WO2020058617A1 - Method for determining the flow rate of combustible fluid injected inside a combustion chamber without additional diaphragm - Google Patents
Method for determining the flow rate of combustible fluid injected inside a combustion chamber without additional diaphragm Download PDFInfo
- Publication number
- WO2020058617A1 WO2020058617A1 PCT/FR2019/052146 FR2019052146W WO2020058617A1 WO 2020058617 A1 WO2020058617 A1 WO 2020058617A1 FR 2019052146 W FR2019052146 W FR 2019052146W WO 2020058617 A1 WO2020058617 A1 WO 2020058617A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- injector
- pressure
- combustible fluid
- combustion chamber
- orifice
- Prior art date
Links
Classifications
-
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
- F02C7/222—Fuel flow conduits, e.g. manifolds
-
- 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
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/263—Control of fuel supply by means of fuel metering valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N1/00—Regulating fuel supply
- F23N1/002—Regulating fuel supply using electronic means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
- G01F1/05—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects
- G01F1/34—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects by measuring pressure or differential pressure
- G01F1/36—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow by using mechanical effects by measuring pressure or differential pressure the pressure or differential pressure being created by the use of flow constriction
- G01F1/40—Details of construction of the flow constriction devices
- G01F1/42—Orifices or nozzles
-
- 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
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/301—Pressure
- F05D2270/3015—Pressure differential pressure
-
- 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
- F05D2270/00—Control
- F05D2270/30—Control parameters, e.g. input parameters
- F05D2270/306—Mass flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N5/00—Systems for controlling combustion
- F23N5/18—Systems for controlling combustion using detectors sensitive to rate of flow of air or fuel
- F23N2005/185—Systems for controlling combustion using detectors sensitive to rate of flow of air or fuel using detectors sensitive to rate of flow of fuel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23N—REGULATING OR CONTROLLING COMBUSTION
- F23N2241/00—Applications
- F23N2241/20—Gas turbines
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F15/00—Details of, or accessories for, apparatus of groups G01F1/00 - G01F13/00 insofar as such details or appliances are not adapted to particular types of such apparatus
- G01F15/001—Means for regulating or setting the meter for a predetermined quantity
- G01F15/002—Means for regulating or setting the meter for a predetermined quantity for gases
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F15/00—Details of, or accessories for, apparatus of groups G01F1/00 - G01F13/00 insofar as such details or appliances are not adapted to particular types of such apparatus
- G01F15/001—Means for regulating or setting the meter for a predetermined quantity
- G01F15/003—Means for regulating or setting the meter for a predetermined quantity using electromagnetic, electric or electronic means
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F15/00—Details of, or accessories for, apparatus of groups G01F1/00 - G01F13/00 insofar as such details or appliances are not adapted to particular types of such apparatus
- G01F15/005—Valves
Definitions
- the present invention relates to a method for determining the flow rate of combustible fluid injected inside a turbine with one or more combustion chambers of a turbine, in particular of a gas turbine.
- the invention also relates to a method for triggering such a determination method.
- a gas turbine generally comprises an intake section, a
- Each combustion chamber may include one or more injectors of combustible fluid.
- a flow path can be defined through the gas turbine.
- the air flows into the compressor, to increase its pressure.
- Compressed air then flows through to all of the combustion chambers, where it mixes with fuel such as gas to form a combustible air-fuel mixture.
- the air-fuel mixture is injected into the combustion chamber to be burned. This combustion generates hot gases injected into the turbine to extract energy from the hot gases. Then the exhaust can be exhausted from the gas turbine through the exhaust section.
- the regulation and protection system for large power gas turbines generally includes protection or limitation during start-up and before detection of combustion or flame.
- This protection consists in limiting the quantity of unburnt gas fuel, during the ignition of the combustion chamber, before the detection of the flame, which enters the turbine and the recovery boiler, located downstream.
- the measurement of the flow rate of the combustible fluid is necessary for regulating the turbine in normal operation and also before the flame detection.
