EP3367001B1 - Zweite stufe kombinationskammer für eine sequentielle verbrennung kammer einer gasturbine - Google Patents

Zweite stufe kombinationskammer für eine sequentielle verbrennung kammer einer gasturbine Download PDF

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Publication number
EP3367001B1
EP3367001B1 EP17158577.1A EP17158577A EP3367001B1 EP 3367001 B1 EP3367001 B1 EP 3367001B1 EP 17158577 A EP17158577 A EP 17158577A EP 3367001 B1 EP3367001 B1 EP 3367001B1
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EP
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Prior art keywords
downstream
flame
combustion chamber
upstream
flame location
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English (en)
French (fr)
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EP3367001A1 (de
Inventor
Andrea Ciani
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Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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Priority to EP17158577.1A priority Critical patent/EP3367001B1/de
Priority to CN201810168642.0A priority patent/CN108506962B/zh
Publication of EP3367001A1 publication Critical patent/EP3367001A1/de
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    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/042—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with fuel supply in stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2207/00—Ignition devices associated with burner
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the present invention relates to a second-stage combustor for a sequential combustor of a gas turbine and to a method of controlling a sequential combustor of gas turbine with a first-stage combustor and a second-stage combustor.
  • control of pollutant emissions is an objective of primary importance in design of any type of thermal machine and, in particular, of gas turbines for power plants.
  • awareness of environmental risks drives towards regulations that set increasingly strict requirements.
  • the organization of modern power market and the continuously variable demand do not allow to operate plants at constant load conditions. Instead, the need to meet demand fluctuations, including sudden rise or drop, and to contribute to control of grid frequency require quite flexible operation.
  • the reduction of pollutant emissions is made critical by such a flexible operation, because conflicting requirements must be balanced.
  • NOx nitrogen oxides
  • CO carbon monoxide
  • US 3 540 216 A discloses a combustor of a gas turbine, comprising a burner and a combustion chamber extending along a flow direction downstream of the burner. Downstream flame location and upstream flame location are defined within the combustion chamber in a flow channel formed by the burner and the combustion chamber. A downstream flame stabilizer is provided at the downstream flame location. A cross section of the flow channel changes gradually along the flow direction in a transition region between the burner and the combustion chamber, whereby the transition region prevents gas flowing through the combustion chamber from recirculating at the upstream flame location.
  • Other examples of known combustors are disclosed in GB 2 287 312 A and in EP 3 015 772 A1 .
  • a second-stage combustor for a sequential combustor of a gas turbine comprising:
  • the downstream flame stabilizer allows control of the second-stage combustor such that, in certain conditions, the flame is anchored and stabilized at the downstream flame location, which may be set as close to the combustion chamber outlet as desired.
  • the flame may be stabilized at the downstream flame location at high-load operating conditions (e.g. full load or for current load above a high load threshold).
  • high-load operating conditions e.g. full load or for current load above a high load threshold.
  • the second-stage combustor can be controlled to set the flame at the upstream flame location at part load, in particular for current load below a low load threshold (which may be lower than or equal to the high load threshold). Flame temperature is lower at part load and production of NOx is normally not an issue. Instead, post flame residence time is high and complete oxidation of carbon takes place, thus keeping CO emissions low.
  • Flow recirculation or backflow may be created by a sudden increase in the cross section of the flow channel along the flow direction and is usually exploited in known combustors to create stagnation regions at the inlet of the combustion chamber, because flame anchoring is favoured by stagnation regions.
  • flame anchoring may be difficult to release in the presence of recirculating flow, so stabilization of the flame at the downstream flame location might be prevented or made critical once the flame has been anchored at the upstream flame location.
  • a smooth transition from the burner to the combustion chamber instead, helps release the flame from the upstream flame location as desired. Stabilization of the flame at the upstream flame location may be achieved through control of the inlet temperature of the mixture to be burned in the combustion chamber.
