CN117627813A - Electric drive type outer stator coil turbine bypass engine and aircraft - Google Patents

Abstract

The invention discloses an electrically driven external stator coil turbine ducted engine and an aircraft, which relates to the technical field of aviation components and includes a turbine duct and at least one duct drive unit. A single duct drive unit includes a turbine fan and a brushless drive. Mechanism, traditional turbine ducted fan, its drive motor is installed on the central axis of the rear end of the fan in the turbine duct. Since the motor installed inside cannot block the ducted airflow, the radius of the motor cannot be too large, so that the overall torque output by the motor If it is too small, the motor must pass a larger current, resulting in high heat loss of the motor current and low operating efficiency. In the present invention, the stator coil and the rotor permanent magnet are located in the peripheral area of the fan. The relative linear speed between them, the motor The overall efficiency is also higher. When the maximum current cannot be increased further and the peak value remains unchanged, the higher the forward injection voltage, the greater the conversion power that the motor can input electrical energy and output mechanical energy.

Description

An electrically driven external stator coil turbine ducted engine and aircraft

Technical field

The invention relates to the technical field of aviation components, and in particular to an electrically driven external stator coil turbine ducted engine and an aircraft.

Background technique

The old turbine ducted fan motor is located on the central axis of the duct, and the motor wiring is very inconvenient. The motor installed on the ducted central shaft occupies the axial space, making the arrangement between the two stages of the multi-stage turbofan not compact enough, resulting in the multi-stage turbine ducted engine being bulky. The coils in the motor are concentrated in a small space near the winding axis, which is not conducive to heat dissipation during motor operation.

For traditional turbine ducted fans, the drive motor is installed on the central axis at the rear end of the fan in the turbine duct. Since the motor installed inside cannot block the ducted airflow, the radius of the motor cannot be too large, resulting in a small overall torque output by the motor. . In order to obtain greater torque, the motor must pass greater current, resulting in high heat loss and low operating efficiency of the motor current. From the perspective of improving operating efficiency, when the relative linear speed between the stator coil and the rotor permanent magnet is faster, the overall efficiency of the motor is higher. Because when the relative linear speed between the stator coil and the rotor permanent magnet is faster, the reverse induced voltage generated by the coil is higher, and the forward injection voltage that the stator coil can withstand will be higher. When the maximum current remains unchanged, In this case, the motor can input/output more power.

The single-stage electric-driven turbine ducted engine cannot continuously accelerate and step-by-step pressurize the airflow in the duct, resulting in the tail jet velocity not being able to further increase, and thus preventing the aircraft from performing high-speed jet flight.

Contents of the invention

The purpose of the present invention is to provide an electrically driven external stator coil turbine ducted engine and an aircraft, which solves the problems of traditional motor-built-in turbine ducted engines with low efficiency, insufficiently compact structure, and inconvenient wiring and maintenance.

The present invention solves the above technical problems through the following technical solutions. The engine of the present invention includes a turbine duct and at least one duct drive unit. The single duct drive unit includes a turbine fan and a brushless drive mechanism. The brushless drive unit The driving mechanism includes a rotor and a stator. A permanent magnet fixed ring is fixedly connected to the outside of the turbine fan. The rotor includes a permanent magnet and soft iron. The permanent magnet is fixedly connected to the outside of the permanent magnet fixed ring. The soft iron is wrapped in Outside the permanent magnet, the stator includes a stator coil and a winding frame. The stator coil is sleeved on the outside of the winding frame. One end of the winding frame is fixedly connected to the inner wall of the turbine duct.

Preferably, retaining rings are fixedly connected to both sides of the permanent magnet fixed ring.

Preferably, a plurality of support ribs for installing the turbine fan are provided in the turbine duct. There are multiple support ribs, one end of which is fixed on the inner wall of the turbine duct, and the other end is fixed on the rotating shaft of the turbine fan.

Preferably, the rotation directions of the blades on any two adjacent turbofans are opposite or the same.

Preferably, the stator coil is electrically connected to a brushless ESC through a wire, and the input terminal of the brushless ESC is electrically connected to a battery or battery pack, and is electrically connected to the control signal output terminal of the flight control system.

Preferably, a plurality of the brushless ESCs are connected to different battery packs, and the power supply and driving voltage of each ducted drive unit are different.

Preferably, multiple brushless ESCs are connected in parallel on the same battery or battery pack, and each ducted drive unit has the same power supply and drive voltage.

