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
  • F23R3/34—Feeding into different combustion zones
• • 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
• • 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
  • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
  • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
  • F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
  • F23D11/103—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber with means creating a swirl inside the mixing chamber
• • 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
  • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
  • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
  • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
• • 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
  • F23R3/10—Air inlet arrangements for primary air
  • F23R3/12—Air inlet arrangements for primary air inducing a vortex
  • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
• • 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
  • F23R3/34—Feeding into different combustion zones
  • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23D—BURNERS
  • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
  • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23D—BURNERS
  • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
  • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability
• • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
  • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
  • F23D—BURNERS
  • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
  • F23D2900/00016—Preventing or reducing deposit build-up on burner parts, e.g. from carbon

Definitions

• the invention relates to a gas turbine combustion chamber injector, in particular a turbine engine, comprising a dual fuel injection circuit.
• the invention also relates to a combustion chamber equipped with at least one such dual circuit injector and single circuit injectors.
• a mixture of compressed air and suitable fuel is generally injected into the combustion chamber using a plurality of injectors.
• the injectors are mounted in the wall of a flame tube arranged, preferably at the bottom of the chamber. This makes it possible to homogeneously distribute the mixtures originating from the various injectors.
• a nozzle introduces fuel at the end of a manifold.
• the fuel is adjusted in a centering guide.
• the air comes from the last stage of a compressor of the gas machine and is introduced into the injector annularly.
• Air and fuel are usually introduced into contra-rotating channel swirlers or tendrils, and the fuel particles are sprayed into the air via a mixer.
• the mixture ignited with a candle located at a certain distance, is burned in the chamber.
• the generated gases then have a high kinetic energy, which is exploited to generate propulsion or mechanical energy.
• the ignition of the chamber is provided by two injectors dedicated to start, each starter injector being associated with a candle.
• the other injectors are dedicated to the post-start systems: transient acceleration or deceleration regimes and stabilized flight regimes.
• This architecture requires the availability of specific starter injectors, and therefore an additional mass, specific mounting holes for these injectors on the flame tube that supports all the injectors, as well as the introduction of additional controls which result.
• combustion chambers equipped with injectors having a dual fuel supply circuit, an auxiliary circuit and a main circuit.
• the auxiliary circuit is dedicated to idle operation, that is to say at low load, while the main circuit or both circuits are solicited at intermediate speeds and stabilized.
• the invention aims to remedy this problem by providing a starter injector that can also be used in all flight regimes without cost or additional mass.
• this starter injector has a particular configuration of dual fuel circuit and air circuit.
• the present invention relates to a gas turbine combustion chamber injector, comprising a dual fuel injection circuit and an air circuit.
• the fuel injection circuits consist of a starter fuel circuit, capable of triggering the ignition of the chamber and then operating in all flight regimes, and a main fuel circuit, able to operate in the engine. all the flight regimes after the start.
• the fuel systems have parallel conduits formed in a common tube of longitudinal axis. The conduit of the starting circuit opens, at one end, substantially in the center of a spherical injector body extending the common tube.
• the duct houses an injection ramp capable of driving the fuel in rotation before projecting it inside the chamber by a central channel passing through a central swirling wall.
• the conduit of the main circuit opens into an annular channel formed in the body facing nozzle channels arranged radially in the main wall around the central channel.
• the air circuit is guided between two portions of concentric spheres constituted by the injector body and a sheath surrounding the injector body and having an opening through which the whirlpool opens.
• the injector according to the invention has a greatly reduced size thanks to its doubly spherical architecture.
• the central starting circuit is thermally protected from coking by the circulation of fuel in the annular channel of the main circuit.
• the main circuit is itself thermally protected by the flow of peripheral air flowing in the inter-spherical space.
• the swirler is in an inclined position with respect to the longitudinal axis of the injector. This inclination makes it possible to position the end of the starting circuit at the center of the latter and to orient the air and fuel jets in the direction of the candle arranged at the bottom of the chamber.
• the fuel line of the starting circuit has at its end a cylindrical recess for accommodating the ramp;
• the central channel is conical in shape narrowing towards the inside of the combustion chamber in which it opens;
• the radial channels have an inclined orientation relative to the axis of the central channel and contra-rotation relative to the inclination of the vanes of the whirlpool; the air flow at the injector outlet then forms an air cone enveloping the fuel cone of the main circuit;
• the injection ramp of the starting circuit is helical;
• the annular channel of the main fuel circuit is not looped on itself and has ends so as not to form a "dead" zone where the fuel could stagnate;
• the invention also relates to a combustion chamber equipped with at least one double circuit injector shown above and single circuit injectors. All the injectors are mounted in alignment on the casing surrounding the combustion chamber and pass through a flame tube through orifices formed along at least one line parallel to the longitudinal axis of the flame tube.
