CN110454417A - A kind of no spindle-type axial flow compressor structure and compressor - Google Patents
A kind of no spindle-type axial flow compressor structure and compressor Download PDFInfo
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- CN110454417A CN110454417A CN201910893941.5A CN201910893941A CN110454417A CN 110454417 A CN110454417 A CN 110454417A CN 201910893941 A CN201910893941 A CN 201910893941A CN 110454417 A CN110454417 A CN 110454417A
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- annular
- leaf dish
- compressor
- axial flow
- spindle
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/06—Units comprising pumps and their driving means the pump being electrically driven
- F04D25/0606—Units comprising pumps and their driving means the pump being electrically driven the electric motor being specially adapted for integration in the pump
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention belongs to Push Technology and aircraft power plant field, a kind of no spindle-type axial flow compressor structure and compressor, including casing, annular generator, annular leaf dish and several blades are disclosed；It is connect on the inside of blade one end and annular leaf dish, the other end is radially extended to the annular leaf dish center of circle；Annular generator one end is connected on the outside of annular leaf dish, for annular generator for driving annular leaf dish to rotate, the annular generator other end connects casing.By the way that blade is directly connect with annular leaf dish inner ring surface, leaf dish is connect with annular generator, leaf dish rotation is driven by annular generator, the effect for pressurization of slowing down can be realized after the blade grid passage that air-flow passes through blade, realize the dereliction axiation of axial flow compressor structure, it is substantially reduced the radial dimension of axial flow compressor, substantially reduced compressor weight of equipment, improve the unit area air quality flow of compressor, increase the negotiability of compressor, the stable operation range of compressor is widened, the impaired probability of blade is reduced, promotes the overall stability of gas pressure mechanism.
Description
Technical field
The invention belongs to Push Technology and aircraft power plant field, it is related to a kind of no spindle-type axial flow compressor structure and pressure
Mechanism of qi.
Background technique
Aero gas turbine engine provides power as the power device of aircraft for aircraft, to push aircraft
Advance, aero gas turbine engine belongs to state key high-tech field, and development level has become a national comprehensive strength
One of the important signs that.In aero gas turbine engine, air is compressed by compressor to improve and enter engine
Air pressure.In addition, compressor is except compressed air required when supply engine works, or cabin pressurization, whirlpool
Wheel heat dissipation and the starting of other engines provide compressed air.
In aero gas turbine engine, generally using axial-flow type, centrifugal and hybrid-type compressor.Wherein,
Axial-flow compressor has many advantages, such as that pressure ratio is high, high-efficient, unit area air quality flow is big, frontal resistance is small, in phase
With bigger thrust can be obtained under the conditions of contour dimension, therefore axial-flow type pressure is generallyd use in aero gas turbine engine
Mechanism of qi.Currently, axial flow compressor technology has achieved significant progress by the development since half a century, shows themselves in that and calmed the anger
The stage load of machine is increasing, and performance is also being continuously improved.
But for aero-engine, evaluating one of most important index of its compressor is exactly contour dimension, especially body
The small turbine engine that present rocket uses, needs smaller size, weight and lower cost.It notices one
As in axial flow compressor structure, turbine wheel shaft occupies most of area of flow channel, this will cause entire engine size
Increase.In addition, it is hydraulic mechanical type, monitoring type electronics that control system, which can be divided into, in general axial flow compressor structure
Formula and Full functional electronic formula, but these three control modes require hydro-mechanical components as executing agency, relative to direct
Electronic control, controls precision and response speed is poor.Furthermore due to the limitation of general axis flow air compressor structure, compressor is each
The revolving speed of grade is consistent, thus people have developed birotor and triple-spool axial flow compressor make every part rotor with it most
Good rotary speed working, to improve pressure ratio and operation flexibility, but multi-rotor engine compressor pressure grade is relatively large in diameter, and shafting knot
Structure is complicated.
Summary of the invention
It is an object of the invention to overcome the big above-mentioned size of compressor in the prior art, control precision and response speed difference
Disadvantage provides a kind of no spindle-type axial flow compressor structure and compressor.
In order to achieve the above objectives, the present invention is achieved by the following scheme:
One aspect of the present invention, a kind of no spindle-type axial flow compressor structure, if including casing, annular generator, annular leaf dish and
Cured leaf piece；It is connect on the inside of the fixing end of blade and annular leaf dish, free end is radially extended to the annular leaf dish center of circle, and several blades
Free end between there are gaps；Annular generator one end is connected on the outside of annular leaf dish, annular generator is for driving annular leaf dish to turn
Dynamic, the annular generator other end connects casing.