- Most of the installed flow measurement systems are suitable for measurement at nominal load, that is to say after the generator is switched on and synchronized with the network.
- This measurement directly infers the instantaneous volume flow.
- This pressure drop located at the level of the diaphragm (or restriction orifice) is not a loss of energy (pressure drop) but a transfer of energy "pressure” into energy "speed”.
- the measurement method requires the use of an additional diaphragm or restriction orifice arranged in the passage of the injected combustible fluid.
- dimensioning of the effective area makes it possible to define the pressure at the inlet of the injector.
- the dimensioning of this effective area ensures that the pressure ratios in the injectors do not exceed the maximum or minimum admissible limits, known as the critical pressure ratio CPR (1.78) beyond which the flow remains constant.
- the invention provides a method for determining the flow rate of combustible fluid injected inside a combustion chamber of a turbine, the combustible fluid being injected inside the combustion chamber at through an orifice of at least one injector, the method comprising the following steps:
- the flow rate of combustible fluid injected inside the combustion chamber is determined as being the sum of the flow rates of combustible fluid flowing through the plurality of injectors.
- the pressure of the combustible fluid downstream of the orifice of the injector is the pressure inside the combustion chamber.
- the combustible fluid is a mixture of gases.
- the pressure of the combustible fluid upstream of the injector orifice is determined
- the determination of the flow rate of combustible fluid injected inside the combustion chamber is carried out before the ignition of the combustion chamber
- the determination of the flow rate of combustible fluid is carried out when the pressure upstream of a space where said at least one injector opens is strictly greater than the pressure at said space.
- the turbine According to one embodiment of the determination method, the turbine
- the turbine According to one embodiment of the determination method, the turbine
- At least one fuel supply circuit of said at least one combustion chamber comprising at least one fuel supply circuit of said at least one combustion chamber, said at least one fuel supply circuit being connected to at least one distribution device making it possible to supply said at least one injector, in which the flow of combustible fluid injected inside the combustion chamber is determined as a function of the pressure measured at a single distribution device.
- the invention also relates to a method for triggering the
- FIG. 1 schematically shows a partial sectional view of a gas turbine.
- FIG. 2 represents an operating diagram of the gas turbine of FIG. 1.
- the auxiliary fuel supply system 10 for a gas turbine 100, is connected to a fuel source at a pressure P1.
- the auxiliary system 10 may include a filter 70, a stop valve 80 and a pressure control valve 90, downstream of which a pressure P2 is maintained.
- the gas turbine 100 includes a section
- Each combustion chamber 120 may include one or more types of injectors 112, 113, 114, 115.
- a flow path can be defined through the gas turbine 100.
- air enters the gas turbine 100 through the intake section 102.
- the air flows into the compressor 104, which compresses the air to form compressed air.
- the compressed air enters through 140 into the combustion chamber assembly, to mix with the fuel such as gas, to form a fuel air-fuel mixture at the space 111.
- One or more of the injectors 112, 113, 114, 115 open into this space 111
- the air-fuel mixture burned in the combustion chamber 120 generates a flow of hot gases passing through a pipe 130 to the turbine section 106 where the kinetic energy of the hot gases is transformed into mechanical energy, before being evacuated by the exhaust section 108.
- combustion is generally expressed in terms of pressure ratios relative to the discharge pressure of the compressor (PCD) measured by the pressure sensor 160.
- This pressure ratio is generally between 1.1 * PCD and 1.5 * PCD.
- a pressure sensor 150 is used to constantly monitor the pressure difference between the fuel line and the PCD pressure at the outlet of the compressor 104.
- Combustion systems can include at least one combustion chamber 120 with at least one type of injector each with a specific flow rate. Homogeneous fuel distribution in each type
- injector is preferably obtained via a dedicated distribution circuit.
- a fuel distribution system for at least one combustion chamber 120 each provided with at least one type of injector, for example four, but only one of each type 112, 113, 114 , 115 was represented per room.
