved, the battery must be used as an energy source when the motor is used, the energy density of the battery is only one thirtieth to one sixtieth of that of fuel oil, and the energy density is very low. What many rotor unmanned aerial vehicle wanted to do is bigger just must bear bigger battery last day, but even the electric quantity is used up when flying, weight can not alleviate the minute milli yet, and it is obviously that this is dead the same thing, can't go on.

Therefore, the turbine electromagnetic engine solves the problem, the turbine electromagnetic engine uses fuel oil as an energy source, the speed control part can keep constant torque and stably control rotating speed output, and the large-size long-endurance multi-rotor aircraft can be manufactured, so that the multi-rotor aircraft can become the third series of manned aircraft. The aircraft that carries on quick engine of turbine electromagnetism accuse makes can compensate and rise perpendicularly to the gesture of gliding and change, compensate the short distance transportation in, carry passenger aircraft vacancy, many rotor crafts take off and land perpendicularly steadily and the wind resistance makes it no longer need the driver, do not need the runway, any county and city can set up the airport of this kind of aircraft, cross city and stride province air traffic and can obtain very big facility, express delivery commodity circulation is not under much, but the quick-witted accuse speed device of turbine electromagnetism among the prior art is leading structure, need axle and axle sleeve cooperation structure, the structure is more complicated, be unfavorable for the miniflight research and development.

SUMMERY OF THE UTILITY MODEL

Therefore, the utility model provides a turbine electromagnetic engine, which aims to solve the problem that a speed control device of the turbine electromagnetic engine in the prior art is of a front structure, needs a matched structure of a shaft and a shaft sleeve, and is relatively complex in structure.

In order to achieve the above purpose, the utility model provides the following technical scheme:

according to the utility model, the turbine electromagnetic engine comprises a turbine engine device and a speed control device, wherein the turbine engine device comprises a gas compressor, a combustion chamber, a turbine of the turbine engine and a first rotating shaft, and the gas compressor and the turbine of the turbine engine are arranged on the first rotating shaft; the speed control device comprises a power acquisition turbine, a motor speed control device and a second rotating shaft, the power acquisition turbine and the motor speed control device are arranged on the second rotating shaft, an air inlet is formed in one end of the turbine engine device, and an air outlet is formed in the output end of the power acquisition turbine.

Further, the turbine electromagnetic engine further comprises a shell, and the shell is arranged on the outer sides of the turbine engine device and the power collecting turbine.

Further, the motor speed control device is a brushless motor speed control device.

Further, the brushless motor speed control device comprises a motor device, an electric speed regulator, a battery device and a rotor end cover; the motor device is used for converting the internal energy of the stable airflow into mechanical energy and is used as a power output end for driving the rotor of the large multi-rotor aircraft to rotate; meanwhile, the motor device also charges the battery device or receives the power supply of the battery device;

the electric regulator is used for regulating the rotating speed of the motor device;

the battery device is used for supplying power to the motor device in time to accelerate the rotating speed of the motor device or charging the brushless motor device in time to decelerate the rotating speed of the brushless motor device when the rotating speed of the motor device needs to be changed.

Further, the center of rotor end cover is provided with the power take-off shaft who is connected with the rotor shaft of many rotor crafts.

The utility model has the following advantages:

according to the turbine electromagnetic engine provided by the utility model, the speed control device is arranged to be a rear structure, so that the turbine engine device and the speed control device can exist independently, research and development, maintenance and repair are facilitated, and the structure is simple.

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 should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.

The structures, ratios, sizes, and the like shown in the present specification are only used for matching with the contents disclosed in the specification, so as to be understood and read by those skilled in the art, and are not used to limit the conditions that the present invention can be implemented, so that the present invention has no technical significance, and any structural modifications, changes in the ratio relationship, or adjustments of the sizes, without affecting the effects and the achievable by the present invention, should still fall within the range that the technical contents disclosed in the present invention can cover.

FIG. 1 is a schematic illustration of a turbine electromagnetic engine shown in accordance with an exemplary embodiment;

FIG. 2 is a schematic block diagram illustrating another perspective of a turbine electromagnetic engine in accordance with an exemplary embodiment;

FIG. 3 is a perspective view of a turbine electromagnetic engine shown in accordance with an exemplary embodiment;

FIG. 4 is a perspective view of another perspective of a turbine electromagnetic engine shown in accordance with an exemplary embodiment;

in the figure: 11. a compressor; 12. a combustion chamber; 13. a turbine engine turbine; 14. a first rotating shaft; 15. an air inlet; 16. an exhaust port; 17. a power take-off shaft; 18. a housing; 19. a motor speed control device; 20. a rotor end cover; 21. a second rotation shaft; 22. a power harvesting turbine.

Detailed Description

The present invention is described in terms of particular embodiments, other advantages and features of the utility model will become apparent to those skilled in the art from the following disclosure, and it is to be understood that the described embodiments are merely exemplary of the utility model and that it is not intended to limit the utility model to the particular embodiments disclosed. 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.

