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
  • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
  • F23R3/44—Combustion chambers comprising a single tubular flame tube within a tubular casing
• • 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
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
  • F23C9/00—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber
  • F23C9/006—Combustion apparatus characterised by arrangements for returning combustion products or flue gases to the combustion chamber the recirculation taking place in the combustion chamber
• • 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
  • 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
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/04—Air inlet arrangements
  • F23R3/06—Arrangement of apertures along the flame tube
• • 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
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
• • 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
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
  • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
  • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection 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
  • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
  • F23R3/26—Controlling the air flow
• • 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
  • F23R3/36—Supply of different fuels
• • 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
  • F05D2220/70—Application in combination with
  • F05D2220/76—Application in combination with an electrical generator
• • 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
  • F05D2240/00—Components
  • F05D2240/35—Combustors or associated equipment
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
  • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
  • F23C2900/03001—Miniaturized combustion devices using fluid fuels
• • 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
• • 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
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

• the present invention relates to a combustion chamber of a turbine, in particular a turbine with a thermodynamic cycle with recuperator, for the production of energy, in particular electrical energy.
• It relates more particularly to a microturbine with recuperator for the production of electricity from a liquid or gaseous fuel.
• microturbine a small power turbine usually less than 200KW.
• a turbine with recuperator generally comprises at least one compression stage with at least one compressor, a combustion chamber (or burner), at least one expansion stage with at least one turbine a heat exchange device (or recuperator) between the compressor and the burner for heating the compressed gases by the compressor to send them with a high temperature to the burner, this exchange device being traversed by the hot gases from the turbine.
• the burner comprises an outer casing through which circulates the hot compressed air from the recuperator and a flame tube, located inside this casing, in which takes place combustion.
• the flame tube comprises a primary zone that receives a portion of the total hot compressed air flow rate and in which combustion occurs and a dilution zone where mixing between the primary zone burned gases and the compressed gases occurs. from the dilution holes on the tube.
• the primary zone further comprises a perforated diffuser allowing the passage of hot compressed air as well as fuel from a fuel injection system (liquid or gas) placed upstream of the diffuser.
• a fuel injection system liquid or gas
• a turbine with recuperator has a low compression ratio (of the order of 3 to 5 bars of pressure) and low inlet temperatures of the turbine in comparison with high-power aeronautical or stationary gas turbines.
• the cost of design is also a lock.
• this type of chamber is characterized by a strong interaction between the flame and the wall which requires the choice of expensive materials on a large volume and a cooling system of the walls of the burner generally consists of multiple holes used to create a cushion of air between the flame and the wall.
• This cooling system leads to a significant additional cost in the manufacturing process and a complexity of implementation. All these disadvantages make it difficult to achieve complete combustion and meet the low emission requirements in terms of nitrogen oxides (NOx), carbon monoxide (CO), unburned hydrocarbons (HC) and particulates (PM) .
• the present invention proposes to overcome the aforementioned drawbacks with a low-emission and low-cost combustion chamber design.
• the present invention relates to a combustion chamber of a turbine, in particular a thermodynamic cycle turbine 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 takes place, and a dilution zone where the mixing between the gases takes place burned from the primary zone and the remaining part of the flow of hot compressed air, said chamber further comprising means for injecting at least one fuel, characterized in that the flame tube carries a flame stabilizer comprising the perforated diffuser, at least one recirculation passage of flue gas and a mixing tube.
• the perforated diffuser mixing tube can be carried by arms connected to the perforated diffuser while being away from the perforated diffuser.
• the perforated diffuser mixing tube can be carried by arms connected to the flame tube while being away from the perforated diffuser.
• the recirculation passage may be formed between the perforated diffuser and the mixing tube.
• the housing may include a baffle wall for directing hot compressed air to the flame tube.
• the deflecting wall may comprise a semi-toroid wall with a concavity directed towards the flame tube.
• the combustion chamber may comprise a multi-fuel injection means.
• the invention also relates to a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising at least one compression stage with at least one gas compressor, an exchanger of heat, a combustion chamber fed 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 for producing energy, characterized in that it comprises a combustion chamber as mentioned above.
• FIG. 1 which is a diagram illustrating a turbine with a combustion chamber according to the invention for the production of energy, in particular electrical energy,
• FIG. 2 which is an axial sectional view showing the combustion chamber according to the invention
• FIG. 3A which is a perspective view of an element of the combustion chamber according to the invention with a front view (FIG. 3B) and a sectional view (FIG. 3C), and
• the turbine illustrated is more particularly a microturbine 10, operating from at least one fuel, such as a liquid fuel, for example of the diesel fuel type, or a gaseous fuel, such as natural gas.
• a fuel such as a liquid fuel, for example of the diesel fuel type, or a gaseous fuel, such as natural gas.
• the turbine comprises at least one compression stage 12 with at least one gas compressor 14, a heat exchanger 1 6 (or recuperator), a combustion chamber 18 (or burner) supplied with fuel by at least one tank 20, at the at least one expansion stage 22 with at least one expansion turbine 24 connected by a shaft 26 to the compressor.