- Each type of injector is supplied by four fuel supply circuits C1, C2, C3, C4 each connected to a distribution device D1, D2, D3, D4 making it possible to supply the injectors 112, 113,
- Each distribution channel can have
- the injectors 112, 113, 114, 115 can be arranged in the same combustion chamber 120, for example in a circular configuration around a longitudinal axis of the combustion chamber 120, as shown in FIG. 2.
- the total number of injectors in the combustion system is the number of types of injectors per chamber times the number of chambers.
- the total flow entering combustion can thus be deduced in a simplified manner by estimating the flow through at least one injector of each type 112, 113, 114, 115 then by multiplying by the number of combustion chambers 120.
- a measurement single on a distribution device is possible in the case of a partial measurement of flow, or for the need of tests of the combustion system.
- the determination method is described below in association with a turbine such as the gas turbine 100 shown in Figures 1 and 2.
- the determination method can be implemented in any turbine comprising at least one combustion chamber provided with at least one injector for injecting a combustible fluid inside the combustion chamber and when in normal operation, the pressure upstream of the network of injectors in each combustion chamber may exceed a pressure downstream.
- the method uses the principle of measuring flow in an orifice, for this it considers the characteristics of at least each type of injector 112, 113, 114, 115 used in combustion 120 such as the effective area (Ae) and the pressures upstream and downstream of each injector.
- downstream and upstream pressure makes it possible to estimate a mass flow rate in each type of injector and then determine the total flow rate of combustible fluid injected into the set of combustion chambers 120.
- the flow rate of combustible fluid injected inside the combustion chambers 120 is determined as being the sum of the estimated flow rates of fuel flowing through each type of injectors 112, 113, 114, 115 and multiplying it. by the number of rooms 120.
- the method considers the use of the effective area of at least each type of injector 112, 113, 114, 115 in the combustion chamber 120.
- Each injector is characterized to have an effective area for the passage of the combustible fluid between the cover 110 and after the injector at 111 whose
- the effective passage area can be likened to an orifice.
- the pressure at the cover at 110 can be calculated for each of the design points based on: mass flow rates, the pressure inside the combustion chamber at 111 and the properties of the combustible gas.
- the term "upstream pressure” is defined as being a static pressure of the fuel at a point 110 located upstream or at the inlet of any of the injectors 112, 113, 114, 115.
- Pc fuel gas pressure
- the pressure downstream of the injectors or inside the combustion chamber at 111 is the pressure of the air / gas mixture in the chamber. This pressure cannot be measured directly, but we can measure a relatively close pressure which is the PCD 160. Indeed, the pressure in the combustion chamber (Pcc) is equivalent to the compressor discharge pressure (CPD) minus the pressure drop of the compressed air leaving the compressor through the combustion chamber (which is known or estimated as a percentage).
- the flow rate of combustible fluid injected inside the combustion chamber can be determined as a function of the flow rate of combustible fluid flowing through the orifice of said at least one injector.
- This orifice is disposed inside the combustion chamber as shown in FIG. 1.
- Each orifice of the plurality of injectors 112, 113, 114, 115 is disposed inside the corresponding combustion chamber.
- This determination therefore does not require the addition of an additional restriction orifice or diaphragm for measuring the flow rate. The determination process is thus simplified and less expensive.
- the absence of diaphragm or additional restriction orifice makes it possible to avoid the creation of an additional pressure loss in the circuit of the combustible fluid.
- the flow rate of combustible fluid injected inside the combustion chamber 120 is determined when the pressure of the combustible fluid P2 upstream of the orifice of the injector 112, 113, 114, 115 is greater than the pressure downstream to the space 111 and before the ignition of the combustion chamber.
- this determination makes it possible to determine the quantity of unburnt gas fuel injected during the ignition of the combustion chamber 120, before the detection of the flame, which enters the turbine 100 and the recovery boiler located downstream. This regulates and therefore protects the gas turbine.
- the determination of the flow rate of combustible fluid injected inside each of the combustion chambers 120 is carried out until all the combustion chambers are ignited.