According to an embodiment of the present invention, there is provided a turbine electromagnetic engine, as shown in fig. 1 to 4, including a turbine engine device and a speed control device, where the turbine engine device includes a compressor 11, a combustion chamber 12, a turbine engine turbine 13 and a first rotating shaft 14, and the compressor 11 and the turbine engine turbine 13 are disposed on the first rotating shaft 14; accuse quick-witted is including power acquisition turbine 22, motor accuse quick-witted 19 and second rotation axis 21, power acquisition turbine 22 with motor accuse quick-witted 19 set up in on the second rotation axis 21, the one end of turbine engine device is provided with air inlet 15, the output of power acquisition turbine is equipped with gas vent 16.

The turbine electromagnetic engine further comprises a housing 18, said housing 18 being arranged outside said turbine engine means and said power harvesting turbine. Providing protection to the components within the housing 18.

The motor speed control device 19 is a brushless motor speed control device. The brushless motor speed control device comprises a motor device, an electric speed regulator, a battery device and a rotor end cover 20; the motor device is used for converting the internal energy of the stable airflow into mechanical energy and is used as a power output end for driving the rotor of the large multi-rotor aircraft to rotate; meanwhile, the motor device also charges the battery device or receives the power supply of the battery device;

the battery device is used for supplying power to the motor device in time to accelerate the rotating speed of the motor device or charging the brushless motor device in time to decelerate the rotating speed of the brushless motor device when the rotating speed of the motor device needs to be changed, wherein the motor device can adopt a brushless motor.

The electric speed regulator, the battery device and the motor device can all use products in the prior art, the model and the specific arrangement mode of the electric speed regulator are not specifically described, and the electric speed regulator can refer to the prior art and is a technical characteristic used in a power system of a large multi-rotor aircraft capable of accurately regulating the speed.

The center of rotor end cover 20 is provided with power take-off shaft 17 connected with the rotor shafts of the multi-rotor aircraft. The multi-rotor aircraft can be powered through the power take-off shaft 17.

When the turbine engine device is used, high-pressure airflow is released after the turbine engine device is started, the airflow pushes the power acquisition turbine 22, the power acquisition turbine 22 is connected with the motor device through the second rotating shaft 21, the motor device rotates, and the end face of the motor device is a power output end and outputs power at the same time. When the feedback rotating speed of the motor device is too high, the magnetic resistance absorption energy is improved and converted into electric energy for storage, and when the feedback rotating speed of the motor device is too low, the electric energy is converted into kinetic energy to improve the rotating speed so as to make up the instant loss of the rotating speed and achieve the purpose of controlling the rotating speed.

The turbine engine device and the power collecting turbine 22 transmit power through gas, so that no stalling phenomenon exists in the process of controlling the rotating speed, and the air clutch does not have the abrasion phenomenon.

Air enters the turbine engine device from the air inlet 15, is compressed by the air compressor 11 and then enters the combustion chamber 12, fuel oil enters the combustion chamber 12, mixed gas of the fuel oil and the compressed air is ignited in the combustion chamber 12 and detonated, and huge airflow is instantly generated and is downwards sprayed until continuous huge airflow is generated in the combustion chamber 12, and the continuous huge airflow pushes the power acquisition turbine 22 to continuously rotate and is output through the rotor end cover 20.

Although the utility model has been described in detail above with reference to a general description and specific examples, it will be apparent to one skilled in the art that modifications or improvements may be made thereto based on the utility model. Accordingly, such modifications and improvements are intended to be within the scope of the utility model as claimed.

Claims

1. The turbine electromagnetic engine is characterized by comprising a turbine engine device and a speed control device, wherein the turbine engine device comprises a compressor, a combustion chamber, a turbine of the turbine engine and a first rotating shaft, and the compressor and the turbine of the turbine engine are arranged on the first rotating shaft; the speed control device comprises a power acquisition turbine, a motor speed control device and a second rotating shaft, the power acquisition turbine and the motor speed control device are arranged on the second rotating shaft, an air inlet is formed in one end of the turbine engine device, and an air outlet is formed in the output end of the power acquisition turbine.

2. The turbine electromagnetic engine of claim 1, further comprising a housing disposed outside of the turbine engine assembly and the power harvesting turbine.

3. A turbo-electromagnetic engine according to claim 1, wherein said motor speed control means is a brushless motor speed control means.

4. A turbo-electromagnetic engine according to claim 3, characterized in that said brushless motor speed control means comprises motor means, electronic regulation, battery means and rotor end covers; the motor device is used for converting the internal energy of the stable airflow into mechanical energy and is used as a power output end for driving the rotor of the large multi-rotor aircraft to rotate; meanwhile, the motor device also charges the battery device or receives the power supply of the battery device;

5. A turbo-electromagnetic engine according to claim 4, wherein the rotor head cover is centrally provided with a power take-off shaft connected to the rotor shaft of a multi-rotor aircraft.