  • the downstream flame stabilizer may be implemented by any measure suitable to ensure ignition of the mixture at the downstream flame location, whether by increasing reactivity of the mixture, or by providing a local heat source or by favouring stagnation of the mixture locally.
  • the streamlined body helps maintain a smooth transition in the flow channel between the burner and the combustion chamber.
  • the streamlined body may smoothly join a central body of the burner to prevent backflow.
  • the upstream flame stabilizer allow to compensate for changes of flame location which could otherwise affect combustion in case of control purely based on inlet temperature.
  • the fact that the upstream flame stabilizer may be selectively activated allows to easily release the flame from the upstream flame location e.g. when gas turbine load increases and there is an advantage to stabilize the flame at the downstream flame location.
  • the upstream flame stabilizer may be implemented e.g. by increasing reactivity of the mixture or by providing a local heat source.
  • a combination of upstream electrode system and upstream pilot burner may be exploited as desired.
  • the downstream flame stabilizer comprises at least one of:
  • downstream electrode system Any combination of downstream electrode system, downstream pilot burner and change in cross section may be exploited as desired.
  • the downstream electrode system comprises a set of downstream electrodes on the streamlined body at the downstream flame location and a downstream voltage supply line running inside the streamlined body.
  • the downstream pilot burner comprises a set of downstream fuel nozzles on the streamlined body at the downstream flame location and a downstream fuel supply line running inside the streamlined body.
  • the streamlined body besides providing its typical aerodynamic function, is exploited also to accommodate voltage and/or fuel supply lines.
  • downstream flame stabilizer can be obtained with virtually no impact on the gas flow through the combustion chamber, which is not appreciably affected.
  • the change in cross section of the combustion chamber is defined by at least one of a truncated downstream end of the streamlined body and a circumferential step in a combustor liner delimiting the combustion chamber around the downstream flame location.
  • At least one intermediate flame stabilizer is provided at a respective intermediate flame location between the upstream flame location and the downstream flame location.
  • Additional stabilized flame locations may be provided along the combustion chamber as desired to further reduce pollutant emissions.
  • a gas turbine comprising a sequential burner, the sequential burner including a first-stage combustor and a second-stage combustor as defined above.
  • the gas turbine comprises a controller configured to set a current flame location at the downstream flame location in a first operating condition, corresponding to load values above a first load threshold, and to set the current flame location at the upstream flame location in a second operating condition, corresponding to load values below a second load threshold, not exceeding the first load threshold.
  • the controller is configured to control a hot gas temperature of hot gas flowing from the first-stage combustor to the second-stage combustor.
  • Hot gas temperature control helps stabilizing flame position. In some conditions, hot gas temperature control may be sufficient for stabilization at the upstream flame location.
  • the controller is configured to activate the downstream flame stabilizer selectively in the first operating condition.
  • the controller is configured to activate the upstream flame stabilizer selectively in the second operating condition.
  • a method of controlling a sequential combustor of gas turbine with a first-stage combustor and a second-stage combustor including:
  • stabilizing the current flame location comprises controlling a hot gas temperature of hot gas flowing from the first-stage combustor to the second-stage combustor.
  • Figure 1 shows a simplified view of a gas turbine assembly, designated as whole with numeral 1.
  • the gas turbine assembly 1 comprises a compressor section 2, a combustor assembly 3 and a turbine section 5.
  • the compressor section 2 and the turbine section 3 extend along a main axis A.
  • An airflow compressed in the compressor section 2 is mixed with fuel and is burned in the combustor assembly 3, possibly added with dilution air.
  • the burned mixture is then expanded to the turbine section 5 and converted in mechanical power.
  • the combustor assembly 3 is a two-stage sequential combustor and comprises a plurality of can combustors 10 arranged around the main axis A.
  • Each of the can combustors 10, one of which is shown in Figure 2 comprises a first-stage combustor 12 and a second-stage combustor 13 sequentially arranged and defining a flow channel 15.
  • the first-stage combustor 12 comprises a burner 16 and a combustion chamber 17.
