EP3438530B1 - Sequenzielle brennkammeranordnung für eine gasturbinenanordnung - Google Patents

Sequenzielle brennkammeranordnung für eine gasturbinenanordnung Download PDF

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Publication number
EP3438530B1
EP3438530B1 EP17184122.4A EP17184122A EP3438530B1 EP 3438530 B1 EP3438530 B1 EP 3438530B1 EP 17184122 A EP17184122 A EP 17184122A EP 3438530 B1 EP3438530 B1 EP 3438530B1
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EP
European Patent Office
Prior art keywords
air
lance
along
mixer
sequential
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.)
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Application number
EP17184122.4A
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English (en)
French (fr)
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EP3438530A1 (de
Inventor
Alessandro Scarpato
Luis TAY-WO-CHONG-HILARES
Mirko Bothien
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.)
Ansaldo Energia Switzerland AG
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Ansaldo Energia Switzerland AG
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Priority to EP17184122.4A priority Critical patent/EP3438530B1/de
Priority to CN201810845402.XA priority patent/CN109323286B/zh
Publication of EP3438530A1 publication Critical patent/EP3438530A1/de
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Publication of EP3438530B1 publication Critical patent/EP3438530B1/de
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Classifications

    • 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
    • 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
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • 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 sequential combustor assembly for a gas turbine assembly.
  • the present invention relates to a sequential combustor assembly for a gas turbine assembly which is part of a plant for the production of electrical power.
  • a sequential combustor assembly comprises a first-stage combustor and a second-stage combustor which is arranged downstream the first-stage combustor along the gas flow.
  • a mixer is arranged between the first-stage combustor and the second-stage combustor. In use, dilution air is selectively injected in said mixer.
  • EP3015772 which disclose the features of the preamble of claim 1.
  • the object of the present invention is therefore to provide a sequential combustor assembly which enables avoiding or at least mitigating the described drawbacks.
  • the lance is provided with a plurality of first air outlets circumferentially aligned and evenly distributed along the circumference centered on the main axis. In this way a better uniform temperature distribution can be reached in the mixer.
  • the plurality of first air outlets have the same outlet section. In this way the amount of the air flowing into the mixer can be controlled.
  • the at least one first air outlet is provided with an insert.
  • the lance is provided with a plurality of second air outlets axially spaced from the first air outlet along the middle portion. In this way a better uniform temperature distribution can be reached in the mixer.
  • the plurality of second air outlets are circumferentially aligned.
  • the first air outlet and the second air outlet are in fluidic communication with the first air channel. In this way the pressure of air injected through the first air outlet and the second air outlet is the same.
  • the lance comprises at least one second air channel distinct from the first air channel; the first air outlet being in fluidic communication with the first air channel while the second air outlet being in fluidic communication with the second air channel.
  • the sequential combustor assembly comprises a liner; a part of the liner defines the mixer; the liner being provided with at least one first air injection along the mixer.
  • the liner is provided with at least one second air injection axially spaced from the first air injection along the mixer. In this way a regulation and an optimization of the damping can be obtained.
  • the at least one first air injection is in fluidic communication with a respective liner air plenum; wherein the liner plenum and the first air channel are adapted such that the pressure of the air in the liner plenum may be greater than the pressure of the air in the first air channel of the lance. It is furthermore an object of the present invention to provide a turbine assembly having an improved efficiency. According to the present invention, there is provided a gas turbine assembly as claimed in claim 14.
  • reference numeral 1 indicates a gas turbine assembly.
  • the gas turbine assembly 1 comprises a compressor section 2, a sequential 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 sequential combustor assembly 3.
  • the burned mixture is then expanded to the turbine section 5 and converted in mechanical power.
  • the sequential combustor assembly 3 comprises at least one can 6 which extends along a main axis B and comprises a first-stage combustor 8 and a second-stage combustor 9 sequentially arranged along the gas flow direction G.
  • the second stage combustor 9 is arranged downstream the first stage combustor 8 along the gas flow.
  • the combustor assembly 3 further comprises a mixer 11 arranged between the first stage combustor 8 and the second stage combustor 9.
  • the first-stage combustor 8 comprises at least one burner 13 and a first combustion chamber 14.
  • the second-stage combustor 9 comprises a second combustion chamber 16.
  • the combustor assembly 3 further comprises a transition element 17 arranged downstream the can 6 for coupling the second combustion chamber 16 to the turbine section 5 (not shown) .
  • the first combustion chamber 14, the second combustion chamber 16 and the mixer 11 are in fluidic communication and are defined by a liner 18 which extends axially.
  • the liner 18 is substantially cylindrical along the first combustion chamber 14, is conical along the mixer 11 and again substantially cylindrical along the second combustion chamber 16.
  • the liner 18 converges along the gas flow direction G.