Preferably, the plurality of turbine ducts are all single-channel turbine ducts or multi-branch confluence turbine ducts, and the turbine ducts at each stage are connected through tees or multi-ventilation pipes.

The present invention also proposes an electrically driven external stator coil turbine ducted engine aircraft and aircraft, which includes the above-mentioned engine and an aircraft body. The engine is provided with two groups, and the two groups of engines are respectively installed on both sides of the aircraft body. side.

Compared with the prior art, the beneficial effect of the present invention is that compared with the motor of the old turbine ducted fan located on the central axis of the duct, the motor of the present invention is located outside the turbine ducted fan. The rotor composed of permanent magnets and soft iron is connected to the periphery of the fan, and the stator coil is fixed on the engine casing. The stator coil wiring is very convenient.

The motor of the old-fashioned turbo ducted fan is installed on the central axis of the duct near the rear of the fan, which occupies the axial space, making the arrangement between the two stages of the multi-stage turbo fan not compact enough, resulting in the volume of the multi-stage turbo ducted engine. huge. The motor in the present invention is located outside the turbine ducted fan, so that the arrangement of the turbine fans between two adjacent stages can be very compact, which greatly reduces the overall volume of the multi-stage turbine ducted engine.

The coils in the motor are distributed in a wide space outside the fan. The large-area distributed coil arrangement creates a larger heat dissipation area, which will be more conducive to the realization of the motor's heat dissipation function. Moreover, the wind speed and wind pressure in the area near the housing in the engine duct are greater than those in the center area around the shaft. The greater air flow velocity will also bring better motor cooling efficiency.

For traditional turbine ducted fans, the drive motor is installed on the central axis at the rear end of the fan in the turbine duct. Since the motor installed inside cannot block the ducted airflow, the radius of the motor cannot be too large, resulting in a small overall torque output by the motor. . In order to obtain greater torque, the motor must pass greater current, resulting in high heat loss and low operating efficiency of the motor current. In the present invention, the stator coil and the rotor permanent magnet are located in the peripheral area of the fan. The relative linear speed between them is faster than that when concentrated in the central area of the rotating shaft, and the overall efficiency of the motor is also higher. Because, when the relative linear speed between the stator coil and the rotor permanent magnet is faster, the reverse induced voltage generated by the coil is higher, and the forward injection voltage that the stator coil can withstand will be higher. When the maximum current cannot be increased further and the peak value remains unchanged, the higher the forward injection voltage, the greater the conversion power that the motor can input electrical energy and output mechanical energy.

The electrically driven external stator coil multi-stage turbine ducted engine of the present invention can continuously accelerate and pressurize the airflow in the duct multiple times, which can promote the further increase of the tail jet flow speed and enable the aircraft to achieve high-speed jet flow. flight. In addition, after the airflow in the duct is continuously accelerated and supercharged multiple times by the multi-stage turbine, the rear-end turbine rotates faster. The relative linear speed between the stator and rotor of the rear-end turbine motor is higher, thereby further improving the conversion efficiency of the rear-end and final stage turbine motors.

Description of drawings

Figure 1 is a cross-sectional view of the stator of a single-stage turbine ducted engine with electric drive outer stator coil according to the present invention;

Figure 2 is a wiring diagram of the electric drive external stator coil single-stage turbine ducted engine stator coil and a single independent ESC according to the present invention;

Figure 3 is a partial enlarged view of the brushless ESC and brushless driving mechanism of Figure 2 of the present invention;

Figure 4 is a wiring diagram of the electric drive external stator coil single-stage turbine ducted engine stator coil and multiple distributed ESCs according to the present invention;

Figure 5 is a partial enlarged view of the brushless ESC and brushless drive mechanism of Figure 4 of the present invention;

Figure 6 is a schematic structural diagram of a multi-stage fan reversely opposed turbine ducted engine according to the present invention;

Figure 7 is a schematic structural diagram of a turbine ducted engine with multi-stage fans running in the same direction and fixed blades rotating in the same direction according to the present invention;

Figure 8 is a schematic structural diagram of a turbine ducted engine installed in a pod according to the present invention;

Figure 9 is a schematic structural diagram of a multi-branch confluence turbine ducted engine in the form of a multi-ventilation duct assembly according to the present invention;

Figure 10 is a three-dimensional view of the multi-branch converging turbine ducted engine of the present invention that is hidden inside the aircraft and installed in a multi-ventilation duct.