  • a fuel lance 18 for feeding fuel to the second-stage combustor 13 extends axially through the combustion chamber 17.
  • the second-stage combustor 13 which is illustrated in greater detail in Figure 3 , comprises a burner 20, a combustion chamber 21 and a transition element 22 for coupling to the turbine section 5, here not shown.
  • the burner 20 is configured to admix a hot gas flow received from the first-stage combustor 12 and fuel received through the fuel lance 18.
  • the burner 20 comprises an outer wall 24 and a central body 25 which extends along a burner axis. Within the burner 20, the flow channel 15 is delimited by the wall 24 and by the central body 25. Fuel is injected in the flow channel 15 through injectors (not shown).
  • the combustion chamber 21 extends along a flow direction downstream of the burner 20.
  • the combustion chamber 21 comprises an outer liner 27, an inner liner 28 and an elongated streamlined body 30.
  • the outer liner 27 surrounds the inner liner 28 at a distance therefrom, so that a cooling channel 31 is defined between the outer liner 27 and the inner liner 28.
  • the inner liner 28 delimits the flow channel 15 outwards in the combustion chamber 21 and joins the wall 24 of the burner 20 in such a way to define a smooth transition without steps and possibly sharp edges.
  • an edge of the wall 24 matches an adjacent edge of the inner liner 27.
  • the streamlined body 30 extends from the burner 20 into the combustion chamber 21 substantially axially until an outlet thereof and joins the central body 25 of the burner 20 also in such a way to define a smooth transition without steps and possibly sharp edges.
  • a transition region 32 between the burner 20 and the combustion chamber 21 a cross section of the flow channel changes gradually along the flow direction. Therefore, the transition region is configured to prevent gas flowing through the combustion chamber 21 from recirculating and creating stagnations regions.
  • a downstream flame location 33 and an upstream flame location 34 are defined within the combustion chamber 21 at a distance from one another.
  • the downstream flame location 33 is defined at an outlet of the combustion chamber 21 and the upstream flame location 34 is defined in the transition region 32 between the burner 20 and the combustion chamber 21, e.g. at an inlet of the combustion chamber 21.
  • the whole space available in the combustion chamber 21 can be exploited to minimize the post flame residence time at full load and high temperature and improve air and fuel mixing, thus reducing NOx emissions, and to maximize the post flame residence time at part load and low temperature, thus reducing CO emissions.
  • the distance between the upstream flame location and the downstream flame location could be lower than in the example of Figures 2 and 3 .
  • a downstream flame stabilizer 35 and an upstream flame stabilizer 36 are provided at the downstream flame location 33 and at the upstream flame location 34, respectively.
  • the downstream flame stabilizer 35 comprises a downstream electrode system, operable to provide ignition energy in the combustion chamber 21 at the downstream flame location 33.
  • the downstream electrode system comprises a set of downstream electrodes 37 on the streamlined body 30 at the downstream flame location 33 and a downstream voltage supply line 38 running inside the streamlined body 30 and the fuel lance 18.
  • the downstream flame stabilizer 35 produces sparks across the combustion chamber 21 and causes ignition of the mixture flowing through the combustion chamber 21 irrespective of temperature conditions and of the self-ignition time of the mixture.
  • the self-ignition time of the mixture may be even so long that the mixture would not self-ignite within the combustion chamber 21, but the downstream flame stabilizer 35 is in any case capable of stabilizing the flame at the downstream flame location 33.
  • the upstream flame stabilizer 36 comprises an upstream electrode system, operable to provide ignition energy in the combustion chamber 21 at the upstream flame location 34.
  • the upstream electrode system comprises a set of upstream electrodes 39 on the streamlined body 30 at the upstream flame location 34 and an upstream voltage supply line 40.
  • the upstream electrodes 39 may be arranged on the central body 25 of the burner 20 at the interface between the burner 20 and the combustion chamber 21.
  • the downstream flame stabilizer 35 and the upstream flame stabilizer 36 are selectively activated by the controller 7 on the basis of the load determined for the gas turbine assembly 1.
