• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The present invention relates to a combustion chamber (18) of a turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising a housing (50) housing a tube flame apparatus (58) with a diffusion partition (60) carrying a flame stabilizer (72) comprising a perforated air diffuser (78) and a mixing tube (88), said chamber further comprising an injection means ( 64) of at least one fuel. According to the invention, the perforated diffuser (78) comprises at least two circumferential rows (C1, C2) of holes (84; 84a, 84b).
    公开号:FR3049044A1
    申请号:FR1652294
    申请日:2016-03-18
    公开日:2017-09-22
    发明作者:Toda Hubert Baya；Jean-Baptiste Michel；Julien Thiriot；Thomas Valin
    申请人:IFP Energies Nouvelles IFPEN；
    IPC主号:
    专利说明:

    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. Generally, it is understood by microturbine a small power turbine usually less than 200KW.
    As better described in the application WO 2012/039611, 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 of 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 of the turbine.
    As described in the aforementioned application, 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 and fuel from a fuel injection system (liquid or gaseous) placed upstream of the diffuser. Generally, 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. One of the consequences of these operating characteristics is the overall richness in the combustion chamber, lower than 0.20 in general, that is to say below the flammability limits of the fuel.
    In addition, there is the problem of the pre-vaporization of the fuel in the case of a liquid fuel. Generally, the combustion mode to achieve low emissions is premixed combustion with poor wealth.
    However, this type of combustion poses significant problems in the stabilization of the flame. These problems are all the more reinforced by the action of the recuperator which increases the air temperature at the burner inlet by increasing the risk of instability of the flame.
    In addition, the cost of design is also a lock. Indeed, 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 results in a significant additional cost in the manufacturing process and a complexity of implementation.
    All these disadvantages make it difficult to achieve complete combustion and compliance with low emission requirements in terms of nitrogen oxides (NOx), carbon monoxide (CO), unburned hydrocarbons (HC) and particulate matter (PM). ).
    To improve the aforementioned turbines, the applicant has proposed a new combustion chamber of a turbine, as is better described in the patent application FR 15/59314.
    This combustion chamber comprises a housing housing a flame tube with a perforated diffuser for the passage of hot compressed air, a flame stabilizer, recirculation passages for combustion gases, a mixing tube and an injection means of a fuel.
    The applicant has further improved the combustion chamber of the aforementioned patent application so as to obtain an increased reduction of the pollutants resulting from the combustion, an absence of soot particles at the exhaust with the usual measurement techniques, a reduction of combustion noise and a reduction of the temperature gradients at the inlet of the turbine. For this purpose, 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 diffusion partition carrying a flame stabilizer comprising a perforated air diffuser and a mixing tube, said chamber further comprising means for injecting at least one fuel, characterized in that the perforated diffuser comprises at least two circumferential rows of holes.
    The diffuser may include a bore for fuel passage and the circumferential rows of holes may be concentrically disposed in said bore.
    The diffuser may include a row of holes whose opening is smaller than the opening of the holes of the other row.
    The diffuser may include one row of holes, the number of which is greater than the number of holes in the other row.
    The diffuser may include holes with a shape in a closed curve.
    The diffuser may comprise holes whose angular spacing between two adjacent holes of a row is a multiple or a sub-multiple of the angular difference between two holes of the other row.
    The perforated diffuser can carry the mixing tube by arms. 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 defined above.
    The other features and advantages of the invention will now appear on reading the following description, given purely by way of illustration and not limitation, and to which are appended: 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, - Figure 2 which is an axial sectional view showing the combustion chamber according to the invention, - Figure 3 which is a view of perspective of an element of the combustion chamber according to the invention and - Figure 4 which is a side view along the arrow A of the element of the combustion chamber of Figure 3.
    In FIG. 1, 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.
    The turbine comprises at least one compression stage 12 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 an expansion stage 22 with at least one expansion turbine 24 connected by a shaft 26 to the compressor. This turbine also comprises a power generation means, here electrical, which comprises an electric generator 28 advantageously placed on the shaft 26 between the compressor and the turbine.
    Of course, 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 compressor 14 comprises a fresh gas inlet containing oxygen, here outside air generally at ambient temperature, and a compressed air outlet 32 leading to a compressed air inlet 34 of the exchanger 16. The hot compressed air outlet 36 of the exchanger 16 arrives at a hot compressed air inlet 38 of the burner 18. The superheated gas outlet 40 of the burner is connected to the inlet 42 of the turbine, the outlet 44 of which is connected to another input 46 of the exchanger. The exchanger 16 also includes a cooled gas outlet 48 to be directed to any means of evacuation and treatment, such as a chimney (not shown).
    Referring to Figure 2, the burner 18 comprises an outer casing 50, here of cylindrical shape, closed at one of its ends by an injector wall 52 and at the other end thereof by a partition 54 with an opening 56 of smaller diameter than that of the housing 50. This burner also comprises a flame tube 58, here 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 56 of the annular partition 54.
    This tube comprises an end closed by a diffusion partition 60 opposite and at a distance from the injector wall 52 and an open end 62 which passes through the annular partition cooperating with the internal diameter of this annular partition to form the exit 40 of this burner.
