阅读说明：本技术 串联增压型电涡轮发动机阶梯分段涡轮风扇系统 (Stepped sectional turbofan system of series supercharged electric turbine engine ) 是由 程翔宇 黄鹏程 魏思源 朱伟林 吴后平 周杨 章杰 杨靖辉 于 2021-10-12 设计创作，主要内容包括：本发明公开一种串联增压型电涡轮发动机阶梯分段涡轮风扇系统,包括若干共轴涡轮加速单元和发动机壳体,所述发动机壳体内设置有若干依次串联设置的加速涵道,所述发动机壳体两端分别设置有低压进气入口和高速喷流出口,气体由所述低压进气入口进入并依次经各所述加速涵道加速后由所述高速喷流出口排出,各所述共轴涡轮加速单元分别设置在各所述加速涵道内；本发明针对发动机加速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,在提高加速单元的输出功率的同时解决了发动机整体输出功率最大化的问题。(The invention discloses a cascade subsection turbofan system of a series supercharged electric turbine engine, which comprises a plurality of coaxial turbine accelerating units and an engine shell, wherein a plurality of accelerating ducts which are sequentially arranged in series are arranged in the engine shell; aiming at different gas density, pressure and temperature states in the accelerating duct of the engine, the invention solves the problem of maximizing the overall output power of the engine while improving the output power of the accelerating unit by setting different turbofan output power and rotating speed parameters for each set of accelerating unit.)

1. A cascade subsection turbofan system of a series supercharged electric turbine engine is characterized by comprising a plurality of coaxial turbine accelerating units and an engine shell, wherein a plurality of accelerating ducts which are sequentially connected in series are arranged in the engine shell, a low-pressure air inlet and a high-speed jet flow outlet are respectively arranged at two ends of the engine shell, air enters from the low-pressure air inlet and is sequentially accelerated by the accelerating ducts and then is discharged from the high-speed jet flow outlet, and the coaxial turbine accelerating units are respectively arranged in the accelerating ducts.

2. The cascade-staged turbofan system of claim 1 wherein the co-axial turbo accelerating units each comprise two single-ended motor-fan assemblies and at least one dual-out-shaft motor-fan assembly, wherein when one dual-out-shaft motor-fan assembly is provided, the two single-ended motor-fan assemblies are respectively disposed on two sides of the dual-out-shaft motor-fan assembly, when two or more dual-out-shaft motor-fan assemblies are provided, the dual-out-shaft motor-fan assemblies are sequentially connected to form a dual-out-shaft connector, and the two single-ended motor-fan assemblies are respectively disposed on two sides of the dual-out-shaft connector.

3. The cascade-supercharged electric-turbine-engine stepped-section turbofan system of claim 2 wherein said single-ended motor-fan assembly is constructed by coaxially coupling a turbofan to a motor, said dual-output-shaft motor-fan assembly is constructed by coaxially coupling two turbofan to a dual-output-shaft motor, and said turbofan in the same said coaxial turbo-acceleration unit is coaxially disposed.

4. The cascade-supercharged, electric-turbine-engine stepped-section turbofan system of claim 3 wherein said turbofan on said single-ended motor-fan assembly is disposed in correspondence with said turbofan on said dual-spool motor-fan assembly adjacent thereto.

5. The tandem supercharged electric turbine engine stepped-section turbofan system of claim 4 wherein said turbofan in each of said coaxial turbo-acceleration units is of decreasing diametric size from said inlet air inlet to said jet outlet; the diameter of each accelerating duct is reduced in a step mode.

6. The tandem supercharged electric turbine engine stepped-section turbofan system of claim 4 wherein the number of said turbofan in each of said coaxial turbo-accelerating units increases gradually from said intake air inlet to said jet stream outlet.

7. The tandem supercharged electric turbine engine stepped-section turbofan system of claim 4 wherein said turbofan within each said coaxial turbo-acceleration unit has a blade width and area that gradually increases from said inlet air inlet to said jet outlet.

8. The cascade-supercharged, electric-turbine-engine stepped-section turbofan system of claim 4 wherein adjustment of the speed and power output of said turbofan in each said coaxial turbo-acceleration unit is based upon air pressure conditions within each said acceleration duct.

9. The cascade-supercharged, electric-turbine-engine stepped-section turbofan system of claim 8 wherein each of said acceleration ducts has an air pressure sensor disposed therein for sensing an air pressure condition within the corresponding acceleration duct.

