CN108301940A - Three rows mouthful turbojet - Google Patents
Three rows mouthful turbojet Download PDFInfo
- Publication number
- CN108301940A CN108301940A CN201810365525.3A CN201810365525A CN108301940A CN 108301940 A CN108301940 A CN 108301940A CN 201810365525 A CN201810365525 A CN 201810365525A CN 108301940 A CN108301940 A CN 108301940A
- Authority
- CN
- China
- Prior art keywords
- air inlet
- pipeline section
- duct
- combustion chamber
- inlet pipeline
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Classifications
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
Abstract
A kind of three rows mouthful turbojet, including engine body, the front of engine body is equipped with air intake duct along the longitudinal direction, the air inlet of air intake duct is located at the front end of engine body, air intake duct compressor is equipped in air intake duct, the air inlet of the gas outlet of air intake duct and middle duct, the air inlet of the air inlet of left duct and right duct communicates, the air inlet of middle duct is located at the dead astern of the gas outlet of air intake duct, middle duct is arranged along the longitudinal direction, front in middle duct is equipped with middle duct combustion chamber, in middle duct turbine is equipped with positioned at the rear of middle duct combustion chamber, turbine is driven by axis to be connected with the transmission of air intake duct compressor, the jet of middle duct is located at the rear end of engine body.Its purpose is to provide a kind of thrust-weight ratios that engine is significantly increased, and improve the utilization ratio of fuel, reduce energy consumption, and can reduce the three rows mouthful turbojet of the discharge capacity of environmentally harmful various pollutants.
Description
Technical field
The present invention relates to a kind of three rows mouthful turbojets.
Background technology
Existing turbojet is during using bavin Water Oil Or Gas or other kinds of fuel, due to injection
The indoor bavin Water Oil Or Gas of burning of inlet casing or other kinds of fuel gasification are not enough, and lead to the utilization ratio to fuel
Relatively low, larger to the consumption of fuel, the discharge capacity of environmentally harmful various pollutants is also larger.
Invention content
The purpose of the present invention is to provide a kind of thrust-weight ratios that engine is significantly increased, and that improves fuel utilizes effect
Rate reduces energy consumption, and can reduce the three rows mouthful turbojet of the discharge capacity of environmentally harmful various pollutants.
The three rows mouthful turbojet of the present invention can also provide the deflecting thrust of diversified forms, and then can allow aircraft
More flexible, higher speed the divertical motion for realizing various complexity.
The three rows mouthful turbojet of the present invention, including engine body, the front of engine body is along front and back
To equipped with air intake duct, the air inlet of air intake duct is located at the front end of engine body, and air intake duct compressor, air inlet are equipped in air intake duct
The gas outlet in road is communicated with the air inlet of the air inlet of middle duct, the air inlet of left duct and right duct, the air inlet of middle duct
Dead astern positioned at the gas outlet of air intake duct, middle duct are arranged along the longitudinal direction, and the front in middle duct is burnt equipped with middle duct
Room, the interior rear positioned at middle duct combustion chamber of middle duct are equipped with turbine, and turbine passes through axis transmission and air intake duct compressor biography
Dynamic to be connected, the jet of middle duct is located at the rear end of engine body；
The air inlet of the left duct is located at the left side at the rear of the gas outlet of air intake duct, and left duct includes a left side from front to back
Air inlet pipeline section and left combustion chamber pipeline section, left air inlet pipeline section are connected with engine body installation, gas outlet and the left side of left air inlet pipeline section
The air inlet of combustion chamber pipeline section is connected, and left combustion chamber pipeline section is arranged along the longitudinal direction, and left combustion chamber is equipped in left combustion chamber pipeline section,
The rear end of left combustion chamber pipeline section is equipped with left spout；
The air inlet of the right duct is located at the right side at the rear of the gas outlet of air intake duct, and right duct includes the right side from front to back
Air inlet pipeline section and right combustion chamber pipeline section, right air inlet pipeline section are connected with engine body installation, gas outlet and the right side of right air inlet pipeline section
The air inlet of combustion chamber pipeline section is connected, and right combustion chamber pipeline section is arranged along the longitudinal direction, and right combustion chamber is equipped in right combustion chamber pipeline section,
The rear end of right combustion chamber pipeline section is equipped with right spout.
