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EP2808611B1 - Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion - Google Patents

Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion Download PDF

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Publication number
EP2808611B1
EP2808611B1 EP13170048.6A EP13170048A EP2808611B1 EP 2808611 B1 EP2808611 B1 EP 2808611B1 EP 13170048 A EP13170048 A EP 13170048A EP 2808611 B1 EP2808611 B1 EP 2808611B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
injector
fuel
longitudinal axis
air mixture
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.)
Not-in-force
Application number
EP13170048.6A
Other languages
German (de)
English (en)
Other versions
EP2808611A1 (fr
Inventor
Christian Beck
Olga Deiss
Werner Krebs
Bernhard Wegner
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP13170048.6A priority Critical patent/EP2808611B1/fr
Priority to US14/289,184 priority patent/US20140352312A1/en
Priority to CN201410235334.7A priority patent/CN104213986A/zh
Publication of EP2808611A1 publication Critical patent/EP2808611A1/fr
Application granted granted Critical
Publication of EP2808611B1 publication Critical patent/EP2808611B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/346—Feeding into different combustion zones for staged combustion

Definitions

  • the present invention relates to an injector for introducing a fuel-air mixture into a combustion chamber, a combustion chamber and a gas turbine.
  • Modern gas turbines should meet the requirements in terms of pollutant emissions and environmental friendliness in a wide operating range. The fulfillment of these requirements depends essentially on the combustion system used in the gas turbine.
  • NOx nitrogen oxides
  • To reduce emissions of nitrogen oxides (NOx) lean premix is used.
  • high turbine inlet temperatures are sought to achieve a high efficiency, which are associated with high flame temperatures.
  • the aforementioned premixed flames are susceptible to thermoacoustic instabilities due to the high thermal power density and the NOx emissions increase exponentially with increasing flame temperature.
  • axial staging consists of a conventional burner that fires a primary combustion zone. This primary zone can in turn be internally graded like conventional burners and covers the load range up to today's firing temperatures. Downstream of the primary zone is followed by a secondary combustion zone. In this additional fuel is injected through an axially offset from the primary zone stage. This is then burned in a diffusion-like regime.
  • the fuel may be diluted with inert components (steam, nitrogen, carbon dioxide) to greatly lower the stoichiometric combustion temperature, thereby suppressing NOx formation.
  • inert components steam, nitrogen, carbon dioxide
  • the US 2011/0067402 A1 discloses a gas turbine with a combustion chamber having a dual stage combustion concept.
  • the combustor includes a combustor head end having a burner assembly, a combustor exit and a combustor wall, the combustor wall extending from the combustor head end to the combustor exit, and a primary zone and a secondary zone.
  • the secondary zone is arranged in the main flow direction of the hot gas downstream of the primary zone.
  • injectors opening into the secondary zone are arranged, which form a second axial stage of the combustion system.
  • the invention has for its object to provide an injector for introducing a fuel-air mixture in a combustion chamber, a combustion chamber and a gas turbine with at least one such combustion chamber, with the / a reduction in emissions of nitrogen oxides (NOx) and low CO emissions can be achieved.
  • NOx nitrogen oxides
  • the first object is achieved by an injector according to claim 1
  • the second object is achieved by a combustion chamber according to claim 8.
  • the third object is achieved by a gas turbine according to claim 15.
  • the injector according to the invention for introducing a fuel-air mixture into a combustion chamber comprises a longitudinal axis and a number of curved, ie not straight, in particular arcuate, flow channels.
  • arcuate is "curved in the form of at least one arc", for example, also S-shaped curved, understood.
  • Each flow channel comprises a fuel inlet opening, a number of air inlet openings and a fuel-air mixture outlet opening.
  • the fuel inlet opening is connected to a fuel distributor.
  • the fuel inlet opening may also have a central axis which runs perpendicular or parallel to the longitudinal axis of the injector.
  • the fuel-air mixture outlet port has a central axis that is perpendicular to the longitudinal axis of the injector.
  • the air inlet openings each have a central axis which runs parallel to the longitudinal axis of the injector.
  • a fuel-air mixture generated in the flow channels can be introduced into a combustion chamber, for example into a secondary stage of a combustion chamber. Due to the curved, for example, also S-shaped curved shape of the flow channels a large mixing length is achieved on a small available space.
