WO2014191495A1 - Chambre de combustion annulaire de turbine à gaz avec injection tangentielle sous forme d'injection maigre retardée - Google Patents

Chambre de combustion annulaire de turbine à gaz avec injection tangentielle sous forme d'injection maigre retardée Download PDF

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Publication number
WO2014191495A1
WO2014191495A1 PCT/EP2014/061133 EP2014061133W WO2014191495A1 WO 2014191495 A1 WO2014191495 A1 WO 2014191495A1 EP 2014061133 W EP2014061133 W EP 2014061133W WO 2014191495 A1 WO2014191495 A1 WO 2014191495A1
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WO
WIPO (PCT)
Prior art keywords
combustion chamber
injector
annular
fuel
annular combustion
Prior art date
Application number
PCT/EP2014/061133
Other languages
German (de)
English (en)
Inventor
Christian Beck
Olga Deiss
Werner Krebs
Bernhard Wegner
Original Assignee
Siemens Aktiengesellschaft
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Filing date
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Application filed by Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2014191495A1 publication Critical patent/WO2014191495A1/fr

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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
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing

Definitions

  • the present invention relates to an annular combustion chamber, a gas turbine and a method for operating a ring 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. To reduce emissions from
  • Nitrogen oxides are used lean premix.
  • high Turbi ⁇ neneintrittstemperaturen be pursued to achieve a high efficiency associated with high flame temperatures.
  • premixed flames due to the high thermal power density ansoci ⁇ ble to thermoacoustic instabilities and NOx emissions decrease with increasing flame temperature exponentially to.
  • This primary zone may in turn as conventional burner be internally stepped and covers the load range up to today's firing temperatures from downstream of the primary zone is followed by a secondary Ver. ⁇ combustion zone in. in this additional fuel is injected by an axially opposite the primary zone offset level. This is then burned in a diffusion type re- regimes.
  • the fuel may be diluted with inert components (vapor, nitrogen, carbon dioxide) to the stoichiometric combustion temperature greatly At the same time, the distribution of heat release across the entire available combustion chamber reduces the tendency of the combustion system to become thermoacoustic instabilities.
  • US 2011/0067402 AI discloses a gas turbine with a combustion chamber, which has a combustion concept with two stages.
  • the combustor includes a combustor head end having a combustor assembly, a combustor exit, and a combustor
  • Combustion chamber wall wherein the combustion chamber wall extends from the Brennkam ⁇ merkopfende to the combustion chamber exit, and a Pri ⁇ marmer zone and a secondary zone.
  • the secondary zone is arranged in the main flow direction of the hot gas downstream of the primary zone.
  • the Se ⁇ kundärzone opens injectors which form a second axial level of the combustion system.
  • a second object of the present invention to provide an advantageous annular combustor which can achieve reduction of nitrogen oxide (NOx) emissions and low CO emissions.
  • a third object of the present invention is to provide an advantageous method for operating an annular combustion chamber or a gas turbine comprising an annular combustion chamber, which makes it possible to reduce emissions of nitrogen oxides and / or to reduce CO emissions.
  • the first object is achieved by an annular combustion chamber according to claim 1.
  • the second object is achieved by a Gasturbi ⁇ ne claim fourteenth
  • the third object is achieved by a method according to claim 15.
  • the dependent Proverbs contain further advantageous embodiments of the invention.
  • the annular combustor of the present invention includes a longitudinal axis, a combustor head end, and a combustor exit. At least one burner is arranged at the combustion chamber head end.
  • the annular combustor further includes a combustor wall extending from the combustor head end to the combustor exit.
  • the annular combustion chamber according to the invention comprises a primary zone and a secondary zone. In this case, the secondary zone is arranged in the main flow direction of the hot gas downstream of the primary zone.
  • the combustion chamber ⁇ includes at least one injector for introducing a fuel-air mixture in the secondary zone.
  • the injector includes fully a flow channel (which may also be referred to with Eindüsö réelle) with a Mün ⁇ Denden in the secondary zone output with an inflow and an in
  • the inflow direction has at least one component in the circumferential direction of the
  • a number of corresponding injectors are arranged on the combustion chamber wall in the region of the secondary zone. Due to the combined injection of air and fuel in the Se ⁇ kundärzone a so-called “air-assisted axial stage" is realized.
