CN110005544B - Self-driven outer duct annular fan blade compression device - Google Patents
Self-driven outer duct annular fan blade compression device Download PDFInfo
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- CN110005544B CN110005544B CN201910391381.3A CN201910391381A CN110005544B CN 110005544 B CN110005544 B CN 110005544B CN 201910391381 A CN201910391381 A CN 201910391381A CN 110005544 B CN110005544 B CN 110005544B
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- duct
- outer duct
- fan blade
- engine
- support frame
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a device for continuously adjusting the bypass ratio of a turbofan engine, in particular to an outer bypass fan ring compression device of the turbofan engine. The engine comprises an inner duct of the engine, wherein the duct arranged on the outer side of the inner duct is a third outer duct, a rotating member is arranged between an inlet guide vane and a stator vane in the third outer duct, and the rotating member is arranged on a duct casing of the third outer duct through a turntable bearing. The invention realizes the driving of an independent motor, so that the control mechanism is independent, and has larger adjustment freedom degree; the design difficulty of the inner channel blade is not increased; the engine can be arranged at different axial positions in the outer duct according to the structural layout characteristics of the engine, so that structural layout optimization is realized.
Description
Technical Field
The invention relates to a device for continuously adjusting the bypass ratio of a turbofan engine, in particular to an outer bypass fan ring compression device of the 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 the cycle parameters such as the supercharging ratio, the flow and the bypass ratio by changing the geometric shapes, the sizes and the positions of certain parts, so that the engine has optimal performance under various working conditions, thereby having good adaptability to the flying height, the Mach number and the like of an airplane.
U.S. patent No. 4043121 to Thomas et al, entitled "dual rotor variable cycle engine", discloses an engine with a tip fan (Flade) that achieves engine cycle variability by controlling air flow by adjusting adjustable vanes in the outer duct of the tip fan.
In U.S. patent No. 005809772a, a dual-culvert variable cycle engine with a Core Drive Fan (CDFS) configuration is disclosed. The main difference of the structure of the engine is that the fan is divided into a front section/a rear section, the front section fan is driven by a low-pressure turbine shaft, the rear Duan Fengshan is connected to a high-pressure shaft, the rear section fan is a core machine driven fan, and the front section fan and the rear section fan are respectively provided with an outer duct. The engine has an optimal bypass ratio over a wide operating range by means of a mode selection valve in the front fan rear bypass and a front area adjustable injector (VABI) adjustment of the CDFS rear bypass.
In US20100180572A1, a three-culvert turbofan engine with CDFS and Flade configurations is disclosed, and a tip fan in the third culvert is directly driven by a culvert fan blade and is disposed at the front end of the engine. Chinese patent CN1619129a discloses an engine with a tail Flade tip fan, wherein the Flade tip fan is connected to a low pressure turbine blade or a free turbine blade and is disposed at the rear end of the engine. This type of three-way turbofan engine is also known as an adaptive cycle engine, or intelligent engine. The flow path not only can enlarge the bypass ratio adjusting range of the engine and optimize the flow matching of the air inlet channel/the engine, but also can be used for the functions of thermal management, stealth and the like of the high-energy weapon.
Because the outer duct Flade blade tip fan and the inner duct blade adopt a direct connection mode, a plurality of disadvantages are brought to the design of the engine: firstly, the strength of the blade is difficult to design, and the tangential speed selection 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
The invention aims to avoid the defects of the prior art and provide an electromagnetic driven outer duct annular fan blade compression system which adopts an integrated design of a motor rotor and a fan ring rotor blade, has compact structure, independent control mechanism and large adjustment freedom, and is mechanically decoupled with an inner duct system.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows: the utility model provides a self-driven outer duct annular flabellum compression device, includes the interior duct of engine, set up in the duct in the interior duct outside is the third outer duct, is equipped with rotary member between import guide vane and the stator blade in the third outer duct, and rotary member passes through the turntable bearing setting on the duct receiver of third outer duct.
Further, the rotating member comprises an annular supporting frame, the annular supporting frame is provided with an inner wall and an outer wall, fan blades are arranged on the inner wall of the annular supporting frame, and an electromagnetic device is arranged on the outer wall of the annular supporting 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 an array manner along the circumferential direction, 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.
Further, the rotating member comprises an annular supporting frame, the annular supporting frame is provided with an inner wall and an outer wall, an electromagnetic device is arranged on the inner wall of the annular supporting frame, and fan blades are arranged on the outer wall of the annular supporting frame; the annular support frame is arranged on the inner casing of the third outer duct through a pair of turntable bearings, motor stators are further arranged on the inner casing corresponding to the electromagnetic device, magnetic poles of the electromagnetic device and the motor stators are arranged in an array mode along the circumferential direction, and the polarities of the electromagnetic device and the motor stators 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 outer casing of the third outer duct.
