CN107882655A - A kind of outer rim formula electric propulsion jet engine system and design method - Google Patents
A kind of outer rim formula electric propulsion jet engine system and design method Download PDFInfo
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- CN107882655A CN107882655A CN201711144190.4A CN201711144190A CN107882655A CN 107882655 A CN107882655 A CN 107882655A CN 201711144190 A CN201711144190 A CN 201711144190A CN 107882655 A CN107882655 A CN 107882655A
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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]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- 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 a kind of outer rim formula electric propulsion jet engine system and design method, belong to technical field of engines.The outer rim formula electric propulsion jet engine system of the present invention includes duct unit, electric motor units and blade unit, the duct unit is in hollow column structure, the electric motor units include rotor and motor stator, the motor stator is fixedly arranged in the duct unit, the inwall that the rotor corresponds to the motor stator is set, the blade unit is arranged in the inwall of the rotor, and it is fixedly connected with the rotor, the rotor, which rotates, can drive the blade unit to rotate, and then produce the power along the duct unit axis direction.The outer rim formula electric propulsion jet engine system of the present invention is adapted to electric propulsion, simple in construction, overall structure is in light weight, pneumatic efficiency is high.
Description
Technical field
The invention belongs to engine design field, more particularly, to a kind of outer rim formula electric propulsion jet engine system
System and design method.
Background technology
As current vehicle develops towards clean energy resource direction, the aircraft using culvert type electric propulsion has occurred
And there is larger potential market in some fields, the product currently occurred has European Air Passenger Airbus E-Fan, Germany
Lilium Jet, also, with the progress of electric power storage technology and fuel cell technology, electric propulsion is it could even be possible in airliner
Or used in military secret.
Currently, the electric power jet engine used on aircraft generally uses conventional petroleum enegy source engine design method, than
Engine such as European Air Passenger Airbus E-Fan and German Lilium Jet is by the turbine of traditional fanjet and burning
Room part has changed motor into, this difference for being designed without considering electric propulsion and fuel oil propulsion simply retrofited, is not directed to
Property design be adapted to electric propulsion aero-engine system, fuel engines due to have complexity fuel element, turbine unit, increasing
Unit is pressed, these units can only be arranged near engine axis, and are built in rectification housing, can not be incorporated into duct shell
In vivo, so as to cause engine structure complicated, pneumatic efficiency is low.
The content of the invention
The technical problems to be solved by the invention are, there is provided a kind of outer rim formula electric power simple in construction, pneumatic efficiency is high
Propulsion jet engine system.
The technical problems to be solved by the invention also reside in, there is provided a kind of outer rim formula electric propulsion suitable for electric propulsion
The design method of jet engine system.
Solution is used by the present invention solves above-mentioned technical problem：A kind of outer rim formula electric propulsion jet hair is provided
Motivation system, including duct unit, electric motor units and blade unit, the duct unit are in hollow column structure, the electricity
Machine unit includes rotor and motor stator, and the motor stator is fixedly arranged in the duct unit, the rotor pair
The inwall of motor stator described in Ying Yu is set, and the blade unit is arranged in the inwall of the rotor, and with the electricity
Machine rotor is fixedly connected, and the rotor, which rotates, can drive the blade unit to rotate, and then is produced along the duct unit
The power of axis direction.
As the further improvement of above-mentioned technical proposal, the blade unit includes some flabellums, and some flabellums are in
Circumference is arranged, and the flabellum includes leaf tip, blade root and the pars intermedia between the leaf tip and the blade root,
The leaf tip is fixedly arranged on the rotor, and the blade root is set close to the axis of the duct unit.
As the further improvement of above-mentioned technical proposal, along the rotor in the radial direction, the blade root, in
Between portion, leaf tip width gradually increase so that the leaf tip chord length is big, it is big to bear load and with point of resultant force it
Between distance it is short, the blade root chord length is small, it is small to bear load and it is long with the distance between point of resultant force.
As the further improvement of above-mentioned technical proposal, annular groove is offered in the duct unit, the electric motor units are embedding
In the annular groove, so that the internal diameter size of the rotor and the internal diameter of the duct unit are equal in magnitude, and then subtract
Air drag caused by the small electric motor units are independently external simultaneously saves the space-consuming of the electric motor units.
