阅读说明：本技术 一种串联增压型电涡轮发动机独立驱动涡轮风扇系统 (Independent driving turbofan system of series supercharged electric turbine engine ) 是由 程翔宇 于 2021-08-10 设计创作，主要内容包括：本发明公开了一种串联增压型电涡轮发动机独立驱动涡轮风扇系统,属于航空涡轮风扇发动机技术领域,包括加压涵道、低压进气入口、高速喷流出口、共轴涡轮加速单元组件。本发明针对发动机加压涵道中不同的气体密度、压力、温度状态,通过对每套加速单元设置不同的涡轮风扇输出功率、转速参数的方法,解决了发动机整体输出功率最大化的问题；可在不增加静叶的情况下,通过两级相邻叶片的反向对转,来提高级间增压效率,降低发动机重量；还对各级涡轮风扇的桨叶数量、桨叶面积进行优化设计,以保障发动机后端涡轮风扇叶片能够对后端高压稠密气体,实现进一步有效增压,从而发挥出每级涡轮风扇的最高推进效率,并实现发动机加压涵道整体的效率最大化。(The invention discloses an independent driving turbofan system of a series supercharged electric turbine engine, belonging to the technical field of aviation turbofan engines. Aiming at different gas density, pressure and temperature states in the engine pressurizing duct, the problem of the maximization of the overall output power of the engine is solved by setting different turbofan output power and rotating speed parameters for each set of accelerating unit; under the condition of not increasing the static blades, the interstage supercharging efficiency is improved and the weight of the engine is reduced through the reverse contra-rotation of two adjacent stages of blades; the number of blades and the area of the blades of each stage of turbofan are optimized to ensure that the rear end turbofan blades of the engine can realize further effective pressurization on the rear end high-pressure dense gas, so that the highest propulsion efficiency of each stage of turbofan is exerted, and the efficiency of the whole engine pressurization duct is maximized.)

1. A series-supercharged electric turbine engine independent-drive turbofan system is characterized in that: the device comprises a pressurizing duct, a low-pressure air inlet, a high-speed jet flow outlet and a coaxial turbine accelerating unit assembly, wherein the low-pressure air inlet is arranged at one end of the pressurizing duct, the high-speed jet flow outlet is arranged at the other end of the pressurizing duct, the coaxial turbine accelerating unit assembly comprises a plurality of coaxial turbine accelerating units which are arranged in the pressurizing duct in a serial mode, one coaxial turbine accelerating unit comprises two or more than two motor-fan assemblies which are oppositely arranged in pairs and are coaxial, one motor-fan assembly comprises a motor and a turbofan, the turbofan is connected with the motor, blades of the two turbofan assemblies arranged in pairs in one coaxial turbine accelerating unit are in a reverse counter-rotating state in the moving direction during work and are arranged from the low-pressure air inlet to the high-speed jet flow outlet, each of the coaxial turbo-acceleration unit fan diameter and the pressurization duct diameter are gradually reduced.

2. The multi-stage turbofan engine having a series boosting function of claim 1 wherein: in the coaxial motor fan assembly which is installed in pairs and is provided with the same coaxial turbine accelerating unit, a motor positioned at the head end is connected with the pressurizing duct through a supporting plate, a motor positioned at the tail end is connected with the pressurizing duct through a static blade, and the rotating directions of the turbine fan blades on the motor positioned at the tail end are opposite to the rotating directions of the static blade structures.

3. The series-supercharged electric turbine engine independently-driven turbofan system of claim 1 further comprising: the number of turbine fan blades in each of the coaxial turbo-acceleration units increases from the low pressure inlet to the high velocity jet outlet.

4. The series-supercharged electric turbine engine independently-driven turbofan system of claim 1 further comprising: the width and the area of a turbine fan blade in each coaxial turbo-acceleration unit are gradually increased from the low-pressure air inlet to the high-speed jet outlet.

5. The series-supercharged electric turbine engine independently-driven turbofan system of claim 1 further comprising: the pressurizing duct comprises a plurality of sections of ducts which are arranged in sequence, and a coaxial turbine accelerating unit is arranged in each section of duct.

6. The series-supercharged electric turbine engine independently-driven turbofan system of claim 1 further comprising: the series supercharged electric turbine engine independent driving turbofan system further comprises a feedback control assembly, wherein the feedback control assembly comprises an external control unit and a plurality of air pressure sensors for detecting air pressure, the air pressure sensors are arranged in the ducts of the sections, the air pressure sensors are in communication connection with the external control unit, and the external control unit is in communication connection with the coaxial turbine accelerating units.