Further, the electromagnetic device is a permanent magnet or a motor rotor coil.
Further, the turntable bearing is a cylindrical roller bearing.
Furthermore, the guide vane is matched with the rotating speed of the rotating member to adjust the installation angle, so that the fan blade of the rotating member obtains the optimal incoming flow attack angle.
Furthermore, the gap between the rotating member and the casing is provided with a comb teeth, and the comb teeth seal tightly 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 third culvert flow is 0, the third culvert is in a closed state, and the aircraft is in a supersonic cruising or power-driven state; when the third culvert flow is 60% of the whole machine flow, the engine is in a state of large culvert 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 culvert flow.
The beneficial effects of the invention are as follows: different from the traditional external duct Flade blade tip fan, the invention adopts the integrated design of the motor rotor and the fan ring fan blade, forms an external duct fan ring compression system with an independent drive, has the characteristics of compact structure, independent control mechanism, mechanical decoupling with an internal duct system and the like, can realize the large-range continuous adjustment of the engine duct ratio, effectively optimizes the matching of the engine and an air inlet duct, reduces or even eliminates overflow resistance, greatly expands the working range of the turbofan engine, is suitable for multi-duct gas turbofan engines, variable cycle gas turbofan engines, self-adaptive cycle engines and intelligent engines with high performance requirements and wide working range and has the variable cycle advantages of the engine.
Meanwhile, the invention adopts a third outer culvert fan ring structure of which the core machine drives a fan (CDFS) +is independently driven, thereby realizing the independent motor driving, and the control mechanism is independent and has larger adjustment freedom degree; the design difficulty of the inner channel blade is not increased; the engine can be arranged at different axial positions in the outer duct according to the structural layout characteristics of the engine, so that structural layout optimization is realized. The method also realizes the selection of multiple working modes, and can meet the high-performance requirements of the aircraft on the engine under multiple working conditions such as subsonic cruise, transonic acceleration, supersonic cruise and the like. In low power states such as subsonic cruising of an aircraft, an engine mode selection valve and a front/rear adjustable area duct ejector are opened, a third outer duct fan ring works under a high-rotation-speed working condition, the engine operates in a large duct ratio state, and at the moment, the engine propulsion efficiency is high and the fuel consumption rate is low. Under the high-power working conditions of climbing, accelerating and supersonic flight of the aircraft, the engines turn down each VABI, so that more air is caused to enter the core engine, and the self-adaptive cycle engine operates in a thrust priority state.
Drawings
FIG. 1 is a schematic diagram of the overall architecture of an adaptive variable cycle engine incorporating the present invention;
FIG. 2 is an enlarged front structural schematic view of the general structure of the engine of FIG. 1;
FIG. 3 is an enlarged rear structural schematic view of the general structure of the engine of FIG. 1;
FIG. 4 is a schematic structural view of embodiment 1 of the present invention;
FIG. 5 is a schematic view showing the constitution of the annular supporting frame, the fan blades and the electromagnetic device in the embodiment 1;
FIG. 6 is a schematic structural view of embodiment 2 of the present invention;
fig. 7 is a schematic view showing the constitution of the annular supporting frame, the fan blade and the electromagnetic device in embodiment 2.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
Example 1: as shown in fig. 1, 2,3, 4 and 5, a self-driven outer duct annular fan blade compression device is provided with an inner side, a middle and an outer side at the rear part of a traditional fan 12, wherein the inner side runner is communicated with a core machine driving fan 13, the middle runner is communicated with an inlet of a second outer duct 14, the outer side runner is communicated with an inlet of a first outer duct 8, an outlet of the second outer duct 14 is communicated with the first outer duct 8 through a front variable area duct ejector 9, and a mode selection valve 6 is further arranged at the inlet of the first outer duct 8; the rear part of the core machine driving fan 13 is provided with an inner annular flow passage and an outer annular flow passage, the inner annular flow passage is communicated with the high-pressure air compressor 15, the middle annular flow passage is communicated with the second outer duct 14, and the rear part of the high-pressure air compressor 15 is sequentially communicated with a combustion chamber 10, a high-pressure turbine 16 and a low-pressure turbine 17; at the outlet of the second outer duct 14, i.e. the tail of the engine, there are two inner and outer flow channels, the inner flow channel is connected with the outlet of the inner duct through the rear variable area duct injector 11, and the outer flow channel is connected with the outlet of the third outer duct 7. The third outer duct 7 is arranged outside the inner duct, a rotating member 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 member is arranged on a duct casing of the third outer duct 7 through a turntable bearing 20. The rotating member 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 device and the motor stator are arranged in an array along the circumferential direction, 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, which refers to the inner casing clearance between the fan blade 4 and the third outer duct 7. The guide vane 1 is matched with the rotating speed of the rotating component to adjust the installation angle, so that the fan blade of the rotating component obtains the optimal incoming flow attack angle.