  • 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 arbitrary position ⁇ between the primary zone and the combustion chamber exit.
  • the airborne axial compressor itself already has several pre ⁇ parts.
  • premixing fuel and air outside the combustion chamber as in conventional burner technology the resulting peak temperatures and thus the NOx emissions can be reduced.
  • Lower residence times in the secondary zone and turbine entry continue to result in lower overall NOx emissions.
  • no additional media are needed, but an operation takes place only with the originating from the compressor outlet air, which are treated with fuel in the axial stage to a Ge ⁇ mixed. Therefore, the resulting system is robust and stable available.
  • the airborne axial compressor is equally a ⁇ He furtherance of the operating range of the combustion system to lower and higher loads.
  • Ring combustion chambers of the prior art can flow in the outer shell with a velocity component in the circumferential direction of the annular combustion chamber resulting from the superposition of the burner flows.
  • the peripheral component of the combustion chamber flow is increased by the inventive injection of the combustion air with at least one component in the circumferential direction of the combustion chamber in the axial stage. From this, the injection, the environmental steering omitted by the guide blades of the first turbine stage in extreme cases, by utilizing the ent ⁇ speaking acceleration downstream.
  • the present invention also has the following specific ⁇ elle advantages: the swirl generation ensures better Mixing with the mainstream. A smoother turbine entry profile reduces emissions. Wei ⁇ terhin a simple and inexpensive construction of the guide vanes of the first turbine stage is possible or saving potential by dispensing with the vanes of the first turbine stage.
  • the combustion chamber wall can hold an outer shell and a hub to ⁇ .
  • at least one injector is arranged on the outer shell and / or on the hub.
  • the annular combustion chamber has the combustion chamber head end to the combustor exit an annular cross-section, with the outer shell forms the part of the combustion chamber wall, wel ⁇ cher constituting the outer edge of the annular cross-section and the hub forms the part of the combustion chamber wall, which the encompassed by the outer edge of the inner edge of the annular cross section is formed.
  • At least one injector may be arranged according to the invention on the outer shell and / or the hub.
  • the inflow direction has at least one component in the circumferential direction of the combustion chamber. If the injector is disposed on the hub, then the circumferential direction is substantially parallel along the inner edge of the annular cross-section of the annular combustion chamber. The injector to the outer shell arranged, then, the circumferential direction Wesent ⁇ union parallel along the outer edge of the annular cross section of the annular combustion chamber.
  • a plurality of injectors in the circumferential direction of the combustion chamber spaced from each other on the hub and / or the outer shell of the combustion chamber wall are arranged.
  • the injectors may, for example, be arranged parallel to one another in the circumferential direction at a distance from one another on the combustion chamber wall.
  • the combustion chamber wall comprises an outer surface.
  • this outer surface comprises the outer surface of the outer shell and the outer surface of the hub facing away from the combustion chamber interior.
  • at least one flow channel of an Injek ⁇ sector is at least partially arranged spirally with respect to the longitudinal axis of the combustion chamber along the outer surface.
  • the flow channels of the injectors may comprise an area arranged outside the combustion chamber.
  • the flow direction of the fuel-air mixture can run in this region of the flow channel with a component in or counter to the main flow direction of the hot gases flowing in the combustion chamber along the outer combustion surface.
  • the term "along the surface” also includes an initially spaced from the surface profile of the Injek ⁇ gate, so that the injector only in a combustion chamber wall traversing portion in direct contact with the combustion chamber wall is.
  • spiral is related to the present
  • the invention is also understood to be helical, for example helices of decreasing diameter, wherein the diameter of the knife of the helix may be substantially circular or elliptical. That the injector or its flow channel at least partially spiral in relation to the
  • Longitudinal axis of the combustion chamber along the outer surface is arranged, also includes such injectors or flow ⁇ channels that follow at least partially a portion of such a spiral or helical path.
  • the advantageous embodiment of the invention has the advantage that results in good utilization of the available space around the combustion chamber, a large premix length in the injectors despite compact design. Furthermore, emissions are reduced and thermoacoustical tuning is possible by adapting deadtime elements in flame transfer functions.
  • the annular combustion chamber comprises at least one fuel distributor, which is connected to at least one nozzle, which opens into a Strö ⁇ mungskanal the at least one injector.