Preferably, the left air inlet pipeline section and right air inlet pipeline section are coaxially disposed in left-right direction, are equipped in left air inlet pipeline section
Left air inlet pipeline section compressor, right air inlet pipeline section is interior to be equipped with right air inlet pipeline section compressor, and the power of right air inlet pipeline section compressor inputs
The power input shaft of axis and left air inlet pipeline section compressor is connected with the pto shaft drive of turbine respectively.
Preferably, the power input shaft of the power input shaft and left air inlet pipeline section compressor of the right air inlet pipeline section compressor
It is coaxially disposed respectively along left and right horizontal direction, the end sleeve of the power input shaft of right air inlet pipeline section compressor is equipped with right driven umbrella tooth
The end sleeve of wheel, the power input shaft of left air inlet pipeline section compressor is equipped with left driven bevel pinion, right driven bevel pinion and active umbrella
The tooth on the right side of gear is meshed, and left driven bevel pinion is meshed with the tooth in the left side of driving bevel gear, driving bevel gear suit
On the power output shaft of turbine.
Preferably, connect for heat-resisting soft between the gas outlet and the air inlet of left combustion chamber pipeline section of the left air inlet pipeline section
It connects, is connected for heat-resisting soft between the gas outlet of right air inlet pipeline section and the air inlet of right combustion chamber pipeline section.
Preferably, 2-6 fuel nozzles are respectively equipped in the right combustion chamber, left combustion chamber and middle duct combustion chamber.
The three rows mouthful turbojet of the present invention, using a kind of very succinct technical solution, using right combustion chamber,
Right combustion chamber, left combustion chamber and middle duct combustion chamber can be had respectively for the layout designs of left combustion chamber and middle duct combustion chamber
There is different combustion states, by the ignition temperature of fuel in duct combustion chamber in more reasonably arranging, turbine can be enabled to make
It is all remarkably enhanced with service life, mechanical efficiency etc., and due to without turbine in right duct and left duct, together
Sample enables it that can be all remarkably enhanced in service life, mechanical efficiency etc., and can allow the present invention can be significantly
Improve the thrust-weight ratio of engine.Therefore, pushing away for engine can be significantly increased in three rows of the invention mouthful turbojet
Compare again, improve the utilization ratio of fuel, reduces energy consumption, and the discharge capacity of environmentally harmful various pollutants can be reduced.
The three rows mouthful turbojet of the present invention can also provide the deflecting thrust of diversified forms, and then can allow aircraft
More flexible, higher speed the divertical motion for realizing various complexity.
The three rows mouthful turbojet of the present invention is described in further detail below in conjunction with the accompanying drawings.
Description of the drawings
Fig. 1 is the structural schematic diagram of the three rows mouthful turbojet of the present invention.
Specific implementation mode
As shown in Figure 1, the three rows mouthful turbojet of the present invention, including engine body 1, engine body 1
Front is equipped with air intake duct 2 along the longitudinal direction, and the air inlet of air intake duct 2 is located at the front end of engine body 1, is equipped in air intake duct 2
Air intake duct compressor 3, the air inlet of the gas outlet of air intake duct 2 and the air inlet of middle duct 4, the air inlet and right duct 9 of left duct 8
Mouth communicates, and the air inlet of middle duct 4 is located at the dead astern of the gas outlet of air intake duct 2, and middle duct 4 is arranged along the longitudinal direction, middle culvert
Front in road 4 is equipped with middle duct combustion chamber 5, and the rear that middle duct combustion chamber 5 is located in middle duct 4 is equipped with turbine 6, turbine
Machine 6 is driven by axis to be connected with the transmission of air intake duct compressor 3, and the jet of middle duct 4 is located at the rear end of engine body 1；
The air inlet of the left duct 8 is located at the left side at the rear of the gas outlet of air intake duct 2, and left duct 8 wraps from front to back
Left air inlet pipeline section 10 and left combustion chamber pipeline section 11 are included, left air inlet pipeline section 10 is connected with the installation of engine body 1, left air inlet pipeline section 10
Gas outlet be connected with the air inlet of left combustion chamber pipeline section 11, left combustion chamber pipeline section 11 is arranged along the longitudinal direction, left combustion chamber pipe
Left combustion chamber 12 is equipped in section 11, the rear end of left combustion chamber pipeline section 11 is equipped with left spout 13；
The air inlet of the right duct 9 is located at the right side at the rear of the gas outlet of air intake duct 2, and right duct 9 wraps from front to back
Right air inlet pipeline section 14 and right combustion chamber pipeline section 15 are included, right air inlet pipeline section 14 is connected with the installation of engine body 1, right air inlet pipeline section 14
Gas outlet be connected with the air inlet of right combustion chamber pipeline section 15, right combustion chamber pipeline section 15 is arranged along the longitudinal direction, right combustion chamber pipe
Right combustion chamber 16 is equipped in section 15, the rear end of right combustion chamber pipeline section 15 is equipped with right spout 17.
