CN205779789U - A kind of air compressor structure with embedded coaxial motor - Google Patents
A kind of air compressor structure with embedded coaxial motor Download PDFInfo
- Publication number
- CN205779789U CN205779789U CN201620577864.4U CN201620577864U CN205779789U CN 205779789 U CN205779789 U CN 205779789U CN 201620577864 U CN201620577864 U CN 201620577864U CN 205779789 U CN205779789 U CN 205779789U
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- Prior art keywords
- compressor
- coaxial motor
- motor
- annular groove
- air compressor
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Abstract
This utility model relates to a kind of air compressor structure with embedded coaxial motor, belong to aviation small-size turbojet engine technical field, it it is critical only that compressor uses the design of high hub ratio, raise compressor inlet inner flow passage height, an axial annular groove is gone out along car from compressor disk inner circle import, high speed coaxial motor is embedded in axial annular groove, on the premise of maintaining compressor aeroperformance and compressor disk intensity, make full use of the space that engine interior is extremely limited, high speed coaxial motor is installed, and engine shaft length can be shortened, meet the demanding kinetics of engine rotor system.This utility model can be directly used for small-size turbojet engine, it is possible to realizes generating function on the premise of not increasing electromotor overall dimensions, abandons aircraft airborne power supply, increases aircraft payload and extend cruising time.
Description
Technical field
This utility model relates to a kind of air compressor structure, particularly relates to the high wheel hub of a kind of embedded coaxial motor of import band
Ratio air compressor structure, is particularly well-suited to need the small-size turbojet engine of power taking, it is possible to maintaining compressor aeroperformance and pressure
Coaxial motor is installed on the premise of mechanism of qi disc strength in rotating shaft, electric power can be provided to aircraft, ensure again whole rotor
The dynamics of system.
Background technology
Small-size turbojet engine is little, lightweight due to its size, is suitable for high speed flight at high altitude, is widely used as middle-size and small-size
Unmanned plane, particularly target drone and reconnaissance UAV power.The most domestic middle-size and small-size unmanned aerial vehicle onboard equipment required electric power is relatively low,
The most all provided by the battery of aircraft prestowage, but on-board batteries volume is big, weight is big and flying power is low, seriously constrains aircraft
Flight time, reduce the payload of aircraft.Therefore, if the shaft work of electromotor self can be utilized to generate electricity, by electromotor to
Aircraft provide electric power, needed for being entirely capable of meeting aircraft, and can effectively extend aircraft flying power, abandon on-board batteries thus
Increasing airplane load, this is also the main trend of Development of UAV both at home and abroad now.
Owing to being limited by unmanned plane dimensional structure, small-size turbojet engine installing space aboard is less, electromotor
Electromotor cannot be installed in outside, and therefore electromotor must be placed in engine interior.And turbojet engine is in order to reduce size, carry
High thrust-weight ratio, textural anomaly own is compact, is " an inch of land is an inch of gold ", has not had unnecessary space electromotor, so can only
Optimize electromotor design to be placed directly within engine shaft.But so certainly will rise appreciably engine shaft, deteriorate rotor
Dynamics, is embodied in rotor system rigidity and reduces, and critical speed declines, and even lures that resonance occurs in electromotor into, and this will be to sending out
Motivation brings structural destruction, is substantially damaged service life of aeroengine.Therefore, need badly and seek a kind of engine rotor structure cloth
Office, installs on the premise of not affecting rotor dynamics and sends out coaxial motor, effectively power to aircraft.
Utility model content
The shortcoming and defect existed for prior art, technical problem to be solved in the utility model is to provide one and sets
Meter rationally, had both realized installing coaxial motor on engine shaft, can guarantee that again and meets engine rotor dynamics requirement
Air compressor structure layout.
This utility model solves above-mentioned technical problem and be the technical scheme is that
A kind of air compressor structure with embedded coaxial motor, including compressor disk, compressor casing and coaxial motor,
It is characterized in that, described compressor disk is installed on the driving shaft, and described compressor disk is within it justified and set on the wheel hub of import
Putting an axial annular groove, described coaxial motor is embedded in described axial annular groove, and wherein, the rotor of described coaxial motor is fixed
In described drive shaft or be fixed on the sidewall of described axial annular groove, the motor stator of described coaxial motor is arranged on described pressure
On mechanism of qi casing.
In the air compressor structure of the embedded coaxial motor of band of the present utility model, compressor disk uses high hub ratio to set
Meter, by raising compressor inlet inner flow passage height so that compressor disk increases therewith, enters from compressor disk inner circle simultaneously
On the wheel hub of mouth, car goes out an annular groove vertically, is embedded by coaxial motor in this axial annular groove, rotor is fixed on drive shaft
Going up or be fixed on the sidewall of axial annular groove, motor stator is arranged on compressor casing, and rotor is with drive shaft or calms the anger
Wheel disc spins, produces alternating current and confesses.