10. The tandem booster electric turbine engine stepped section turbofan system of claim 9 further comprising an external intelligent control unit connected to each of the air pressure sensors and each of the coaxial turbo acceleration units simultaneously.

Technical Field

The invention relates to the technical field of aviation turbofan engines, in particular to a stepped sectional turbofan system of a series supercharged electric turbofan engine.

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 accelerating duct cavity, so that the continuous pressurizing performance of the propeller blades of the engine can be improved, the propelling efficiency of the turbine propeller system is improved, and the turbine fan blades of the engine and surrounding objects can be protected from being scratched by the running of the high-speed blades.

However, if a plurality of sets of coaxial turbo-accelerating units are simply arranged in series in the accelerating duct, the airflow is gradually compressed by the accelerating units in the series in the engine duct, and the temperature state of the gas is different along with the difference of the compression ratio of each section in the accelerating duct, so that the airflow resistance of each set of accelerating units is different, and in this case, the output power of each stage of accelerating units can not be improved and the overall output efficiency and the thrust-weight ratio of the engine can not be maximized by simply connecting the accelerating units in series.

In view of the above-mentioned drawbacks, the inventors of the present invention have finally obtained the present invention through a long period of research and practice.

Disclosure of Invention

In order to solve the technical defects, the invention adopts the technical scheme that a cascade subsection turbofan system of a series supercharged electric turbine engine is provided, and the cascade subsection turbofan system comprises a plurality of coaxial turbine accelerating units and an engine shell, wherein a plurality of accelerating ducts which are sequentially connected in series are arranged in the engine shell, a low-pressure air inlet and a high-speed jet flow outlet are respectively arranged at two ends of the engine shell, air enters from the low-pressure air inlet and is sequentially accelerated by the accelerating ducts and then is discharged from the high-speed jet flow outlet, and the coaxial turbine accelerating units are respectively arranged in the accelerating ducts.

Preferably, the coaxial turbo accelerating unit includes two single-ended motor fan assemblies and at least one double-output-shaft motor fan assembly, when the double-output-shaft motor fan assembly is set to be one, the two single-ended motor fan assemblies are respectively arranged on two sides of the double-output-shaft motor fan assembly, when the double-output-shaft motor fan assembly is set to be two or more, the two double-output-shaft motor fan assemblies are sequentially connected to form a double-output-shaft connector, and the two single-ended motor fan assemblies are respectively arranged on two sides of the double-output-shaft connector.

Preferably, the single-end motor fan assembly is formed by coaxially connecting a turbine fan through a motor, the double-output-shaft motor fan assembly is formed by coaxially connecting two turbine fans through double-output-shaft motors, and the turbine fans in the same coaxial turbine acceleration unit are coaxially arranged.

Preferably, the turbofan on the single-end motor fan assembly and the turbofan on the double-output-shaft motor fan assembly adjacent to the turbofan are arranged correspondingly.

Preferably, the diameter of said turbofan in each said coaxial turbo-acceleration unit decreases in size from said inlet to said jet outlet; the diameter of each accelerating duct is reduced in a step mode.

Preferably, the number of said turbofan in each said coaxial turbo-acceleration unit is increased gradually from said intake air inlet to said jet flow outlet.

Preferably, the width and area of the blades of the turbofan in each of the coaxial turbo-accelerating units are gradually increased from the air inlet to the jet outlet.

Preferably, the adjustment of the speed and the output power of said turbofan in each of said coaxial turbo-accelerating units is performed based on the air pressure conditions in each of said accelerating ducts.

Preferably, each accelerating duct is internally provided with an air pressure sensor, and the air pressure sensor is used for detecting the air pressure condition in the corresponding accelerating duct.

Preferably, the cascade-supercharged electric turbine engine stepped section turbofan system further comprises an external intelligent control unit, and the external intelligent control unit is simultaneously connected with each air pressure sensor and each coaxial turbo accelerating unit.

Compared with the prior art, the invention has the beneficial effects that: aiming at different gas density, pressure and temperature states in the accelerating duct of the engine, the invention solves the problem of maximizing the overall output power of the engine while improving the output power of the accelerating unit by setting different turbofan output power and rotating speed parameters for each set of accelerating unit.

Drawings

FIG. 1 is a structural view of a first embodiment of a cascade-staged turbofan system for a supercharged electric turbine engine;

FIG. 2 is a structural view of the single-ended motor-fan assembly;

FIG. 3 is a structural view of the fan assembly with dual output shafts;

FIG. 4 is a structural view of the coaxial turbo-acceleration unit;

FIG. 5 is a structural view of a second embodiment of the cascade-supercharged electric turbine engine stepped-section turbofan system.