The numbers in the figure represent:

1-Turbo duct; 2-First turbo fan; 3-Brushless drive mechanism; 4-Brushless ESC; 5-Second turbo fan; 6-Third turbo fan; 7-Fourth turbo fan; 8- The fifth turbofan; 9-the first fan blade; 10-the second fan blade; 11-the first multi-stage turbine duct; 12-engine; 13-aircraft body; 14-three ventilation ducts; 16-aircraft; 17- Connecting shaft; 18-second multi-stage turbine duct; 19-support rib; 20-permanent magnet fixed ring; 21-permanent magnet; 22-soft iron; 23-retaining ring.

Detailed ways

The above and other technical features and advantages of the present invention will be described in more detail below with reference to the accompanying drawings.

Embodiment 1

This embodiment provides a technical solution: an electrically driven external stator coil turbine ducted engine, as shown in Figures 1 and 4, including a turbine duct 1 and at least one duct drive unit. The duct drive unit includes a third A turbine fan 2 and a brushless drive mechanism 3. The first turbofan 2 in the single-stage duct drive unit is located inside the duct, and the brushless drive mechanism 3 in the single-stage duct drive unit is located relative to the duct. The outer position of the first turbofan 2 .

The electrically driven external stator coil single-stage turbine ducted engine includes a brushless drive mechanism 3 in a single-stage ducted drive unit. The power supply input end of the brushless drive mechanism 3 is connected to the output end of the brushless ESC 4, and the input end of the brushless ESC 4 is connected to the battery or battery pack and the control signal output end of the flight control system.

Considering the heat dissipation performance of the ESC: the brushless ESC is composed of 3 distributed brushless ESCs 4. The turbine motor is driven by three distributed brushless ESCs, which is more conducive to heat dissipation of power components in the ESCs.

Considering the convenience of wiring operation and installation and maintenance: the brushless drive mechanism 3 in the present invention is located outside the first turbine fan 2 of the turbine duct. Compared with the old turbine ducted fan, the motor is located on the central axis of the duct, and the wiring It needs to be connected to the internal rotating shaft after passing through the engine casing. The brushless driving mechanism of the present invention is more convenient for wiring at 3 positions. The rotor composed of permanent magnets and soft iron is connected to the periphery of the fan, and the stator coil is fixed on the engine casing. The stator coil is located on the periphery of the engine, making coil wiring very convenient.

Considering the volume occupied by the engine: the brushless drive mechanism 3 in the present invention is located outside the first turbine fan 2 of the turbine duct, and the two are almost on the same axial cross-section, so that the turbofan arrangement between two adjacent stages , can be very compact. The motor of the old turbo ducted fan is installed on the central axis of the duct close to the rear of the fan, which occupies the axial space, resulting in a lot of useless space at the rear end of the fan, resulting in insufficient arrangement between the two stages of the multi-stage turbo fan. Compactness results in multi-stage turbine ducted engines being bulky. The invention reduces the axial space of the multi-stage turbine ducted engine and reduces the overall volume of the engine.

From the perspective of motor heat dissipation: the stator coils of the motor are distributed in a wide space outside the first turbofan 2. The large-area distributed coil arrangement creates a larger heat dissipation area, which will be more conducive to the realization of the motor heat dissipation function. Moreover, the wind speed and wind pressure in the area near the housing in the engine duct are greater than those in the center area around the shaft. The greater air flow velocity will also bring better motor cooling effect.

From the perspective of engine conversion efficiency: For traditional turbine ducted fans, the drive motor is installed on the central axis of the rear end of the fan in the turbine duct. Since the motor installed inside cannot block the ducted airflow, the radius of the motor cannot be too large, causing the motor to The overall torque output is relatively small. In order to obtain greater torque, the motor must pass greater current, resulting in high heat loss and low operating efficiency of the motor current. In the present invention, the stator coil and the rotor permanent magnet are located in the peripheral area of the first turbofan 2. The relative linear speed between the stator coil and the rotor permanent magnet is faster than the linear speed when concentrated in the central area of the rotating shaft, and the overall efficiency of the motor is also higher. high. Because, when the relative linear speed between the stator coil and the rotor permanent magnet is faster, the reverse induced voltage generated by the coil is higher, and the forward injection voltage that the stator coil can withstand will be higher. When the maximum current cannot be increased further and the peak value remains unchanged, the higher the forward injection voltage, the greater the conversion power that the motor can input electrical energy and output mechanical energy.