The present invention without spindle-type axial flow compressor structure further improvement is that
The annular generator includes motor housing, motor stator, rotor and two fixing bearings；On the outside of motor housing
It is connect with casing, annular fitting groove is set inside motor housing；Motor stator is connect in a ring and with assembly trench bottom, and motor turns
Son in a ring and is set in the annular distance of motor stator, and the annular groove support by opening up in annular leaf dish；Rotor
There are gap between motor stator, the permanent magnet of annular is also set up on rotor；Two fixing bearings are respectively sleeved at ring
On the radial protrusion of shape leaf dish both ends setting, and two fixing bearings are connect with motor housing inside.
It is threadedly coupled with casing by attachment screw on the outside of the motor housing.
Several thermal vias are set on the motor housing.
It further include connector；Connector is hollow annular construction, and connector outer wall and the free end of several blades are all connected with.
The blade and annular leaf dish inner ring surface mortise-tenon joint.
The installation cavity for installing gas pressure mechanism auxiliary device is opened up inside the casing.
Another aspect of the present invention, a kind of no spindle-type axial flow compressor are each calmed the anger including several above-mentioned gas pressure mechanisms
Several connection through-holes are respectively provided on the casing of mechanism, several gas pressure mechanisms are axially coupled by connection through-hole.
Compared with prior art, the invention has the following advantages:
Compared to conventional axial flow compressor, remove main axle structure, by the way that blade is directly connect with annular leaf dish inner ring surface, leaf
Disk is connect with annular generator, is driven leaf dish rotation by annular generator, is realized that the dereliction axiation of axial flow compressor structure, the invention have
Following advantage: first, it is substantially reduced the radial dimension of axial flow compressor, hence it is evident that mitigate compressor weight of equipment, compared to tradition
Shafting structure the most complicated, either still dimensionally has pole in weight using annular generator structure in axial flow engine
Big advantage can be such that the weight of gas pressure mechanism and size is substantially reduced.Second, improve the unit area air quality of gas pressure mechanism
Flow increases the negotiability of compressor, and the space that airflow is used for inside compressor of the invention is bigger, can be smaller
Size under bigger negotiability may be implemented, while setting fixing end for conventional axial flow gas compressor blade top region, block
A possibility that operating condition occurs is greatly reduced.Third improves the overall performance and efficiency of gas pressure mechanism, widens the stabilization of gas pressure mechanism
Working range, gas pressure mechanism of the invention directly control revolving speed by annular generator, can shorten the response time of control, raising pair
The precision of revolving speed control, so that the revolving speed between each compressor stage has better matching, and also gets rid of compressor and whirlpool simultaneously
Take turns cooperative limitation.4th, reduce the impaired probability of rotor blade, compressor rotor blade free end of the invention in
Linear velocity lower region, impaired probability substantially reduce.5th, the thrust ratio of engine is improved, thrust ratio is the important of engine
Performance parameter, gas pressure mechanism of the invention can promote the engine overall performance for installing it.6th, the reliability of gas pressure mechanism
And maintainability is greatly improved, compressor of the invention is not necessarily to consider the strength problem of bearing, wheel disc etc., significantly reduces structure
The complexity of design, while also having prevented the challenge in shafting system.7th, the application range of compressor expands, this
The compressor of invention significantly reduces weight and size, can be applied to wider field, such as special aircraft is small
H type engine h, unmanned plane etc..
Further, rotor is embedded with the permanent magnet of annular, based on permanent-magnet brushless DC electric machine excitation principle,
Driving motor rotation, at the same it is big to the revolving speed of the i.e. controllable rotor of size of current of annular generator by control output at this time
It is small, be the direction of rotation of controllable rotor to the current direction of annular generator by control output, realize revolving speeds at different levels and
To rotary-die type.
Further, it is threadedly coupled with casing by attachment screw on the outside of motor housing, stable connection and easily disassembled dimension
It repairs.
Further, several thermal vias are set on motor housing, are rationally radiated to annular generator, entire machine is promoted
The stability of structure.
Further, blade and annular leaf dish inner ring surface mortise-tenon joint, facilitate the replacement and maintenance of blade.
Further, the installation cavity for installing gas pressure mechanism auxiliary device is opened up inside casing, installation cavity is for installing
Required auxiliary device when some gas pressure mechanism specific works, for example, transformer, heat dissipation equipment, electric control system equipment and
Filter harmonic wave equipment etc..
