EP3059501A1 - Procédé de commande d'un système de combustion - Google Patents

Procédé de commande d'un système de combustion Download PDF

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Publication number
EP3059501A1
EP3059501A1 EP15155961.4A EP15155961A EP3059501A1 EP 3059501 A1 EP3059501 A1 EP 3059501A1 EP 15155961 A EP15155961 A EP 15155961A EP 3059501 A1 EP3059501 A1 EP 3059501A1
Authority
EP
European Patent Office
Prior art keywords
air
oxygen
burner arrangement
pilot burner
lean
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.)
Withdrawn
Application number
EP15155961.4A
Other languages
German (de)
English (en)
Inventor
Mats Andersson
Olle Lindman
Tomas Öfverstedt
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP15155961.4A priority Critical patent/EP3059501A1/fr
Priority to PCT/EP2016/051891 priority patent/WO2016131634A1/fr
Publication of EP3059501A1 publication Critical patent/EP3059501A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • 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
    • F23R2900/03343—Pilot burners operating in premixed mode

Definitions

  • combustion section main burner arrangement, pilot burner arrangement, air-fuel mixture, fuel, compressor section, valve, mixing device and feed line
  • O 2 -lean should be understood as having a an oxygen content that is lower than the oxygen contend or air and/or that is lower than an conventional compressor feed stream and/or as having an oxygen content of about 16% to 10% or even less.
  • the at least one main burner arrangement is operated with air having an oxygen content that is less than 13% or even less than 10%.
  • the method further comprises the step of: Mixing the air of the - resulting - air-fuel mixture of the at least one pilot burner arrangement with the air having a higher percentage of oxygen than O 2 -lean air and the fuel resulting in the air-fuel mixture for operating the at least one pilot burner arrangement.
  • the air O 2 -lean
  • the fuel and the air having a higher percentage of oxygen than O 2 -lean air - are mixed simultaneously.
  • an air-fuel mixture that is homogenously mixed can be combined used.
  • a mass flow of the air (O 2 -lean) is not specifically controlled; it is dependent on the pressure drop over the burner arrangement(s) which depends on the engine load.
  • the air (having a higher percentage of oxygen than O 2 -lean air) and fuel mass flow can be controlled by each feeding pressure.
  • the method further comprises the step of: Determining a feeding pressure of the air having a higher percentage of oxygen than O 2 -lean air and/or determining a feeding pressure the fuel and, controlling a flame stability of a pilot flame of the at least one pilot burner arrangement due to the determined feeding pressure of the air having a higher percentage of oxygen than O 2 -lean air and/or the feeding pressure the fuel.
  • two independent parameters can be used to influence the combustion process and the flame stability.
  • the present invention further relates to a combustion system of a combustion section of a gas turbine engine comprising at least one main burner arrangement and at least one pilot burner arrangement, wherein the at least one main burner arrangement and the at least one pilot burner arrangement are operateable with an air-fuel mixture and wherein the at least one main burner arrangement is operateable with O 2 -lean air.
  • the combustion system is characterised by at least one mixing device that is able to increasing the percentage of oxygen of the air-fuel mixture of the at least one pilot burner arrangement by feeding of air having a higher percentage of oxygen than the O 2 -lean air.
  • FIG 1 shows an example of a gas turbine engine unit 44 with a gas turbine engine 14 and a unit 46 for an oxygen extraction process in a sectional view.
  • the gas turbine engine 14 comprises, in flow series of a working fluid, like air 22, 24 or a combustion gas 48, an air inlet 50 and a compressor section 28 with a compressor 52, a combustion section 12 with a combustion system 10 and a turbine section 54 with a turbine 56, which are generally arranged in flow series in the direction of a longitudinal or rotational axis 58.
  • the gas turbine engine 14 further comprises a shaft 60 which is rotatable about the rotational axis 58 and which extends longitudinally through the gas turbine engine 14. The shaft 60 drivingly connects the turbine section 54 to the compressor section 28.
  • air 24 which is taken in through the air inlet 50 is compressed by the compressor section 28 and delivered to the combustion section 12 or burner section.
  • the compressed air 24 passing through the compressor section 28 is an O 2 -rich working fluid with about 21% O 2 content.
  • the combustion section 12 comprises a burner plenum 62, one or more combustion chambers 64 with a wall encasing the combustion chamber 64 and exemplarily one burner 66 fixed to the combustion chambers 64 defined by a double wall can 68 and at least one burner 66 fixed to each combustion chamber 64.
  • the combustion chamber 64 and the burner 66 are located inside the burner plenum 62.
  • the O 2 -rich flow medium or air 24 After traveling the compressor section 28 the O 2 -rich flow medium or air 24 enters a diffuser 70 of the compressor section 28 and is discharged from the diffuser 70 into a channel 72 extending through the combustion section 12 and connecting the gas turbine engine 14 or the combustion section 12 with the unit 46 for the oxygen extraction process.
  • the unit 46 for the oxygen extraction process is embodied in such a way to extract O 2 from the heated O 2 -rich air 24. Therefore, the extraction unit 46 comprises for example an ion transport membrane to perform the oxygen extraction process (not shown in detail).
  • the turbine section 54 comprises a number of blade carrying discs 78 attached to the shaft 60.
  • the turbine section 54 comprises two discs 78 each carry an annular array of turbine blades 80.
  • the number of blade carrying discs 78 could be different, i.e. only one disc 78 or more than two discs 78.
  • guiding vanes 82 of a turbine cascade which are fixed to a stator 84 of the gas turbine engine 14, are disposed between the turbine blades 80. Between the exit of the combustion chamber 64 and the leading turbine blades 80 inlet guiding vanes 88 are provided.
  • the combustion gas 48 from the combustion chamber 64 enters the turbine section 54 and drives the turbine blades 80 which in turn rotate the shaft 60.
  • the guiding vanes 82, 86 serve to optimise the angle of the combustion or working gas 48 on to the turbine blades 80.
  • the compressor section 28 comprises an axial series of guide vane stages 88 and rotor blade stages 90.
  • FIG 2 shows a burner head 92 of the combustion system 10 of the combustion section 12.
  • the burner head 92 comprises a main burner arrangement 16 (see FIG 3 ) and a pilot burner arrangement 18 which are operateable with the air-fuel mixture 20 (see FIG 4 ).
  • the pilot burner arrangement 18 comprises several pilot burners 94 each having an injection nozzle 96 to inject the air-fuel mixture 20 in to the downstream combustion chamber 64 for ignition in the pilot flame 30 (see FIG 3 ).
  • O 2 -lean air 22 is injected through holes 98 or similar from the burner plenum 62 into the pilot burner arrangement 18 (not shown in FIG 3 ).
  • the main burner arrangement 16 is embodied as a central burner (not shown in detail) that is circumferentially surrounded by the pilot burners 94, which in turn are exemplarily embodied as external pilot burners 94.
  • the main burner arrangement 16 and the pilot burner arrangement 18 are feed with the O 2 -lean air 22 from the oxygen extraction process.
  • the pilot burner arrangement 18 is embodied selectively for this purpose. As stated above, the pilot burner arrangement 18 is feed with O 2 -lean air 22. This may cause an unstable pilot flame 30 and the pilot burner 94 may lose his stabilising effect.
  • the main flame 100 is feed by an air-fuel mixture 20 that contains the same air 22 with reduced oxygen content (O 2 -lean) as the air 22 feed to the pilot burner arrangement 18 but this mixture 20 is not doped with air 24 having a higher percentage of oxygen than the O 2 -lean air 22.
  • O 2 -lean reduced oxygen content
  • the mixing device 34 can be embodied as a pre-mixer or as a swirler.
  • a mixing cavity 104 that receives the flow mediums air 22, air 24 having a higher percentage of oxygen than the O 2 -lean air 22, fuel 26
  • a mixing cavity 104 that receives the flow mediums has two swirler wings 106 that are arranged in close proximity to the respective nozzle 96 for injection in the combustion chamber 64 (see FIG 4 ).
  • the method for operating the combustion system 10 comprises the following steps: Increasing the percentage of oxygen of the air-fuel mixture 20 of the pilot burner arrangement 18 by feeding of air 24 having a higher percentage of oxygen than the O 2 -lean air 22, and specifically, an air 22 of the air-fuel mixture 20 of the pilot burner arrangement 18 by feeding of air 24 having a higher percentage of oxygen than the O 2 -lean air 22 and further specified by enriching the air 22 of the air-fuel mixture 20 of the pilot burner arrangement 18 with air (24) so that an oxygen content of the air-fuel mixture 20 burned by the pilot burner arrangement 18 is at least 5% higher or about 8% higher than an oxygen content of the air 22 feed to the pilot burner arrangement 18 beforehand of the mixing with the air 24.
  • the air 22 is enriched by the air 24 so that the oxygen content of the resulting air-fuel mixture 20 is about 21%.
  • a further valve may be located in or at the fuel feed line (not shown).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP15155961.4A 2015-02-20 2015-02-20 Procédé de commande d'un système de combustion Withdrawn EP3059501A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP15155961.4A EP3059501A1 (fr) 2015-02-20 2015-02-20 Procédé de commande d'un système de combustion
PCT/EP2016/051891 WO2016131634A1 (fr) 2015-02-20 2016-01-29 Procédé de fonctionnement d'un système de combustion