The constantly changing magnetic field generated by the plurality of stator coils continuously forms a repulsive or attractive force on the magnetic field on the permanent magnet 21 in the rotor, thereby pushing the rotor to rotate. This constantly changing magnetic field is controlled by the electronic control system and the flight control system to collaboratively control the voltage and current changes in multiple stator coils, thereby achieving continuous repelling or attracting actions to the permanent magnets 21 in the rotor, thereby generating continuous drive force, driving the rotor to rotate continuously.

Embodiment 2

This embodiment provides a technical solution: an electrically driven external stator coil turbine ducted engine. As shown in Figure 6, the engine is in the form of a first multi-stage turbine ducted 11, and the engine components are composed of multiple stages. , each stage is composed of a first turbofan 2 and a brushless drive mechanism 3 to form a single-stage ducted drive unit. The first turbofan 2 in the single-stage ducted drive unit is located inside the duct. The single-stage ducted drive The brushless drive mechanism 3 in the unit is in an outer position relative to the ducted fan.

The electrically driven external stator coil multi-stage turbine ducted engine includes a brushless drive mechanism 3 in a single-stage ducted drive unit. The power supply input end of the brushless drive mechanism 3 is connected to the output end of the brushless ESC 4, and the input end of the brushless ESC 4 is connected to the battery or battery pack, and the control signal output end of the flight control system. Each stage drive unit is connected to a single independent brushless ESC, and the 3-stage engine is connected to a total of 3 brushless ESCs4.

The power supply input terminals of the three brushless ESCs 4 are respectively connected to three different battery packs, so the power supply and driving voltage of each turbine stage are different. And as the rear-stage airflow accelerates and the rear-stage fan speed gradually increases, the power supply voltage of the rear-stage turbine ESC is higher, so the efficiency of the rear-stage motor is higher.

The inclination direction of the turbine fan blades of two adjacent stages is the same, and their running directions are in the same direction. That is, the blades of the second turbofan 5 and the third turbofan 6 are in the same direction, and the blades of the third turbofan 6 and the fourth turbofan 7 are in the same direction. They rely on support ribs 19 in the form of support ribs provided on the engine casing to circumferentially decelerate the vortex airflow in the duct. The support ribs also have the function of circumferentially decelerating the vortex airflow in the duct, and supporting the connection and fixation between the central axis of the fan and the casing.

Embodiment 3

This embodiment is further optimized on the basis of Embodiment 2. The same parts as the foregoing technical solution will not be repeated here, as shown in Figure 4, Figure 5 and Figure 7. Further, in order to better realize the present invention, in particular The following arrangement is adopted: in the form of a second multi-stage turbine duct 18, the engine component unit is composed of multiple stages, and each stage is composed of a first turbine fan 2 and a brushless drive mechanism 3 to form a single-stage duct drive unit. , the first turbofan 2 in the single-stage ducted drive unit is located inside the duct, and the brushless drive mechanism 3 in the single-stage ducted drive unit is located outside the ducted fan.

This electrically driven external stator coil multi-stage turbine ducted engine includes a brushless drive mechanism 3 in a single-stage ducted drive unit. The power supply input end of the brushless drive mechanism 3 is connected to the output end of the brushless ESC 4, and the input end of the brushless ESC 4 is connected to the battery or battery pack and the control signal output end of the flight control system. Each stage drive unit is connected to 3 ESCs, and the 3-stage engine is connected to a total of 9 ESCs.

This method of using multiple ESCs to connect and drive the motor in a distributed manner reduces the power of each brushless ESC to 1/3 of using one brushless ESC, thus causing each brushless ESC to generate The heat has been reduced. Therefore, using the distributed connection method of three small brushless ESCs, the device has better heat dissipation performance and working stability than using a single large brushless ESC (see Embodiment 2).

The inclination directions of the turbine fan blades of two adjacent stages are different, and the running direction is reverse rotation. That is, the blades of the second turbofan 5 and the fifth turbofan 8 are in a counter-rotating state, and the blades of the fifth turbofan 8 and the fourth turbofan 7 are in a counter-rotating state.

The support rib plane provided on the turbine duct is parallel to the central axis of the turbine duct, and does not require tilting or deflection when it guides the airflow in the turbine duct. By setting the turbine fan blades of two adjacent stages in opposite running directions, the airflow in the duct can be decelerated and stopped in the circumferential direction without relying on support ribs to decelerate and stop the airflow in the duct in the circumferential direction. This can reduce the number of support ribs in the duct, further reduce the structural weight of the engine, improve the compactness of the engine, and reduce the overall volume of the engine.