7. The series-supercharged electric turbine engine independently-driven turbofan system of claim 6 wherein: the feedback control assembly also includes a power sensor for sensing the output power of each coaxial turbo-acceleration unit, the power sensor being communicatively coupled to the external control unit.

8. The series-supercharged electric turbine engine independently-driven turbofan system of claim 7 wherein: the feedback control assembly further comprises a supercharging efficiency arithmetic unit for detecting the supercharging efficiency of the engine, and the supercharging efficiency arithmetic unit is in communication connection with each air pressure sensor and the external control unit respectively, continuously and uninterruptedly provides pressure increase data of each part in the engine for the external control unit.

Technical Field

The invention relates to the technical field of aviation turbofan engines, in particular to a series-connection supercharged electric turbofan engine independent driving system.

Background

The driving devices of common helicopters, quad-rotor unmanned planes and the like are generally open single-propeller or double-propeller rotor systems. The open type propeller driving system is serially arranged in a sealed pressurizing duct cavity, so that the continuous pressurizing performance of the propeller blades of the engine can be improved, and the propelling efficiency of the turbine propeller system is improved. And can protect the turbine blades of the engine, and surrounding objects, from being scratched by the operation of the high-speed blades. Has obvious technical progress.

However, new problems arise if only a plurality of sets of coaxial turbo-acceleration units are simply arranged in series within the pressurized duct. As the air flow is in the engine duct, it is progressively compressed by the accelerating cells connected in series therein. As the compression ratio of each section in the pressurized duct is different, the temperature state of the gas is also different. Therefore, the airflow resistance experienced by each set of accelerating units is not the same. If the diameters of each propeller and each accelerating turbine unit are consistent with the rotating speed of the motor, each set of accelerating unit cannot be ensured to work in the maximum power output state, and the improvement of the overall output efficiency of the engine is not facilitated.

Chinese utility model patent with patent publication No. CN209483501U, publication No. 2019, 10, 11, and name "multistage electric turbofan jet engine" discloses a multistage electric turbofan jet engine, and the shortcomings are: between two opposite motor turbine blades, the structure rotation direction is not reversed; the moving direction is not reversely contra-rotating during working; the document prevents the circumferential high-speed rotation of the airflow through the stator blade fans, and the arrangement of a large number of stator blade fans increases the weight of the engine, and reduces the thrust-weight ratio and the continuous supercharging efficiency of the engine. To this end, a series supercharged electric turbine engine independently driven turbofan system is proposed.

Disclosure of Invention

The technical problem to be solved by the invention is as follows: the problem of how to improve the output power of each stage of accelerating unit and maximize the overall output efficiency of the engine in the working process of the series supercharged electric turbine engine is solved.

The invention solves the technical problem by the following technical scheme, the invention comprises a pressurizing duct, a low-pressure air inlet, a high-speed jet flow outlet and a coaxial turbine accelerating unit assembly, wherein the low-pressure air inlet is arranged at one end of the pressurizing duct, the high-speed jet flow outlet is arranged at the other end of the pressurizing duct, the coaxial turbine accelerating unit assembly comprises a plurality of coaxial turbine accelerating units which are arranged in the pressurizing duct in a serial mode, one coaxial turbine accelerating unit comprises two or more than two motor fan assemblies which are arranged in pairs in a face-to-face mode and are coaxial, one motor fan assembly comprises a motor and a turbine fan, the turbine fan is connected with the motor, the blades of the two turbine fans arranged in pairs in one coaxial turbine accelerating unit are in a reverse counter-rotating state in the moving direction during work, each of the coaxial turbo-acceleration unit fan diameters and the pressurization duct diameters are gradually reduced from the low pressure intake inlet to the high velocity jet outlet.

Furthermore, in the coaxial motor-fan assembly mounted in pairs of the same coaxial turbo-accelerating unit, the motor at the head end is connected with the pressurizing duct through the support plate, the motor at the tail end is connected with the pressurizing duct through the stationary blade, and the rotating directions of the turbine fan blades on the motor at the tail end are opposite to the rotating directions of the stationary blade structures.

Further, the number of turbine fan blades in each of the coaxial turbo acceleration units increases from the low pressure intake inlet to the high speed jet outlet.

Further, the width and area of the turbine fan blades in each of the coaxial turbo-acceleration units gradually increase from the low-pressure intake inlet to the high-speed injection outlet.

Furthermore, the pressurized duct comprises a plurality of ducts arranged in sequence, and each duct is provided with a coaxial turbine accelerating unit.