  • the injector can be arranged on the combustion chamber such that its longitudinal axis extends substantially parallel to a longitudinal axis of the combustion chamber.
  • the longitudinal axis of the injector may coincide with a longitudinal axis of the combustion chamber.
  • the air inlet openings of a flow channel are arranged in at least one row. In this way, a continuous mixing of the fuel introduced into the flow channel through the fuel inlet opening with the air introduced into the flow channel through the air inlet openings is achieved.
  • the air inlet openings may have a circular cross-section. In particular, they can be designed as bores.
  • a number of air inlet openings may preferably extend in a spiral shape, for example spirally with respect to an axis parallel to the longitudinal axis of the injector.
  • Each flow channel can in particular one at least have at least one row of the air inlet openings parallel to the center line of the flow channel.
  • the fuel distributor can be designed annular.
  • the fuel distributor may be arranged radially outside of the curved, in particular arcuate, flow channels, in particular with respect to the longitudinal axis of the injector.
  • the fuel distributor can be arranged in the axial direction next to the arcuate flow channels.
  • the curved, for example, arcuate, flow channels may have a curvature angle greater than 0 ° and less than 180 °, for example between 10 ° and 90 °, advantageously between 30 ° and 60 °.
  • at least one of the curved, in particular arcuate, flow channels can have a curvature axis that runs parallel to the longitudinal axis of the injector.
  • all the axes of curvature of the flow channels are parallel to the longitudinal axis of the injector.
  • the injector may comprise two disks arranged substantially parallel to each other.
  • the discs may comprise the side walls of the flow channels and the air inlet openings or in particular form the side walls of the flow channels.
  • an annular fuel distributor can be firmly connected via the two disks arranged in parallel with a combustion chamber, for example with the liner of a combustion chamber or the combustion chamber wall.
  • the air inlet openings may be spirally arranged in the disks in the form of air holes in several rows. Several side walls between the two discs can separate the individual flow channels or mixing channels.
  • the fuel can be injected via several fuel inlet openings, for example in the form of bores, on the inside of the fuel distributor with respect to the longitudinal axis of the injector in the mixing channels.
  • the air may be added perpendicular to and mixed with the fuel flow vertically through the spirally disposed air holes.
  • the fuel-air mixture then passes into the combustion chamber of a combustion chamber through a plurality of openings, such as holes, and ignites there.
  • the combustion chamber according to the invention comprises at least one previously described injector.
  • the combustor may include a longitudinal axis, a combustor head end, a combustor exit, and a combustor wall extending from the combustor head end to the combustor exit. It may further include a primary zone and a secondary zone disposed in the main flow direction of the hot gas downstream of the primary zone.
  • the at least one injector may be arranged in the region of the secondary zone on the combustion chamber wall such that the fuel-air mixture outlet openings open into the secondary zone. In this case, the injector can serve for introducing a fuel-air mixture into the secondary zone.
  • the fuel-air mixture outlet ports may be spaced from each other along a circumferential line on the combustion chamber wall.
  • the combustion chamber may include a liner region that includes the at least one injector.
  • the liner region can connect to the primary zone in the main flow direction.
  • a transition area may connect to the combustor exit.
  • the at least one injector may be arranged at the liner area or be configured in one piece with the liner area.
  • the liner region may comprise a longitudinal axis which coincides with the longitudinal axis of the injector.
  • the longitudinal axis of the Injector can also run parallel to the longitudinal axis of the liner area.
  • the liner region can only form a region of the combustion chamber or be designed as a separate component. It can be arranged between the primary zone and the combustion chamber outlet, for example in the region of the secondary zone.
  • At least one injector according to the invention is arranged on the combustion chamber wall in the region of the secondary zone.
  • a so-called “air-assisted axial stage” is realized.
  • the combustion chamber may be a tube combustion chamber or an annular combustion chamber. At least one burner may be arranged at the end of the combustion chamber.
  • the primary zone is determined by the area in which the fuel supplied via the burner is primarily burned within the combustion chamber.
  • the secondary zone is characterized by the fact that in it the hot gas generated in the primary zone is further burned out as completely as possible.