  • the controller 7 activates the downstream flame stabilizer 35 and deactivates the upstream flame stabilizer 36, thus setting a current flame location at the downstream flame location 33.
  • the controller 7 activates the upstream flame stabilizer 36 and deactivates the downstream flame stabilizer 35. Accordingly, the current flame location is set at the upstream flame location 34.
  • the low load threshold does not exceed the high load threshold.
  • a second-stage combustor 113 comprises a burner 120 and a combustion chamber 121.
  • the combustion chamber 121 comprises a downstream flame stabilizer 135 at a downstream flame location 133, substantially as described with reference to Figure 2 and 3 , and an upstream flame stabilizer 136 at an upstream flame location 134 at an inlet of the combustion chamber 121.
  • the burner 120 and the combustion chamber 121 are configured to prevent recirculation of hot gas flow at the upstream flame location 134.
  • the upstream flame stabilizer 136 is defined by an upstream pilot burner that comprises upstream fuel nozzles 139 and an upstream fuel supply line 140 coupled to the upstream fuel nozzles 139 and running through the fuel lance 18.
  • the upstream fuel nozzles 139 are uniformly distributed in a circumferential direction on the streamlined body, here designated by 130, and may be provided in the form of radially extending injection conduits which end at an intermediate radial distance between the streamlined body 130 and the inner liner, here 128, of the combustor chamber 121.
  • the upstream fuel nozzles may be provided in the form of openings in a lateral surface of the streamlined body 130.
  • a second-stage combustor 213 comprises a burner 220 and a combustion chamber 221.
  • the combustion chamber 221 in turn comprises a downstream flame stabilizer 235 at a downstream flame location 233 and an upstream flame stabilizer 236 at an upstream flame location 234 at an inlet of the combustion chamber 221.
  • the burner 220 and the combustion chamber 221 are configured to prevent recirculation of hot gas flow at the upstream flame location 234.
  • the downstream flame stabilizer 235 is defined by a downstream pilot burner having a set of downstream fuel nozzles 241 on the streamlined body, here designated by 230, at the downstream flame location 233 and a downstream fuel supply line 242 coupled to the downstream fuel nozzles 241 and running inside the streamlined body 230.
  • the downstream fuel nozzles 241 are uniformly distributed in a circumferential direction on the streamlined body 230, and may be provided in the form of radially extending injection conduits which end at an intermediate radial distance between the streamlined body 230 and the inner liner, here designated by 228, of the combustor chamber 221.
  • the downstream fuel nozzles may be provided also in the form of openings in a lateral surface of the streamlined body 230, as an alternative.
  • the upstream flame stabilizer 236 is defined by an upstream pilot burner (as already described with reference to Figure 4 ) that comprises upstream fuel nozzles 239 and an upstream fuel supply line 240 coupled to the upstream fuel nozzles 239 and running through the fuel lance 18.
  • Fuel supply to the downstream flame stabilizer 235 and to the upstream flame stabilizer 236 is determined by the controller 7 based on current load of the gas turbine 1. Specifically, the controller activates the downstream flame stabilizer 235 and deactivates the upstream flame stabilizer 236 when the current load exceeds a high load threshold; and activates the upstream flame stabilizer 236 and deactivate the downstream flame stabilizer 235 when the current load is below a low load threshold.
  • a second-stage combustor 313 comprises a burner 320 and a combustion chamber 321.
  • the combustion chamber 321 comprises an outer liner 327, an inner liner 328 and an elongated streamlined body 330.
  • the inner liner 328 delimits a flow channel 315 outwards in the combustion chamber 321 and joins a wall 324 of the burner 320 in such a way to define a smooth transition without steps and possibly sharp edges, substantially as already described with reference to Figures 2 and 3 .
  • the streamlined body 330 extends from the burner 320 into the combustion chamber 321 substantially axially until an outlet thereof and joins a central body 325 of the burner 320 also in such a way to define a smooth transition without steps and possibly sharp edges.