Furthermore, the series supercharged electric turbine engine independently driven turbofan system further comprises a feedback control assembly, wherein the feedback control assembly comprises an external control unit and a plurality of air pressure sensors for detecting air pressure, the air pressure sensors are arranged in the ducts of the sections, the air pressure sensors are in communication connection with the external control unit, and the external control unit is in communication connection with the coaxial turbo accelerating units.

Still further, the feedback control assembly further includes a power sensor for sensing the output power of each coaxial turbo-acceleration unit, the power sensor being communicatively coupled to the external control unit.

Furthermore, the feedback control assembly further comprises a supercharging efficiency arithmetic unit for detecting the supercharging efficiency of the engine, wherein the supercharging efficiency arithmetic unit is respectively in communication connection with each air pressure sensor and the external control unit and continuously provides pressure increase data of each part in the engine for the external control unit.

Compared with the prior art, the invention has the following advantages: the series supercharged electric turbine engine independently drives the turbofan system, and the problem of the maximization of the integral output power of the engine is solved by setting different turbofan output power and rotating speed parameters for each set of accelerating unit aiming at different gas density, pressure and temperature states in the engine pressurizing duct; under the condition of not increasing the stationary blades, the interstage supercharging efficiency is improved through the reverse contra-rotation of two adjacent stages of blades, the overall weight of the engine is reduced, and additional stationary blade guide blades do not need to be added in the middle of the interstage supercharging efficiency; because of the serial pressurization of the engine, the gas density in the pressurization duct is in a gradually increased state, so that the rear-end turbofan of the engine should have a wider blade area and a denser blade arrangement; the rear end of the engine is ensured to be capable of pressurizing high-pressure dense gas at the rear end by the turbine fan blades, so that further effective pressurization is realized; thereby exerting the highest propulsion efficiency of each stage of turbofan, realizing the maximization of the overall efficiency of the engine pressurization duct and being worth popularizing and using.

Drawings

FIG. 1 is a schematic diagram of an overall configuration of an independently driven turbofan system for a series supercharged electric turbine engine in accordance with one embodiment of the present invention;

FIG. 2 is an enlarged schematic view of a portion of the structure of FIG. 1;

FIG. 3 is a schematic structural diagram of a motor-fan assembly according to an embodiment of the present invention;

FIG. 4 is a schematic diagram of a set of coaxial turbo-accelerator units according to one embodiment of the present invention;

FIG. 5 is a schematic view of the overall configuration of an independently driven turbofan system of a series supercharged electric turbine engine according to a second embodiment of the present invention;

FIG. 6 is an enlarged view of a portion of the structure of FIG. 5;

fig. 7 is a schematic diagram of system electrical control connection in the second embodiment of the present invention.

Detailed Description

The following examples are given for the detailed implementation and specific operation of the present invention, but the scope of the present invention is not limited to the following examples.

As shown in fig. 1 to 4, the present embodiment provides a technical solution: a series supercharged electric turbine engine independent driving turbofan system comprises a plurality of motors (motors 1 and 12)1, a plurality of turbofan (turbofan 2 and 10), a pressurizing duct 3 of the engine, a low-pressure air inlet 4 and a high-speed jet flow outlet 5, wherein one motor is coaxially connected with one turbofan 2 to form a motor fan combination body 6. Two motor-fan assemblies 6 are mounted face-to-face and coaxially to form a set of coaxial turbo-accelerating units 7. A plurality of sets of coaxial turbo-acceleration units 7 are installed in series in the pressurizing duct 3, forming a coaxial turbo-acceleration unit assembly having a continuous acceleration pressurizing effect. The coaxial turbo accelerating unit 7 formed by the motor-fan assembly 6 uses the existing series motors without special manufacture, has low cost, high efficiency, mature part products and high research and development production speed, and is a preferred scheme of a series supercharged electric turbine engine independent driving turbo fan system with high efficiency and reliability.

From the low pressure inlet 4 to the high velocity jet outlet 5, the fan diameter of each set of coaxial turbo-acceleration units 7 is progressively reduced in size, while the diameter of the pressurizing duct 3 is also progressively reduced. As the density ρ of the air flow in the pressurizing duct 3 is higher and higher, the velocity v is higher and higher, and the flow q is equal to ρ vA, the sectional area a of the pressurizing duct 3 should be gradually reduced with the increase of the number of stages, and the diameter is reduced. The high pressure airflow at the end of the engine requires a turbofan with more blades to further boost the airflow backwards, so as to prevent the sparse impeller distribution from generating destructive vibration and surge backflow of the air during the working process.