  • the secondary zone can in principle be arranged at any desired position between the primary zone and the combustion chamber exit.
  • the airborne axial stage itself has several advantages. By premixing fuel and air outside the combustion chamber as with conventional burner technology, the resulting peak temperatures and thus NOx emissions can be reduced. Lower residence times in the secondary zone and turbine entry continue to result in lower overall NOx emissions. In addition, no additional media are needed, but an operation takes place only with the originating from the compressor outlet air, which with fuel in the axial stage to a mixture is processed. Therefore, the resulting system is robust and stable available.
  • the fuel supply to the axial stage is completely shut off and then behaves like an air bypass. This allows the primary zone to operate at very low loads with a high local flame temperature, which ensures good burnout and low CO emissions.
  • the airborne axial stage therefore equally serves to expand the operating range of the combustion system to lower and higher loads.
  • the present invention also has the following special advantages: Due to the curved, in particular spiral-shaped arrangement, a long mixing length can be achieved in the flow channels of the injector despite its compact design. This achieves a high premix quality on a small available space.
  • the swirl generation provides for the generation of additional gradients and shear layers and thus for a better mixing with the main flow.
  • a smoother turbine entry profile reduces emissions.
  • a simple and inexpensive construction of the guide vanes of the first turbine stage (TLe 1) is made possible.
  • the present invention opens up great potential for saving cooling air and possibly saving potential by dispensing with the vanes of the first turbine stage (TLe 1).
  • the gas turbine according to the invention comprises a combustion chamber described above. It has the same characteristics and advantages as the combustion chamber described above.
  • FIG. 1 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103 with a shaft 101, which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings.
  • the hot gas channel 111 of a row of guide vanes 115 is followed by a row 125 formed of rotor blades 120.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • iron, nickel or cobalt-based superalloys are used as the material for the components, in particular for the turbine blades 120, 130 and components of the combustion chamber 110.
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • the FIG. 2 schematically shows a combustion chamber 110 of a gas turbine.
  • the combustor 110 shown is configured as a so-called annular combustor in which a plurality of burners 107 circumferentially disposed about a longitudinal axis of the combustor 102 open into a common combustor chamber 154 which generates flames.
  • the combustion chamber 110 is configured in its entirety as an annular structure which is positioned around the longitudinal axis 102.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M side with an inner lining formed from heat shield elements 155.
  • FIG. 3 schematically shows a part of a combustion chamber in a partially perspective and partially sectioned view.
  • the combustion chamber comprises a combustion chamber wall 1 and a combustion chamber outlet 6.
  • the main flow direction of the hot gas in the combustion chamber during operation of the combustion chamber is indicated by an arrow 3.
  • the combustion chamber further comprises a primary zone 4, in which the fuel introduced from the burner into the combustion chamber is burned.
  • a secondary zone 5 adjoins the primary zone in the direction of flow 3.
  • the hot gas from the primary zone 4 is further burned off. This is done by additionally introducing a fuel-air mixture 14 in the secondary zone 5 by means of injectors. 8
  • the injectors 8 comprise an air supply 13 and an outlet 9 opening into the combustion chamber. Furthermore, a fuel nozzle 10 is arranged in the interior of each injector 8. The fuel nozzle 10 is connected to a fuel distributor 11, preferably an annular fuel distributor 11. With the help of the fuel nozzle 10, fuel is injected into the interior of the injector 8 and in this way generates a fuel-air mixture in the interior of the injector 8. The fuel-air mixture thus produced is then injected through the injector outlet or the injection opening 9 into the combustion chamber in the region of the secondary zone 5.
  • a liner region 7 and a transition region 25 which in the FIG. 3 are each designed as separate components.
  • a sealing ring 12 is arranged between the primary zone 4 and the liner area 7 between the primary zone 4 and the liner area 7 .
  • at least one sealing ring 12 is also arranged between the liner region 7 and the transitional component 25.
  • the injectors 8 are connected to the liner area 7.
  • the injector or injection ports 9 open in the region of the liner region 7 in the secondary zone 5 of the combustion chamber.