As the further improvement of above-mentioned technical proposal, the trailing edge of the duct unit is provided with sawtooth portion, the sawtooth portion
The large-scale vortex structure of the air-flow of the trailing edge of the duct unit is broken to form microvortex structure, to reduce noise.
The present invention also provides a kind of design method of above-mentioned outer rim formula electric propulsion jet engine system, including as follows
Step：Step 1: with reference to real engine type, size of engine, design point thrust, maximum thrust, efficiency parameters are determined；Step
Rapid two, electric motor units design point output power, working speed, peak power output are determined according to design point thrust and efficiency；Step
Rapid three, the parameter designing of the electric motor units determined goes out duct unit and blade unit.
The beneficial effects of the invention are as follows：
The outer rim formula electric propulsion jet engine system of the present invention, its blade unit are fixedly arranged on the inwall of rotor
On, and rotor is then fixedly arranged on the inwall of duct unit, the outer rim formula electric propulsion jet engine system, improves biography
System engine blade unit is arranged at the structure on duct unit axis, effectively alleviates the structure weight of engine system
Amount, and pneumatic efficiency is obviously improved；
Annular groove is further opened with duct unit, and electric motor units are embedded in annular groove so that blade unit and duct list
Gap between member is completely eliminated, and then pneumatic efficiency is further lifted.
The design method of the outer rim formula electric propulsion jet engine system of the present invention, there is provided above-mentioned outer rim formula electric power pushes away
Enter the design procedure of jet engine system.
Brief description of the drawings
Fig. 1 is the overall structure diagram of the outer rim formula electric propulsion jet engine system of the present invention；
Fig. 2 is the cross-section axonometric drawing of the outer rim formula electric propulsion jet engine system of the present invention；
Fig. 3 is the fractionation structural representation of the outer rim formula electric propulsion jet engine system of the present invention；
Fig. 4 is the local structural graph of this blade unit；
Fig. 5 is the flow chart of the design method of the outer rim formula electric propulsion jet engine system of the present invention.
Embodiment
Carried out below with reference to the design of embodiment and accompanying drawing to the present invention, concrete structure and caused technique effect clear
Chu, it is fully described by, to be completely understood by the purpose of the present invention, feature and effect.Obviously, described embodiment is this hair
Bright part of the embodiment, rather than whole embodiments, based on embodiments of the invention, those skilled in the art is not paying
The other embodiment obtained on the premise of creative work, belongs to the scope of protection of the invention.In addition, it is related in patent
All connection/annexations, not singly refer to component and directly connect, and refer to can according to specific implementation situation, by addition or
Couple auxiliary is reduced, to form more excellent draw bail.Each technical characteristic in the present invention, before not conflicting conflict
Putting can be with combination of interactions.
Please with reference to Fig. 1 to Fig. 3, the present invention is intended to provide a kind of outer rim formula electric propulsion spray for being adapted to electric propulsion
Gas engine system, it includes duct unit 1, electric motor units 2 and blade unit 3, and duct unit 1 is in hollow column knot
Structure, electric motor units 2 are fixedly arranged on the inwall of duct unit 1, and blade unit 3 is fixedly arranged on the inwall of electric motor units 2, during work,
Electric motor units 2 move, and then drive blade unit 3 to rotate, after producing thrust required when aircraft advances or landing
The required resistance when slowing down on runway.
In the present embodiment, electric motor units 2 include rotor 20, motor stator 21, and motor stator 21 is fixedly arranged on duct list
On the inwall of member 1, rotor 20 is arranged on the inwall of motor stator 21, and rotor 20 electrically connects with motor stator 21,
During work, motor stator 21 coordinates with rotor 20, rotates rotor 20, so as to which rotor 20 drives blade unit
3 rotate.
Electric motor units 2 also include motor leading edge cover 22, motor trailing edge cover 23 and motor outer rim structural member 24, motor leading edge cover
22 are covered with rotor 20 and motor stator 21 along two on the axis direction of duct unit 1 respectively with motor trailing edge cover 23
Side, motor outer rim structural member 24 are fixedly arranged between duct unit 1 and motor stator 21, the both sides of motor outer rim structural member 24 respectively with
The inwall and motor stator 21 of duct unit 1 are fixedly connected, motor leading edge cover 22, motor trailing edge cover 23, motor outer rim structure
Part 24 is used as force transferring part, and power caused by engine and torque are passed into aircraft.