- the method corresponds to a method of indirect measurement of flow rate
- the method is particularly simple to implement because it does not use an additional diaphragm to estimate the flow rate and does not produce any additional pressure drop.
- the flow measurement as close as possible to the injection into the combustion chamber makes it possible to have the fairest possible value (apart from measurement errors) unlike the flow meter measurement often made upstream on the line fuel supply.
- the supply line can have many leaks between this flowmeter and the combustion chambers, as is the case with gas vents, which can distort the measurement.
- a measurement by flow meter upstream of the line, by a vent which leaks too much will cause a loss of operability of the machine.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Feeding And Controlling Fuel (AREA)
- Combined Controls Of Internal Combustion Engines (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP19794597.5A EP3853561A1 (en) | 2018-09-21 | 2019-09-16 | Method for determining the flow rate of combustible fluid injected inside a combustion chamber without additional diaphragm |
JP2021516469A JP2022501597A (en) | 2018-09-21 | 2019-09-16 | A method for determining the flow rate of combustible fluid injected into the combustion chamber without an additional orifice plate. |
CN201980062077.2A CN113167610A (en) | 2018-09-21 | 2019-09-16 | Method for determining the flow rate of combustible fluid injected into a combustion chamber without using an additional orifice plate |
US17/278,382 US11994289B2 (en) | 2018-09-21 | 2019-09-16 | Method for determining the flow rate of combustible fluid injected into a combustion chamber without an additional orifice plate |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1858607 | 2018-09-21 | ||
FR1858607A FR3086344A1 (en) | 2018-09-21 | 2018-09-21 | METHOD FOR DETERMINING THE FUEL GAS FLOW INJECTED WITHIN A GAS TURBINE WITH ONE OR MORE COMBUSTION CHAMBERS WITHOUT ADDITIONAL DIAPHRAGM |
FR1873577 | 2018-12-20 | ||
FR1873577A FR3086345B1 (en) | 2018-09-21 | 2018-12-20 | PROCESS FOR DETERMINING THE FLOW OF FUEL FLUID INJECTED INSIDE A COMBUSTION CHAMBER WITHOUT AN ADDITIONAL DIAPHRAGM |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2020058617A1 true WO2020058617A1 (en) | 2020-03-26 |
Family
ID=68344895
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/FR2019/052146 WO2020058617A1 (en) | 2018-09-21 | 2019-09-16 | Method for determining the flow rate of combustible fluid injected inside a combustion chamber without additional diaphragm |
Country Status (1)
Country | Link |
---|---|
WO (1) | WO2020058617A1 (en) |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1999067617A1 (en) | 1998-06-23 | 1999-12-29 | H.R. Krueger Machine Tool, Inc. | Flowmeter |
US20070186557A1 (en) | 2006-02-15 | 2007-08-16 | General Electric Company | Pressure control method and system to reduce gas turbine fuel supply pressure requirements |
US20090071119A1 (en) * | 2004-06-10 | 2009-03-19 | Snecma Moteurs | Method and system for protecting gas turbine fuel injectors |
US20130312421A1 (en) * | 2012-05-24 | 2013-11-28 | Solar Turbines Incorporated | Fuel control system for a gas turbine engine |
-
2019
- 2019-09-16 WO PCT/FR2019/052146 patent/WO2020058617A1/en active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1999067617A1 (en) | 1998-06-23 | 1999-12-29 | H.R. Krueger Machine Tool, Inc. | Flowmeter |
US20090071119A1 (en) * | 2004-06-10 | 2009-03-19 | Snecma Moteurs | Method and system for protecting gas turbine fuel injectors |
US20070186557A1 (en) | 2006-02-15 | 2007-08-16 | General Electric Company | Pressure control method and system to reduce gas turbine fuel supply pressure requirements |