    The housing carries, on its periphery and near the annular partition 54, the inlet of hot compressed air 38 for introducing this air into the space formed between the housing and the flame tube as well as in the space formed between the injector partition and the diffusion partition.
    As best illustrated in FIG. 2, the injector partition comprises a plate 64, through which is mounted an injection means 66 of at least one fuel, here in the form of an injector coaxial with the flame tube. . This plate is surrounded by an air deflecting wall 68, here semi-toric whose concavity is directed towards the flame tube and which is connected to the periphery of the housing.
    The flame tube comprises circumferential rows of radial dilution orifices 70 placed at a distance from the diffusion partition 60 and close to the annular partition of the casing, being distributed regularly advantageously opposite the inlet 38.
    This flame tube also comprises a flame stabilizer 72 which is placed on the diffusion partition 60 and inside the tube being housed in an orifice 74 provided in this diffusion partition.
    The burner also comprises an ignition device 76 for a fuel mixture. By way of example, this device may be a spark plug of the type for internal combustion engine with spark ignition, a glow plug, ignition electrodes, etc.
    Referring now to FIGS. 3 and 4 which illustrate an exemplary embodiment of a flame stabilizer 72.
    This stabilizer comprises a perforated air diffuser 78 in the form of a flat circular soleplate 80 intended to be housed in the orifice 74 of the diffusion partition 60.
    This sole includes a central axial bore 82 for the passage of fuel from the injector 64 and comprises a plurality of holes 84 which pass through the thickness of the sole being in the same axial direction as that of the bore.
    As better visible in these figures, the holes 84 are distributed in a plurality of concentric circumferential rows to the bore 82. The example illustrated in these figures show that these holes are regularly distributed circumferentially in two circumferential rows C1 and C2.
    One of the rows C1 of holes, called outer row, which is located closest to the outer edge of the sole, comprises holes 84a which have an opening which is smaller than the opening of the holes 84b of the other row C2 of holes.
    More precisely, the holes are of circular shape and the holes 84a of the outer row have a diameter D1 which is smaller than the diameter D2 of the holes 84b of the other row C2 of holes.
    The holes 84a of the outer row C1 are advantageously in greater number than those of the inner row C2 In the example illustrated, the holes 84a are twice as numerous as those of the inner row.
    Of course, the shape of the holes 84a, 84b is not limited to that of the circular shape, as illustrated in the figures, but may be a completely different shape with a closed curve, such as a square, ellipsoidal, trapezoidal, triangular shape etc.
    Likewise, the circumferential angular gap between two adjacent holes may be constant or variable throughout the row.
    Finally, the angular difference between two adjacent holes of a row may be a multiple or a sub-multiple of the angular difference between two holes of the other row.
    Thus, for the outer row, the angular difference α between two adjacent holes 84a of the outer row is half the angle β between two adjacent holes of the inner row.
    Returning to FIG. 3, the sole 80 continues in an axial direction and away from the partition by axial arms 86, here three arms arranged at 120 ° from each other, and carrying at their ends a mixing tube 88 of outside diameter less than the inside diameter of the flame tube 58.
    It can also be provided that the mixing tube 88 is connected by radial arms to the flame tube 58 instead of being connected to the soleplate
    In operation, the fuel, here in liquid form, is injected by the injector 64 in the direction of the perforated plate 80 to pass through the central hole 82. The hot compressed air coming from the inlet 38 enters the space 90 between the partitions, is then deflected by the deflecting wall 68. This air then passes through the holes 84a and 84b of the sole and is directed into the mixing tube 88 in which takes place the evaporation of the liquid fuel, then the combustion.
    Thanks to the arrangement of the rows of holes, the recirculations around the flame catch are favored and the speed of passage of the air is relatively important.
    In addition, the location of a row of holes that shave the tube hangs flame increases the flow that flows.
    Thus by promoting recirculation and with sufficient air velocity, it avoids the stabilization of the flame in the flame hook, which leads to a diffusive jet flame type structure, recirculates burnt gases which favor the evaporation, and more generally the mixture, and the drops of fuel are evaporated before arriving in the flame, - one has a relatively premixed combustion, that is to say without rich areas so with low pollutant productions, - the combustion chamber can operate at low average resources, for example at 0.35 in stability limit.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    1) combustion chamber (18) of a turbine, including a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising a housing (50) housing a flame tube (58) with a diffusion partition (60) carrying a flame stabilizer (72) comprising a perforated air diffuser (78) and a mixing tube (88), said chamber further comprising injection means (64) at least one fuel, characterized in that the perforated diffuser (78) comprises at least two circumferential rows (C1, C2) of holes (84; 84a, 84b).
    [0002]
    2) combustion chamber according to claim 1, characterized in that the diffuser comprises a bore (82) for the passage of the fuel and in that the circumferential rows (C1, C2) of holes are arranged concentrically in said bore.
    [0003]
    3) combustion chamber according to claim 1 or 2, characterized in that the diffuser comprises a row (C1) of holes (84a) whose opening (D1) is smaller than the opening (D2) holes (84b ) of the other row (C2).