Preferably, annular groove 10, motor outer rim structural member 24, rotor 20, motor are offered on the inwall of duct unit 1
Stator 21 is embedded in annular groove 10, so that the internal face of the internal face of rotor 20 and duct unit 1 maintains an equal level.
In the present embodiment, as shown in figure 4, blade unit 3 includes some flabellums, inwall of some flabellums along rotor 20
Rounded arrangement, and flabellum one end is fixedly installed on the inwall of rotor 20, the other end of flabellum is arranged at rotor
At 20 home position.
Along the radial direction of rotor 20, flabellum is disposed with leaf tip 30, pars intermedia 31 and blade root 32, leaf
Tip 30 is fixedly connected with the inwall of rotor 20, and the home position of blade root 32 close to rotor 20 is set, along electricity
In the radial direction, blade root 32, pars intermedia 31, the width of leaf tip 30 increase machine rotor 20 successively, so that flabellum is whole
The force action power of body is close to the opening position of leaf tip 30, when blade unit 3 rotates with the rotation of rotor 20, flabellum
The chord length of leaf tip 30 it is big, therefore its load born is big, and the distance of leaf tip 30 and flabellum point of resultant force is short, therefore, shows
The torque for reducing leaf tip 30 write, similarly, the chord length of blade root 32 of flabellum is small, and its load for bearing of aunt is small, and blade root
32 with the distance of flabellum point of resultant force, therefore, effectively balance the torque at blade root 32, see on the whole, whole fan
Contribution on leaf to torque is visibly homogeneous, significantly increases the structure efficiency of flabellum.
Preferably, pars intermedia 31 favours leaf tip 30 and the plane to be formed is connected with the center of circle of rotor 20, and motor turns
When son 20 rotates, leaf tip 30 rotates with rotor 20, so as to blade root 32, pars intermedia 31, the common rotation of leaf tip 30, production
Raw aircraft thrust required when advancing or drop fall behind in resistance required when slowing down on runway.
The outer rim formula electric propulsion jet engine system of the present invention, its duct unit 1 and electric motor units 2 and flabellum list
Member 3 matches, in addition, blade unit 3 is fixedly arranged on the inwall of rotor 20, and rotor 20 is embedded in annular groove 10,
The internal face of rotor 20 is set to be in the internal face of duct unit 1 on same disc, in this way, the leaf tip 30 of flabellum is fixed
In on the inwall of rotor 20, greatly reducing the loss of momentum of flabellum tip, meanwhile, electric motor units 2 are embedded at culvert
In the annular groove 10 of road unit 1, space-consuming is effectively saved, on the whole, outer rim formula electric propulsion jet of the invention is started
Machine system can effectively lift propulsive efficiency.
Further, outer rim formula electric propulsion jet engine system of the invention, one end of its duct unit 1 is also set up
There is sawtooth portion 11, sawtooth portion 11 has the function that flowing control, and the air-flow by the end of duct unit 1 is mainly large scale eddy
Structure, when it is behind sawtooth portion 11, sawtooth portion 11 can break the large-scale vortex structure, and then be transformed into microvortex
Structure, noise is interfered between vortex and the inwall of duct unit 1 so as to weaken, so as to reach the purpose for reducing noise.
In the present embodiment, the outer rim formula electric propulsion jet engine system is preferably applied in airspace engine, but
It is that, by the outer rim formula electric propulsion jet engine system in the present embodiment to be carried out to the simple adjustment in size, it also may be used
So that suitable for the waters surface such as ship, submarine, underwater robot and submarine navigation device, therefore, these applications also should be the present invention's
In protection domain.
Present invention also offers the design method based on above-mentioned outer rim formula electric propulsion jet engine system, such as Fig. 5
It is shown, comprise the following steps：
S100, the size of engine, design point thrust, maximum thrust, efficiency are determined for the type of engine application；
S110, determine that the design point output power of electric motor units, work turn according to obtained design point thrust and efficiency
Speed, peak power output；
S120, duct unit, electric motor units, blade unit are designed according to the parametric joint of obtained electric motor units.
