CN209800118U

CN209800118U - Self-driven outer duct annular fan blade compression device

Info

Publication number: CN209800118U
Application number: CN201920670357.9U
Authority: CN
Inventors: 黄秀全; 王丁喜; 曹东明; 钱文韬
Original assignee: Northwest University of Technology
Current assignee: Northwestern Polytechnical University; Northwest University of Technology
Priority date: 2019-05-12
Filing date: 2019-05-12
Publication date: 2019-12-17
Anticipated expiration: 2029-05-12

Abstract

The utility model relates to a device of turbofan engine bypass ratio continuous adjustment especially relates to outer duct fan ring compressor arrangement of turbofan engine. The self-driven outer duct annular fan blade compression device comprises an inner duct of an engine, a duct arranged on the outer side of the inner duct is a third outer duct, a rotating component is arranged between an inlet guide vane and a stator vane in the third outer duct, and the rotating component is arranged on a duct casing of the third outer duct through a turntable bearing. The utility model realizes independent motor drive, so that the control mechanism is independent and has larger adjustment freedom degree; the design difficulty of the inner duct blade is not increased; the structure layout can be optimized by arranging the engine in different axial positions in the outer duct according to the structure layout characteristics of the engine.

Description

Self-driven outer duct annular fan blade compression device

Technical Field

The utility model relates to a device of turbofan engine bypass ratio continuous adjustment especially relates to outer duct fan ring compressor arrangement of turbofan engine.

Background

One typical requirement for the next generation of aircraft gas turbine fan engines is variable cycle. The variable cycle engine realizes the change of cycle parameters such as a pressure increase ratio, a flow rate, a bypass ratio and the like by changing the geometric shapes, the sizes and the positions of certain components, so that the engine has optimal performance in various working states, and has good adaptability to the flying height, the Mach number and the like of an airplane.

U.S. utility model patent No. US4043121 to Thomas et al, entitled "dual rotor variable cycle engine", discloses an engine with a tip fan (Flade) that achieves variability in engine cycle by adjusting adjustable vanes in the outer duct of the tip fan to control air flow.

In US patent US005809772A, a dual-cycle, additive cycle engine with a Core Driven Fan (CDFS) configuration is disclosed. The main difference of the structure of the engine is that the fan is divided into a front part and a rear part, the front part fan is driven by a low-pressure turbine shaft, the rear part fan is connected on a high-pressure shaft, the rear part fan is a core machine driven fan, and the front part fan and the rear part fan are respectively provided with an outer duct. The engine has an optimum bypass ratio over a wide operating range with mode selection valves in the front fan aft bypass and variable front area ejector (VABI) adjustment of the CDFS aft bypass.

In US20100180572a1, a three-bypass turbofan engine with both CDFS and Flade configurations is disclosed, the tip fan in the third bypass being directly driven by the inner bypass fan blades and disposed at the front end of the engine. Chinese patent CN1619129A discloses an engine with a tail Flade blade tip fan, wherein the Flade blade tip fan is connected with a low pressure turbine blade or a free turbine blade and is arranged at the rear end of the engine. This type of three-bypass turbofan engine is also known as an adaptive cycle engine, or smart engine. The third bypass is added on the basis of the double-bypass variable-cycle engine, the bypass ratio adjusting range of the engine can be enlarged through the flow path, the flow matching of the air inlet/the engine is optimized, and the third bypass can be used for heat management, stealth and the like of a high-energy weapon.

because outer duct Flade apex fan adopts the mode of directly linking with inside duct blade, has brought a great deal of disadvantages for the engine design: firstly, the strength of the blade is difficult to design, and the tangential speed of the blade is limited; secondly, the coupling connection makes the control system more complex, the degree of freedom of adjustment becomes smaller, and the expansion of the working range of the engine is not facilitated; thirdly, the performance of each duct cannot be considered, and the multi-duct engine is greatly limited to exert the variable cycle advantage.

Disclosure of Invention

An object of the utility model is to avoid prior art's not enough to provide an adopt electric motor rotor and fan ring rotor blade integrated design, compact structure, control mechanism are independent, with interior duct system mechanical decoupling zero, and adjust the electromagnetic drive's that the degree of freedom is big outer duct annular flabellum compression system.