The gap between the rotating member and the casing is provided with a comb teeth, and the comb teeth are tightly sealed to reduce air leakage 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 third culvert flow is 0, the third culvert is in a closed state, and the aircraft is in a supersonic cruising or power-driven state at the moment, so that the aircraft is in a working state similar to the existing double-culvert engine; when the third culvert flow is 60% of the whole machine flow, the engine is in a state of large culvert 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 culvert flow.
Example 2: as shown in fig. 6 and 7, the same as in example 1 is different in that: the rotating component comprises an annular supporting frame, the annular supporting frame is provided with an inner wall and an outer wall, an electromagnetic device 19 is arranged on the inner wall of the annular supporting frame, and fan blades are arranged on the outer wall of the annular supporting frame; the annular support frame is arranged on the inner casing of the third outer duct 7 through a pair of turntable bearings 20, the motor stator 3 is further arranged on the inner casing corresponding to the electromagnetic device, magnetic poles of the electromagnetic device 19 and the motor stator 3 are arrayed 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 foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910391381.3A CN110005544B (en) | 2019-05-12 | 2019-05-12 | Self-driven outer duct annular fan blade compression device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910391381.3A CN110005544B (en) | 2019-05-12 | 2019-05-12 | Self-driven outer duct annular fan blade compression device |
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| CN110005544A CN110005544A (en) | 2019-07-12 |
| CN110005544B true CN110005544B (en) | 2024-09-10 |
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| CN201910391381.3A Active CN110005544B (en) | 2019-05-12 | 2019-05-12 | Self-driven outer duct annular fan blade compression device |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113236441B (en) * | 2021-04-28 | 2022-06-28 | 中国科学院工程热物理研究所 | A turboshaft fan dual-mode engine and its adjustment method |
| CN113738530B (en) * | 2021-10-15 | 2022-06-17 | 清华大学 | Multi-duct aero-engine casing structure with blade tip fan |
| CN114954960A (en) * | 2022-04-11 | 2022-08-30 | 西北工业大学 | An electric double ducted engine |
| CN119712347B (en) * | 2024-12-30 | 2025-10-28 | 厦门大学 | An external electric drive variable cycle turbofan engine |
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| CN108891595A (en) * | 2018-07-11 | 2018-11-27 | 中国航空发动机研究院 | Across the medium flight device power device sealed using medium sensing device and duct |
| CN209800118U (en) * | 2019-05-12 | 2019-12-17 | 西北工业大学 | Self-driven outer duct annular fan blade compression device |
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| GB1197711A (en) * | 1964-12-02 | 1970-07-08 | Gen Electric | Improvements in Turbofan Type Engine. |
| GB1330904A (en) * | 1971-04-19 | 1973-09-19 | Secr Defence | Gas turbine jet propulsion engines |
| US7246484B2 (en) * | 2003-08-25 | 2007-07-24 | General Electric Company | FLADE gas turbine engine with counter-rotatable fans |
| FR2866073B1 (en) * | 2004-02-11 | 2006-07-28 | Snecma Moteurs | TURBOREACTOR HAVING TWO SOLIDARITY CONTRAROTATIVE BLOWERS OF A CONTRAROTATIVE LOW-PRESSURE COMPRESSOR |
| RU2358138C1 (en) * | 2007-12-18 | 2009-06-10 | Николай Борисович Болотин | Helical fan aviation gas-turbine engine |
| US8984891B2 (en) * | 2010-12-30 | 2015-03-24 | General Electric Company | Flade discharge in 2-D exhaust nozzle |
| CN104481696B (en) * | 2014-12-05 | 2016-04-13 | 南昌航空大学 | The empty dual-purpose motor of a kind of contrarotating purchasing ore water |
| FR3033363B1 (en) * | 2015-03-04 | 2017-04-07 | Andre Chaneac | TURBOJET ENGINEERING WHETHER A BLOWER IS A GENERATOR AND ITS MOUNTING ON A VERTICAL TAKE-OFF AND VERTICAL AIRCRAFT AIRCRAFT |
| CN106742075B (en) * | 2017-01-06 | 2023-03-03 | 西安觉天动力科技有限责任公司 | Distributed propulsion system |
| CN107313876B (en) * | 2017-07-04 | 2019-06-04 | 南京航空航天大学 | A maglev extension fan for aviation turbofan engine |
| DE102017119070B4 (en) * | 2017-08-21 | 2021-03-11 | Finn Schöning | Jet engine |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108891595A (en) * | 2018-07-11 | 2018-11-27 | 中国航空发动机研究院 | Across the medium flight device power device sealed using medium sensing device and duct |
| CN209800118U (en) * | 2019-05-12 | 2019-12-17 | 西北工业大学 | Self-driven outer duct annular fan blade compression device |
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