  • a downstream flame location 333 and an upstream flame location 334 are defined in the combustion chamber 321 at a distance from one another and a downstream flame stabilizer 335 and an upstream flame stabilizer 336 are provided at the downstream flame location 333 and at the upstream flame location 334, respectively.
  • the downstream flame stabilizer 335 comprises a change in cross section of the combustion chamber 321 along the flow direction at the downstream flame location 333.
  • the change in cross section is configured to cause gas flowing through the combustion chamber 321 to recirculate at the downstream flame location 333.
  • the change in cross section of the combustion chamber 321 is defined by a truncated downstream end 330a of the streamlined body 330 and by a circumferential step 328a in the inner liner 327 delimiting the combustion chamber 321 around the downstream flame location 333.
  • the change in cross section maybe defined only by the truncated downstream end of the streamlined body or only by the circumferential step of the inner liner.
  • the upstream flame stabilizer 336 may comprise an upstream electrode system as disclosed with reference to Figures 2 and 3 .
  • the upstream flame stabilizer may comprise an upstream pilot burner.
  • Figure 7 shows another embodiment, in which a second-stage combustor 413 comprises a burner 420 and a combustion chamber 421.
  • a downstream flame location 433 and an upstream flame location 434 are defined in the combustion chamber 421 at a distance from one another and a downstream flame stabilizer 445 is provided at the downstream flame location 433.
  • the downstream flame stabilizer 435 may be of any kind previously described, e.g. including an electrode system, a pilot burner or a change in cross section of the flow channel.
  • electrodes 437 are provided on a streamlined body 430 of the combustion chamber 421, with a voltage supply line 438 in the streamlined body 430.
  • a transition region 432 between the burner 420 and the combustion region 421 is configured to prevent gas flowing through the combustion chamber form recirculating at the upstream flame location 434, as described with reference to Figures 2 and 3 .
  • the controller 7 is configured to control an inlet gas temperature of hot gas from the first-stage combustor 12 to the second-stage combustor 413 and to selectively activate the downstream flame stabilizer 435 as desired based on the current load of the gas turbine 1.
  • the controller 7 may act e.g. on a power split or power ratio of power delivered by the first-stage combustor 12 to power delivered by the second-stage combustor 413, and/or on a flow of dilution air admixed to the hot gas from the first-stage combustor 12 before entering the second-stage combustor 413.
  • the controller 7 uses temperature control to set a current flame location at the upstream flame location 434, in this case without the aid of a upstream flame stabilizer.
  • the controller may set the current flame location also at the downstream flame location by controlling the inlet gas temperature instead of or in addition to using a stabilizer in the combustion chamber.
  • the current flame location may be set at the upstream flame location by temperature control or with the aid of a selectively activatable upstream flame stabilizer.
  • a second-stage combustor 513 comprises a burner 520 and a combustion chamber 521.
  • a downstream flame stabilizer 535 and an upstream flame stabilizer 536 are respectively provided on a streamlined body 530 of the combustion chamber 521 at a downstream flame location 533 and at an upstream flame location 534, which are defined in the combustion chamber 521.
  • one or more intermediate flame locations 550 are defined in the combustion chamber between the upstream flame location 234 and the downstream flame location 233 and a respective intermediate flame stabilizer 551 is provided at each intermediate flame location 550.
  • the burner 520 and the combustion chamber 521 are configured to prevent recirculation of hot gas flow at the upstream flame location 534.
  • the downstream flame stabilizer 535 and the upstream flame location 536 may comprise an electrode system, having a set of downstream electrodes 537 and a downstream voltage supply line 538 and a set of upstream electrodes 539 and an upstream voltage supply line 540, respectively.
  • Each intermediate flame stabilizer 551 comprises a respective set of intermediate electrodes 552 at the respective intermediate flame location 550 and a respective voltage supply line 553, running in the streamlined body 530 and in the fuel lance 18.