  • FIG. 4 shows a section of the already in the FIG. 3 partially shown combustion chamber in perspective and sectional view.
  • a fuel supply 15 is shown, which supplies the fuel distributor 11 with fuel.
  • FIG. 5 schematically shows the liner region with an injector 28 according to the invention, which is referred to below as Spiralinjektor, in a perspective view.
  • the liner region 7 comprises an outer surface 32 on which the spiral injector 28 is arranged.
  • the spiral injector 28 comprises outlet openings 9, through which the fuel-air mixture generated within the spiral injector 28 is introduced into the interior of the combustion chamber.
  • the Outlet openings 9 a rectangular, for example square, shape. Alternatively, they may also have a circular cross-section.
  • the spiral injector 28 includes an annular fuel manifold 41 disposed about the outer surface 32 of the liner region 7.
  • the annular fuel distributor 41 forms in the embodiment variant shown here at the same time with respect to the longitudinal axis or central axis 44 of the liner region 7 radially outwardly disposed portion of the Spiralinjektors 28.
  • the central axis or longitudinal axis 44 of the liner region 7 corresponds to the central axis or longitudinal axis of the injector 28 according to the invention.
  • the annular fuel distributor 41 comprises at least one fuel supply 45.
  • two fuel supply means 45 are arranged opposite each other with respect to the longitudinal axis 44 of the injector.
  • the spiral injector 28 further comprises flow channels or injector channels 48 arranged between the fuel distributor 41 and the outer surface 32 (see FIGS. 6 and 7 ).
  • the injector channels 48 are arranged in a disc-shaped region which connects the outer surface 32 of the liner region 7 to the annular fuel distributor 41.
  • the air holes 42 are preferably provided on both sides of the spiral injector, that is, on the upstream and downstream surfaces 50 with respect to the main flow direction 3.
  • the air holes 42 are arranged side by side in individual rows.
  • Each row of air holes is assigned to an injector channel 48.
  • the respective injector channel 48 and corresponding to the respective air hole row has a curved, preferably spiral shape leading to the central axis 44 towards.
  • the air inlet openings or air bores 42 each have a central axis 54, which runs parallel to the longitudinal axis 44 of the injector.
  • FIGS. 6 and 7 In each case, sections through partial regions of a spiral injector 28 according to the invention are shown in a partially perspective view. It runs in the FIG. 6 shown section perpendicular to the longitudinal axis 44 of the injector and in the FIG. 7 shown section parallel to the longitudinal axis 44th
  • the fuel conducted through the annular fuel distributor 41 to the injector channels 48 is introduced into the injector channels 48 in the flow direction 46. Air is supplied to the injector channels 48 via the air bores 42 at the same time. As a result, a fuel-air mixture is generated in the interior of the injector channels 48, which is then introduced through the outlet openings 9 into the combustion chamber.
  • the individual injector channels 48 are delimited from each other by side walls 49.
  • the spiral injector 28 is perpendicular to the liner region 7, that is perpendicular to the central axis 44 of the liner region 7, installed, wherein the longitudinal axis 44 of the injector, which can also be referred to the central axis 44 of the injector, in the illustrated embodiment with the central axis of the injector Liners coincides.
  • the annular fuel distributor 41 is fixedly connected to the liner area 7, for example, via two disks arranged in parallel. In these discs, the air holes 42 are arranged spirally or arcuately in a plurality of rows. A plurality of side walls 49 between the two discs separate different mixing channels or injector channels 48 from each other.
  • the fuel is through several openings, such as holes 43, on the inside of the fuel distributor 41 in the mixing channels 48th injected.
  • the air is added and mixed vertically through the spirally arranged air holes 42 to the fuel flow 46.
  • the fuel-air mixture then passes into the combustion chamber through a plurality of openings 9, for example holes, in the liner area 7 and ignites there.
  • the fuel inlet openings 43 each have a central axis 55, which extends perpendicularly, in particular tangentially, to the central axis 44 of the injector.
  • FIG. 8 shows a further embodiment variant, in which the fuel distributor 41 is arranged in relation to the longitudinal axis 44 of the injector 8 in the axial direction adjacent to the arcuate flow channels 48.
  • the direction of flow of the fuel is identified by the reference numeral 51.
  • the direction of flow of the air is indicated by the reference numeral 52.
  • FIG. 9 schematically shows a section through a portion of an injector according to the invention perpendicular to the central axis.
  • the injector 48 are configured S-shaped.
  • the air inlet openings 42 are arranged in an S shape.