Preferably, described coaxial motor is brushless AC motor.
Preferably, described drive shaft is engine shaft.
Preferably, inner flow passage height is outer flow passage height 40%～the 50% of described compressor inlet section, described axially
The degree of depth of annular groove is the 30%～40% of compressor disk axial overall length.
Preferably, the maximum outside diameter of described coaxial motor is less than the import inner flow passage of compressor, the axle of described coaxial motor
To 80%～100% that total length is compressor overall length.
Preferably, described coaxial motor embed described axial annular groove axial length is coaxial motor total length 40%～
60%.
Preferably, the drive shaft of described coaxial motor and compressor motor section a diameter of compressor section diameter 60%～
70%.
Compared with small sized turbine jet engine traditional structure layout, this utility model uses the embedded coaxial motor of import
After high hub ratio air compressor structure layout, effectively high speed alternator driven motor is implanted engine interior, utilize electromotor self
Rotational energy, coaxial motor can stably send alternating current, greatly meet the electricity needs of aircraft, thus abandon
Heavy airborne power supply, significantly increases the payload of aircraft and improves the cruising time of aircraft.Compressor improves simultaneously
High hub ratio, by design embedded for coaxial motor, is effectively reduced compressor weight and rotor axial length increases less, completely
Meet engine rotor system demanding kinetics.Certain type turbojet engine adopts the structure layout, ground run and aerial
Taking a flight test respond well, the development to China's aviation industry serves facilitation.
Accompanying drawing explanation
Fig. 1 is the high hub ratio air compressor structure schematic layout pattern of embedded coaxial motor of the present utility model.
Detailed description of the invention
For making the purpose of this utility model, technical scheme and advantage clearer, develop simultaneously enforcement referring to the drawings
Example, further describes this utility model.It should be noted that the following stated is only preferable enforcement of the present utility model
Example, the most therefore limits protection domain of the present utility model.
It should be noted that the implementation not illustrating in accompanying drawing or describing, for ordinary skill people in art
Form known to Yuan.Additionally, the direction term mentioned in following example, such as " on ", D score, "front", "rear", " left ",
" right ", " top ", " end " etc., be only the direction with reference to accompanying drawing.Therefore, the direction term of use is used to illustrate not for limiting
This utility model.
As it is shown in figure 1, the air compressor structure of the embedded coaxial motor of band of the present utility model, including compressor disk 3, pressure
Mechanism of qi casing 1 and coaxial motor 2, compressor disk 3 is arranged in drive shaft 4, and compressor disk 3 within it justifies the wheel hub of import
On an axial annular groove is set, coaxial motor 2 is embedded in axial annular groove, and the rotor of coaxial motor 2 is fixed in drive shaft 4
Or be fixed on the sidewall of axial annular groove, the motor stator of coaxial motor 2 is arranged on compressor casing 1.Wherein drive shaft 4 is
Engine shaft, is supported by bearing 5.
Air compressor structure of the present utility model can be used in small-size turbojet engine, by flowing in raising the import of compressor
Road, it is ensured that inner flow passage height is the 40%～50% of outer flow passage height, so that compressor disk 3 height increases.Exist simultaneously
Compressor disk 3 leading edge car vertically goes out annular groove, and the annular groove degree of depth is the 30%～40% of compressor disk 3 axial overall length,
Ensure to provide space for realizing embedded coaxial motor 2 on the premise of compressor disk 3 requirement of strength.Coaxial motor 2 uses height
Speed alternating-current brushless design, its maximum outside diameter be less than compressor inlet inner flow passage, axial overall length be compressor 3 overall length 80%～
100%, wherein embed axial length is motor total length 40%～the 60% of compressor disk annular groove.Coaxial motor 2 quiet
Subdivision relies on compressor casing 1 to position, and rotor portion is then arranged on engine shaft 4 and fixes.Design electromotor simultaneously
Rotating shaft 4 is Step Shaft, it is desirable to it at a diameter of compressor 3 the 60%～70% of diameter, ensures coaxially with this at coaxial motor 2
Motor has sufficiently large volume, produces sufficiently large power during work.