  • the combustor assembly 3 further comprises a lance 19, which extends axially through the first combustion chamber 14 of the first-stage combustor 8, through the mixer 11 and discharges in the second combustion chamber 16.
  • the lance 19 is arranged along the axis B, i.e. substantially centrally with respect to the liner 18.
  • the lance 19 is configured to feed air and at least one fuel.
  • the lance 19 comprises at least one fuel channel 20 and at least one air channel 21.
  • Air flowing in the air channel 21 comes from a respective lance plenum (not illustrated) wherein air has a determined pressure.
  • the lance comprises a further fuel channel.
  • the lance comprises a plurality of air channels, in each of which flows air coming from different plena having preferably different air pressure.
  • the fuel channel 20 is centrally arranged, while the air channel 21 extends about the fuel channel 20.
  • the lance 19 comprises an inlet portion 22 housed in the first combustion chamber 14, a middle portion 23 and an outlet portion 24 housed in the second combustion chamber 16.
  • the lance 19 is provided with at least one fuel discharge 26 in the outlet portion 24 in order to provide fuel to the second combustion chamber 16.
  • the lance 19 comprises a swirler 27 and one first fuel discharge 26 located at the swirler 27 and at least one second fuel discharge 26 located near the tip of the lance 19.
  • the lance 19 is further provided with at least one air outlet 28 along the middle portion 23 housed in the mixer 11.
  • the lance 19 is provided with a plurality of air outlets 28 circumferentially aligned.
  • the plurality of air outlets 28 are evenly distributed along the circumference.
  • the plurality of air outlets are unevenly distributed in order to create zones of air injections substantially separated.
  • the plurality of air outlets 28 have the same outlet section.
  • the plurality of air outlets can have different outlet sections in order to regulate the air flow rate entering in the mixer 11.
  • the at least one air outlet 28 is provided with an insert.
  • the insert can be configured to regulate the outlet section and/or to create turbulence and/or to deviate the flow in a desired direction and/or to modify the position of the injection of the air flow inside the mixer.
  • the air outlet 28 can be a slot realized on the middle portion 23 of the lance 19.
  • the slot is an annular slot.
  • the lance 19 is provided with at least one first air outlet 30, at least one second air outlet 31 and, preferably, at least a third air outlet 32.
  • the first air outlet 30, the second air outlet 31 and the third air outlet 32 are axially spaced along the middle portion 23.
  • air exiting through the first air outlet 30, the second air outlet 31 and the third air outlet 32 comes from the same air channel 21.
  • the second air outlet and the third air outlet comes from respective separate air channels supplied with air coming from different plena having different air pressures.
  • the lance 19 is provided with a plurality of first air outlets 30, a plurality of second air outlets 31 and, preferably, a plurality of third air outlets 32.
  • the plurality of first air outlets 30 are circumferentially aligned
  • the plurality of second air outlets 31 are circumferentially aligned
  • the plurality of third air outlets 32 are circumferentially aligned.
  • the plurality of first air outlets 30, the plurality of second air outlets 31 and the plurality of third air outlets 32 are evenly distributed along the respective circumferences.
  • the liner 18 is provided with at least one air injection 35 along the mixer 11.
  • the liner 18 is provided with a first air injection 35a, a second air injection 35b and a third air injection 35c.
  • the first air injection 35a, the second air injection 35b and the third air injection 35c are axially spaced along the mixer 11.
  • the liner 18 is provided with a plurality of first air injections 35a, a plurality of second air injections 35b and a plurality of third air injections 35c.
  • air exiting through the air injection 35 or through the air injections 35a, 35b, 35c comes from a respective liner plenum (not illustrated) wherein air has a determined pressure.
  • the liner plenum air has a pressure different from the pressure of the air in the lance plenum.
  • the liner plenum and the lance plenum can have the same pressure.
  • the liner plenum and the lance plenum can coincide. Thanks to the presence of the air injections 35a, 35b, 35c, the air jet penetration required for air outlets 28, 30, 31, 32 in the lance 16 to create a uniform temperature distribution is lower since air is injected from both the liner wall (through air injections 35a, 35b, 35c) and the central lance 16 (through air outlets 28, 30, 31, 32). Consequently the required pressure drop in air outlets 28, 30, 31, 32 is also lower.
  • Axial positions of air injections 35a, 35b, 35c and of air outlets 30, 31, 32 can be defined in the designing phase in order to conveniently damp the temperature fluctuations at the inlet of the second-stage combustor 9.
  • air injections 35a, 35b, 35c can be designed in order to direct air towards distal zones of the mixer 11 near the wall of the liner 18 while the air outlets 30, 31, 32 can be designed in order to direct air towards proximal zones of the mixer 11 near the lance 16.
  • air outlets 30, 31, 32 direct air mainly towards zone of the mixer which are radially proximal with respect to axis B
  • air injections 35a, 35b, 35c direct air mainly towards zone of the mixer which are radially distal with respect to axis B.
  • the axial position of air injections 35a, 35b, 35c and of air outlets 30, 31, 32 can be selected in order to have a uniform distribution of the air injected from the lance 16 and from the liner 18 or in order to focus the air injection towards one or more zones of the mixer 11 wherein temperature fluctuations are particularly relevant.
  • the design and the axial position of air injections 35a, 35b, 35c and of air outlets 30, 31, 32 can be optimized in order to damp different unstable modes affecting the mixer 11.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Claims (14)