  • each of the intermediate flame stabilizer 551 is selectively activatable by the controller 7 to set a current flame location at the respective intermediate flame location 550 based on a current load of the gas turbine 1 as desired.

Claims (12)

  1. Zweitstufen-Verbrenner für einen sequentiellen Verbrenner einer Gasturbine, umfassend:
    einen Brenner (20; 120; 220; 320; 420; 520);
    eine Brennkammer (21; 121; 221; 321; 421; 521), die sich entlang einer Strömungsrichtung stromabwärts des Brenners (20; 120; 220; 320; 420; 520) erstreckt, wobei der Brenner (20; 120; 220; 320; 420; 520) und die Brennkammer (21; 121; 221; 321); 421; 521) einen Strömungskanal (15) bilden und eine stromabwärts gelegene Flammenposition (33; 133; 233; 333; 433; 533) und eine stromaufwärts gelegene Flammenposition (34; 134; 234; 334; 434; 534) innerhalb der Brennkammer (21; 121; 221; 321; 421; 521) definiert sind; und
    einen stromabwärts gelegenen Flammenstabilisator (35; 135; 235; 335; 435; 535) an der stromabwärts gelegenen Flammenposition (33; 133; 233; 333; 433; 533);
    wobei sich ein Querschnitt des Strömungskanals (15) entlang der Strömungsrichtung in einem Übergangsbereich (32; 432) zwischen dem Brenner (20; 120; 220; 320; 420; 520) und der Brennkammer (21; 121; 221; 321; 421; 521) allmählich ändert, wodurch der Übergangsbereich (32; 432) verhindert, dass das durch die Brennkammer (21; 121; 221; 321; 421; 521) strömende Gas an der stromaufwärts gelegenen Flammenposition (34; 134; 234; 334; 434; 534) rezirkuliert;
    gekennzeichnet durch:
    einen langgestreckten stromlinienförmigen Körper (30; 130; 230; 330; 430; 530), der sich von dem Brenner (20; 120; 220; 320; 420; 520) in die Brennkammer (21; 121; 221; 321; 421; 521) erstreckt, wobei der Brenner (20; 120; 220; 320; 420; 520) mit einem zentralen Körper (25) versehen ist und der stromlinienförmige Körper (30; 130; 230; 330; 430; 530) sich von dem Brenner (20; 120; 220; 320; 420; 520) im Wesentlichen axial bis zu einem Auslass der Brennkammer (21; 121; 221; 321; 421; 521) erstreckt und so an den zentralen Körper (25) anschließt, dass ein glatter Übergang ohne Stufen und möglicherweise scharfe Kanten definiert wird, wodurch er dafür konfiguriert ist, zu verhindern, dass das durch die Brennkammer (21; 121; 221; 321; 421; 521) strömende Gas an der stromaufwärts gelegenen Flammenposition (34; 134; 234; 334; 434; 534) rezirkuliert; und
    einen selektiv aktivierbaren stromaufwärts gelegenen Flammenstabilisator (36; 136; 236; 336; 536) an der stromaufwärts gelegenen Flammenposition (34; 134; 234; 334; 434; 534), wobei der stromaufwärts gelegene Flammenstabilisator (36; 136; 236; 336; 536) wenigstens eines umfasst von:
    einem stromaufwärts gelegenen Elektrodensystem (39, 40; 539, 540), das betreibbar ist, um Zündenergie in der Brennkammer (21; 121; 221; 321; 421; 521) an der stromaufwärts gelegenen Flammenposition (34; 134; 234; 334; 434; 534) bereitzustellen; und
    einem stromaufwärts gelegenen Zündbrenner (139, 140; 239, 240) an der stromaufwärts gelegenen Flammenposition (34; 134; 234; 334; 434; 534).