  • the nozzle may, for example, such project into the flow channel, that it is coaxially vice ⁇ ben from the flow channel.
  • the fuel distributor may be disposed upstream or downstream of the at least one nozzle on the combustion chamber wall with respect to a main flow direction of the hot gases in the combustion chamber.
  • An arrangement downstream of the at least one nozzle is suitable, for example, for injectors whose flow channels a
  • the at least one fuel distributor may be an annular fuel distributor.
  • At least one fuel distributor can be arranged along the outer surface of the hub.
  • the fuel distributor can supply fuel to such injectors which comprise a flow channel opening through the hub through into the secondary zone. It can also be regarded as advantageous that the Minim ⁇ least a fuel manifold is positioned around the outer shell around on the combustion chamber wall.
  • the fuel distributor may supply such injectors with fuel, comprising an opening out through the outer shell to pass into the secondary flow channel zone umfas ⁇ sen.
  • the at least one injector comprises a flow channel having an outlet with a central axis pointing in an inflow direction.
  • a further advantageous embodiment of the invention may provide that the central axis encloses an angle ⁇ , ⁇ between 0 ° and 180 ° with the main flow direction in the combustion chamber at the position of the respective injector outlet. This means that the fuel-air mixture can be introduced both in the opposite direction and in the main flow direction in the secondary zone.
  • the center axis of the injector outlet determines the inflow direction of the injected fuel-air mixture into the combustion chamber.
  • the main flow direction of the hot gas in the combustion chamber is in particular by the
  • the main flow direction may be in the form of a curved curve extending from the burner to the combustion chamber exit.
  • the burners at the end of the combustion chamber each comprise a burner axis.
  • the at least one injector may comprise an outlet with a center axis pointing in the inflow direction, which may enclose an angle 0, 2 between 0 ° and 180 ° with the burner axis parallel to the location of the outlet of a burner arranged substantially upstream of the injector at the combustion head end ,
  • the angle 0, 2 between 0 ° and 90 °, preferably between 20 ° and 70 ° or between 90 ° and 180 °, in particular between 110 ° and 160 °, which corresponds to an inflow in the main flow direction and counter to the main flow direction.
  • the angle 0, 2 is greater than 45 ° and smaller than ⁇ 90 ° or less than 70 ° or less than 135 ° and greater than 90 °, preferably greater than 110 °, to a favorable intermixing of the introduced To achieve fuel-air mixture with the main flow with simultaneous swirl generation.
  • the output of the injector can be such arranged relative to the main flow direction, that a radial to Hauptströ ⁇ flow direction line intersecting the central axis of the injector in the area of its output at an angle ß if. Furthermore, the output of the injector can be arranged with respect to the burner axis such that a radial line to the burner axis intersects the center axis of the injector in the region of its output at an angle ß2, the angles ßi and ß2 respectively in the range between 0 ° and 90 ° , Advantageously ⁇ between 20 ° and 70 ° or between 45 ° and 90 ° or between 45 ° and 70 °, lie.
  • Injektorausgangs a radial direction with respect to the main ⁇ flow direction.
  • the inflow direction and / or the center axis of the injector can perpendicular to the main flow ⁇ direction an angle ßi with the radial direction with respect to the main flow direction between 0 ° and 90 °, advantageously between 20 ° and 70 ° or between 45 ° and 90 ° or between 45 ° and 70 °. This means that the
  • Inlet direction and / or the center axis of the injector perpendicular to the main flow direction has a component.
  • Injector output having a radial direction which is perpendicular to the burner axis of a burner arranged substantially upstream of the injector.
  • the inflow direction and / or the center axis of the injector may be perpendicular to the burner axis an angle ß2 with the radial
  • Direction relative to the burner axis between 0 ° and 90 °, advantageously between 20 ° and 70 °, preferably between 45 ° and 90 ° or between 45 ° and 70 °.
  • This ⁇ be indicated includes that the inflow direction and / or the center axis of the injector a perpendicular described by the angle ß2 extending to the burner axis component.
  • the combustion chamber may include heat shield stones.
  • the heat shield bricks may preferably be ceramic heat shield bricks.
  • the heat shield bricks can also be referred to as heat shield elements or heat shield tiles.
  • the heat shields are, for example, under Relegation of expansion gaps areally adjacent to each other on the inner surface of the combustion chamber wall ⁇ arranged.