In order to achieve the above purpose, the utility model adopts the following technical scheme: the utility model provides a self-driven outer duct annular flabellum compressor arrangement, includes the inner duct of engine, set up in the duct in the inner duct outside is third outer duct, is equipped with rotating member between the import guide vane in the third outer duct and stator blade, and rotating member passes through the bearing setting of carousel on the duct casket of third outer duct.

Furthermore, the rotating component comprises an annular support frame, the annular support frame is provided with an inner wall and an outer wall, the inner wall of the annular support frame is provided with fan blades, and the outer wall of the annular support frame is provided with an electromagnetic device; the annular support frame is arranged on an outer casing of the third outer duct through a pair of turntable bearings, and a motor stator is further arranged on the outer casing corresponding to the electromagnetic device; the magnetic poles of the electromagnetic device and the motor stator are arranged in a circumferential array mode, and the polarities of the electromagnetic device and the motor stator are opposite.

Further, the bearing clearance of the turntable bearing is smaller than the blade tip clearance, and the blade tip clearance refers to the clearance between the fan blade and the inner casing of the third outer duct.

Furthermore, the rotating component comprises an annular support frame, the annular support frame is provided with an inner wall and an outer wall, the inner wall of the annular support frame is provided with an electromagnetic device, and the outer wall of the annular support frame is provided with fan blades; the annular support frame is arranged on an inner casing of the third outer duct through a pair of turntable bearings, a motor stator is further arranged on the inner casing corresponding to the electromagnetic device, magnetic poles of the electromagnetic device and the motor stator are arranged in an array mode along the circumferential direction, and the polarity of the electromagnetic device is opposite to that of the motor stator.

Further, the bearing clearance of the turntable bearing is smaller than the blade tip clearance, and the blade tip clearance refers to the clearance between the fan blade and an outer casing of the third outer duct.

Furthermore, the electromagnetic device is a permanent magnet or a motor rotor coil.

Furthermore, the turntable bearing is a cylindrical roller bearing.

Furthermore, the guide vanes are matched with the rotating speed of the rotating component to adjust the installation angle, so that the fan blades of the rotating component obtain the optimal incoming flow attack angle.

Furthermore, a clearance between the rotating component and the casing is provided with a labyrinth which is sealed to reduce air leakage and flow.

Further, the flow of the third outer duct is changed within the range of 0-60% of the flow of the whole machine; when the flow of the third culvert is 0, the third culvert is in a closed state, and the airplane is in an ultrasonic cruise or maneuvering state at the moment; when the third bypass flow is 60% of the total flow, the engine is in a state of large bypass ratio, namely the aircraft is in a subsonic cruising state. In actual flight, the engine can meet the working performance requirement by adjusting the third bypass flow.

The utility model has the advantages that: different with traditional outer duct Flade apex fan, the utility model discloses an electric motor rotor and fan ring flabellum integrated design, outer duct fan ring compression system with motor independent drive has been formed, compact structure has, the control mechanism is independent, with characteristics such as inner duct system mechanical decoupling zero, can realize the continuous regulation on a large scale of engine duct ratio, effectively optimize the matching of engine and intake duct, reduce or even eliminate the overflow resistance, enlarge turbofan engine's working range greatly, be applicable to the performance requirement height, working range is wide, many duct gas turbine fan engine of working mode, become circulation gas turbine fan engine, self-adaptation circulation engine and intelligent engine, can give play to this type of engine's the variable cycle advantage more.

Meanwhile, the utility model adopts the core machine driving fan (CDFS) + independently driven third culvert fan ring structure, realizing independent motor driving, so that the control mechanism is independent and has more freedom degree of adjustment; the design difficulty of the inner duct blade is not increased; the structure layout can be optimized by arranging the engine in different axial positions in the outer duct according to the structure layout characteristics of the engine. The selection of various working modes is realized, and the requirement of the airplane on the high performance of the engine under the working conditions of subsonic cruising, transonic accelerating, supersonic cruising and the like can be met. In low-power states such as subsonic cruising of the airplane, the engine mode selection valve and the front/rear area-adjustable bypass ejector are both opened, the third outer bypass fan ring works under the high-rotating-speed working condition, the engine runs in a large bypass ratio state, and at the moment, the engine has high propulsion efficiency and low fuel consumption rate. Under the high-power working condition of climbing, accelerating and supersonic flying of the airplane, the engine is turned down by each VABI, so that more air enters the core machine, and the self-adaptive cycle engine operates in a thrust priority state.