• the dual circuit injectors are directed towards the spark plug so that these injectors are capable of projecting an air / fuel cone at the outlet of the whirlpool directed towards the bottom of the combustion chamber.
• the combustion chamber is equipped with two non-adjacent dual circuit injectors on the injector line.
• FIGS. 1a and 1b an exploded view and a sectional view of an exemplary dual circuit injector according to the invention
• FIG. 3 a partial perspective view of a combustion chamber equipped with dual circuit injectors presented above and single circuit injectors.
• an injector 1 comprises a fastening flange 10 on a casing 2 of the annular combustion chamber 3, a tube common 1 1 longitudinal axis X'X reference of the injector, and a circular swirl 4 central wall 14 and axis of symmetry ⁇ inclined relative to the axis X'X.
• This central wall 14 allows to project, through the opening 15 of a sleeve 5, an air / fuel mixture in a flame tube 6 which bears on the sleeve 5.
• the swirl 4 is dimensioned so that the fins 40 of this whirlpool, regularly distributed around the periphery of the central wall 14, support in a self-adjusting and self-centering manner on the edge of the opening 15.
• the dual fuel injection circuit consists of a starting fuel circuit C1, able to trigger the ignition of the chamber 3 and operate in all flight modes, and a fuel system C2 main, able to operate in all flight regimes after startup.
• C1 and C2 circuits are coupled to fuel supply pipes (not shown). These circuits consist of access bores 2a, 2b formed in the fastening flange 10, in connection with parallel longitudinal conduits, respectively 12a and 12b, extending in the tube January 1 bearing on sealing sleeves 13a and 13b housed in this tube. These ducts extend in the tube 1 1 parallel to the longitudinal axis X'X and open into the combustion chamber 3 through the central wall 14.
• the conduit 12a opens - at one end 12e - substantially in the center of a hemispherical injector body 1 1 s in extension of the tube 1 January.
• the duct 12a houses - in a cylindrical recess 21 with an inclined axis coinciding with the axis ⁇ of the swirler 4 - a helical fuel rail 7.
• the recess 21 has a tapered end 21c coupled, through the central wall 14 of the swirler 4, to a central channel
• a nozzle 8 is advantageously mounted in the access bore 2b of the flange 10. This nozzle makes it possible to calibrate the flow of fuel which varies according to the phases of flight.
• the longitudinal duct 12b is oriented in a final portion 12f parallel to the axis ⁇ and opens into an annular channel 16 formed in the spherical body 11s.
• This annular channel 16 advantageously has two ends 16e. In other words, this channel is not looped on itself. Thus, no "dead" zone where fuel could stagnate is formed.
• the annular channel 16 is brazed to the central wall with a suitable solder 20 which reveals the non-looped shape of the annular channel 16. This annular channel 16 communicates with sprinkler channels
• the sprinkler channels 42 arranged radially and distributed equidistantly around the central channel 41.
• these sprinkler channels have the same diameter.
• the radial channels 42 advantageously have an orientation along axes K'K symmetrically inclined with respect to the axis ⁇ of the central channel 41 (See in particular FIG. 1 b), and in contra-rotation with respect to the inclination of the fins 40 of the swirler 4.
• the number of radial channels 42 is equal to a multiple of the number of vanes 40 of the swirler 4
• the inlet air flow F E - coming from the last compression stage - passes through openings 170 formed in a flared lid 17 extending the tube 1 1, and is then guided in an air circuit.
• This space "E” is formed between two portions of concentric spheres formed by the injector body 1 1 s and partially by the sleeve 5 in a spherical portion 5s surrounding the injector body 1 1 s.
• the sleeve also has a cylindrical portion with a circular section 5c, which makes it possible to provide support for the flame tube 6 and the flared lid 17 of the tube 11.
• the injector according to the invention has a minimal bulk thanks to this inter-spherical passage.
• central starting circuit C1 is thermally protected from coking by the circulation of fuel in the annular channel 16 of the main circuit C2, the main circuit being itself thermally protected by the peripheral air flow F circulating in the inter-spherical space "E" of the air circuit C3.
• the air flow F s advantageously forms, passing between the fins 40, an air cone Ca enveloping the fuel outlet cone Cs of the main circuit C2.
• the illustrated injector 1 takes elements from the previous example. These identical elements are therefore represented with the same reference signs: the foregoing description of these elements is directly applicable to FIGS. 2a and 2b in their structure and function.
• the modifications come mainly from the configuration of the connection between the longitudinal tube 1 1 and the sleeve 5.
• the tube 1 1 'does not have a flared lid 17 to form the access openings 170 of the air flow F E in the circuit C3.
• the tube 1 ' is extended directly by the spherical body 1 1 s.
• the sheath 5 extends in its cylindrical portion until it is fixed on the flange 10.
• the conical end portion 21c of the recess 21 passes through the central wall 14 of the swirler 4 and acts as a central channel 41.
• the partial perspective view illustrates the combustion chamber 3 equipped with injectors mounted on the wall of the flame tube 6: two dual circuit injectors 1 shown above and seven injectors single circuit 100.
• the chamber is partially cut to reveal some injectors in full and the candle 101 on the bottom side 3f of the chamber.
• All the injectors 1, 100 are mounted regularly on the annular periphery of the chamber 3. Orifices 60 were made in the tube 6 to enclose the sleeves 5 of the injectors 1, 100.
• the dual circuit injectors 1 are directed towards the spark plug 101. Thanks to the inclined orientation of the nozzle channels 42 and the central channels 41, the dual circuit injectors 1 are able to project air / fuel cones Ca / Cs at the outlet of the swirlers to the bottom 3f of the combustion chamber 3. After ignition, the flame goes to the bottom 3f, turns and comes out the opposite output 3s.
• the two dual circuit injectors 1 are separated by a single circuit injector 100 so as to facilitate the orientation of the dual circuit injectors 1 to the candle 101.
• the invention is not limited to the embodiment described and shown.
• the body of the injector may form a more or less complete sphere part depending on the opening size or the diameter of the common tube. It is also possible to form several lines of injectors in the flame tube.