    [0004]
    4) Combustion chamber according to one of the preceding claims, characterized in that the diffuser comprises a row (C1) of holes (84a) whose number is greater than the number of holes (84b) of the other row.
    [0005]
    5) Combustion chamber according to one of the preceding claims, characterized in that the diffuser comprises holes (84; 84a, 84b) with a shape in a closed curve.
    [0006]
    6) combustion chamber according to one of the preceding claims, characterized in that the diffuser comprises holes (84a, 8b), the angular distance (α, β) between two adjacent holes (84a) of a row is a multiple or a sub-multiple of the angular difference (β, a) between two holes (84b) of the other row.
    [0007]
    7) Combustion chamber according to one of the preceding claims, characterized in that the perforated diffuser (78) carries the mixing tube (88) by arms (86).
    [0008]
    8) Turbine, in particular a thermodynamic cycle turbine with recuperator, for the production of energy, in particular electrical energy, comprising at least one compression stage (12) with at least one gas compressor (14), a heat exchanger (16), a combustion chamber (18) supplied with fuel by at least one reservoir (20), at least one expansion stage (22) with at least one expansion turbine (24) connected by a shaft (26) compressor, and energy generating means (28), characterized in that it comprises a combustion chamber (18) according to one of the preceding claims.
    类似技术:
    公开号 | 公开日 | 专利标题
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    同族专利:
    公开号 | 公开日
    WO2017157631A1|2017-09-21|
    EP3430316A1|2019-01-23|
    FR3049044B1|2019-12-20|
    EP3430316B1|2020-10-21|
    CN108779918B|2020-10-30|
    CN108779918A|2018-11-09|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2517015A|1945-05-16|1950-08-01|Bendix Aviat Corp|Combustion chamber with shielded fuel nozzle|
    GB624779A|1946-01-09|1949-06-16|Bendix Aviat Corp|An improved burner for gaseous, liquid or powdered solid fuel|
    WO2012039611A1|2010-09-21|2012-03-29|Micro Turbine Technology Bv|Combustor with a single limited fuel-air mixing burner and recuperated micro gas turbine|WO2020025234A1|2018-07-30|2020-02-06|IFP Energies Nouvelles|Combustion chamber comprising a passage section of a flame tube, which is modified, particularly for a turbine designed to generate power, particularly electrical power|
    WO2020025233A1|2018-07-30|2020-02-06|IFP Energies Nouvelles|Combustion chamber for a gas turbine for the production of energy, particularly electrical energy, comprising asymmetric dilution holes in a flame tube|
    FR3088969A1|2018-11-27|2020-05-29|IFP Energies Nouvelles|Fuel injector with cooling means|US2621477A|1948-06-03|1952-12-16|Power Jets Res & Dev Ltd|Combustion apparatus having valve controlled passages for preheating the fuel-air mixture|
    DE1627878A1|1967-03-14|1970-08-06|Schloemann Ag|Device to compensate for the spring deflection on machines, in particular on forging presses or the like.|
    DE2020416A1|1970-04-27|1971-11-11|Motoren Turbinen Union|Combustion chamber for gas turbine engines|
    GB1335134A|1970-12-05|1973-10-24|Nissan Motor|Combustion apparatus of a gas turbine engine|
    DE10064259B4|2000-12-22|2012-02-02|Alstom Technology Ltd.|Burner with high flame stability|
    US6968693B2|2003-09-22|2005-11-29|General Electric Company|Method and apparatus for reducing gas turbine engine emissions|
    JP4959620B2|2007-04-26|2012-06-27|株式会社日立製作所|Combustor and fuel supply method for combustor|
    法律状态:
    2017-03-27| PLFP| Fee payment|Year of fee payment: 2 |
    2017-09-22| PLSC| Search report ready|Effective date: 20170922 |
    2018-03-28| PLFP| Fee payment|Year of fee payment: 3 |
    2019-03-27| PLFP| Fee payment|Year of fee payment: 4 |
    2020-03-26| PLFP| Fee payment|Year of fee payment: 5 |
    2021-03-26| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1652294|2016-03-18|
    FR1652294A|FR3049044B1|2016-03-18|2016-03-18|COMBUSTION CHAMBER OF A TURBINE, IN PARTICULAR OF A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, PARTICULARLY ELECTRICAL ENERGY.|FR1652294A| FR3049044B1|2016-03-18|2016-03-18|COMBUSTION CHAMBER OF A TURBINE, IN PARTICULAR OF A THERMODYNAMIC CYCLE TURBINE WITH RECUPERATOR, FOR THE PRODUCTION OF ENERGY, PARTICULARLY ELECTRICAL ENERGY.|
    EP17705924.3A| EP3430316B1|2016-03-18|2017-02-23|Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy|
    PCT/EP2017/054167| WO2017157631A1|2016-03-18|2017-02-23|Combustion chamber of a turbine, particularly a turbine with a thermodynamic cycle comprising a recuperator, for producing energy, particularly electrical energy|
    CN201780016328.4A| CN108779918B|2016-03-18|2017-02-23|Turbine for generating energy and combustion chamber thereof|
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