In the present embodiment, the motor 1 is fixedly connected with the inner wall of the pressurizing duct 3 through the support plate 9.

In the present embodiment, the motor 12 is fixedly connected to the inner wall of the pressurizing duct 3 via the stationary blade 11.

Example two

As shown in fig. 5, the series supercharged electric turbine engine of the present embodiment independently drives the turbofan, and in addition to the first embodiment, a plurality of air pressure sensors 13 are added at different acceleration stage positions inside the pressurizing duct 3. The rotating speed and the output power of each set of coaxial turbine accelerating unit 7 can be independently adjusted in real time through an external control unit according to the air pressure change conditions measured at different accelerating stage positions in the inner cavity of the pressurizing duct 3. If a certain stage of the supercharging effect is not good or the turbofan 2 is overloaded, a feedback control assembly (the feedback control assembly comprises an external control unit, an air pressure sensor 13, a power sensor for detecting the output power of the motor and a supercharging efficiency calculator for detecting the supercharging efficiency of the engine, each air pressure sensor 13, the power sensor (consisting of a current sensor and a voltage sensor) and the supercharging efficiency calculator are all in communication connection with the external control unit, and the supercharging efficiency calculator is simultaneously in communication connection with the air pressure sensor 13 and the external control unit; the external control unit is also in communication connection with a current and voltage monitoring meter of the motor and an output power controller of the motor per se for controlling the output power and the rotating speed of the motor) can be used for controlling the output power and the rotating speed of the motor according to the air pressure data of the air pressure sensor 13 and the power parameter of the motor, and adjusting the output power and the rotating speed of the corresponding motor in time. When the feedback control component finds that a certain stage of the turbo fan 2 is in a resonant or surge backflow state, that is, when the power sensor finds that the output power of the coaxial turbo accelerating unit 7 is very large (the output power data (power is equal to a current value multiplied by a voltage value) is obtained by monitoring the current and the voltage of the motor, the current meter and the voltage meter of the motor are respectively connected in series and in parallel in a power supply loop of the motor), and the boost efficiency is very low (the boost efficiency data is obtained by a boost efficiency calculator, and the boost efficiency calculator is connected between the air pressure sensor 13 and an external control unit), the feedback control component can increase or decrease the rotating speed of the coaxial turbo accelerating unit 7 to adjust the rotating speed of the stage of the coaxial turbo accelerating unit 7, so that the rotating speed is separated from a rotating speed area causing mechanism resonance. Thereby improving the pressurization efficiency of the turbofan system of the series supercharged electric turbine engine and the overall power output of the engine.

To sum up, the series supercharged electric turbine engine independent driving turbofan system of the above embodiment solves the problem of maximizing the overall output power of the engine by setting different turbofan output powers and rotation speed parameters for each set of accelerating unit according to different gas density, pressure and temperature states in the engine pressurizing duct; because the serial pressurization of the engine, the gas density in the pressurization duct is in a gradually increased state, so the rear-end turbofan of the engine should have a wider paddle area and more dense paddle arrangement, so as to ensure that the rear-end turbofan blades of the engine can realize further effective pressurization on high-pressure dense gas at the rear end. Thereby exerting the highest propelling efficiency of each stage of turbofan and realizing the maximization of the overall efficiency of the engine pressurization duct;

moreover, when the gas compression ratio at the rear end of the engine is high, the reverse air leakage is more easily generated by the sparse turbofan, and the tail part cannot be effectively pressurized in the forward direction. Therefore, the rear end of the engine has a dense distribution characteristic of the turbine fan blades relative to the front end of the engine, so that the problem of reverse leakage of high-pressure dense gas at the rear end can be solved. When the gas compression ratio at the rear end of the engine is higher, the sparse turbofan generates reverse air leakage and is easy to generate asthma, so that the vibration of the blades of the engine is caused, the structure of the engine is damaged, and the problem of the asthma caused by the dense distribution characteristics of the blades of the turbofan at the rear end of the engine can be avoided. When the air density at the rear end of the engine is increased and the flow through the bypass is kept constant, the cross-sectional area of the pressurizing bypass at the rear end of the engine is kept in a gradually contracted state relative to the front end, so that the conditions that: in the engine rear end bypass, there is a problem of internal negative pressure due to volume expansion, and the occurrence of such negative pressure is disadvantageous for further improvement of the internal pressure of the engine jet outlet. The advantages of a single motor coupled to a single turbofan are: the rotating speed of each fan can be independently and accurately regulated according to different air pressures and flows in the duct, so that the overall pressurizing efficiency of the engine is improved, and the maximization is easier to achieve.

Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.