  • the heat shield bricks can be arranged in to the combustion chamber wall ⁇ circumferential rows.
  • the at least one injector may, for example, in the region of the penultimate row in front of the combustion chamber exit through the heat shield into the secondary zone.
  • a number of injectors can be arranged on the preferably ceramic heat shield bricks, wherein, for example, an injector is arranged essentially on each nth preferably ceramic heat shield brick of at least one row such that it opens through the heat shield brick into the secondary zone, n is present a natural number. It can ⁇ In projectors or their flow channel outputs at substantially each or every second, or every third, etc. position of a ceramic heat shield stone in series are arranged.
  • an elliptical opening can be introduced into the respective, preferably ceramic heat shield block, through which the respective flow channel of the injector opens into the combustion chamber. If this is not possible, for example, Festig ⁇ keitshuntn, can at the positions of Injektoraus Vietnamese, the ceramic heat shield bricks by substantially metallic - preferably cooled metal - heat shield bricks are replaced, similar to the flame ⁇ guardian.
  • Adjacent injector exits may have a distance S to each other.
  • the flow channels of the injectors can each have a diameter d, in particular at their outlet.
  • the ratio between the distance S of adjacent injector exits and the diameter d of the flow channels of the injectors in the region of their exits between 5 and 20, ie 5 ⁇ S / d ⁇ 20.
  • the distance in the circumferential direction of the combustion chamber of adjacent injector exits between fivefold and twentyfold Chen diameter d of the flow channels of the injectors amount.
  • the gas turbine of the invention comprises a previously beschrie ⁇ bene annular combustion chamber. It has the same characteristics and advantages as the annular combustion chamber described above.
  • the inventive method for operating a ring combustion chamber or a gas turbine with an annular combustion chamber is characterized in that a fuel-air mixture through at least one injector in a downstream of a Primary zone disposed secondary zone of the combustion chamber is so ⁇ introduced that the inflow direction has a component in the circumferential direction of the combustion chamber.
  • the method according to the invention has the same advantages as the annular combustion chamber according to the invention described above. In particular, an improved skillsmi ⁇ tion of the main flow and a reduction of emissions are achieved by a more uniform turbine inlet profile by the swirl generation with the help of introduced into the secondary zone ⁇ fuel-air mixture.
  • a mass flow into the combustion chamber which amounts to between 5% and 20% of the total mass flow leaving the combustion chamber at the combustion chamber exit, can be introduced by the injectors.
  • the injectors all attached to the combustion chamber injectors are meant for introducing a fuel-air mixture in the seconding ⁇ därzone the combustion chamber in this context.
  • the fuel-air mixture can be introduced on the hub side and / or outer shell side in the secondary zone. Description of the embodiments
  • Figure 3 shows schematically a part of a combustion chamber in a partially perspective and partially cut ⁇ ge view.
  • FIG. 4 shows a section of the combustion chamber partly already shown in FIG. 3 in a perspective and sectional view.
  • Figure 5 schematically shows a basic arrangement
  • FIG. 6 shows schematically the center axis of the injector
  • FIG. 7 shows schematically a component of FIG
  • Figure 8 shows schematically an inventive annular combustion chamber ⁇ partially in perspective, partially sectioned view.
  • FIG. 9 schematically shows a detail of an annular combustion chamber in a perspective view.
  • FIG. 10 schematically shows a combustion chamber according to the invention in a perspective view.
  • Figure 11 shows schematically a plan view of the ring ⁇ combustion chamber from the combustion chamber head end.
  • FIG. 12 shows a further perspective view of the embodiment variant shown in FIGS. 8 and 9
  • Figure 13 shows a plan view of the ge in Figure 12 showed ⁇ combustion chamber from the combustion chamber exit.
  • Figure 14 shows schematically an annular combustion chamber according to the invention, in a partially sectioned and partially perspective view as a detail.
  • the axial combustion stage according to the invention in the annular combustion chamber can be realized both on the outer shell and on the hub of the combustion chamber.
  • An annular fuel distributor is attached around the outer shell (or hub), for example.
  • the fuel distributor distributes the fuel to a plurality of nozzles (nozzles) which flow into the flow channels of the injectors. These inject the fuel into the flow channels (scoops) of the injectors. In the flow channels of the injectors, the fuel is mixed with the air and then injected into the combustion chamber with a component in the circumferential direction of the combustion chamber.