Above is presently preferred embodiments of the present invention is illustrated, but the present invention is not limited to the embodiment,
Those skilled in the art can also make a variety of equivalent variations or replacement on the premise of without prejudice to spirit of the invention, this
Equivalent deformation or replacement are all contained in the application claim limited range a bit.
Claims (6)
- A kind of 1. outer rim formula electric propulsion jet engine system, it is characterised in that：Including duct unit, electric motor units and flabellum Unit, the duct unit are in hollow column structure, and the electric motor units include rotor and motor stator, the motor Stator is fixedly arranged in the duct unit, and the inwall that the rotor corresponds to the motor stator is set, the flabellum list Member is arranged in the inwall of the rotor, and is fixedly connected with the rotor, and the rotor is rotated and can driven The blade unit rotates, and then produces the power along the duct unit axis direction.
- 2. outer rim formula electric propulsion jet engine system according to claim 1, it is characterised in that：The blade unit Including some flabellums, some flabellums are circumferentially arranged, and the flabellum includes leaf tip, blade root and positioned at the blade tip Pars intermedia between portion and the blade root, the leaf tip are fixedly arranged on the rotor, and the blade root is close to described The axis of duct unit is set.
- 3. outer rim formula electric propulsion jet engine system according to claim 2, it is characterised in that：Turn along the motor In the radial direction, the blade root, pars intermedia, leaf tip width gradually increase son so that the leaf tip chord length it is big, It is big and short with the distance between point of resultant force to bear load, the blade root chord length is small, it is small to bear load and with making a concerted effort to make It is long with the distance between point.
- 4. the outer rim formula electric propulsion jet engine system according to any one of claim 1-3, it is characterised in that：Institute State and annular groove is offered in duct unit, the electric motor units are embedded in the annular groove, so that the internal diameter of the rotor is big It is small equal in magnitude with the internal diameter of the duct unit, and then reduce air drag caused by the electric motor units and save the electricity The space-consuming of machine unit.
- 5. outer rim formula electric propulsion jet engine system according to claim 4, it is characterised in that：The duct unit Trailing edge be provided with sawtooth portion, the sawtooth portion large-scale vortex structure of the air-flow of the trailing edge of the duct unit is broken to be formed it is small Yardstick vortex structure, to reduce noise.
- A kind of 6. design side of outer rim formula electric propulsion jet engine system according to any one of claim 1-5 Method, it is characterised in that comprise the following steps：Step 1: with reference to real engine type, size of engine, design point thrust, maximum thrust, efficiency parameters are determined；Step 2: electric motor units design point output power, working speed, maximum work output are determined according to design point thrust and efficiency Rate；Step 3: the parameter designing of the electric motor units determined goes out duct unit and blade unit.
Priority Applications (1)
| 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 |
Applications Claiming Priority (1)
| 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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107882655A true CN107882655A (en) | 2018-04-06 |
| CN107882655B CN107882655B (en) | 2023-06-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711144190.4A Active CN107882655B (en) | 2017-11-17 | 2017-11-17 | Outer edge type electric propulsion jet engine system and design method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4122817A1 (en) * | 2021-07-22 | 2023-01-25 | Rolls-Royce plc | Aircraft propulsion system |
Citations (5)
| 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 |
| US20160363050A1 (en) * | 2015-06-10 | 2016-12-15 | General Electric Company | Pitch change mechanism for shrouded fan with low fan pressure ratio |
| FR3087824A1 (en) * | 2018-10-26 | 2020-05-01 | Safran Aircraft Engines | ELECTRIC AIRCRAFT BLOWER MODULE HAVING IMPROVED FASTENING BLADES |
-
2017
- 2017-11-17 CN CN201711144190.4A patent/CN107882655B/en active Active
Patent Citations (5)
| 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 |
| US20160363050A1 (en) * | 2015-06-10 | 2016-12-15 | General Electric Company | Pitch change mechanism for shrouded fan with low fan pressure ratio |
| FR3087824A1 (en) * | 2018-10-26 | 2020-05-01 | Safran Aircraft Engines | ELECTRIC AIRCRAFT BLOWER MODULE HAVING IMPROVED FASTENING BLADES |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4122817A1 (en) * | 2021-07-22 | 2023-01-25 | Rolls-Royce plc | Aircraft propulsion system |
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| Publication number | Publication date |
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| CN107882655B (en) | 2023-06-20 |
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