Detailed description of the invention
Fig. 1 is no spindle-type axial flow compressor structure structural schematic diagram of the invention；
Fig. 2 is the partial cutaway schematic of no spindle-type axial flow compressor structure annular generator of the invention.
Wherein: 1- casing；2- annular generator；3- blade；4- annular leaf dish；5- motor housing；6- motor stator；7- is fixed
Bearing；8- rotor.
Specific embodiment
In order to enable those skilled in the art to better understand the solution of the present invention, below in conjunction in the embodiment of the present invention
Attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is only
The embodiment of a part of the invention, instead of all the embodiments.Based on the embodiments of the present invention, ordinary skill people
The model that the present invention protects all should belong in member's every other embodiment obtained without making creative work
It encloses.
It should be noted that description and claims of this specification and term " first " in above-mentioned attached drawing, "
Two " etc. be to be used to distinguish similar objects, without being used to describe a particular order or precedence order.It should be understood that using in this way
Data be interchangeable under appropriate circumstances, so as to the embodiment of the present invention described herein can in addition to illustrating herein or
Sequence other than those of description is implemented.In addition, term " includes " and " having " and their any deformation, it is intended that cover
Cover it is non-exclusive include, for example, the process, method, system, product or equipment for containing a series of steps or units are not necessarily limited to
Step or unit those of is clearly listed, but may include be not clearly listed or for these process, methods, product
Or other step or units that equipment is intrinsic.
The invention will be described in further detail with reference to the accompanying drawing:
Referring to Fig. 1, the present invention without spindle-type axial flow compressor structure, including casing 1, annular generator 2, annular leaf dish 4 and
It is connected on the inside of several blades 3,3 fixing end of blade and annular leaf dish 4, free end is radially extended to annular 4 center of circle of leaf dish, and several
There are gap or the free ends of several blades 3 to be connected by connector between the free end of blade 3, and connector is hollow
Cyclic structure；2 one end of annular generator is connected on the outside of annular leaf dish 4, annular generator 2 is for driving annular leaf dish 4 to rotate, annular electro
2 other end of machine connects casing 1, and blade 3 and annular generator 2 are connected to become that a collection is integral by annular leaf dish 4 being capable of synchronous rotation
Turn.
Referring to fig. 2, the partial cutaway schematic of no spindle-type axial flow compressor annular generator of the invention, annular generator 2
Including motor housing 5, motor stator 6, rotor 8 and two fixing bearings 7.Annular groove work is machined in motor housing 5
To assemble storehouse, assembly orlop portion is equipped with cricoid motor stator 6, turns wherein being successively connected with fixing bearing 7, leaf dish 4, motor
Gap is arranged in son 8 and another fixing bearing 7, rotor 8 and motor stator 6 between the two, forms the entirety of annular generator 2
Structure, rotor 8 can be realized and be freely rotated.The insertion of rotor 8 is installed in the annular groove opened up in annular leaf dish 4,
And the rotor-support-foundation system of axial flow compressor structure of the invention is collectively formed with blade 3, it is solid by two that are located at 5 end of motor housing
Dead axle holds 7 and is installed on inside assembly storehouse, and it is integral that blade 3 and the connection of rotor 8 are formed as a collection by annular leaf dish 4, makes
Obtaining blade 3 can rotate synchronously with rotor 8.
Blade 3 is fixed on annular 4 inner ring surface of leaf dish, is calmed the anger with conventional axial flow such as dovetail type tenon using tenon form
Unlike mechanism, annular leaf dish 4 is similar on wheeling disk structure installation and the engine shaft in conventional axial flow gas pressure mechanism,
And it is mounted to 2 inside of annular generator, the rotor-support-foundation system of compressor of the present invention is collectively constituted with the rotor 8 of annular generator 2.
In addition, another significantly different place with conventional axial flow gas pressure mechanism is, it is lesser that the free end of blade 3 is located at linear velocity
Close to the region of rotation center, the fixing end of blade 3 is located at the maximum separate rotation center region of linear velocity, can mitigate blade
It is impaired, while saving complicated sealing structure.Fixing end is set by conventional axial flow gas compressor blade top region simultaneously, has prevented leaf
The presence in gap is pushed up, a possibility that operating condition occurs is blocked and is greatly reduced, solve the presence due to clearance leakage of blade tip, will cause
Rotor stall, the problem of influencing compressor working efficiency.