  2. Zweitstufen-Verbrenner nach Anspruch 1, wobei der stromabwärts gelegene Flammenstabilisator (35; 135; 235; 335; 435; 535) wenigstens eines umfasst von:
    einem stromabwärts gelegenen Elektrodensystem (37, 38; 437, 438; 537, 538), das betreibbar ist, um Zündenergie in der Brennkammer (21; 121; 221; 321; 421; 521) an der stromabwärts gelegenen Flammenposition (33; 133; 233; 333; 433; 533) bereitzustellen;
    einem stromabwärts gelegenen Zündbrenner (241, 242) an der stromabwärts gelegenen Flammenposition (33; 133; 233; 233; 333; 433; 533); und
    einer Querschnittsänderung (328a, 330a) der Brennkammer (21; 121; 221; 321; 421; 521) entlang der Strömungsrichtung an der stromabwärts gelegenen Flammenposition (33; 133; 233; 333; 433; 533), wobei die Querschnittsänderung (328a, 330a) dafür konfiguriert ist, eine Rezirkulation von durch die Brennkammer (21; 121; 221; 321; 421; 521) strömendem Gas an der stromabwärts gelegenen Flammenposition (33; 133; 233; 333; 433; 533) zu bewirken, wobei die Querschnittsänderung (328a, 330a) der Brennkammer (321) durch ein abgestumpftes stromabwärts gelegenes Ende (330a) des stromlinienförmigen Körpers (330) und/oder eine Umfangsstufe (328a) in einer Brennkammerauskleidung (328), die die Brennkammer (321) um die stromabwärts gelegene Flammenposition (233) herum begrenzt, definiert ist.
  3. Zweitstufen-Verbrenner nach Anspruch 2, wobei das stromabwärts gelegene Elektrodensystem (37, 38; 437, 438; 537, 538) einen Satz stromabwärts gelegener Elektroden (37; 437; 537) auf dem stromlinienförmigen Körper (30; 430; 530) an der stromabwärts gelegenen Flammenposition (33; 433; 533) und eine stromabwärts gelegene Spannungsversorgungsleitung (38; 437; 538), die innerhalb des stromlinienförmigen Körpers (30; 430; 530) verläuft, umfasst.
  4. Zweitstufen-Verbrenner nach Anspruch 2 oder 3, wobei der stromabwärts gelegene Zündbrenner (241, 242) einen Satz stromabwärts gelegener Brennstoffdüsen (241) an dem stromlinienförmigen Körper (230) an der stromabwärts gelegenen Flammenposition (233) und eine stromabwärts gelegene Brennstoffzufuhrleitung (242), die innerhalb des stromlinienförmigen Körpers (230) verläuft, umfasst.
  5. Zweitstufen-Verbrenner nach einem der vorangehenden Ansprüche, der wenigstens einen Zwischenflammenstabilisator (551) an einer entsprechenden Zwischenflammenposition (551) zwischen der stromaufwärts gelegenen Flammenposition (34; 134; 234; 334; 434; 534) und der stromabwärts gelegenen Flammenposition (33; 133; 233; 333; 433; 533) umfasst.
  6. Gasturbine mit einem sequentiellen Verbrenner, wobei der sequentielle Verbrenner einen Erststufen-Verbrenner (12) und einen Zweitstufen-Verbrenner (13; 113; 213; 313; 413; 513) nach einem der vorangehenden Ansprüche aufweist.
  7. Gasturbine nach Anspruch 6, die eine Steuer/Regelvorrichtung (7) umfasst, die dafür konfiguriert ist, in einem ersten Betriebszustand, der Lastwerten über einem ersten Lastschwellenwert entspricht, eine aktuelle Flammenposition an der stromabwärts gelegenen Flammenposition (33; 133; 233; 333; 433; 533) einzustellen und in einem zweiten Betriebszustand, der Lastwerten unter einem zweiten Lastschwellenwert entspricht, der den ersten Lastschwellenwert nicht überschreitet, die aktuelle Flammenposition an der stromaufwärts gelegenen Flammenposition (34; 134; 234; 334; 434; 534) einzustellen.