US20130312421A1 (en) * | 2012-05-24 | 2013-11-28 | Solar Turbines Incorporated | Fuel control system for a gas turbine engine |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US9828947B2 (en) | Fuel gas supply method and supply unit for gas engine | |
EP2325462A1 (en) | Method of detection of abnormal combustion for internal combustion engines based on a plurality of combustion indicators | |
EP0153207B1 (en) | Control system for a supercharged internal-combustion engine with a by-pass conduit and an auxiliary combustion chamber | |
FR2705734A1 (en) | Method and device for improving the safety of fluid filters. | |
FR2978211A1 (en) | METHOD FOR MONITORING A PRESSURE RELIEF VALVE OF A FUEL INJECTION CIRCUIT FOR TURBOMACHINE | |
EP0307264B1 (en) | Fuel distribution circuit affording enhanced fuel cooling | |
FR2965586A1 (en) | METHOD AND DEVICE FOR STARTING GAS TURBINE | |
FR2629867A1 (en) | GAME CONTROL DEVICE | |
FR3030629A1 (en) | INSTALLATION AND METHOD FOR SUPPLYING A COMBUSTION CHAMBER HAVING A VENTILATED CAVITY BY HOT AIR FROM PURGE | |
FR3030628A1 (en) | INSTALLATION AND METHOD FOR SUPPLYING A COMBUSTION CHAMBER, IN PARTICULAR A GAS TURBINE, WITH WATER INJECTION IN A CAVITY OF A PURGE CIRCUIT | |
EP3874249A1 (en) | Device and method for monitoring the lifetime of a hydraulic apparatus of an aircraft | |
FR3081514A1 (en) | PROPELLANT AIRCRAFT ASSEMBLY AND METHOD FOR REDUCING VENTILATION AIR FLOW IN THE AIRCRAFT PROPELLANT ASSEMBLY | |
WO2017216490A1 (en) | Clogging monitoring in a starter injector purge circuit for a turbomachine | |
EP3853561A1 (en) | Method for determining the flow rate of combustible fluid injected inside a combustion chamber without additional diaphragm | |
WO2020058617A1 (en) | Method for determining the flow rate of combustible fluid injected inside a combustion chamber without additional diaphragm | |
FR2779807A1 (en) | VARIABLE GEOMETRY GAS TURBINE COMBUSTION CHAMBER | |
CA2643672C (en) | Annular combustion chamber for gas turbine engines | |
WO2011154528A1 (en) | Method and device for starting or stopping a gas turbine engine | |
FR2681377A1 (en) | PROTECTION SYSTEM AGAINST THE EXTINGUISHING OF A TURBOMACHINE IN CASE OF INGESTION OF MASSIVE WATER OR HAIL. | |
FR3088956A1 (en) | LUBRICATION SYSTEM FOR AN AIRCRAFT TURBOMACHINE, INCLUDING IMPROVED LEAKAGE DETECTION MEANS | |
FR2962490A1 (en) | DEVICE FOR EXTINGUISHING GAS LEAKS IN A GAS FUEL SUPPLYING DEVICE OF A GAS TURBINE AND METHOD THEREOF | |
FR2712979A1 (en) | Method and apparatus for determining the exhaust gas temperature with a lambda probe used in a motor vehicle or a heating installation | |
FR2958012A1 (en) | Annular combustion chamber for use between upstream high pressure compressor and downstream high pressure turbine of airplane, has rotary walls comprising orifices whose axis is inclined with respect to axis of chamber at specific angle | |
FR3090042A1 (en) | Improved feed flow control device | |
FR2971295A1 (en) | METHOD AND DEVICE FOR MONITORING A PRESSURE DIFFERENCE SENSOR |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
121 | Ep: the epo has been informed by wipo that ep was designated in this application |
Ref document number: 19794597 Country of ref document: EP Kind code of ref document: A1 |
|
ENP | Entry into the national phase |
Ref document number: 2021516469 Country of ref document: JP Kind code of ref document: A |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2021108350 Country of ref document: RU |
|
ENP | Entry into the national phase |
Ref document number: 2019794597 Country of ref document: EP Effective date: 20210421 |