Embodiment 4

This embodiment provides a technical solution: an electrically driven external stator coil turbine ducted engine. As shown in Figure 8, two engines 12 are installed outside the aircraft in the form of pods. It has strong universality and does not require any modifications. The aircraft body 13 is renovated and upgraded as a whole. It only needs to be equipped with two pylons that match the engine and the aircraft to complete the matching installation between the two, saving the cost of modification and adaptive assembly time between the engine and the aircraft.

Embodiment 5

This embodiment provides a technical solution: an electrically driven outer stator coil turbine ducted engine. As shown in Figures 9 and 10, the electrically driven outer stator coil multi-stage turbine ducted engine has a multi-branch confluence type. Turbine duct. The three-way or multi-ventilation pipe 14 is used to connect the turbine ducted engines 12 at each stage and to complete the branching or converging function of the airflow in the duct.

The engine uses a multi-branch converging turbine duct to be designed conformally with the aircraft and is installed inside the aircraft 16 to reduce flight wind resistance. At the same time, it also reduces the exposed area of the engine casing and blades, which can increase the stealth efficiency of the aircraft coating.

Among the three ducted engines 12, the airflow inside the duct of the ducted engine located at the rear is formed by the confluence of the airflows in the first two engines. Therefore, the tail end engine has higher air pressure and flow velocity, resulting in the tail engine's turbofan having a higher speed. Therefore, the tail engine can be loaded with higher voltage, and the motor has higher output efficiency.

A combined turbine ducted engine formed by three ducted engines connected in parallel or in series has higher internal jet pressure and tail jet velocity. Therefore, it can propel the aircraft 16 to achieve higher flight and cruising speeds.

The above descriptions are only preferred embodiments of the present invention, which are illustrative rather than restrictive of the present invention. Those skilled in the art understand that many changes, modifications, and even equivalences can be made within the spirit and scope defined by the claims of the present invention, but they will all fall within the protection scope of the present invention.

Claims (9)

1. An electrically driven outer stator coil turbine ducted engine, characterized by: the engine comprises a turbine duct and at least one duct driving unit, wherein the single duct driving unit comprises a turbine fan and a brushless driving mechanism, the brushless driving mechanism comprises a rotor and a stator, a permanent magnet fixing ring is fixedly connected to the outer side of the turbine fan, the rotor comprises a permanent magnet and soft iron, the permanent magnet is fixedly connected to the outer side of the permanent magnet fixing ring, the soft iron is wrapped on the outer side of the permanent magnet, the stator comprises a stator coil and a winding framework, the stator coil is sleeved on the outer side of the winding framework, and one end of the winding framework is fixedly connected to the inner wall of the turbine duct.

2. The electrically driven outer stator coil turbine ducted engine of claim 1, wherein the retaining rings are fixedly connected to both sides of the permanent magnet retaining ring.

3. The electrically driven outer stator coil turbine bypass engine of claim 1, wherein a plurality of support ribs for mounting a turbofan are disposed in the turbine bypass, one end of each support rib is fixed on an inner wall of the turbine bypass, and the other end of each support rib is fixed on a rotating shaft of the turbofan.

4. The electrically driven outer stator coil turbine ducted engine of claim 1, wherein the blades on any adjacent two of said turbofans are counter-rotating or identical.

5. The electrically driven external stator coil turbine ducted engine of claim 1, wherein the stator coils are electrically connected with a brushless electric motor via wires, and the brushless electric motor input is electrically connected with a battery or a battery pack and electrically connected with a control signal output of the flight control system.

6. The electrically driven external stator coil turbine ducted engine of claim 5, wherein a plurality of said brushless electric regulators are each connected to a different battery pack, and wherein each of said ducted drive units is powered at a different drive voltage.

7. The electrically driven external stator coil turbine ducted engine of claim 5, wherein a plurality of said brushless electric regulators are connected in parallel on the same battery or battery pack, each of said ducted drive units having the same supply, drive voltage.

8. The electrically driven external stator coil turbine ducted engine of claim 1, wherein a plurality of said turbine ducted are single-channel turbine ducted or multi-tributary converging turbine ducted, and the connection between the turbine ducted stages is made by tee or multi-ventilation pipe.

9. An aircraft comprising an engine according to any one of claims 1 to 8, and further comprising an aircraft body, said engines being provided in two groups, said two groups being mounted on respective sides of the aircraft body.