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

Claims (16)

  1. Injecteur (8) d'introduction d'un mélange de combustibles et d'air dans une chambre de combustion, dans lequel
    l'injecteur ( 8 ) comporte un axe ( 44 ) longitudinal et un certain nombre de canaux ( 48 ) d'écoulement incurvés, chaque canal ( 48 ) d'écoulement comprenant une ouverture ( 43 ) d'entrée de combustible, un certain nombre d'ouvertures ( 42 ) d'entrée d'air et une ouverture ( 9 ) de sortie du mélange de combustible et d'air, l'ouverture ( 43 ) d'entrée du combustible communiquant avec un répartiteur ( 41 ) de combustible et l'ouverture ( 9 ) de sortie du mélange de combustible et d'air ayant un axe médian qui est perpendiculaire à l'axe ( 44 ) longitudinal de l'injecteur ( 8 ), les ouvertures ( 42 ) d'entrée d'air ayant respectivement un axe ( 54 ) médian qui est parallèle à l'axe ( 44 ) longitudinal de l'injecteur ( 8 ).
  2. Injecteur ( 8 ) suivant la revendication 1, dans lequel
    les ouvertures ( 42 ) d'entrée d'air d'un canal d'écoulement sont disposées en au moins une rangée.
  3. Injecteur ( 8 ) suivant l'une des revendications 1 ou 2, dans lequel le répartiteur ( 41 ) de combustible est conformé de manière annulaire.
  4. Injecteur ( 8 ) suivant la revendication 3, dans lequel
    le répartiteur ( 41 ) de combustible est disposé par rapport à l'axe ( 44 ) longitudinal de l'injecteur ( 8 ) radialement à l'extérieur des canaux ( 48 ) d'écoulement incurvés ou en direction axiale à côté des canaux ( 48 ) d'écoulement en forme d'arc.
  5. Injecteur ( 8 ) suivant l'une des revendications 1 à 4, dans lequel
    les canaux ( 48 ) d'écoulement incurvés ont un angle de courbure plus grand que 0° et plus petit que 180°.
  6. Injecteur ( 8 ) suivant l'une des revendications 1 à 5, dans lequel
    au moins l'un des canaux ( 48 ) d'écoulement incurvés a un axe de courbure qui est parallèle à l'axe ( 44 ) longitudinal de l'injecteur ( 8 ).
  7. Injecteur ( 8 ) suivant l'une des revendications 1 à 6, dans lequel
    l'injecteur ( 8 ) a deux disques disposés sensiblement parallèlement l'un à l'autre, les disques comprenant les parois ( 49 ) latérales des canaux ( 48 ) d'écoulement et les ouvertures ( 42 ) d'entrée d'air.
  8. Chambre de combustion qui comprend au moins un injecteur ( 8 ) suivant l'une des revendications 1 à 7.
  9. Chambre de combustion suivant la revendication 8, lorsqu'elle comprend au moins un injecteur ( 8 ) seulement suivant la revendication 1, dans laquelle
    l'injecteur ( 8 ) est disposé sur la chambre de combustion de façon à ce que son axe ( 44 ) longitudinal soit sensiblement parallèle à un axe ( 102 ) longitudinal de la chambre de combustion ou coïncide avec celui-ci.
  10. Chambre de combustion suivant la revendication 8, dans laquelle
    la chambre de combustion a un axe ( 102 ) longitudinal, une extrémité de tête de chambre de combustion, une sortie ( 6 ) de chambre de combustion, une paroi ( 1 ) de chambre de combustion qui s'étend de l'extrémité de tête de la chambre de combustion à la sortie ( 6 ) de chambre de combustion, une zone ( 4 ) primaire et une zone ( 5 ) secondaire, qui est disposée dans le sens ( 3 ) d'écoulement principal du gaz chaud en aval de la zone ( 4 ) primaire, et le au moins un injecteur ( 8 ) est disposé sur la paroi ( 1 ) de chambre de combustion de manière à ce que les ouvertures ( 9 ) de sortie du mélange de combustible et d'air débouchent dans la zone secondaire.
