EP3887721A1 - Injecteur de carburant avec moyens de refroidissement - Google Patents
Injecteur de carburant avec moyens de refroidissementInfo
- Publication number
- EP3887721A1 EP3887721A1 EP19801922.6A EP19801922A EP3887721A1 EP 3887721 A1 EP3887721 A1 EP 3887721A1 EP 19801922 A EP19801922 A EP 19801922A EP 3887721 A1 EP3887721 A1 EP 3887721A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- passage
- fuel
- fuel injector
- propeller
- cooling
- 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- Withdrawn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
- 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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/36—Details, e.g. burner cooling means, noise reduction means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
- F23L15/00—Heating of air supplied for combustion
- F23L15/04—Arrangements of recuperators
-
- 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
- F23R3/005—Combined with pressure or heat exchangers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2214/00—Cooling
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/34—Indirect CO2mitigation, i.e. by acting on non CO2directly related matters of the process, e.g. pre-heating or heat recovery
Definitions
- the present invention relates to the field of fuel injectors for a combustion chamber, in particular for a combustion chamber of a gas turbine.
- a fuel injector includes a fuel channel (also called a fuel line), for transporting the fuel and, at the end of the fuel channel, a nozzle for dispersing the fuel within a combustion chamber.
- the nozzle can also be called the injector nose.
- the fuel injector can guarantee the flow rate, the speed, the quantity of fuel injected.
- these parameters are dependent on the temperature: the physical state of the fuel can be modified by the temperature.
- the fuel injector When a fuel injector is placed in the combustion chamber, in which the temperature conditions can be high, the fuel can also be subjected to significant temperature variations which can influence the physical properties of the fuel over time. In the case of liquid fuel, there is also a risk of vaporization of the fuel.
- part of the fuel circuit is in contact with hot air from the outlet of the compressor, possibly heated by an exchanger upstream of the combustion chamber.
- This air can reach high temperatures, which can be between 1500 and 7000.
- temperatures lead to a certain number of consequences concerning the fuel, if it is not or badly cooled.
- deposits can also form on the nozzle, which can eventually deteriorate it, or even cause hot spots favorable to unwanted combustions.
- the cooling of the fuel injector can be implemented by water cooling, the water circulating below the fuel channel in a first direction d flow, and flowing over the fuel channel in a second direction of flow.
- FIG. 1 schematically illustrates such a fuel injector according to the prior art.
- the fuel injector 1 has a fuel channel 2, and a nozzle 3 at the end of the channel 2.
- the fuel injector 1 is provided with water cooling means.
- the arrows represent the circulation of water.
- the body of the fuel injector 1 has a hollow area 4 in the lower part of the fuel injector 1, into which the cooling water is injected.
- the body of the fuel injector 1 has a hollow area 5 in the upper part of the fuel injector, and from which the water (heated water) is extracted.
- the connection of the hollow zones 4 and 5 is not shown.
- Such a system does not allow the fuel to be cooled over the entire length of the fuel injector; in particular the nozzle is not cooled.
- the cooling is not homogeneous: the lower part of the injector is at a temperature lower than the temperature of the upper part of the injector.
- this cooling does not allow an optimized heat exchange.
- the present invention relates to a fuel injector comprising a fuel channel (fuel line), a nozzle, and cooling means with circulation of a fluid extending along the fuel channel.
- the cooling means comprise a first passage around the fuel channel, and a second passage around the first passage.
- the cooling means are configured so that the cooling fluid passes successively through the first passage and then through the second passage in the opposite direction.
- the arrangement of the first passage around the channel, and the second passage around the first passage allows optimal cooling, with temperature uniformity (“around” implies around the periphery of the fuel channel and of the first passage respectively).
- the fuel operating temperature is controlled throughout the line, preventing the formation of vapor in the line, which makes the injector usable with all types of fuels, including petrol even under high temperature conditions.
- fouling is avoided, and due to the efficiency of cooling, air can be used as a coolant, which simplifies the design compared to water cooling.
- this configuration along the fuel channel allows the channel to cool down to the nozzle.
- the present invention relates to a combustion chamber with such a fuel injector and a gas turbine with such a combustion chamber.
- the invention relates to a fuel injector for a combustion chamber, in particular for a combustion chamber of a gas turbine, said fuel injector comprising a fuel channel provided at its end with a nozzle, and cooling means. extending along said fuel channel, a cooling fluid flowing in said cooling means.
