CN221942567U - Built-in turbine engine - Google Patents

Abstract

The utility model relates to the technical field of aviation power equipment, in particular to a built-in turbine engine. It has solved the unable problem that realizes longer duration. The engine comprises an engine body, two ends of the engine body penetrate through, the middle part of the engine body is coaxially connected with a drum shaft in a rotating mode, two ends of the drum shaft are respectively provided with a power generation component, the outer ends of the power generation components are respectively connected with energy storage equipment, a compressor, a combustion chamber and a turbine are axially arranged between the engine body and the outer side of the drum shaft in sequence, a spray pipe is arranged at one end, close to the turbine, of the engine body, an air inlet channel is arranged at one end, close to the compressor, of the engine body, and the air inlet channel is communicated with the compressor. The utility model realizes the complete conversion of electric energy, mechanical energy, thermal energy, mechanical energy and electric energy, thereby realizing the complete turbine engine hybrid power scheme.

Description

An internal turbine engine

Technical Field

The utility model relates to the technical field of aviation power equipment, in particular to a built-in turbine engine.

Background Art

There are two main ways for conventional aircraft to fly. One is fixed-wing aircraft, which uses a turbojet or turbofan engine as the propulsion power for forward flight, and the aircraft wings provide lift. The other is a wingless rotor helicopter, which uses a rotor to provide lift and achieve vertical take-off and landing, and its power is a turboshaft engine. Both use conventional fuel power.

With the maturity of electric technology and the improvement of environmental awareness, transportation has gradually become electrified, and rotary-wing drones have gradually become an important force in low-speed aircraft. Rotary-wing drones are mostly driven by batteries and motors. Due to the low energy density of batteries at this stage, the aircraft cannot achieve a long endurance while ensuring the load capacity, and it is difficult to achieve hybrid power.

Summary of the invention

The utility model provides a built-in turbine engine, which realizes a complete conversion of electric energy, mechanical energy, thermal energy, mechanical energy and electric energy, and achieves a longer endurance, thereby realizing a complete turbine engine hybrid power solution.

In order to solve the above technical problems, the utility model adopts the following technical solutions:

A built-in turbine engine comprises an engine body, both ends of the engine body are penetrated, the middle part of the engine body is coaxially connected with a drum shaft, both ends of the drum shaft are provided with power generation components, the outer ends of the power generation components are connected to energy storage devices, a compressor, a combustion chamber and a turbine are axially arranged in sequence between the engine body and the outer side of the drum shaft, a nozzle is provided at one end of the engine body close to the turbine, and an air inlet is provided at one end of the engine body close to the compressor, and the air inlet is connected to the compressor.

Furthermore, the power generation component includes a stator, a rotor and an electromagnetic coil. The two stators are coaxially fixed at the opening of the engine body, the rotor is coaxially fixed at both ends of the drum shaft, the electromagnetic coil is arranged on the outside of the rotor, the electromagnetic coil is located between the stator and the rotor, and the electromagnetic coil is electrically connected to the energy storage device.

Furthermore, the energy storage device is connected to a motor.

Furthermore, the motor is connected to a power source.

Furthermore, the compressor adopts an axial flow structure.

Beneficial effects of the utility model:

Realize a complete conversion of electrical energy, mechanical energy, thermal energy, mechanical energy and electrical energy, achieve longer endurance, and thus realize a complete turbo engine hybrid solution.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG1 is a schematic diagram of the overall structure of the built-in turbine engine;

FIG2 is a structural cross-sectional view of an engine body;

Description of reference numerals:

1. Engine body; 101. Energy storage device; 2. Drum shaft; 3. Power generation component; 31. Stator; 32. Rotor; 33. Electromagnetic coil; 4. Compressor; 5. Combustion chamber; 6. Turbine; 7. Nozzle; 8. Inlet duct; 9. Motor; 10. Power supply.

DETAILED DESCRIPTION

In order to facilitate the understanding of those skilled in the art, the present invention is further described below in conjunction with embodiments and drawings. The contents mentioned in the implementation modes are not intended to limit the present invention.

As shown in Figures 1 and 2, an internal turbine engine includes an engine body 1, both ends of the engine body 1 are penetrated, the middle part of the engine body 1 is coaxially connected to a drum shaft 2, both ends of the drum shaft 2 are provided with power generation components 3, the outer ends of the power generation components 3 are connected to energy storage devices 101, and a compressor 4, a combustion chamber 5 and a turbine 6 are axially arranged in sequence between the engine body 1 and the outer side of the drum shaft 2, a nozzle 7 is provided at one end of the engine body 1 close to the turbine 6, and an air inlet 8 is provided at one end of the engine body 1 close to the compressor 4, and the air inlet 8 is connected to the compressor 4.