  1. Sequenzielle Brennkammeranordnung für eine Gasturbinenanordnung (1), wobei sich die sequenzielle Brennkammeranordnung (3) entlang einer Hauptachse (B) erstreckt und enthält:
    - eine erste Brennkammerstufe (8);
    - eine zweite Brennkammerstufe (9), die stromabwärts der ersten Brennkammerstufe (8) entlang dem Gasstrom angeordnet ist;
    - einen Mischer (11), der zwischen der ersten Brennkammerstufe (8) und der zweiten Brennkammerstufe (9) angeordnet ist; und
    - eine Lanze (19), die entlang der Hauptachse (B) angeordnet ist und durch die erste Brennkammerstufe (8), durch den Mischer (11) und zumindest teilweise durch die zweite Brennkammerstufe (9) verläuft, wobei die Lanze (19) mindestens einen ersten Luftkanal (21) aufweist, wobei die Lanze (19) einen Einlassteil (22), der in der ersten Brennkammerstufe (8) untergebracht ist, einen Mittelteil (23), der in dem Mischer (11) untergebracht ist, und einen Auslassteil (24), der in der zweiten Brennkammerstufe (9) untergebracht ist, aufweist; wobei die Lanze (19) entlang dem Mittelteil (23) mit mindestens einem ersten Luftauslass (30) und entlang dem Mittelteil (23) mit mindestens einem zweiten Luftauslass versehen ist;
    wobei die Anordnung dadurch gekennzeichnet ist, dass
    - die Lanze (19) entlang dem Mittelteil (23) ferner mit mindestens einem dritten Luftauslass (32) versehen ist;
    - der mindestens eine erste Luftauslass (30), der mindestens eine zweite Luftauslass (31) und der mindestens eine dritte Luftauslass (32) entlang dem Mittelteil (23) axial beanstandet sind.
  2. Sequenzielle Brennkammeranordnung nach Anspruch 1, wobei die Lanze (19) mit einer Vielzahl von ersten Luftauslässen (30) versehen ist, die über den Umfang um die Hauptachse (B) ausgerichtet sind.
  3. Sequenzielle Brennkammeranordnung nach Anspruch 2, wobei die Vielzahl von ersten Luftauslässen (30) entlang dem um die Mittelachse (B) zentrierten Umfang gleichmäßig verteilt ist.
  4. Sequenzielle Brennkammeranordnung nach Anspruch 2 oder 3, wobei die Vielzahl der ersten Luftauslässe (30) den gleichen Auslassquerschnitt hat.
  5. Sequenzielle Brennkammeranordnung nach einem der vorhergehenden Ansprüche, wobei der mindestens eine erste Luftauslass (30) mit einem Einsatz versehen ist.
  6. Sequenzielle Brennkammeranordnung nach einem der vorhergehenden Ansprüche, wobei die Lanze mit einer Vielzahl von zweiten Luftauslässen (31) versehen ist, die entlang dem Mittelteil (23) von dem mindestens einen ersten Luftauslass (30) axial beanstandet sind.
  7. Sequenzielle Brennkammeranordnung nach Anspruch 6, wobei die Vielzahl der zweiten Luftauslässe (31) über den Umfang um die Hauptachse (B) ausgerichtet ist.
  8. Sequenzielle Brennkammeranordnung nach einem der vorhergehenden Ansprüche, wobei der mindestens eine erste Luftauslass (30) und der mindestens eine zweite Luftauslass (31) in Fluidverbindung mit dem ersten Luftkanal (21) stehen.
  9. Sequenzielle Brennkammeranordnung nach einem der Ansprüche 2 bis 7, wobei die Lanze (19) mindestens einen zweiten Luftkanal aufweist, der von dem ersten Luftkanal (21) verschieden ist; wobei der mindestens eine erste Luftauslass (30) in Fluidverbindung mit dem ersten Luftkanal (21) steht, während der mindestens eine zweite Luftauslass (31) in Fluidverbindung mit dem zweiten Luftkanal steht.
  10. Sequenzielle Brennkammeranordnung nach einem der vorhergehenden Ansprüche, enthaltend eine Auskleidung (18), wobei ein Teil der Auskleidung (18) den Mischer (11) bildet, wobei die Auskleidung (18) mit mindestens einer ersten Lufteinspritzung (35; 35a, 35b, 35c) entlang dem Mischer (11) versehen ist.
  11. Sequenzielle Brennkammeranordnung nach Anspruch 10, wobei die Auskleidung (18) mit mindestens einer zweiten Lufteinspritzung (35b, 35c, 35d) versehen ist, die entlang dem Mischer (11) von der ersten Lufteinspritzung (35a, 35b, 35c) axial beanstandet ist.
  12. Sequenzielle Brennkammeranordnung nach Anspruch 10 oder 11, wobei die mindestens eine erste Lufteinspritzung (35; 35a, 35b, 35c) in Fluidverbindung mit einem jeweiligen Auskleidungsluftraum steht.
  13. Sequenzielle Brennkammeranordnung nach Anspruch 12, wobei der Auskleidungsluftraum und der erste Luftkanal (21) so ausgelegt sind, dass der Luftdruck in dem Auskleidungsluftraum größer sein kann als der Luftdruck in dem ersten Luftkanal (21) der Lanze (19).
  14. Gasturbinenanordnung, enthaltend einen Verdichterabschnitt (2), einen Turbinenabschnitt (5) und eine sequenzielle Brennkammeranordnung (3) nach einem der vorstehenden Ansprüche.
EP17184122.4A 2017-07-31 2017-07-31 Sequenzielle brennkammeranordnung für eine gasturbinenanordnung Active EP3438530B1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP17184122.4A EP3438530B1 (de) 2017-07-31 2017-07-31 Sequenzielle brennkammeranordnung für eine gasturbinenanordnung
CN201810845402.XA CN109323286B (zh) 2017-07-31 2018-07-27 用于燃气涡轮组件的顺序燃烧器组件