- Said cooling means comprise a first passage of said cooling fluid around said fuel channel, and a second passage of said cooling fluid around said first passage, said cooling means being configured so that said cooling fluid flows successively in said first passage then in said second passage in a direction opposite to the direction of flow within said first passage.
- said first passage and / or said second passage (9) have heat exchange projections.
- said heat exchange projections form at least one propeller, and / or a fin and / or a rib.
- the pitch of said propeller is determined as a function of the speed of said cooling fluid in said cooling means.
- said first and second passages respectively comprise a propeller, the height of the propeller of said second passage being less than or equal to the height of the propeller of said first passage, and the pitch of the propeller of said second passage being greater or equal to the pitch of the propeller of said first pass.
- said first passage is delimited by the outer surface of said fuel channel and by the inner surface of a cylindrical sleeve.
- said second passage is delimited by the external surface of said cylindrical sleeve and by the internal surface of an external casing.
- said cooling means comprise means for connecting said first passage to said second passage at the level of said nozzle of said fuel injector.
- said cooling fluid is air, water, oil, or a refrigerating fluid.
- the invention relates to a combustion chamber of a gas turbine, in particular a gas turbine with thermodynamic cycle with recuperator, for the production of energy, in particular electrical energy, comprising a housing housing a flame tube with a perforated diffuser for the passage of hot compressed air, a primary zone, which receives part of the flow of hot compressed air and in which combustion occurs, and a dilution zone where mixing takes place between the burnt gases from the primary zone and the remaining part of the hot compressed air flow.
- Said chamber further comprises a fuel injector according to one of the preceding characteristics.
- the invention relates to a gas turbine, in particular a gas turbine with thermodynamic cycle with recuperator, for the production of energy, in particular electrical energy, comprising at least one compression stage with at least one gas compressor, a heat exchanger, a combustion chamber supplied with fuel by at least one tank, at least one expansion stage with at least one expansion turbine connected by a shaft to the compressor, and a means of energy production .
- a gas turbine in particular a gas turbine with thermodynamic cycle with recuperator, for the production of energy, in particular electrical energy, comprising at least one compression stage with at least one gas compressor, a heat exchanger, a combustion chamber supplied with fuel by at least one tank, at least one expansion stage with at least one expansion turbine connected by a shaft to the compressor, and a means of energy production . It includes a combustion chamber according to one of the preceding characteristics.
- FIG. 1, already described, illustrates a fuel injector according to the prior art.
- FIG. 2 illustrates a fuel injector according to an embodiment of the invention.
- FIG. 3 illustrates a fuel injector according to an embodiment of the invention.
- FIG. 4 illustrates a combustion chamber according to an embodiment of the invention.
- FIG. 5 schematically illustrates a gas turbine according to an embodiment of the invention.
- the present invention relates to a fuel injector for a combustion chamber.
- the fuel injector injects the fuel into the combustion chamber by means of a fuel channel (also called fuel line) provided at its end placed in the combustion chamber of a nozzle, the function of which is to distribute the fuel in the oxidizer chamber.
- the fuel injector has cooling means for cooling the fuel in the fuel channel and in the nozzle. These are cooling means with circulation of a fluid, for example water, air, oil or a refrigerating fluid, or any other fluid which can be used for cooling in the system using the injector.
- the fuel channel and the nozzle can be of any type known to those skilled in the art.
- the cooling means comprise a first passage of the cooling fluid around the fuel channel.
- the cooling means comprise a second passage of the cooling fluid around the first passage.
- the fuel injector includes the fuel channel, the first passage of the coolant and the second pass of the coolant.
- This configuration of the cooling means allows optimized cooling of the fuel in the injector.
- the first pass allows the cooling of the fuel and the second pass makes it possible to maintain the first pass at a low temperature, thus increasing the efficiency of the cooling of the fuel.
- fouling of the fuel injector is avoided, and due to the cooling efficiency, air can be used as the coolant, which simplifies design compared to water cooling.
- the fuel injector can have a substantially cylindrical shape.
- the fuel channel, the first passage and the second passage may be substantially coaxial.
- the cooling means extend along the fuel channel, which allows cooling of the entire fuel channel, and as close as possible to the nozzle, located at the end of the fuel channel.
- the cooling means are configured so that the fluid flows in the second passage in a direction opposite to the direction of flow of the fluid in the first passage.