In this embodiment, the power generation component 3 includes a stator 31, a rotor 32 and an electromagnetic coil 33. The two stators 31 are coaxially fixed at the opening of the engine body 1, and the rotor 32 is coaxially fixed at both ends of the drum shaft 2. The electromagnetic coil 33 is arranged on the outside of the rotor 32. The electromagnetic coil 33 is located between the stator 31 and the rotor 32, and the electromagnetic coil 33 is electrically connected to the energy storage device 101.

In this embodiment, the energy storage device 101 is connected to a motor 9 .

In this embodiment, the motor 9 is connected to a power source 10 .

In this embodiment, the compressor 4 adopts an axial flow structure.

Working principle: As shown in Figures 1 and 2, first use the power supply 10 to energize the motor 9. The motor 9 acts as a power input to drive the drum shaft 2 to rotate, and the gas flows in through the intake duct 8. As the speed of the drum shaft 2 gradually increases, the pressure ratio of the compressor 4 gradually increases, and the power consumption also increases. The ignition and combustion problem of the combustion chamber 5 is improved. The combustion gas in the combustion chamber 5 expands and does work through the turbine 6, driving the compressor 4 to rotate, and gradually replacing the motor 9 to achieve power balance and acceleration and deceleration operations. Finally, the gas that has been cooled and reduced in pressure by the turbine 6 is further reduced in pressure and increased in speed through the nozzle 7 and discharged from the outside of the engine body 1. The engine also generates reverse thrust because of the high-speed gas generated by the nozzle 7, which pushes the engine body 1 to fly forward, thereby completing a complete cycle of the turbine 6 engine.

When the turbine 6 engine is operating normally, the motor 9 can be converted to the generator 9 mode according to demand. When the aircraft is in cruise or low performance requirements or other functional requirements, and the engine thrust demand is not large, the turbine 6 drives the motor 9 to generate electricity and output it to other power components or energy storage devices to achieve electric energy conversion or output. Through the built-in generator 9, a complete conversion of electric energy, mechanical energy, thermal energy, mechanical energy and electric energy is achieved, and a longer endurance is achieved, thereby realizing a complete turbine 6 engine hybrid solution.

Therefore, the energy storage device 101 is used to provide power reserve to the motor 9, storing power that can drive the drum shaft 2 to rotate. After the aircraft engine is successfully started, forward thrust is gradually provided; the aircraft cuts off the rotor power, shuts down the vertical take-off and landing system, and gradually switches to fixed-wing level flight cruise using the turbine 6 engine. According to power requirements, the turbine 6 engine is controlled to generate electricity to supply the energy storage device 101 or the motor 9, realizing the turbine engine hybrid power solution and realizing the composite wing aircraft solution with dual functions of fixed-wing and rotor vertical take-off and landing.

All technical features in this embodiment can be freely combined according to actual needs.

It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

Although the embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

The above embodiments are preferred implementation schemes of the present invention. In addition, other implementation schemes are also included. Any obvious replacement without departing from the concept of the present technical solution is within the protection scope of the present invention.

Claims (5)

1. A built-in turbine engine, characterized in that it comprises an engine body (1), the two ends of the engine body (1) are penetrated, the middle part of the engine body (1) is coaxially connected to a drum shaft (2), both ends of the drum shaft (2) are provided with power generation components (3), the outer ends of the power generation components (3) are connected to energy storage devices (101), a compressor (4), a combustion chamber (5) and a turbine (6) are axially arranged in sequence between the engine body (1) and the outer side of the drum shaft (2), a nozzle (7) is provided at one end of the engine body (1) close to the turbine (6), and an air inlet (8) is provided at one end of the engine body (1) close to the compressor (4), and the air inlet (8) is connected to the compressor (4). 2. The built-in turbine engine according to claim 1 is characterized in that the power generation component (3) includes a stator (31), a rotor (32) and an electromagnetic coil (33), the two stators (31) are coaxially fixed at the opening of the engine body (1), the rotor (32) is coaxially fixed at both ends of the drum shaft (2), the electromagnetic coil (33) is arranged on the outside of the rotor (32), the electromagnetic coil (33) is located between the stator (31) and the rotor (32), and the electromagnetic coil (33) is electrically connected to the energy storage device (101). 3. The internal turbine engine according to claim 2, characterized in that a motor (9) is connected to the energy storage device (101). 4. The internal turbine engine according to claim 3, characterized in that a power source (10) is connected to the motor (9). 5. The internal turbine engine according to claim 1, characterized in that the compressor (4) adopts an axial flow structure.