  8. Gasturbine nach Anspruch 7, wobei die Steuer/Regelvorrichtung (7) dafür konfiguriert ist, eine Heißgastemperatur des von dem Erststufen-Verbrenner zu dem Zweitstufen-Verbrenner strömenden Heißgases zu steuern/regeln.
  9. Gasturbine nach Anspruch 7 oder 8, wobei die Steuer/Regelvorrichtung (7) dafür konfiguriert ist, den stromabwärts gelegenen Flammenstabilisator (35; 135; 235; 435; 535) selektiv im ersten Betriebszustand zu aktivieren.
  10. Gasturbine nach Anspruch 9, wenn abhängig von Anspruch 6, wobei die Steuer/Regelvorrichtung (7) dafür konfiguriert ist, den stromaufwärts gelegenen Flammenstabilisator (36; 136; 236; 336; 536) selektiv im zweiten Betriebszustand zu aktivieren.
  11. Verfahren zum Steuern/Regeln eines sequentiellen Verbrenners einer Gasturbine mit einer Erststufen-Verbrenner (12) und einem Zweitstufen-Verbrenner (13; 113; 213; 313; 413; 513) nach Anspruch 1;
    wobei das Verfahren das Stabilisieren einer aktuellen Flammenposition an der stromabwärts gelegenen Flammenposition (33; 133; 233; 333; 433; 533) in einem ersten Betriebszustand, der Lastwerten über einem ersten Lastschwellenwert entspricht, und das Stabilisieren der aktuellen Flammenposition an der stromaufwärts gelegenen Flammenposition (34; 134; 234; 334; 434; 534) in einem zweiten Betriebszustand, der Lastwerten unter einem zweiten Lastschwellenwert entspricht, der den ersten Lastschwellenwert nicht überschreitet, umfasst.
  12. Verfahren nach Anspruch 11, wobei das Stabilisieren der aktuellen Flammenposition das Steuern/Regeln der Heißgastemperatur des von dem Erststufen-Verbrenner zu dem Zweitstufen-Verbrenner strömenden Heißgases umfasst.
EP17158577.1A 2017-02-28 2017-02-28 Zweite stufe kombinationskammer für eine sequentielle verbrennung kammer einer gasturbine Active EP3367001B1 (de)

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CN201810168642.0A CN108506962B (zh) 2017-02-28 2018-02-28 用于燃气轮机的连续燃烧器的第二级燃烧器

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US2771743A (en) * 1951-08-10 1956-11-27 Rolls Royce Gas-turbine engine with reheat combustion equipment
US2974488A (en) * 1956-11-27 1961-03-14 Snecma Combustion devices for continuous-flow internal combustion machines
US3540216A (en) * 1967-01-23 1970-11-17 Snecma Two-flow gas turbine jet engine
US4790744A (en) * 1986-03-14 1988-12-13 Centre National De La Recherche Scientifique Burner with low emission of polluting gases

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JP2950720B2 (ja) * 1994-02-24 1999-09-20 株式会社東芝 ガスタービン燃焼装置およびその燃焼制御方法
CN100552301C (zh) * 2003-09-05 2009-10-21 德拉文公司 燃气轮机引擎的稳定燃烧用导引燃烧器室
CN104541104A (zh) * 2012-08-24 2015-04-22 阿尔斯通技术有限公司 利用稀释气体混合器的连续燃烧
EP3015772B1 (de) * 2014-10-31 2020-01-08 Ansaldo Energia Switzerland AG Brennkammeranordnung für eine gasturbine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2771743A (en) * 1951-08-10 1956-11-27 Rolls Royce Gas-turbine engine with reheat combustion equipment
US2974488A (en) * 1956-11-27 1961-03-14 Snecma Combustion devices for continuous-flow internal combustion machines
US3540216A (en) * 1967-01-23 1970-11-17 Snecma Two-flow gas turbine jet engine
US4790744A (en) * 1986-03-14 1988-12-13 Centre National De La Recherche Scientifique Burner with low emission of polluting gases

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