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15155961.4A EP3059501A1 (fr) 2015-02-20 2015-02-20 Procédé de commande d'un système de combustion

Publications (1)

Publication Number Publication Date
EP3059501A1 true EP3059501A1 (fr) 2016-08-24

Family

ID=52477740

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15155961.4A Withdrawn EP3059501A1 (fr) 2015-02-20 2015-02-20 Procédé de commande d'un système de combustion

Country Status (2)

Country Link
EP (1) EP3059501A1 (fr)
WO (1) WO2016131634A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5901547A (en) * 1996-06-03 1999-05-11 Air Products And Chemicals, Inc. Operation method for integrated gasification combined cycle power generation system
EP1110034A1 (fr) 1998-08-27 2001-06-27 Siemens Aktiengesellschaft Systeme de bruleurs comportant un bruleur a flamme pilote primaire et un bruleur a flamme pilote secondaire
EP1269094B1 (fr) * 2000-03-21 2006-05-24 L'air Liquide, S.A. à Directoire et Conseil de Surveillance pour l'Etude et l'Exploitation des Procédés Georges Claude Procede et installation de generation d'energie
US20080141645A1 (en) * 2006-12-14 2008-06-19 General Electric Company System and method for low emissions combustion

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5901547A (en) * 1996-06-03 1999-05-11 Air Products And Chemicals, Inc. Operation method for integrated gasification combined cycle power generation system
EP1110034A1 (fr) 1998-08-27 2001-06-27 Siemens Aktiengesellschaft Systeme de bruleurs comportant un bruleur a flamme pilote primaire et un bruleur a flamme pilote secondaire
EP1269094B1 (fr) * 2000-03-21 2006-05-24 L'air Liquide, S.A. à Directoire et Conseil de Surveillance pour l'Etude et l'Exploitation des Procédés Georges Claude Procede et installation de generation d'energie
US20080141645A1 (en) * 2006-12-14 2008-06-19 General Electric Company System and method for low emissions combustion

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures

Also Published As

Publication number Publication date
WO2016131634A1 (fr) 2016-08-25

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