  • the exits or exits of the injectors are located in the region of the penultimate row of the preferably ceramic heat shields (CHS: Ceramic Heat Shield).
  • CHS Ceramic Heat Shield
  • the injectors may be positioned such that the flow direction in the flow channels has, for example, a component in or opposite to the main flow direction of the hot gases in the combustion chamber.
  • the flow direction at the outlet of the flow channel has at least one component in the circumferential direction of the combustion chamber. This creates a twist in the combustion chamber, which allows a more favorable flow onto the turbine guide vane 1 (TLe 1).
  • the mass flow, the flow conducted through the injectors may be between 5% and 50%.
  • 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 annular 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 . As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • 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.
  • Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 135 is sucked by the compressor 105 through the intake housing and ver ⁇ seals.
  • the 105 ⁇ be compressed air provided at the turbine end of the compressor is ge ⁇ leads 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 blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the blades 120 drive the rotor 103 and this drives the working 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.
  • FIG. 2 schematically shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is configured, for example, as so-called ⁇ annular combustion chamber, in which a plurality of spaced circumferentially about an axis of rotation 102. burners 107 open into a common combustion chamber space 154 and generate flames 156th
  • the Brennkam- mer is ⁇ staltet 110 overall is of annular configuration positioned around the axis of rotation 102.
  • the axis of rotation 102 may also be referred to the longitudinal axis of the combustion chamber.
  • the annular combustion chamber has a combustion chamber wall 153, which encloses an outer shell and a hub.
  • the annular combustion chamber 110 has an annular cross section of the combustion chamber space 154, the shape and diameter of which may be formed differently from the combustion chamber head end to the combustion chamber exit.
  • 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 the Häme ⁇ medium M side facing with an inner lining formed of heat shield elements 155.
  • FIG. 3 shows schematically 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.
  • the primary zone is adjoined in the direction of flow 3 by a secondary zone 5.
  • the hot gas from the primary zone 4 is further burned off. This he follows ⁇ by additional introduction of 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 focal ⁇ material nozzle 10 is connected to a fuel rail 11, as a preferential annular fuel manifold 11, respectively.
  • Injector or the injection port 9 is injected into the combustion chamber in the region of the secondary zone 5.
  • a liner portion 7 and a transition region 25 is disposed between the primary zone of the combustor 4 and the output 6, which are designed in Figure 3 as separate construction ⁇ parts. Between the primary zone 4 and the liner area 7, at least one sealing ring 12 is arranged. net. Furthermore, a sealing ring is at least 12 arranged ⁇ also between the liner section 7 and the junction device 25th The injectors 8 are connected to the liner area 7. The injector exits or injection openings 9 open in the region of the liner area 7 in the secondary zone 5 of the combustion ⁇ chamber.
  • FIG. 4 shows a section of the combustion chamber partly already shown in FIG. 3 in a perspective and sectional view.
  • FIG. 4 shows a fuel supply 15 which supplies fuel to the fuel distributor 11.
  • FIG. 5 shows schematically a basic arrangement of the main burner and the axially offset burner stage as from ⁇ winding.
  • a turbine 16 is arranged at the combustion chamber exit 6.
  • burners 17 are arranged at the combustion chamber head end 24 burners 17 are arranged.
  • Each burner 17 comprises a burner axis 20.
  • the schematically shown outputs of the injectors 9 and the injection openings 9 each comprise a central axis 2.
  • the center axes 2 of the injection openings 9 close with the main axis of the respective burner 17 an angle 0.2.
  • the angle 0.2 can be for an injection direction 23 in the main flow ⁇ direction 3 between 0 ° and 90 °, preferably between 20 ° and 70 °, for example, between 45 ° and 70 °, amount.
  • Basic ⁇ additionally the angle between 0.2 and 45 ° and 90 °
  • FIG. 6 schematically shows the central axis 2 of the injector 8 and the inflow direction 23 with respect to the main flow direction 3 of the hot gas in the combustion chamber.
  • the main flow direction 3 is shown schematically in the form of an axis.
  • the central axis of the injector 2 and the The inflow direction 23 of the fuel-air mixture flowing from the injector outlet 9 into the combustion chamber closes with the main flow direction 3 at an angle ⁇ , ⁇ .