The figures in the drawings represent:

1-a first acceleration duct; 2-double output shaft motor fan assembly; 3-single end motor fan assembly; 4-a low pressure inlet; 5-a second acceleration duct; 6-a third accelerating duct; 7-high speed jet outlet; 8-a turbofan; 9-a motor; 10-double output shaft motor; 11-air pressure sensor.

Detailed Description

The above and further features and advantages of the present invention are described in more detail below with reference to the accompanying drawings.

Example one

As shown in fig. 1, fig. 1 is a structural view of a first embodiment of a cascade-staged turbofan system for a supercharged electric turbine engine; the cascade subsection turbofan system of the series supercharged electric turbine engine comprises a plurality of coaxial turbine accelerating units and an engine shell, wherein an accelerating duct is arranged in the engine shell, two ends of the accelerating duct are respectively provided with a low-pressure air inlet 4 and a high-speed jet flow outlet 7, each coaxial turbine accelerating unit is arranged in the accelerating duct, and the coaxial turbine accelerating units are sequentially arranged from the low-pressure air inlet 4 to the high-speed jet flow outlet 7.

Specifically, in this embodiment, the accelerating duct is sequentially provided with a first accelerating duct 1, a second accelerating duct 5 and a third accelerating duct 6 from the low-pressure air inlet 4 to the high-speed jet outlet 7, and the coaxial turbine accelerating unit is disposed in each of the first accelerating duct 1, the second accelerating duct 5 and the third accelerating duct 6.

As shown in fig. 2, 3 and 4, fig. 2 is a structural view of the single-ended motor fan assembly; FIG. 3 is a structural view of the fan assembly with dual output shafts; fig. 4 is a structural view of the coaxial turbo-acceleration unit.

Coaxial turbine accelerating unit all includes two single-end motor fan assembly 3 and at least one pair of axle motor fan assembly 2, when two axle motor fan assembly 2 set up to one, two single-end motor fan assembly 3 sets up respectively two axle motor fan assembly 2's both sides, when two axle motor fan assembly 2 sets up to two and more than two, each two axle motor fan assembly 2 connects gradually and forms two axle connectors, two single-end motor fan assembly 3 sets up respectively two axle connectors's both sides.

The single-end motor fan assembly 3 is coaxially connected with a turbofan 8 through a motor 9 to form the double-output-shaft motor fan assembly 2, the double-output-shaft motor fan assembly is coaxially connected with two turbofans 8 through a double-output-shaft motor 10 to form the double-output-shaft motor fan assembly, and the turbofans 8 in the same coaxial turbo acceleration unit are coaxially arranged.

The turbofan 8 on the single-end motor fan assembly 3 is arranged corresponding to the turbofan 8 on the double-output-shaft motor fan assembly 2 adjacent to the turbofan 8.

A plurality of sets of said coaxial turbo-acceleration units are mounted in series in each of said acceleration ducts to form a coaxial turbo-acceleration unit system assembly having a sustained acceleration pressurization effect.

Preferably, the diameter of the turbofan 8 in each of said coaxial turbo-acceleration units decreases progressively from said inlet 4 to said jet outlet 7; the diameter of each accelerating duct is gradually reduced in a step mode. When the air density at the rear end of the engine is increased and the flow rate passing through the bypass is kept constant, the sectional area of the accelerating bypass at the rear end of the engine is kept in a gradually contracted state relative to that at the front end of the accelerating bypass. This can be used to prevent the problem of internal negative pressure in the engine rear end bypass due to volume expansion, which would be detrimental to further increase of internal pressure in the region near the outlet of the engine jet.

Preferably, when the motor fan assemblies at two adjacent positions work, the rotation directions of the motors are opposite.

The single-end motor fan assembly 3 with distribute all around the motor of two play axle motor fan assembly 2 and have quiet leaf, quiet leaf will single-end motor fan assembly 3 or two play axle motor fan assembly 2 are connected fixedly to on the engine housing.

The benefits of the stepped segmented turbofan are: the turbofan and the matched components thereof can be selected from a product series size table, so that the size of each turbofan is not specially customized due to continuous channel reduction, and the development time of the engine is prolonged.

Preferably, the number of said turbofan 8 in each said coaxial turbo acceleration unit increases gradually from said inlet 4 to said jet outlet 7.