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17184122.4A EP3438530B1 (de) 2017-07-31 2017-07-31 Sequenzielle brennkammeranordnung für eine gasturbinenanordnung

Publications (2)

Publication Number Publication Date
EP3438530A1 EP3438530A1 (de) 2019-02-06
EP3438530B1 true EP3438530B1 (de) 2020-03-04

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EP17184122.4A Active EP3438530B1 (de) 2017-07-31 2017-07-31 Sequenzielle brennkammeranordnung für eine gasturbinenanordnung

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EP (1) EP3438530B1 (de)
CN (1) CN109323286B (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3702669B1 (de) * 2019-02-28 2022-08-03 Ansaldo Energia Switzerland AG Verfahren zum betrieb einer sequenziellen brennkammer einer gasturbine und gasturbine mit dieser sequenziellen brennkammer
EP3772615B1 (de) * 2019-08-08 2024-03-20 Ansaldo Energia Switzerland AG Sequenzielle brennkammeranordnung für eine gasturbinenanordnung und verfahren zum betreiben dieser sequentiellen brennkammeranordnung

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120304660A1 (en) * 2011-06-06 2012-12-06 Kupratis Daniel B Turbomachine combustors having different flow paths
EP2966356B1 (de) * 2014-07-10 2020-01-08 Ansaldo Energia Switzerland AG Sequentielle brennkammeranordnung mit einem mischer
EP2993404B1 (de) * 2014-09-08 2019-03-13 Ansaldo Energia Switzerland AG Verdünnungsgas oder Luftmischer für eine Brennkammer einer Gasturbine
EP3015772B1 (de) * 2014-10-31 2020-01-08 Ansaldo Energia Switzerland AG Brennkammeranordnung für eine gasturbine
EP3015771B1 (de) * 2014-10-31 2020-01-01 Ansaldo Energia Switzerland AG Brennkammeranordnung für eine gasturbine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
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None *

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Publication number Publication date
EP3438530A1 (de) 2019-02-06
CN109323286A (zh) 2019-02-12
CN109323286B (zh) 2022-03-08

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