  • the angle ⁇ , ⁇ basically assume the same values as the angle 0, 2 described in connection with FIG.
  • FIG. 7 schematically shows the component of FIG
  • the combustion chamber wall comprises a hub 18 and an outer shell 17.
  • a radial to the main flow direction 3 line connecting the center axis of ⁇ 2 of the injector 8 is cut in the area of its output 9 characterized by the reference numeral 19th
  • Wei ⁇ terhin is a to the burner axis 20 radial line which intersects the central axis 2 of the injector 8 in the region of its output 9 also indicated by the reference numeral 19.
  • the radial line 19 has a right angle to the main flow direction 3 or alternatively to a right angle to the burner axis 20.
  • the respective radial direction or radial line 19 encloses an angle ⁇ i with the inflow direction 23 or with the center axis of the injector 2, if the radial line 19 relates to the main flow direction 3. If the radial line 19 refers to the burner axis 20, then the radial direction 19 with the inflow direction 23 or the central axis 2 of the injector 9 forms an angle ⁇ 2 .
  • the angles ßi and ß 2 can be between 0 ° and 90 °, preferably between 20 ° and 70 °, for example between 45 ° and 70 °.
  • the injector 9 may be arranged on the outer shell 17, as shown in FIG. 7, or on the hub 18.
  • An arrangement on the outer shell is shown in FIGS. 8 to 13, an arrangement on the hub is shown in FIG. 8 shows schematically an inventive an annular combustion chamber in a partially perspective, partially sectioned view.
  • Shawcrokopfende 24 Bren ⁇ ner 107 is arranged with a burner axis 20. With the help of the burner, a fuel-air mixture is burned in the primary zone of the combustion chamber. This is shown schematically by a flame 22.
  • the secondary zone 5 connects.
  • Injekto ⁇ ren 8 a fuel-air mixture is injected in the secondary zone into the combustion chamber in addition.
  • the combustion chamber is lined inside with heat shield bricks 21.
  • the heat shield bricks are preferably ceramic heat shield bricks.
  • the injection openings 9, which may be guided, for example, by elliptical openings in the preferably ceramic heat shield bricks, are distributed uniformly along the circumference of the secondary zone. Preferably, they are arranged in the penultimate or, as shown in Figure 8, third last row of ceramic heat shield bricks 21 in front of the combustion chamber exit 6. If an arrangement in the ceramic heat shield bricks 21 for reasons of strength is not possible, can at the positions of the
  • the ceramic heat shield bricks are replaced by substantially metallic - preferably cooled metallic - heat shield elements.
  • the injectors may be attached to substantially each, or the second, or each third, and so forth position of a preferably ceramic heat shield brick 21 in the respective row of the preferably ceramic heat shield bricks 21 ⁇ .
  • the constant distance between the injectors need not apply to the beginning / end of the row, since the number of stones in a row is generally not a multiple of n.
  • the illustrated injectors are positioned on the combustion chamber wall such that the flow direction in the flow channels of the injectors 8 have a component in the main flow direction of the hot gases in the combustion chamber. FIG.
  • annular combustion chamber 9 schematically shows a detail of an annular combustion chamber in a perspective view.
  • annular fuel distributor 11 is arranged, which supplies the fuel nozzles 10 leading to the respective flow channels of the injectors 8 with fuel.
  • the injectors 8 are arranged distributed in the circumferential direction of the combustion chamber at a distance from the outer shell 17 and arranged at least partially spirally along the outer surface of the outer shell with respect to the Hauptströmungsrich ⁇ tion 3 and with respect to the axis of rotation 102 of the combustion chamber.
  • FIG. 10 shows schematically an inventive combustion chamber ⁇ in perspective view.
  • a combustion chamber according to the invention with a
  • the injectors 8 are arranged downstream of the fuel distributor 11 and upstream of the combustion chamber exit 6 on the outer shell
  • the fuel distributor 11 is arranged downstream of the at least one nozzle supplied by the fuel distributor and upstream of the combustion chamber exit 6
  • the flow direction of the combustion ⁇ material-air mixture in the flow channels of the injectors 8 has a component counter to the main flow direction.
  • the injectors 8 extend at least in sections spirally with respect to the longitudinal axis of the combustion chamber along the outer surface of the outer shell.
  • Inflow direction comprises a component in the circumferential direction of the combustion chamber.
