CN107882655B - Outer edge type electric propulsion jet engine system and design method - Google Patents
Outer edge type electric propulsion jet engine system and design method Download PDFInfo
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- CN107882655B CN107882655B CN201711144190.4A CN201711144190A CN107882655B CN 107882655 B CN107882655 B CN 107882655B CN 201711144190 A CN201711144190 A CN 201711144190A CN 107882655 B CN107882655 B CN 107882655B
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- 241000883990 Flabellum Species 0.000 description 3
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 241000234435 Lilium Species 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 230000002093 peripheral effect Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
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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
- F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
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- G06F30/15—Vehicle, aircraft or watercraft design
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- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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Abstract
The invention discloses an outer edge type electric propulsion jet engine system and a design method, and belongs to the technical field of engines. The outer edge type electric propulsion jet engine system comprises a duct unit, a motor unit and a fan blade unit, wherein the duct unit is of a hollow columnar structure, the motor unit comprises a motor rotor and a motor stator, the motor stator is fixedly arranged in the duct unit, the motor rotor is arranged corresponding to the inner wall of the motor stator, the fan blade unit is arranged in the inner wall of the motor rotor and is fixedly connected with the motor rotor, and the motor rotor rotates to drive the fan blade unit to rotate so as to generate force along the axial direction of the duct unit. The outer edge type electric propulsion jet engine system is suitable for electric propulsion, and has the advantages of simple structure, light weight of the whole structure and high pneumatic efficiency.
Description
Technical Field
The invention belongs to the technical field of engine design, and particularly relates to an outer edge type electric propulsion jet engine system and a design method.
Background
As current vehicles move toward clean energy, airplanes employing ducted electric propulsion have emerged and have a large potential market in some areas, the products that have emerged currently are european Airbus E-Fan, germany Lilium Jet, and with advances in electric storage technology and fuel cell technology, electric propulsion is even possible on large airliners or military machines.
Currently, electric Jet engines used on aircraft generally adopt a traditional petroleum energy engine design mode, for example, engines of European air passenger Airbus E-Fan and German Lilium Jet are characterized in that a turbine and a combustion chamber part of a traditional turbofan engine are replaced by motors, the simple modification design does not consider the difference between electric propulsion and fuel propulsion, an aeroengine system suitable for electric propulsion is not specifically designed, and the fuel engine has complex combustion units, turbine units and supercharging units, and the units can only be arranged near the central axis of the engine and are built in a rectifying shell and cannot be integrated into a bypass shell, so that the engine is complex in structure and low in aerodynamic efficiency.
Disclosure of Invention
The invention aims to solve the technical problem of providing an outer edge type electric propulsion jet engine system with simple structure and high pneumatic efficiency.
The invention also aims to provide a design method of the outer edge type electric propulsion jet engine system suitable for electric propulsion.
The invention solves the technical problems by adopting the following solutions: the utility model provides an outer fringe formula electric propulsion jet engine system, including duct unit, motor unit and flabellum unit, the duct unit is hollow columnar structure, the motor unit includes motor rotor and motor stator, the motor stator set firmly in the duct unit, motor rotor corresponds to motor stator's inner wall sets up, flabellum unit set up in motor rotor's inner wall, and with motor rotor fixed connection, motor rotor rotates and can drive flabellum unit rotates, and then produces and follow duct unit axis direction's power.
As a further improvement of the above technical solution, the fan blade unit includes a plurality of fan blades, and a plurality of fan blades are circumferentially arranged, the fan blades include a blade tip portion, a blade root portion, and a middle portion located between the blade tip portion and the blade root portion, the blade tip portion is fixedly arranged on the motor rotor, and the blade root portion is close to the central axis of the duct unit.
As a further improvement of the technical scheme, the widths of the blade root, the middle part and the blade tip are gradually increased along the radial direction of the motor rotor, so that the chord length of the blade tip is long, the bearing load is large, the distance between the blade root and the combined force acting point is short, and the chord length of the blade root is small, the bearing load is small, and the distance between the blade root and the combined force acting point is long.