- the coolant flows in the first passage in a flow direction identical to the direction of flow of the fuel in the fuel channel, and flows in the second passage in a direction of flow opposite to the direction of flow of fuel in the fuel channel. This in particular makes it possible to limit the size of the means for injecting and withdrawing the cooling fluid.
- the first passage and / or the second passage may include heat exchange projections.
- the purpose of these projections is to increase the contact surface between the cooling fluid and the structure of the exchanger, which is intended to increase the heat exchanges.
- the first pass and the second pass include heat exchange projections. This configuration is optimal in terms of heat exchange.
- the projections can form a propeller and / or a fin and / or a rib and / or any other similar element.
- the projections Preferably, the projections form a helix.
- This design allows, in addition to promoting heat exchange, to give a movement of the fluid over the entire periphery of the channel, which ensures a uniform heat exchange.
- the fuel operating temperature is controlled throughout the fuel channel, preventing the formation of vapor in the fuel channel, which makes the injector usable with all types of fuels, including gasoline even under conditions high temperatures.
- the first passage and the second passage comprise a propeller.
- the dimensions of the propellers can be determined as a function of the speed of the cooling fluid in the first and second passages.
- the height of the propeller of the second passage is less than or equal, preferably strictly less, than the height of the propeller of the first passage.
- the pitch of the propeller of the second pass is greater than or equal, preferably strictly greater than the pitch of the propeller of the first pass.
- the fluid flow in the second passage is substantially identical to the fluid flow in the first passage. This design allows the compactness of the fuel injector, while maintaining high cooling performance.
- the first passage can be delimited by the outer surface of the fuel channel, and by the inner surface of a cylindrical sleeve. This achievement is easy to implement and assemble.
- the projections for example the propeller, can be made on the outer surface of the fuel channel.
- the second passage can be limited by the external surface of the cylindrical sleeve and by the internal surface of an external casing.
- the outer casing can have a substantially cylindrical shape. This achievement is easy to implement and assemble.
- the projections for example the propeller, can be made on the outer surface of the cylindrical sleeve.
- protrusions can also be provided on the internal surface of the sleeve to increase the heat exchange surfaces, and therefore the cooling, between the first passage and the second passage.
- the cooling means may include means for connecting the first passage to the second passage at the nozzle.
- these connection means fulfill the role of cooling the nozzle, and the role of implementing the flow of the fluid from the first passage to the second passage.
- These connection means can take the form of a volume at the end of the first passage, this connection volume being connected on the one hand to the first passage and on the other hand to the second passage.
- FIG. 2 illustrates, schematically and in a nonlimiting manner, a fuel injector according to an embodiment of the invention.
- Figure 2 is a three-dimensional sectional view.
- the injector 1 conventionally comprises a fuel channel 2 and a nozzle 3, arranged at the end of the fuel channel 2.
- the outer surface of the channel 2 is provided with a propeller 7, which delimits a first passage 6 of the cooling with a cylindrical sleeve 1 1.
- the external surface of the cylindrical sleeve 1 1 is provided with a propeller 10, which delimits a second passage 9 of the cooling fluid with an external casing 12.
- the height of the propeller 10 of the second passage 9 is less than the propeller 7 of the first passage 6.
- the pitch of the propeller 10 of the second passage 9 is greater than the pitch of the propeller 7 of the first passage 6.
- the fuel injector 1 has a volume 8 serving as a connection between the first passage 6 and the second passage 9. The volume 8 is located at the end of the fuel channel 2 near the nozzle 3.
- the coolant circulates in the first passage 6 in the direction of the nozzle 3 (direction from left to right for the representation of the figure) passing between the turns of the propeller 7, then through the connection volume 8, then in the second passage 9 from the nozzle 3 (direction from right to left for the representation of the figure) passing between the turns of the propeller 10.
- FIG 3 illustrates schematically and without limitation, some components of a fuel injector according to an embodiment of the invention.
- This figure corresponds to the embodiment of Figure 2, in which the casing 12 is not shown.
- the cylindrical sleeve 11 is shown in transparency.
- the injector comprises a fuel channel 2 and a nozzle 3, arranged at the end of the fuel channel 2.
- the outer surface of the channel 2 is provided with a propeller 7, which delimits a first passage 6 of the coolant with a cylindrical sleeve 1 1.
- the outer surface of the cylindrical sleeve 1 1 is provided with a propeller 10, which defines a second passage 9 of the cooling fluid with an outer casing (not shown).
- the height of the propeller 10 of the second passage 9 is less than the propeller 7 of the first passage 6.