Annular generator 2 based on permanent-magnet brushless DC electric machine excitation principle, by motor stator 6 and rotor 8 it
Between magnetic field transmit torque, driving motor rotor 8 rotates.By controlling power supply, such as battery pack, export to annular generator 2
Size of current be controllable rotor 8 revolving speed size, by control output to annular generator 2 current direction, that is, it is controllable
The direction of rotation of rotor 8 processed then then can realize at different levels turns in the multilevel system of axial flow compressor structure of the invention
Speed and to rotary-die type.
About casing 1, the shape provided in figure is only made to illustrate, and shape is not necessarily circle, is a circular casing
Body structure, inner wall on the outside of connection bolt and annular generator 2 by being connected, as no spindle-type axial flow compressor structure of the invention
Shell, inside open up installation cavity for installing required auxiliary device when some compressors work normally, such as transformation
Device, heat dissipation equipment, electric control system equipment and filtering harmonic wave equipment etc..Casing 1 mainly rises and reduces resistance, protects compressor
The effect of auxiliary device, but gas pressure mechanism auxiliary device is not emphasis of the invention, and there is existing equipment in these equipment, and
And the auxiliary device that gas pressure mechanism of the invention needs under different application scenarios is also different.
The invention also discloses a kind of no spindle-type axial flow compressors each to calm the anger including several above-mentioned gas pressure mechanisms
Several connection through-holes are respectively provided on the casing 1 of mechanism, by the installation connection bolt on connection through-hole, by each compressor stage along axis
To connection, integral compressor is organized.
Using aero gas turbine engine as backgrounds, the course of work of the present invention without spindle-type axial flow compressor is such as
Shown in lower:
Using battery pack as power supply, powers first to annular generators 2 at different levels, gradually form stabilizing magnetic field, pushing motor
Rotor 8, leaf dish 4 and blade 3 rotate, and axial flow compressor structure starts work at this time, into start operating performance.Start in compressor
Afterwards, engine turbine also starts therewith, by control battery pack output, ramps up gas pressure mechanism, the air in engine
When flow field is established and reaches combustion chamber ignition requirement, it is at this time nominal situation, at this time that combustion chamber ignition, engine, which is started to work,
The effect for pressurization of slowing down can be realized in compressor high speed rotations at different levels, air-flow after the blade grid passage by compressor blades 3 at different levels.
The rotational speed regulation control of each grade blade 3 is controlled by the size of current to annular generators 2 at different levels to be realized, machine is different from
Tool is adjusted, and this electromagnetic induction, which is adjusted, has quick, accurate and automation advantage.Simultaneously as present invention eliminates hairs
Motivation shaft transmission system, not by the matched constraint of secondary speed, at different levels revolving speeds can be matched preferably, reduce compressor surge
The problems such as generation.Without the co-operation limitation for considering compressor and turbine when switching between different working condition.
The above content is merely illustrative of the invention's technical idea, and this does not limit the scope of protection of the present invention, all to press
According to technical idea proposed by the present invention, any changes made on the basis of the technical scheme each falls within claims of the present invention
Protection scope within.
Claims (8)
1. a kind of no spindle-type axial flow compressor structure, which is characterized in that including casing (1), annular generator (2), annular leaf dish (4)
With several blades (3)；
It being connect on the inside of the fixing end of blade (3) and annular leaf dish (4), free end is radially extended to annular leaf dish (4) center of circle, and if
There are gaps between the free end of cured leaf piece (3)；Annular generator (2) one end, annular generator (2) are connected on the outside of annular leaf dish (4)
For driving annular leaf dish (4) to rotate, annular generator (2) other end connects casing (1).
2. no spindle-type axial flow compressor structure according to claim 1, which is characterized in that the annular generator (2) includes
Motor housing (5), motor stator (6), rotor (8) and two fixing bearings (7)；
It is connect on the outside of motor housing (5) with casing (1), annular fitting groove is set inside motor housing (5)；Motor stator (6) is in
It annular and is connect with assembly trench bottom, rotor (8) in a ring and is set in the annular distance of motor stator (6), and passes through ring
The annular groove support opened up in shape leaf dish (4)；There are gap, rotors between rotor (8) and motor stator (6)
(8) permanent magnet of annular is also set up on；Two fixing bearings (7) are respectively sleeved at the radial convex of annular leaf dish (4) both ends setting
On rising, and two fixing bearings (7) connect with motor housing (5) inside.