At work, extraneous air was entered by air intake duct 2 before this to be started the three rows mouthful turbojet of the present invention
In machine body 1, then air intake duct compressor 3 can compress into the air in air intake duct 2 and be delivered to it backward middle duct 4,
In left duct 8 and right duct 9, the compressed air of duct 4 can be burnt back into middle duct combustion chamber 5 in middle duct in
Continue injection backward after room 5 is combustion-supporting and flow through turbine 6, push the power output shaft rotation of turbine 6, turbine 6 then drive into
Air flue compressor 3 is rotated and is compressed into the air in air intake duct 2, and the gas come out by middle duct combustion chamber 5 finally can be therefrom
The jet of duct 4 sprays, can be back into left combustion chamber 12, in left combustion chamber into the compressed air in left duct 8
In 12 it is combustion-supporting it is subsequent it is continuous spray backward, finally sprayed from left spout 13, and entering the compressed air in right duct 9 can be to laggard
Enter right combustion chamber 16, in right combustion chamber 16 it is combustion-supporting it is subsequent it is continuous spray backward, finally sprayed from right spout 17；Due to right duct 9
The high thermal current exported in left combustion chamber 12 in interior right combustion chamber 16 and in left duct 8 need not be used to push turbine to turn
It is dynamic, therefore can allow the ignition temperature of 12 fuel of 16 fuel of right combustion chamber and left combustion chamber that can be significantly larger than existing turbine
Jet engine, and the air flow rate sprayed backward provided can also be some larger provides three whirlpools Pai Kou with this
The main forward thrust of jet engine is taken turns, relative to existing turbojet, hair can be significantly increased in the present invention
The thrust-weight ratio of motivation, and the power that middle duct combustion chamber 5 generates then is mainly used for driving air intake duct compressor 3.
As a further improvement on the present invention, above-mentioned left air inlet pipeline section 10 and right air inlet pipeline section 14 are coaxially set in left-right direction
It sets, left air inlet pipeline section compressor 18 is equipped in left air inlet pipeline section 10, right air inlet pipeline section compressor 19 is equipped in right air inlet pipeline section 14,
The power input shaft of the power input shaft of right air inlet pipeline section compressor 19 and left air inlet pipeline section compressor 18 respectively with turbine 6
The transmission of power output shaft 7 is connected.
It is interior equipped with right air inlet pipeline section that left air inlet pipeline section compressor 18, right air inlet pipeline section 14 are equipped in above-mentioned left air inlet pipeline section 10
The power input shaft of compressor 19, the power input shaft of right air inlet pipeline section compressor 19 and left air inlet pipeline section compressor 18 respectively with
The connected design of the transmission of power output shaft 7 of turbine 6, can allow left combustion in right combustion chamber 16 and left duct 8 in right duct 9
The compressed air that room 12 obtains higher pressure is burnt, allows the ignition temperature higher of right combustion chamber 16 and left combustion chamber 12, it is generated
Thrust bigger.
As a further improvement on the present invention, the power input shaft of above-mentioned right air inlet pipeline section compressor 19 and left air inlet pipeline section
The power input shaft of compressor 18 is coaxially disposed along left and right horizontal direction respectively, the power input shaft of right air inlet pipeline section compressor 19
End sleeve right driven bevel pinion 20 is housed, the end sleeve of the power input shaft of left air inlet pipeline section compressor 18 is equipped with left driven umbrella
Gear 21, right driven bevel pinion 20 are meshed with the tooth on the right side of driving bevel gear 22, left driven bevel pinion 21 and active umbrella tooth
The tooth in the left side of wheel 22 is meshed, and driving bevel gear 22 is sleeved on the power output shaft 7 of turbine 6.