  11. Chambre de combustion suivant la revendication 8 ou la revendication 10, dans laquelle
    les ouvertures ( 9 ) de sortie du mélange de combustible et d'air sont disposées suivant une ligne de pourtour sur la paroi ( 1 ) de chambre de combustion.
  12. Chambre de combustion suivant l'une des revendications 8, 10 ou 11, dans laquelle
    la chambre de combustion comprend une partie ( 7 ) de chemise qui comprend le au moins un injecteur ( 8 ).
  13. Chambre de combustion suivant la revendication 12, dans laquelle
    la partie ( 8 ) de chemise a un axe ( 44 ) longitudinal qui coïncide avec l'axe longitudinal de l'injecteur ( 8 ).
  14. Chambre de combustion suivant la revendication 12 ou 13, dans laquelle
    la partie ( 7 ) de chemise est conformée sous la forme d'une pièce distincte.
  15. Chambre de combustion suivant l'une des revendications 8, 10 à 14, dans laquelle
    la chambre de combustion est conformée sous la forme d'une chambre ( 106 ) de combustion annulaire ou d'une chambre de combustion tubulaire.
  16. turbin ( 100 ) à gaz qui comprend une chambre de combustion suivant l'une des revendications 8 à 15.
EP13170048.6A 2013-05-31 2013-05-31 Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion Not-in-force EP2808611B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP13170048.6A EP2808611B1 (fr) 2013-05-31 2013-05-31 Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion
US14/289,184 US20140352312A1 (en) 2013-05-31 2014-05-28 Injector for introducing a fuel-air mixture into a combustion chamber
CN201410235334.7A CN104213986A (zh) 2013-05-31 2014-05-29 用于将燃料空气混合物加入燃烧室的喷射器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13170048.6A EP2808611B1 (fr) 2013-05-31 2013-05-31 Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion

Publications (2)

Publication Number Publication Date
EP2808611A1 EP2808611A1 (fr) 2014-12-03
EP2808611B1 true EP2808611B1 (fr) 2015-12-02

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EP13170048.6A Not-in-force EP2808611B1 (fr) 2013-05-31 2013-05-31 Injecteur pour l'introduction d'un mélange air-carburant dans une chambre de combustion

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US (1) US20140352312A1 (fr)
EP (1) EP2808611B1 (fr)
CN (1) CN104213986A (fr)

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US9803555B2 (en) * 2014-04-23 2017-10-31 General Electric Company Fuel delivery system with moveably attached fuel tube
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US12066188B2 (en) * 2021-03-26 2024-08-20 Rtx Corporation Modular injector bolt for an engine
US12072101B2 (en) 2022-02-18 2024-08-27 Rtx Corporation Fuel injector with splash plate for an engine
CN115234943A (zh) * 2022-06-30 2022-10-25 北京航空航天大学 中心分级与轴向分级耦合式燃烧室

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CN104213986A (zh) 2014-12-17
US20140352312A1 (en) 2014-12-04

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