As a further improvement of the technical scheme, the duct unit is internally provided with the annular groove, and the motor unit is embedded in the annular groove, so that the inner diameter of the motor rotor is equal to that of the duct unit, and the air resistance generated when the motor unit is independently arranged outside is reduced, and the occupied space of the motor unit is saved.
As a further improvement of the above technical solution, the trailing edge of the duct unit is provided with a serration portion, and the serration portion breaks the large-scale vortex structure of the airflow at the trailing edge of the duct unit to form a small-scale vortex structure so as to reduce noise.
The invention also provides a design method of the outer edge type electric propulsion jet engine system, which comprises the following steps: step one, determining engine size, design point thrust, maximum thrust and efficiency parameters by referring to an actual engine model; step two, determining the design point output power, the working rotating speed and the maximum output power of the motor unit according to the design point thrust and the efficiency; step three, designing a duct unit and a fan blade unit according to the determined parameters of the motor unit.
The beneficial effects of the invention are as follows:
according to the outer edge type electric propulsion jet engine system, the fan blade units are fixedly arranged on the inner wall of the motor rotor, and the motor rotor is fixedly arranged on the inner wall of the duct unit;
the duct unit is internally provided with a ring groove, and the motor unit is embedded in the ring groove, so that the gap between the fan blade unit and the duct unit is completely eliminated, and the pneumatic efficiency is further improved.
The invention provides a design method of an outer edge type electric propulsion jet engine system, which provides the design steps of the outer edge type electric propulsion jet engine system.
Drawings
FIG. 1 is a schematic view of the overall structure of an outboard-type electric propulsion jet engine system of the present invention;
FIG. 2 is a partially cut-away, isometric view of an outer rim electric propulsion jet engine system of the present invention;
FIG. 3 is a schematic illustration of a split construction of the peripheral-edge electric propulsion jet engine system of the present invention;
FIG. 4 is a partial block diagram of the present fan blade unit;
fig. 5 is a flow chart of a method of designing an outer rim electric propulsion jet engine system of the present invention.
Detailed Description
The conception, specific structure, and technical effects produced by the present invention will be clearly and completely described below with reference to the embodiments and the drawings to fully understand the objects, features, and effects of the present invention. It is apparent that the described embodiments are only some embodiments of the present invention, but not all embodiments, and that other embodiments obtained by those skilled in the art without inventive effort are within the scope of the present invention based on the embodiments of the present invention. In addition, all the coupling/connection relationships referred to in the patent are not direct connection of the single-finger members, but rather, it means that a better coupling structure can be formed by adding or subtracting coupling aids depending on the specific implementation. The technical features of the invention can be interactively combined on the premise of no contradiction and conflict.
Referring to fig. 1 to 3, the present invention aims to provide an outer edge type electric propulsion jet engine system adapted to electric propulsion, which comprises a duct unit 1, a motor unit 2 and a fan blade unit 3, wherein the duct unit 1 is in a hollow column structure, the motor unit 2 is fixedly arranged on the inner wall of the duct unit 1, the fan blade unit 3 is fixedly arranged on the inner wall of the motor unit 2, and when in operation, the motor unit 2 moves to drive the fan blade unit 3 to rotate, so as to generate thrust required by an aircraft when in advance or resistance required by deceleration on a runway after landing.
In this embodiment, the motor unit 2 includes a motor rotor 20 and a motor stator 21, the motor stator 21 is fixedly disposed on the inner wall of the duct unit 1, the motor rotor 20 is disposed on the inner wall of the motor stator 21, the motor rotor 20 is electrically connected with the motor stator 21, and during operation, the motor stator 21 cooperates with the motor rotor 20 to rotate the motor rotor 20, so that the motor rotor 20 drives the fan blade unit 3 to rotate.
The motor unit 2 further comprises a motor front edge cover 22, a motor rear edge cover 23 and a motor outer edge structural member 24, wherein the motor front edge cover 22 and the motor rear edge cover 23 are respectively covered on two sides of the motor rotor 20 and the motor stator 21 along the axial direction of the duct unit 1, the motor outer edge structural member 24 is fixedly arranged between the duct unit 1 and the motor stator 21, two sides of the motor outer edge structural member 24 are respectively fixedly connected with the inner wall of the duct unit 1 and the motor stator 21, and the motor front edge cover 22, the motor rear edge cover 23 and the motor outer edge structural member 24 are used as force transmission components for transmitting force and moment generated by an engine to an airplane.