As a further improvement on the present invention, the air inlet of the gas outlet and left combustion chamber pipeline section 11 of above-mentioned left air inlet pipeline section 10
23 are connected for heat-resisting soft between mouthful, is resistance to height between the gas outlet of right air inlet pipeline section 14 and the air inlet of right combustion chamber pipeline section 15
Temperature is flexible coupling 23.When in use, left spout 13, the right side can be changed by rotating left combustion chamber pipeline section 11, right combustion chamber pipeline section 15
The injection direction of spout 17, and then the deflecting that the three rows mouthful turbojet of the present invention can be allowed to be capable of providing diversified forms pushes away
Power, and then can allow aircraft is more flexible, the divertical motion for realizing various complexity of higher speed.
As a further improvement on the present invention, in above-mentioned right combustion chamber 16, left combustion chamber 12 and middle duct combustion chamber 5 respectively
Equipped with 2-6 fuel nozzles.
The three rows mouthful turbojet of the present invention utilizes right combustion chamber using a kind of very succinct technical solution
16, the layout designs of left combustion chamber 12 and middle duct combustion chamber 5, allow right combustion chamber 16, left combustion chamber 12 and middle duct combustion chamber 5
It can be respectively provided with different external acting states, by the ignition temperature of fuel in duct combustion chamber 5 in more reasonably arranging,
Turbine 6 can be enabled all to be remarkably enhanced in service life, mechanical efficiency etc., and in right duct 9 and left duct 8 by
In without turbine 6, equally enabling it that can be all remarkably enhanced in service life, mechanical efficiency etc., and can
Allow the present invention that the thrust-weight ratio of engine can be significantly increased.Therefore, three rows of the invention mouthful turbojet can be substantially
Degree ground improves the thrust-weight ratio of engine, improves the utilization ratio of fuel, reduces energy consumption, and can reduce environmentally harmful each
The discharge capacity of kind pollutant.
The three rows mouthful turbojet of the present invention can also provide the deflecting thrust of diversified forms, and then can allow aircraft
More flexible, higher speed the divertical motion for realizing various complexity.
Claims (5)
1. three rows mouthful turbojet, including engine body (1), the front of engine body (1) are set along the longitudinal direction
There are air intake duct (2), the air inlet of air intake duct (2) to be located at the front end of engine body (1), air intake duct pressure is equipped in air intake duct (2)
Mechanism of qi (3), the gas outlet of air intake duct (2) and the air inlet of middle duct (4), the air inlet of left duct (8) and right duct (9) into
Gas port communicates, and the air inlet of middle duct (4) is located at the dead astern of the gas outlet of air intake duct (2), and middle duct (4) sets along the longitudinal direction
It sets, the front in middle duct (4) is equipped with middle duct combustion chamber (5), and the rear of middle duct combustion chamber (5) is located in middle duct (4)
Equipped with turbine (6), turbine (6) is driven by axis to be connected with air intake duct compressor (3) transmission, and middle duct (4) goes out gas blowout
Mouth is located at the rear end of engine body (1)；
The air inlet of the left duct (8) is located at the left side at the rear of the gas outlet of air intake duct (2), and left duct (8) is from front to back
Including left air inlet pipeline section (10) and left combustion chamber pipeline section (11), left air inlet pipeline section (10) is connected with engine body (1) installation, left
The gas outlet of air inlet pipeline section (10) is connected with the air inlet of left combustion chamber pipeline section (11), and left combustion chamber pipeline section (11) is along the longitudinal direction
Setting, left combustion chamber pipeline section (11) is interior to be equipped with left combustion chamber (12), and the rear end of left combustion chamber pipeline section (11) is equipped with left spout (13)；
The air inlet of the right duct (9) is located at the right side at the rear of the gas outlet of air intake duct (2), and right duct (9) is from front to back
Including right air inlet pipeline section (14) and right combustion chamber pipeline section (15), right air inlet pipeline section (14) is connected with engine body (1) installation, right
The gas outlet of air inlet pipeline section (14) is connected with the air inlet of right combustion chamber pipeline section (15), and right combustion chamber pipeline section (15) is along the longitudinal direction
Setting, right combustion chamber pipeline section (15) is interior to be equipped with right combustion chamber (16), and the rear end of right combustion chamber pipeline section (15) is equipped with right spout (17).