- the pitch of the propeller 10 of the second passage 9 is greater than the pitch of l propeller 7 of the first passage 6.
- the fuel injector according to the invention can be used in a whole hot environment.
- the fuel injector can be used in a combustion chamber, in particular of a gas turbine.
- the fuel injector can be used in a boiler or industrial oven burner for example.
- the invention also relates to a combustion chamber, in particular of a gas turbine, and more particularly of a gas turbine with thermodynamic cycle with recuperator for the production of energy.
- the combustion chamber comprises a housing with a flame tube fitted with a perforated diffuser for the passage of hot compressed air, a primary zone, which receives part of the flow of hot compressed air, and in which the combustion, and a dilution zone where the mixing takes place between the burnt gases from the primary zone and the remaining part of the hot compressed air flow.
- the combustion chamber further comprises a fuel injector according to any one of the combinations of variants described above.
- the injector according to the invention is particularly suitable for such an application, since the injector allows a good functioning even when the injector is arranged in a medium at high temperature, as is the case within of such a combustion chamber.
- the invention relates to a gas turbine, in particular a thermodynamic cycle gas turbine with recuperator for the production of energy, in particular electrical energy.
- a gas turbine comprises at least one compression stage with a gas compressor, a heat exchanger, a combustion chamber supplied with fuel by at least one tank, an expansion stage with an expansion turbine connected by a shaft to the compressor, and a means of energy production.
- the gas turbine includes a combustion chamber as described above.
- Such a combustion chamber and such a gas turbine can comply with those described in the applicant's patent applications FR 3041742 (WO 2017/055074) and FR 3,049,044 (WO 2017/157631).
- the illustrated gas turbine is more particularly a microturbine 100, operating from at least one fuel, such as a liquid fuel, for example of the diesel, gasoline or jet fuel type, or a gaseous fuel, such than natural gas.
- a fuel such as a liquid fuel, for example of the diesel, gasoline or jet fuel type, or a gaseous fuel, such than natural gas.
- the gas turbine comprises at least one compression stage 13 with at least one gas compressor 14, a heat exchanger 16 (or recuperator), a combustion chamber 18 (or burner) supplied with fuel by at least one tank 20, at least one expansion stage 22 with at least one expansion turbine 24 connected by a shaft 26 to the compressor.
- This gas turbine also includes a means of producing energy, here electric, which includes an electric generator 28 advantageously placed on the shaft 26 between the compressor and the turbine.
- this generator can be alternately connected to the expansion turbine or to the compressor by a shaft other than that connecting the turbine and the compressor.
- the heat exchanger 16 can be a cross-flow exchanger, for example of the shell-tube type or with alternating plates with two inlets and two outlets.
- the compressor 14 comprises an inlet 30 for fresh gas containing oxygen, here outside air generally at room temperature, and an outlet for compressed air 32 leading to an inlet for compressed air 34 of the exchanger 16 by a line 36.
- the hot compressed air outlet 38 of this exchanger is connected by a line 40 to a hot compressed air inlet 42 of the burner 18.
- the superheated gas outlet 44 of the burner is connected by a line 45 to the 'inlet 46 of the turbine, the outlet 48 of which is connected to another inlet 50 of the exchanger by a line of expanded superheated gases 52.
- the exchanger 16 also includes an outlet of cooled gases 54 to be directed to all means of evacuation and treatment, such as a chimney (not shown).
- the burner 18 comprises an outer casing 56, of cylindrical shape, closed at one of its ends by an injector bulkhead 58 and at the other of its ends by an annular bulkhead 60 with an opening 62.
- This burner also comprises a flame tube 64, also of substantially cylindrical shape, housed coaxially in the housing being of diameter smaller than the housing but of diameter identical to that of the opening 62 of the annular partition 60.
- This tube comprises one end closed by a diffusion partition 66 opposite and at a distance from the injector-carrying partition 58 and an open end 67 which passes through the annular partition cooperating in leaktightness with the internal diameter of this annular partition to form the outlet 44 ( Figure 5) of this burner.
- the housing carries, on its periphery 68 and near the annular partition 60, the admission of hot compressed air 42 to introduce this air into the space 70 formed between the housing and the flame tube as well as into the space 72 formed between the injector bulkhead and the diffusion bulkhead.
- the injector bulkhead comprises a plate, through which is mounted a fuel injector 1 (as described above), here in the form of an injector coaxial with the flame tube.