Drawings

Fig. 1 is a schematic view of the overall structure of an adaptive variable cycle engine according to the present invention;

FIG. 2 is an enlarged front view of the general structure of the engine of FIG. 1;

FIG. 3 is an enlarged rear view of the general structure of the engine of FIG. 1;

Fig. 4 is a schematic structural diagram of embodiment 1 of the present invention;

FIG. 5 is a schematic view of the structure of the ring-shaped supporting frame, the fan blades and the electromagnetic device in example 1;

Fig. 6 is a schematic structural diagram of embodiment 2 of the present invention;

Fig. 7 is a schematic view of the structure of the ring-shaped supporting frame, the fan blades and the electromagnetic device in embodiment 2.

Detailed Description

The principles and features of the present invention are described below in conjunction with the following drawings, the examples given are only intended to illustrate the present invention and are not intended to limit the scope of the present invention.

example 1: as shown in fig. 1, 2, 3, 4 and 5, a self-driven ducted ring fan blade compression device is provided with three flow passages, namely an inner flow passage, a middle flow passage and an outer flow passage, which are arranged at the rear part of a traditional fan 12, wherein the inner flow passage is communicated with a core machine driven fan 13, the middle flow passage is communicated with an inlet of a second ducted passage 14, the outer flow passage is communicated with an inlet of a first ducted passage 8, an outlet of the second ducted passage 14 is communicated with the first ducted passage 8 through a front variable area ducted ejector 9, and a mode selection valve 6 is arranged at the inlet of the first ducted passage 8; the rear part of the core machine driving fan 13 is provided with two annular flow channels of the inner side and the outer side, the annular flow channel of the inner side is communicated with the high-pressure compressor 15, the annular flow channel of the middle part is communicated with the second outer duct 14, and the rear part of the high-pressure compressor 15 is sequentially communicated with a combustion chamber 10, a high-pressure turbine 16 and a low-pressure turbine 17; an inner flow passage and an outer flow passage are arranged at the outlet of the second outer duct 14, namely the tail part of the engine, the inner flow passage is communicated with the outlet of the inner duct through a rear variable-area duct ejector 11, and the outer flow passage is communicated with the outlet of the third outer duct 7. The third outer duct 7 is arranged at the outer side of the inner duct, a rotating component is arranged between the inlet guide vane 1 and the stator vane 5 in the third outer duct 7 of the turbofan engine, and the rotating component is arranged on a duct casing of the third outer duct 7 through a turntable bearing 20. The rotating component comprises an annular supporting frame 18, the annular supporting frame 18 is provided with an inner wall and an outer wall, the inner wall of the annular supporting frame 18 is provided with fan blades 4, and the outer wall of the annular supporting frame 18 is provided with an electromagnetic device 19; the annular supporting frame is arranged on an outer casing of the third outer duct 7 through a pair of turntable bearings 20, and a motor stator 3 is further arranged on the outer casing corresponding to the electromagnetic device; the magnetic poles of the electromagnetic devices and the motor stator are arranged in a circumferential array, and the polarities of the electromagnetic devices 19 and the motor stator 3 are opposite. The electromagnetic device 19 is a permanent magnet or a motor rotor coil. The bearing clearance of the turntable bearing 20 is smaller than the blade tip clearance, and the blade tip clearance refers to the inner casing clearance between the fan blade 4 and the third outer duct 7. The guide vanes 1 are matched with the rotating speed of the rotating component to adjust the installation angle, so that the fan blades of the rotating component obtain the optimal incoming flow attack angle.