2. three row mouthful turbojet according to claim 1, it is characterised in that：The left air inlet pipeline section (10) and
Right air inlet pipeline section (14) is coaxially disposed in left-right direction, and left air inlet pipeline section compressor (18) is equipped in left air inlet pipeline section (10), right
Be equipped with right air inlet pipeline section compressor (19) in air inlet pipeline section (14), the power input shaft of right air inlet pipeline section compressor (19) and it is left into
The power input shaft of tracheae section compressor (18) is connected with the power output shaft of turbine (6) (7) transmission respectively.
3. three row mouthful turbojet according to claim 2, it is characterised in that：The right air inlet pipeline section compressor
(19) power input shaft of power input shaft and left air inlet pipeline section compressor (18) is coaxially disposed along left and right horizontal direction respectively,
The end sleeve of the power input shaft of right air inlet pipeline section compressor (19) is equipped with right driven bevel pinion (20), left air inlet pipeline section compressor
(18) end sleeve of power input shaft is equipped with left driven bevel pinion (21), right driven bevel pinion (20) and driving bevel gear (22)
The tooth on right side be meshed, left driven bevel pinion (21) is meshed with the tooth in the left side of driving bevel gear (22), driving bevel gear
(22) it is sleeved on the power output shaft (7) of turbine (6).
4. three row mouthful turbojet according to claim 1 or 2 or 3, it is characterised in that：The left air inlet pipeline section
(10) it is connect for heat-resisting soft between gas outlet and the air inlet of left combustion chamber pipeline section (11), the outlet of right air inlet pipeline section (14)
Mouth is connect between the air inlet of right combustion chamber pipeline section (15) for heat-resisting soft.
5. three row mouthful turbojet according to claim 4, it is characterised in that：The right combustion chamber (16), a left side
It is respectively equipped with 2-6 fuel nozzles in combustion chamber (12) and middle duct combustion chamber (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810365525.3A CN108301940A (en) | 2018-04-23 | 2018-04-23 | Three rows mouthful turbojet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810365525.3A CN108301940A (en) | 2018-04-23 | 2018-04-23 | Three rows mouthful turbojet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108301940A true CN108301940A (en) | 2018-07-20 |
Family
ID=62848505
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810365525.3A Withdrawn CN108301940A (en) | 2018-04-23 | 2018-04-23 | Three rows mouthful turbojet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108301940A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023241021A1 (en) * | 2022-06-14 | 2023-12-21 | 韩培洲 | Gas jet stream splitting-type rotor supercharged gas turbine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106481368A (en) * | 2015-08-28 | 2017-03-08 | 中航商用航空发动机有限责任公司 | Electromotor Middle casing |
| CN106523187A (en) * | 2015-09-14 | 2017-03-22 | 高荣江 | Divided flow gas turbine engine |
| FR3042009A1 (en) * | 2015-10-05 | 2017-04-07 | Snecma | TURBO MOTOR WITH BLOWERS DEPORTEES WITH A DIFFERENTIAL SYSTEM |
| US20170369179A1 (en) * | 2016-06-22 | 2017-12-28 | Rolls-Royce Plc | Gas turbine engine |
| CN208138060U (en) * | 2018-04-23 | 2018-11-23 | 孟金来 | Three rows mouthful turbojet |
-
2018
- 2018-04-23 CN CN201810365525.3A patent/CN108301940A/en not_active Withdrawn
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106481368A (en) * | 2015-08-28 | 2017-03-08 | 中航商用航空发动机有限责任公司 | Electromotor Middle casing |
| CN106523187A (en) * | 2015-09-14 | 2017-03-22 | 高荣江 | Divided flow gas turbine engine |
| FR3042009A1 (en) * | 2015-10-05 | 2017-04-07 | Snecma | TURBO MOTOR WITH BLOWERS DEPORTEES WITH A DIFFERENTIAL SYSTEM |
| US20170369179A1 (en) * | 2016-06-22 | 2017-12-28 | Rolls-Royce Plc | Gas turbine engine |
| CN208138060U (en) * | 2018-04-23 | 2018-11-23 | 孟金来 | Three rows mouthful turbojet |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023241021A1 (en) * | 2022-06-14 | 2023-12-21 | 韩培洲 | Gas jet stream splitting-type rotor supercharged gas turbine |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
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| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20180720 |
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| WW01 | Invention patent application withdrawn after publication |