3. no spindle-type axial flow compressor structure according to claim 2, which is characterized in that on the outside of the motor housing (5)
It is threadedly coupled with casing (1) by attachment screw.
4. no spindle-type axial flow compressor structure according to claim 2, which is characterized in that set on the motor housing (5)
Set several thermal vias.
5. no spindle-type axial flow compressor structure according to claim 1, which is characterized in that further include connector；Connector
For hollow annular construction, connector outer wall and the free end of several blades (3) are all connected with.
6. no spindle-type axial flow compressor structure according to claim 1, which is characterized in that the blade (3) and annular leaf
Disk (4) inner ring surface mortise-tenon joint.
7. no spindle-type axial flow compressor structure according to claim 1, which is characterized in that opened up inside the casing (1)
For installing the installation cavity of gas pressure mechanism auxiliary device.
8. a kind of no spindle-type axial flow compressor, which is characterized in that including several gas pressure mechanisms described in claim 1, each
Several connection through-holes are respectively provided on the casing (1) of gas pressure mechanism, several gas pressure mechanisms are axially coupled by connection through-hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910893941.5A CN110454417A (en) | 2019-09-20 | 2019-09-20 | A kind of no spindle-type axial flow compressor structure and compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910893941.5A CN110454417A (en) | 2019-09-20 | 2019-09-20 | A kind of no spindle-type axial flow compressor structure and compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110454417A true CN110454417A (en) | 2019-11-15 |
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ID=68492550
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|---|---|---|---|
| CN201910893941.5A Pending CN110454417A (en) | 2019-09-20 | 2019-09-20 | A kind of no spindle-type axial flow compressor structure and compressor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112083185A (en) * | 2020-09-07 | 2020-12-15 | 西安交通大学 | Liquid metal flow velocity measurement experiment system on surface of liquid metal pump blade |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140159378A1 (en) * | 2010-02-16 | 2014-06-12 | Sine Waves, Inc. | Engine and Induction Generator |
| CN105240293A (en) * | 2015-10-17 | 2016-01-13 | 李德生 | Efficient suction and exhaust hollow ring shaftless motor fan |
| CN205707256U (en) * | 2016-04-11 | 2016-11-23 | 浙江国际海运职业技术学院 | A kind of wheel rim propeller peculiar to vessel |
| CN207500161U (en) * | 2017-09-23 | 2018-06-15 | 西北工业大学 | A kind of shaftless wind turbine of wheel rim drive-type |
| CN109083849A (en) * | 2018-08-14 | 2018-12-25 | 成都市弘盛科技有限公司 | A kind of axial flow compressor |
| CN109296549A (en) * | 2018-11-21 | 2019-02-01 | 兴城市水泵制造有限公司 | The shaftless blade electric pump of brushless, permanently |
| CN109505738A (en) * | 2019-01-29 | 2019-03-22 | 佛山市致德建材有限公司 | A kind of non-shaft wind power generation machine |
-
2019
- 2019-09-20 CN CN201910893941.5A patent/CN110454417A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140159378A1 (en) * | 2010-02-16 | 2014-06-12 | Sine Waves, Inc. | Engine and Induction Generator |
| CN105240293A (en) * | 2015-10-17 | 2016-01-13 | 李德生 | Efficient suction and exhaust hollow ring shaftless motor fan |
| CN205707256U (en) * | 2016-04-11 | 2016-11-23 | 浙江国际海运职业技术学院 | A kind of wheel rim propeller peculiar to vessel |
| CN207500161U (en) * | 2017-09-23 | 2018-06-15 | 西北工业大学 | A kind of shaftless wind turbine of wheel rim drive-type |
| CN109083849A (en) * | 2018-08-14 | 2018-12-25 | 成都市弘盛科技有限公司 | A kind of axial flow compressor |
| CN109296549A (en) * | 2018-11-21 | 2019-02-01 | 兴城市水泵制造有限公司 | The shaftless blade electric pump of brushless, permanently |
| CN109505738A (en) * | 2019-01-29 | 2019-03-22 | 佛山市致德建材有限公司 | A kind of non-shaft wind power generation machine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112083185A (en) * | 2020-09-07 | 2020-12-15 | 西安交通大学 | Liquid metal flow velocity measurement experiment system on surface of liquid metal pump blade |
| CN112083185B (en) * | 2020-09-07 | 2021-06-22 | 西安交通大学 | Liquid metal flow velocity measurement experiment system on surface of liquid metal pump blade |
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Application publication date: 20191115 |
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