The gap between the rotating component and the casing is provided with a labyrinth which is sealed to reduce air leakage and flow. The flow of the third outer duct 7 is changed within the range of 0-60% of the flow of the whole machine; when the flow of the third culvert is 0, the third culvert is in a closed state, and the airplane is in a supersonic cruise or maneuvering state at the moment, which is the same as the working state of the existing double-culvert engine; when the third bypass flow is 60% of the total flow, the engine is in a state of large bypass ratio, namely the aircraft is in a subsonic cruising state. In actual flight, the engine can meet the working performance requirement by adjusting the third bypass flow.

Example 2: as shown in fig. 6 and 7, the same as in example 1, except that: the rotating component comprises an annular supporting frame, the annular supporting frame is provided with an inner wall and an outer wall, the inner wall of the annular supporting frame is provided with an electromagnetic device 19, and the outer wall of the annular supporting frame is provided with fan blades; the annular support frame is arranged on an inner casing of the third outer duct 7 through a pair of turntable bearings 20, the inner casing corresponding to the electromagnetic device is further provided with the motor stator 3, magnetic poles of the electromagnetic device 19 and the motor stator 3 are arranged in an array mode along the circumferential direction, and the polarities of the electromagnetic device 19 and the motor stator 3 are opposite. The bearing clearance of the turntable bearing 20 is smaller than the blade tip clearance, and the blade tip clearance refers to the outer casing clearance between the fan blade 4 and the third outer duct 7.

the above description is only for the preferred embodiment of the present invention, and is not intended to limit the present invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included within the protection scope of the present invention.

Claims

1. The utility model provides a self-driven outer duct annular flabellum compressor arrangement, its characterized in that, includes the inner duct of engine, set up in the duct of the inner duct outside is third outer duct, is equipped with rotating member between the import guide vane in the third outer duct and stator blade, and rotating member passes through the bearing of rotary table and sets up on the duct casket of third outer duct.

2. The self-propelled ducted outer annular fan blade compression device of claim 1, wherein the rotating member comprises an annular support frame having inner and outer walls, the fan blades being disposed on the inner wall of the annular support frame, the electromagnetic device being disposed on the outer wall of the annular support frame; the annular support frame is arranged on an outer casing of the third outer duct through a pair of turntable bearings, and a motor stator is further arranged on the outer casing corresponding to the electromagnetic device; the magnetic poles of the electromagnetic device and the motor stator are arranged in a circumferential array mode, and the polarities of the electromagnetic device and the motor stator are opposite.

3. the self-propelled ducted outer annular fan blade compression device of claim 2 in which the bearing clearance of the turntable bearing is less than the tip clearance, the tip clearance being the inner cartridge clearance of the fan blade from the third ducted outer.

4. The self-propelled ducted outer annular fan blade compression device of claim 1, wherein the rotating member comprises an annular support frame having inner and outer walls, the inner wall of the annular support frame being provided with the electromagnetic device, the outer wall of the annular support frame being provided with the fan blades; the annular support frame is arranged on an inner casing of the third outer duct through a pair of turntable bearings, a motor stator is further arranged on the inner casing corresponding to the electromagnetic device, magnetic poles of the electromagnetic device and the motor stator are arranged in an array mode along the circumferential direction, and the polarity of the electromagnetic device is opposite to that of the motor stator.

5. The self-propelled ducted ring fan blade compressor assembly in accordance with claim 4 wherein the bearing clearance of the turntable bearing is less than the tip clearance, the tip clearance being the outer casing clearance of the fan blade from the third ducted ring fan.

6. The self-propelled ducted ring fan blade compressor assembly as defined in any one of claims 2-5 in which said electromagnetic means is a permanent magnet or a motor rotor coil.

7. The self-propelled ducted ring fan blade compressor assembly as defined in any one of claims 2-5 in which said rotary disc bearings are cylindrical roller bearings.

8. the self-propelled ducted ring fan blade compressor assembly as claimed in any one of claims 2-5 wherein the guide vanes are angularly adjustable in response to the rotational speed of the rotating member to optimize the angle of attack of the rotating member blades.

9. The self-propelled ducted outer annular fan blade compressor assembly as defined in any one of claims 1 to 4 wherein the gap between said rotating member and said casing is provided with a labyrinth, said labyrinth being sealed to reduce air leakage flow.