- a fuel injector 1 as described above
- This plate is surrounded by a air deflecting wall 78, here semi-toric whose concavity is directed towards the flame tube and which is connected to the periphery 68 of the housing.
- the flame tube comprises circumferential rows of radial dilution orifices 80 placed at a distance from the diffusion partition and close to the annular partition of the housing, being regularly distributed advantageously opposite the inlet 42.
- This flame tube comprises also a flame stabilizer 82 which is placed on the diffusion partition 66 and inside the tube while being housed in an orifice 84 provided in this diffusion partition.
- This flame stabilizer makes it possible to generate zones of recirculation of burnt gases facilitating the ignition of the fuel and locally providing inert materials in the reaction zone. It also allows the physico-chemical stabilization of the flame as well as the confinement of combustion.
- the burner also includes an ignition device 86 for a fuel mixture.
- this device can be a spark plug of the type for an internal combustion engine with spark ignition, a glow plug, ignition electrodes, etc.
- the position of the ignition device must be in an area of the burner which is not directly exposed to the flame in order to preserve it.
- the active end of this ignition device is located just after the flame stabilizer.
- the burner thus formed comprises a flame tube with an injection / mixing zone ZM where the hot compressed air is mixed with the fuel and the start of combustion, a primary zone ZP in which combustion takes place, a ZD dilution zone where the mixing takes place between the burnt gases from the primary zone and the hot compressed air from the dilution holes.
- the main purpose of this dilution zone is to reduce the temperature of the gases leaving the dilution zone and to allow good spatial homogenization of these before entering the expansion turbine.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1871910A FR3088969B1 (fr) | 2018-11-27 | 2018-11-27 | Injecteur de carburant avec moyens de refroidissement |
PCT/EP2019/081817 WO2020109089A1 (fr) | 2018-11-27 | 2019-11-19 | Injecteur de carburant avec moyens de refroidissement |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3887721A1 true EP3887721A1 (fr) | 2021-10-06 |
Family
ID=66218197
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19801922.6A Withdrawn EP3887721A1 (fr) | 2018-11-27 | 2019-11-19 | Injecteur de carburant avec moyens de refroidissement |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP3887721A1 (fr) |
FR (1) | FR3088969B1 (fr) |
WO (1) | WO2020109089A1 (fr) |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2166395A5 (fr) * | 1971-02-09 | 1973-08-17 | Lehougre Jean | |
DE19645961A1 (de) * | 1996-11-07 | 1998-05-14 | Bmw Rolls Royce Gmbh | Kraftstoffeinspritzvorrichtung für eine Gasturbinen-Brennkammer mit einer flüssigkeitsgekühlten Einspritzdüse |
US6357237B1 (en) * | 1998-10-09 | 2002-03-19 | General Electric Company | Fuel injection assembly for gas turbine engine combustor |
FR2817016B1 (fr) * | 2000-11-21 | 2003-02-21 | Snecma Moteurs | Procede d'assemblage d'un injecteur de combustible pour chambre de combustion de turbomachine |
US10739005B2 (en) * | 2013-08-16 | 2020-08-11 | Raytheon Technologies Corporation | Cooled fuel injector system for a gas turbine engine |
US10385809B2 (en) * | 2015-03-31 | 2019-08-20 | Delavan Inc. | Fuel nozzles |
FR3041742B1 (fr) | 2015-09-30 | 2017-11-17 | Ifp Energies Now | Chambre de combustion d'une turbine, notamment d'une turbine a cycle thermodynamique avec recuperateur, pour la production d'energie, en particulier d'energie electrique. |
FR3049044B1 (fr) | 2016-03-18 | 2019-12-20 | IFP Energies Nouvelles | Chambre de combustion d'une turbine, notamment d'une turbine a cycle thermodynamique avec recuperateur, pour la production d'energie, en particulier d'energie electrique. |
-
2018
- 2018-11-27 FR FR1871910A patent/FR3088969B1/fr active Active
-
2019
- 2019-11-19 EP EP19801922.6A patent/EP3887721A1/fr not_active Withdrawn
- 2019-11-19 WO PCT/EP2019/081817 patent/WO2020109089A1/fr unknown
Also Published As
Publication number | Publication date |
---|---|
FR3088969B1 (fr) | 2021-02-19 |
FR3088969A1 (fr) | 2020-05-29 |
WO2020109089A1 (fr) | 2020-06-04 |
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