CN209800119U - Self-driven outer duct contra-rotating annular fan blade compression device - Google Patents
Self-driven outer duct contra-rotating annular fan blade compression device Download PDFInfo
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- CN209800119U CN209800119U CN201920671104.3U CN201920671104U CN209800119U CN 209800119 U CN209800119 U CN 209800119U CN 201920671104 U CN201920671104 U CN 201920671104U CN 209800119 U CN209800119 U CN 209800119U
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Abstract
The utility model relates to a device that turbofan engine bypass ratio continuous control especially relates to outer duct contra-rotating fan ring compressor arrangement of turbofan engine. The utility model provides a self-driven outer duct is to revolving annular flabellum compressor arrangement, includes the inner duct of engine, set up in the duct of the inner duct outside is third outer duct, is equipped with two rows of revolving rotary members that revolve to between the import guide vane in the third outer duct and stator blade, and two rows of revolving rotary members that revolve to be the upper reaches rotary member and low reaches rotary member respectively, and upper reaches rotary member and low reaches rotary member set up on the duct machine casket of third outer duct through the carousel bearing respectively. The utility model discloses a two rows of contra-rotating fan ring structures make the outer duct of third press than with flow under the same condition, effectively reduce rotor structure's rotational speed and reduce the outer duct size of third to reduce noise, power consumption and the design degree of difficulty, enlarge turbofan engine's working range greatly, give play to this type engine's the change cycle advantage more greatly.
Description
Technical Field
The utility model relates to a device that turbofan engine bypass ratio continuous control especially relates to outer duct contra-rotating 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 configured 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 to revolving 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 to revolving ring shape 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 is to revolving annular flabellum compressor arrangement, includes the inner duct of engine, set up in the duct of the inner duct outside is third outer duct, is equipped with two rows of revolving rotary members that revolve to between the import guide vane in the third outer duct and stator blade, and two rows of revolving rotary members that revolve to be the upper reaches rotary member and low reaches rotary member respectively, and upper reaches rotary member and low reaches rotary member set up on the duct machine casket of third outer duct through the carousel bearing respectively.
Furthermore, the two rows of counter-rotating components comprise upstream fan blades and downstream fan blades, the upstream fan blades and the downstream fan blades are respectively arranged on the inner walls of the two annular support frames, each annular support frame is provided with an inner wall and an outer wall, and the outer wall of each 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. The rotating component formed by the upstream fan blades, the annular supporting frame and the electromagnetic device is an upstream rotating component, and the rotating component formed by the downstream fan blades, the annular supporting frame and the electromagnetic device is a downstream rotating component.
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 upstream fan blade and the downstream fan blade and the inner casing of the third outer duct.
Furthermore, the two rows of counter-rotating components comprise upstream fan blades and downstream fan blades, the upstream fan blades and the downstream fan blades are respectively arranged on the outer walls of the two annular support frames, each annular support frame is provided with an inner wall and an outer wall, and an electromagnetic device is arranged on the inner wall of each annular support frame; 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. The rotating component formed by the upstream fan blades, the annular supporting frame and the electromagnetic device is an upstream rotating component, and the rotating component formed by the downstream fan blades, the annular supporting frame and the electromagnetic device is a downstream rotating component.
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 upstream fan blade and the downstream fan blade and the outer box 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 speeds of the two rows of the contra-rotating members to carry out installation angle adjustment, so that the upstream fan blades of the upstream rotating members obtain the optimal incoming flow attack angle.
Furthermore, a gap between the counter-rotating component and the casing is provided with a comb tooth, and the comb tooth 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: the utility model discloses a two rows of contra-rotating fan ring structures can make the outer duct of third press than and flow under the same condition, effectively reduce rotor structure's rotational speed and reduce the outer duct size of third to reduce noise, power consumption and the design degree of difficulty. The pressure ratio and the flow of the third outer duct can be improved by adopting the two rows of counter-rotating fan ring structures at the same rotating speed, the airflow angle at the outlet of the downstream counter-rotating component is closer to the axial direction, the circumferential speed is effectively reduced, and even an outlet guide vane can be omitted.
Different with traditional outer duct Flade apex fan, the utility model discloses a rotor and the design of contra-rotating fan ring flabellum integration, the outer duct contra-rotating fan ring compression system of taking 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, it is high to be applicable to the performance requirement, the working range is wide, many ducts 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 change circulation advantage more.
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 engine can be configured at different axial positions in the outer duct according to the structural layout characteristics of the engine, so that structural layout optimization is realized. Meanwhile, multiple working modes are selected, and the requirement of the airplane on high performance of the engine under multiple working conditions such as subsonic cruise, transonic acceleration and supersonic cruise 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 works on the rotating fan ring 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 annular contra-rotating 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 driving fan 13, the middle flow passage is communicated with the inlet of a second ducted 14, the outer flow passage is communicated with the inlet of a first ducted 8, the outlet of the second ducted 14 is communicated with the first ducted 8 through a front variable area ducted ejector 9, and the inlet of the first ducted 8 is also provided with a mode selection valve 6; 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, two rows of counter-rotating components are arranged between the inlet guide vanes 1 and the stator vanes 5 in the third outer duct 7, the two rows of counter-rotating components are respectively an upstream rotating component and a downstream rotating component, and the upstream rotating component and the downstream rotating component are respectively arranged on the duct casing of the third outer duct 7 through turntable bearings 20.