Preferably, the inner wall of the duct unit 1 is provided with a ring groove 10, and the motor outer edge structural member 24, the motor rotor 20 and the motor stator 21 are all embedded in the ring groove 10, so that the inner wall surface of the motor rotor 20 is level with the inner wall surface of the duct unit 1.
In this embodiment, as shown in fig. 4, the fan blade unit 3 includes a plurality of fan blades, the plurality of fan blades are circularly arranged along the inner wall of the motor rotor 20, one end of each fan blade is fixedly arranged on the inner wall of the motor rotor 20, and the other end of each fan blade is arranged at the center of the motor rotor 20.
Along the radial direction of the motor rotor 20, the blade tip 30, the middle part 31 and the blade root 32 are sequentially arranged on the blade, the blade root 32 is close to the center of the motor rotor 20, the widths of the blade root 32, the middle part 31 and the blade tip 30 are sequentially increased along the radial direction of the motor rotor 20, so that the integral resultant force acting force of the blade is close to the position of the blade tip 30, when the blade unit 3 rotates along with the rotation of the motor rotor 20, the chord length of the blade tip 30 of the blade is large, the load born by the blade tip 30 is large, the distance between the blade tip 30 and the combined force acting point of the blade is short, therefore, the moment of the blade tip 30 is obviously reduced, and similarly, the chord length of the blade root 32 of the blade is small, the load born by the blade root 32 and the combined force acting point of the blade are long, therefore, the moment at the blade root 32 is effectively balanced, the integral force acting on the blade is very uniform, and the structural efficiency of the blade is greatly increased.
Preferably, the middle part 31 is inclined to a plane formed by connecting the tip part 30 with the center of the motor rotor 20, and when the motor rotor 20 rotates, the tip part 30 rotates along with the motor rotor 20, so that the blade root part 32, the middle part 31 and the blade tip part 30 rotate together to generate thrust required by the aircraft when advancing or resistance required by the aircraft when decelerating on a runway after landing.
In the outer edge type electric propulsion jet engine system, the duct unit 1 is matched with the motor unit 2 and the fan blade unit 3, in addition, the fan blade unit 3 is fixedly arranged on the inner wall of the motor rotor 20, and the motor rotor 20 is embedded in the annular groove 10, so that the inner wall surface of the motor rotor 20 and the inner wall surface of the duct unit 1 are positioned on the same circular surface, the blade tip part 30 of the fan blade is fixedly arranged on the inner wall of the motor rotor 20, the momentum loss of the blade tip part is greatly reduced, and meanwhile, the motor unit 2 is embedded in the annular groove 10 of the duct unit 1, so that the occupied space is effectively saved, and the outer edge type electric propulsion jet engine system can effectively improve the propulsion efficiency.
Furthermore, in the outer edge type electric propulsion jet engine system, the sawtooth part 11 is arranged at one end of the duct unit 1, the sawtooth part 11 has the function of flow control, the airflow passing through the end part of the duct unit 1 is mainly of a large-scale vortex structure, and after the airflow passes through the sawtooth part 11, the sawtooth part 11 can break the large-scale vortex structure and further is converted into a small-scale vortex structure, so that the mutual interference noise between vortex and the inner wall of the duct unit 1 is reduced, and the aim of reducing noise is fulfilled.
In the present embodiment, the peripheral electric propulsion jet engine system is preferably applied to the space engine, but the peripheral electric propulsion jet engine system in the present embodiment can be simply adjusted in size, and it is also applicable to water surfaces such as ships, submarines, underwater robots, and underwater vehicles, and therefore, these applications should also be within the scope of the present invention.
The invention also provides a design method of the outer edge type electric propulsion jet engine system, as shown in fig. 5, comprising the following steps:
s100, determining the size, design point thrust, maximum thrust and efficiency of an engine according to the type of engine application;
s110, determining design point output power, working rotation speed and maximum output power of the motor unit according to the obtained design point thrust and efficiency;
s120, jointly designing a duct unit, a motor unit and a fan blade unit according to the parameters of the obtained motor unit.