Preferably, the width and area of the blades of the turbofan 8 in each of the coaxial turbo-accelerating units increases gradually from the inlet 4 to the jet outlet 7. When the gas compression ratio at the rear end of the engine is high, the sparse turbofan is easy to generate reverse air leakage and cannot effectively pressurize towards the tail part 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 avoided. When the gas compression ratio at the rear end of the engine is high, 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, and the structure of the engine is damaged. Thus, the denser turbine fan blade distribution features at the aft end of the engine may avoid its surge problem.

While the regulation of the speed and the output power of the turbofan 8 in each of the coaxial turbo-acceleration units is carried out on the basis of the conditions of the air pressure in each of the acceleration ducts.

Because the double-output-shaft motor fan assembly 2 and the two end motor fan assemblies 3 are adopted to form the coaxial turbine accelerating unit, the double-output-shaft motor fan assembly 2 further compresses the volume space, the structural weight and the production and manufacturing cost of an accelerating and pressurizing module in the engine, and the thrust-weight ratio of the engine is improved.

The coaxial turbo accelerating unit is composed of one or more double-output-shaft motor fan assemblies 2 and two end motor fan assemblies 3, the used motors can adopt series motors in the market, and the method is free from specially manufacturing, low in cost, high in efficiency, mature in part products, high in research and development speed and high in production speed, and is a preferred scheme of a series supercharged stepped sectional turbo fan system of the electric turbo engine with higher efficiency and reliability.

From the inlet 4 to the jet outlet 7, the diameter of the turbofan 8 on each of the coaxial turbo-accelerating units is gradually reduced in size, while the diameters of the first, second and third accelerating ducts 1, 5 and 6 are also gradually reduced. As the air flow density ρ in the first accelerating duct 1, the second accelerating duct 5 and the third accelerating duct 6 is higher and higher, the speed v is higher and higher, and the flow q ═ ρ vA is kept constant, the sectional area a of the accelerating duct should be gradually reduced with the increase of the number of stages, and the diameter is reduced. The high pressure air flow near the engine end 7 requires a more bladed turbofan for further back-pressurization to prevent the sparse impeller distribution from generating destructive vibrations during operation, and surge back flow of air.

Aiming at different gas density, pressure and temperature states in the accelerating duct of the engine, the invention solves the problem of maximizing the overall output power of the engine while improving the output power of the accelerating unit by setting different turbofan output power and rotating speed parameters for each set of accelerating unit. Because the gas density is in a gradually increased state in the serial pressurization and acceleration duct of the engine, the rear-end turbofan of the engine should have a wider paddle area and a denser paddle arrangement to ensure the rear-end turbofan blades of the engine, and can implement further effective pressurization on the high-pressure dense gas at the rear end, thereby exerting the highest propulsion efficiency of each stage of turbine and realizing the problem of maximizing the overall efficiency of the acceleration duct of the engine. A set of coaxial turbo accelerating unit is formed by the two end motor fan assemblies and more than one double-output-shaft motor fan assembly instead of the two end motor fan assemblies, so that the space utilization rate of the coaxial turbo accelerating unit is improved, and the integral thrust-weight ratio of the engine is improved.

Example two

FIG. 5 is a structural view of a second embodiment of a cascade-supercharged, electric turbine engine, stepped-section turbofan system, as shown in FIG. 5; in addition to the first embodiment, a plurality of air pressure sensors 11 distributed at different acceleration stage positions inside each acceleration duct are added. The rotating speed and the output power of each set of coaxial turbine accelerating unit can be independently adjusted in real time through an external intelligent control unit according to the air pressure change conditions measured at different accelerating stage positions in the inner cavity of the accelerating duct.

If a certain level of increasing effect is not good or the turbo fan is overloaded, the feedback control system can adjust the output power and the rotating speed of the corresponding motor in time according to the air pressure of the sensor and the power parameter of the motor. When the feedback control system finds that a certain stage of turbofan is in a resonance or surge backflow state, namely when the output power of the coaxial turbo accelerating unit is very high and the supercharging efficiency is very low through a sensor, the feedback control system can adjust the rotating speed of the coaxial turbo accelerating unit of the stage upwards or downwards to enable the rotating speed to be 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 level of the engine.

The foregoing is merely a preferred embodiment of the invention, which is intended to be illustrative and not limiting. It will be understood by those skilled in the art that various changes, modifications and equivalents may be made therein without departing from the spirit and scope of the invention as defined in the appended claims.