Landscapes

• Engineering & Computer Science (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Mechanical Engineering (AREA)
• General Engineering & Computer Science (AREA)
• Fuel-Injection Apparatus (AREA)
• Ignition Installations For Internal Combustion Engines (AREA)
• Jet Pumps And Other Pumps (AREA)
• Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)

Priority Applications (1)

Applications Claiming Priority (2)

Publications (2)

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Family Applications (1)

Country Status (11)

Families Citing this family (24)

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• 2011
  • 2011-02-02 FR FR1150807A patent/FR2971039B1/fr active Active
• 2012
  • 2012-01-27 CN CN201280007105.9A patent/CN103354890B/zh active Active
  • 2012-01-27 US US13/982,608 patent/US9347667B2/en active Active
  • 2012-01-27 RU RU2013139354/06A patent/RU2584741C2/ru active
  • 2012-01-27 JP JP2013552244A patent/JP5985514B2/ja not_active Expired - Fee Related
  • 2012-01-27 WO PCT/FR2012/050177 patent/WO2012104525A1/fr not_active Ceased
  • 2012-01-27 KR KR1020137022157A patent/KR101877591B1/ko not_active Expired - Fee Related
  • 2012-01-27 EP EP12706638.9A patent/EP2671028B1/fr active Active
  • 2012-01-27 PL PL12706638T patent/PL2671028T3/pl unknown
  • 2012-01-27 ES ES12706638.9T patent/ES2686560T3/es active Active
  • 2012-01-27 CA CA2825864A patent/CA2825864C/fr not_active Expired - Fee Related

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