While the preferred embodiment of the present invention has been described in detail, the present invention is not limited to the embodiment, and various equivalent modifications and substitutions can be made by those skilled in the art without departing from the spirit of the present invention, and these equivalent modifications and substitutions are intended to be included in the scope of the present invention as defined in the appended claims.
Claims (1)
1. A method of designing an external-edge electric propulsion jet engine system, comprising the steps of:
step one, determining engine size, design point thrust, maximum thrust and efficiency parameters by referring to an actual engine model;
step two, determining the design point output power, the working rotating speed and the maximum output power of the motor unit according to the design point thrust and the efficiency;
step three, designing a duct unit and a fan blade unit according to the determined parameters of the motor unit;
the outer edge type electric propulsion jet engine system comprises a duct unit, a motor unit and a fan blade unit, wherein the duct unit is of a hollow columnar structure, the motor unit comprises a motor rotor and a motor stator, the motor stator is fixedly arranged in the duct unit, the motor rotor is arranged corresponding to the inner wall of the motor stator, the fan blade unit is arranged in the inner wall of the motor rotor and is fixedly connected with the motor rotor, and the motor rotor rotates to drive the fan blade unit to rotate so as to generate force along the axial direction of the duct unit;
the fan blade unit comprises a plurality of fan blades which are circumferentially distributed, the fan blades comprise blade tips, blade roots and middle parts between the blade tips and the blade roots, the blade tips are fixedly arranged on the motor rotor, and the blade roots are arranged close to the central axis of the duct unit;
along the radial direction of the motor rotor, the widths of the blade root, the middle part and the blade tip are gradually increased, so that the chord length of the blade tip is long, the bearing load is large, the distance between the blade root and the action point of the combined force is short, and the chord length of the blade root is small, the bearing load is small, and the distance between the blade root and the action point of the combined force is long;
the inside of the duct unit is provided with a ring groove, and the motor unit is embedded in the ring groove, so that the inside diameter of the motor rotor is equal to the inside diameter of the duct unit, thereby reducing the air resistance generated by the motor unit and saving the occupied space of the motor unit;
the tail edge of the duct unit is provided with a sawtooth part, and the sawtooth part breaks the large-scale vortex structure of the airflow at the tail edge of the duct unit to form a small-scale vortex structure so as to reduce noise.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711144190.4A CN107882655B (en) | 2017-11-17 | 2017-11-17 | Outer edge type electric propulsion jet engine system and design method |
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| CN201711144190.4A CN107882655B (en) | 2017-11-17 | 2017-11-17 | Outer edge type electric propulsion jet engine system and design method |
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| CN107882655A CN107882655A (en) | 2018-04-06 |
| CN107882655B true CN107882655B (en) | 2023-06-20 |
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| GB202110536D0 (en) * | 2021-07-22 | 2021-09-08 | Rolls Royce Plc | Aircraft propulsion system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101725431A (en) * | 2008-10-31 | 2010-06-09 | 南昌航空大学 | Electric fuel oil jet propeller |
| CN103629011A (en) * | 2013-11-21 | 2014-03-12 | 孙朝宽 | Engine |
| US9143023B1 (en) * | 2010-05-17 | 2015-09-22 | Richard Christopher Uskert | Electromagnetic propulsive motor |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9963981B2 (en) * | 2015-06-10 | 2018-05-08 | General Electric Company | Pitch change mechanism for shrouded fan with low fan pressure ratio |
| FR3087824B1 (en) * | 2018-10-26 | 2021-10-15 | Safran Aircraft Engines | AIRCRAFT BLOWER ELECTRIC MODULE CONTAINING IMPROVED MOUNTING BLADES |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101725431A (en) * | 2008-10-31 | 2010-06-09 | 南昌航空大学 | Electric fuel oil jet propeller |
| US9143023B1 (en) * | 2010-05-17 | 2015-09-22 | Richard Christopher Uskert | Electromagnetic propulsive motor |
| CN103629011A (en) * | 2013-11-21 | 2014-03-12 | 孙朝宽 | Engine |
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