• This turbine also comprises a means of energy production, here electrical, which includes a 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 1 6 may be a cross-flow heat exchanger, for example of the tube-calender or alternating plate with two inputs and two outputs.
• the compressor 14 comprises a fresh gas inlet 30 containing oxygen, in this case outside air generally at ambient temperature, and a compressed air outlet 32 leading to a compressed air inlet 34 of the exchanger 16 via a line 36.
• the hot compressed air outlet 38 of this exchanger is connected by a line 40 to an inlet of hot compressed air 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 whose outlet 48 is connected to another inlet 50 of the exchanger by a line of superheated gas expanded 52.
• the exchanger 1 6 also includes a cooled gas outlet 54 to be directed to any means d evacuation and treatment, like a chimney (not shown).
• the burner 18 comprises an outer casing 56, of cylindrical shape of diameter D1, closed at one of its ends by an injector wall 58 and at the other end thereof by a partition annular 60 with an opening 62 of inner diameter D2.
• This burner also comprises a flame tube 64, also of substantially cylindrical shape, housed coaxially in the housing being of smaller diameter than the housing but of identical diameter to that of the opening 62 of the annular partition 60.
• This tube comprises one end closed by a diffusion partition 66 opposite and away from the injector partition 58 and an open end 67 which passes through the annular partition cooperating sealingly with the inner diameter of the annular partition to form the outlet 44 of the burner.
• the housing carries, on its periphery 68 and near the annular partition 60, the hot compressed air inlet 42 for introducing this air into the space 70 formed between the housing and the flame tube as well as in the space 72 formed between the injector partition and the diffusion partition.
• the injector partition comprises a plate 74, through which is mounted a means for injecting at least one fuel 76, here in the form of an injector coaxial with the flame tube.
• This plate is surrounded by an air deflecting wall 78, here semi-toroid 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 spaced apart from the diffusion partition and close to the annular partition of the housing, being distributed advantageously 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 being housed in an orifice 84 provided in this diffusion partition.
• This flame stabilizer makes it possible to generate burnt gas recirculation zones facilitating the ignition of the fuel and bringing inertes locally into the reaction zone. It also allows the physicochemical 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 internal combustion engine with spark ignition, a glow plug, ignition electrodes, ....
• the position of the ignition device must be in an area of the burner that 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 constituted comprises a flame tube with a zone of injection / mixture ZM where the mixing of the hot compressed air with the fuel and the beginning of the combustion is carried out, a primary zone ZP in which the combustion takes place, a ZD dilution zone where the mixing between the burnt gases from the primary zone and the hot compressed air coming from the dilution holes takes place.
• This dilution zone has as main aims to reduce the temperature of the gases leaving the dilution zone and to allow a good spatial homogenization thereof before entering the expansion turbine.
• FIGS. 3A to 3C which illustrate an exemplary embodiment of a flame stabilizer.
• This stabilizer comprises a perforated diffuser in the form of a flat circular soleplate 88 intended to be housed in the orifice 84 of the diffusion partition 66 and comprising a multiplicity of axial holes 90 regularly distributed circumferentially on the sole and a central axial hole 91.
• This sole continues in an axial direction and opposite the wall by axial arms 92, here three arms arranged at 120 ° from each other, and carrying at their ends a mixing tube 94 of limited axial extent to arrive at the beginning of the primary zone ZP and of outside diameter less than the inside diameter of the flame tube 64.
• a free axial passage 96 is thus created between the outer periphery of the mixing tube and the inner periphery of the flame tube (see FIG. 2) as well as at least one radial recirculation passage 98, here three, between the sole and the tube. mixer and arms.
• the fuel here in liquid form, is injected by the injector 76 in the direction of the perforated sole 88 to pass through the central hole 91.
• the hot compressed air coming from the inlet 42 enters the space 72 between the partitions, is then deflected by the deflecting wall 78 to pass through the holes 90 of the soleplate and is directed into the mixing tube 94 in which takes place. evaporation of the liquid fuel, then combustion.
• This stabilizer thus facilitates the vaporization of the fuel by bringing part of the burned gases from the primary zone ZP, inert and hot, to the fuel jet from the injector through the recirculation passages 98 located between the sole 88 and the mixing tube 94 (arrows in broken lines in Figure 2).
• the mixing tube must be placed at a distance from the soleplate so that a portion of the burnt gases from the primary zone ZP can be directed towards the fuel jet through the space between the soleplate and the mixing tube.
• the mixing tube is connected by radial arms to the flame tube instead of being connected to the soleplate.
• the air from the inlet 42 is in countercurrent with the burnt gases of the combustion chamber, but it can be envisaged that this air is co-current with these burned gases. It may also be envisaged to place a valve means, such as a valve (not shown) on the air intake 42 to allow control of the amount of air in the primary zone and in the dilution zone.
• a valve means such as a valve (not shown) on the air intake 42 to allow control of the amount of air in the primary zone and in the dilution zone.
• FIG. 4 shows a variant of the injector as illustrated for the burner of FIG. 2.
• the injector may be a multi-fuel gas-liquid injector.
• the burner injector could be adapted.
• the injector comprises a body 100 and an injection head 102 with an injection nozzle 104 for a fuel and another injection nozzle 106 for another fuel.
• the body is composed of two concentric tubes 108, 110 with a central portion 108 provided with a passage 112 for injecting a fuel, for example in liquid form, through the injection nozzles 104 and with a peripheral passage 14 between the two tubes for injecting a fuel of another nature (gas) through the nozzles 106.
• this injector is associated with a fuel injection circuit with two reservoirs and the various control and / or control devices for performing the injection of one or the other fuel.

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• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)

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• 2015
  • 2015-09-30 FR FR1559314A patent/FR3041742B1/fr active Active
• 2016
  • 2016-09-13 US US15/762,679 patent/US10948190B2/en not_active Expired - Fee Related
  • 2016-09-13 WO PCT/EP2016/071533 patent/WO2017055074A1/fr active Application Filing
  • 2016-09-13 EP EP16770706.6A patent/EP3356737B1/fr active Active
  • 2016-09-13 CN CN201680055581.6A patent/CN108027144A/zh active Pending

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