The two rows of counter-rotating components comprise upstream fan blades 4 and downstream fan blades 21, the upstream fan blades 4 and the downstream fan blades 21 are respectively arranged on the inner walls of the two annular support frames 18, the annular support frames 18 are provided with inner walls and outer walls, and the outer walls of the annular support frames 18 are provided with electromagnetic devices 19; the annular supporting frame is arranged on an outer casing of the third outer duct 7 through a pair of turntable bearings, and a motor stator 3 is further arranged on the outer casing corresponding to the electromagnetic device; the magnetic poles of the electromagnetic device 19 and the motor stator 3 are arranged in a circumferential array, and the polarities of the electromagnetic device 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 clearance between the upstream fan blade 4 and the downstream fan blade 21 and the inner casing of the third outer duct 7. The guide vanes 1 are matched with two rows of rotating speed of the contra-rotating component to carry out installation angle adjustment, so that the upstream fan blades 4 of the upstream rotating component obtain the optimal incoming flow attack angle.
The gap between the contra-rotating component and the casing is provided with a comb tooth, and the comb tooth 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 two rows of counter-rotating components comprise upstream fan blades 4 and downstream fan blades 21, the upstream fan blades 4 and the downstream fan blades 21 are respectively arranged on the outer walls of the two annular support frames 18, the annular support frames 18 are provided with inner walls and outer walls, and the inner walls of the annular support frames 18 are provided with electromagnetic devices 19; the annular support frame 18 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 polarity of the electromagnetic device 19 is opposite to that of the motor stator 3. The bearing clearance of the turntable bearing 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 (9)
1. The self-driven outer duct contra-rotating annular fan blade compression device is characterized by comprising an inner duct of an engine, wherein the duct arranged outside the inner duct is a third outer duct, two rows of contra-rotating members are arranged between an inlet guide vane and a stator vane in the third outer duct, the two rows of contra-rotating members are respectively an upstream rotating member and a downstream rotating member, and the upstream rotating member and the downstream rotating member are respectively arranged on a duct casing of the third outer duct through turntable bearings.
2. The self-propelled ducted externally counter-rotating annular fan blade compressor assembly as defined in claim 1 wherein said two rows of counter-rotating members comprise upstream fan blades and downstream fan blades, said upstream fan blades and said downstream fan blades being disposed on the inner walls of two annular supports, said annular supports having inner and outer walls, and electromagnetic means disposed on the outer walls of said annular supports; 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 counter-rotating annular fan blade compression device of claim 2, wherein the bearing clearance of the turntable bearing is smaller than the blade tip clearance, which is the clearance between the upstream and downstream fan blades and the inner casing of the third ducted outer blade.
4. The self-propelled ducted externally counter-rotating annular fan blade compressor assembly as claimed in claim 1, wherein said two rows of counter-rotating members comprise upstream fan blades and downstream fan blades, said upstream fan blades and said downstream fan blades being disposed on outer walls of two annular supports, respectively, said annular supports having inner and outer walls, and electromagnetic means being disposed on inner walls of said annular supports; 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 counter-rotating annular fan blade compression device of claim 4, wherein the bearing clearance of the turntable bearing is smaller than the blade tip clearance, which is the outer casing clearance of the upstream and downstream fan blades and the third ducted outer casing.
6. The self-propelled ducted counter-rotating annular fan blade compression device as in any one of claims 2 to 5, wherein said electromagnetic means are permanent magnets or coils of an electric motor rotor.
7. The self-propelled ducted counter-rotating annular fan blade compressor assembly as claimed in any one of claims 2 to 5, wherein said rotary disc bearings are cylindrical roller bearings.
8. The self-propelled ducted contra-rotating annular fan blade compressor assembly according to any of claims 2 to 5, wherein the guide vanes are angularly adjustable in response to the rotational speed of the two counter-rotating members to provide an optimum angle of attack for the upstream blades of the upstream rotating members.
9. the self-driven bypass contra-rotating annular fan blade compression device as claimed in any one of claims 1 to 4, wherein a gap between the contra-rotating member and the casing is provided with a labyrinth which is sealed to reduce air leakage flow.
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| CN201920671104.3U CN209800119U (en) | 2019-05-12 | 2019-05-12 | Self-driven outer duct contra-rotating annular fan blade compression device |
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| CN201920671104.3U CN209800119U (en) | 2019-05-12 | 2019-05-12 | Self-driven outer duct contra-rotating annular fan blade compression device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109973244A (en) * | 2019-05-12 | 2019-07-05 | 西北工业大学 | From driving by-pass air duct to change shape flabellum compression set |
| CN112627990A (en) * | 2020-12-23 | 2021-04-09 | 华中科技大学 | Flow passage adjusting structure of direct-drive combined engine and control method thereof |
| CN114562385A (en) * | 2022-03-21 | 2022-05-31 | 西北工业大学 | Empty water integration spouts matter engine |
-
2019
- 2019-05-12 CN CN201920671104.3U patent/CN209800119U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109973244A (en) * | 2019-05-12 | 2019-07-05 | 西北工业大学 | From driving by-pass air duct to change shape flabellum compression set |
| CN112627990A (en) * | 2020-12-23 | 2021-04-09 | 华中科技大学 | Flow passage adjusting structure of direct-drive combined engine and control method thereof |
| CN112627990B (en) * | 2020-12-23 | 2021-11-19 | 华中科技大学 | Flow passage adjusting structure of direct-drive combined engine and control method thereof |
| CN114562385A (en) * | 2022-03-21 | 2022-05-31 | 西北工业大学 | Empty water integration spouts matter engine |
| CN114562385B (en) * | 2022-03-21 | 2023-10-31 | 西北工业大学 | Air-water integrated spray engine |
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