  • FIG. 11 shows schematically in a plan view of the combustion chamber an annular combustion chamber from the head end.
  • FIG. 12 shows a further perspective view of the embodiment variant shown and described in FIGS. 8 and 9.
  • FIG. 13 shows a plan view of the combustion chamber shown in FIG. 12 from the combustion chamber exit.
  • FIG. 14 shows schematically an inventive an annular combustion chamber, in which the injectors differing from those shown in Figures 8 through 13 embodiments 8 and the fuel manifold 11 are arranged on the hub 18th
  • FIG. 14 shows the corresponding combustion chamber in a partially sectioned and partially perspective view as a detail. All of them can in a corresponding manner to that shown in Figure 14liensvari- in conjunction with the figures 8 to 13 ⁇ be written embodiments are applied ante. That is, the injectors 8 may have an inflow direction 23 into the combustion chamber that extends both in and against the main flow direction 3.
  • the arrangement of the fuel distributor 11 reference is made to the statements relating to FIGS. 8 to 13.

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

Abstract

L'invention concerne une chambre de combustion annulaire qui possède un axe longitudinal, une tête de chambre de combustion (24) sur laquelle au moins un brûleur (107) est disposé, une sortie de chambre de combustion (6) et une paroi de chambre de combustion. La paroi de la chambre de combustion s'étend de la tête (24) jusqu'à la sortie (6). La chambre de combustion annulaire comprend une zone primaire (4) et une zone secondaire (5) disposée en aval de la zone primaire (4) dans la direction d'écoulement principal (3) du gaz chaud. La chambre de combustion comprend au moins un injecteur (8) disposé contre la paroi de chambre de combustion pour introduire un mélange air/carburant dans la zone secondaire (5). L'injecteur (8) comprend un conduit d'écoulement avec une sortie (9) débouchant dans la zone secondaire et il possède un axe central tourné dans une direction d'écoulement, laquelle présente une composante orientée dans le sens de la circonférence de la chambre de combustion.
PCT/EP2014/061133 2013-05-31 2014-05-28 Chambre de combustion annulaire de turbine à gaz avec injection tangentielle sous forme d'injection maigre retardée WO2014191495A1 (fr)

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US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10584638B2 (en) 2016-03-25 2020-03-10 General Electric Company Turbine nozzle cooling with panel fuel injector
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
DE102021123513A1 (de) 2021-09-10 2023-03-16 Man Energy Solutions Se Brenner und Verfahren zu dessen Herstellung
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5261224A (en) * 1989-12-21 1993-11-16 Sundstrand Corporation High altitude starting two-stage fuel injection apparatus
JP2000199626A (ja) * 1998-12-28 2000-07-18 Kawasaki Heavy Ind Ltd 燃焼方法および燃焼装置
US20060156735A1 (en) * 2005-01-15 2006-07-20 Siemens Westinghouse Power Corporation Gas turbine combustor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5261224A (en) * 1989-12-21 1993-11-16 Sundstrand Corporation High altitude starting two-stage fuel injection apparatus
JP2000199626A (ja) * 1998-12-28 2000-07-18 Kawasaki Heavy Ind Ltd 燃焼方法および燃焼装置
US20060156735A1 (en) * 2005-01-15 2006-07-20 Siemens Westinghouse Power Corporation Gas turbine combustor

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US10641175B2 (en) 2016-03-25 2020-05-05 General Electric Company Panel fuel injector
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US10584638B2 (en) 2016-03-25 2020-03-10 General Electric Company Turbine nozzle cooling with panel fuel injector
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10641176B2 (en) 2016-03-25 2020-05-05 General Electric Company Combustion system with panel fuel injector
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10655541B2 (en) 2016-03-25 2020-05-19 General Electric Company Segmented annular combustion system
US10690056B2 (en) 2016-03-25 2020-06-23 General Electric Company Segmented annular combustion system with axial fuel staging
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
US10724441B2 (en) 2016-03-25 2020-07-28 General Electric Company Segmented annular combustion system
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US11002190B2 (en) 2016-03-25 2021-05-11 General Electric Company Segmented annular combustion system
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
DE102021123513A1 (de) 2021-09-10 2023-03-16 Man Energy Solutions Se Brenner und Verfahren zu dessen Herstellung
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

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