This topology layout that this utility model uses so that high speed coaxial motor 2 can successfully embed high hub ratio
Compressor disk 3, efficiently utilizes the axially and radially space of engine interior.Meanwhile, compact structure layout so that send out
The axial length of motivation rotor-support-foundation system shortens dramatically, and rotor weight decreases, and has fully met the rotor dynamics of electromotor
Characteristic.During work, coaxial motor 2 rotates with engine shaft 4, produces electrical power output, effectively meets the use of aircraft
Electricity demand.
In sum, this utility model uses the high hub ratio air compressor structure layout with embedded coaxial motor, can be straight
Connect for small-size turbojet engine, it is possible on the premise of not increasing electromotor overall dimensions, realize electromotor power taking, abandon and fly
Machine airborne power supply, increases aircraft payload and extends cruising time.
Furthermore, it is necessary to explanation, the specific embodiment described in this specification, the shape of its parts and components, it is named
Titles etc. can be different.All equivalences done according to structure, feature and the principle described in this utility model inventional idea or simple change,
All it is included in the protection domain of this utility model patent.This utility model person of ordinary skill in the field can be to being retouched
The specific embodiment stated makes various amendment or supplements or use similar mode to substitute, without departing from this utility model
Structure or surmount scope defined in the claims, protection domain of the present utility model all should be belonged to.
Claims (7)
1. the air compressor structure with embedded coaxial motor, including compressor disk, compressor casing and coaxial motor, its
Being characterised by, described compressor disk is installed on the driving shaft, and described compressor disk within it justifies setting on the wheel hub of import
One axial annular groove, described coaxial motor is embedded in described axial annular groove, and wherein, the rotor of described coaxial motor is fixed on
In described drive shaft or be fixed on the sidewall of described axial annular groove, the motor stator of described coaxial motor be arranged on described in calm the anger
On machine casing.
Air compressor structure the most according to claim 1, it is characterised in that described coaxial motor is brushless AC motor.
Air compressor structure the most according to claim 1, it is characterised in that described drive shaft is engine shaft.
Air compressor structure the most according to claim 1, it is characterised in that the inner flow passage height of described compressor inlet section is
The 40%～50% of outer flow passage height, the degree of depth is compressor disk axial overall length 30%～the 40% of described axial annular groove.
Air compressor structure the most according to claim 1, it is characterised in that the maximum outside diameter of described coaxial motor is less than calming the anger
The import inner flow passage of machine, the axial overall length of described coaxial motor is the 80%～100% of compressor overall length.
Air compressor structure the most according to claim 1, it is characterised in that described coaxial motor embeds described axial annular groove
Axial length is the 40%～60% of coaxial motor total length.
Air compressor structure the most according to claim 1, it is characterised in that the drive shaft of described coaxial motor and compressor exists
The 60%～70% of motor section a diameter of compressor section diameter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620577864.4U CN205779789U (en) | 2016-06-13 | 2016-06-13 | A kind of air compressor structure with embedded coaxial motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620577864.4U CN205779789U (en) | 2016-06-13 | 2016-06-13 | A kind of air compressor structure with embedded coaxial motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205779789U true CN205779789U (en) | 2016-12-07 |
Family
ID=58131721
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620577864.4U Expired - Fee Related CN205779789U (en) | 2016-06-13 | 2016-06-13 | A kind of air compressor structure with embedded coaxial motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205779789U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109611377A (en) * | 2018-12-12 | 2019-04-12 | 中国北方发动机研究所(天津) | A kind of electric booster impeller |
| CN109654046A (en) * | 2018-12-12 | 2019-04-19 | 中国北方发动机研究所(天津) | A kind of electric booster |
| CN109707513A (en) * | 2018-12-10 | 2019-05-03 | 中国航发四川燃气涡轮研究院 | A kind of more electric engin inlet casing |
| CN110043486A (en) * | 2019-04-02 | 2019-07-23 | 中国北方发动机研究所(天津) | A kind of dynamoelectric compressor |
-
2016
- 2016-06-13 CN CN201620577864.4U patent/CN205779789U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109707513A (en) * | 2018-12-10 | 2019-05-03 | 中国航发四川燃气涡轮研究院 | A kind of more electric engin inlet casing |
| CN109707513B (en) * | 2018-12-10 | 2021-11-26 | 中国航发四川燃气涡轮研究院 | Multi-electric engine air inlet casing |
| CN109611377A (en) * | 2018-12-12 | 2019-04-12 | 中国北方发动机研究所(天津) | A kind of electric booster impeller |
| CN109654046A (en) * | 2018-12-12 | 2019-04-19 | 中国北方发动机研究所(天津) | A kind of electric booster |
| CN110043486A (en) * | 2019-04-02 | 2019-07-23 | 中国北方发动机研究所(天津) | A kind of dynamoelectric compressor |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161207 Termination date: 20210613 |