EP3650757A1 - Turbine à gaz et procédé de fonctionnement d'une turbine à gaz - Google Patents

Turbine à gaz et procédé de fonctionnement d'une turbine à gaz Download PDF

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Publication number
EP3650757A1
EP3650757A1 EP18205178.9A EP18205178A EP3650757A1 EP 3650757 A1 EP3650757 A1 EP 3650757A1 EP 18205178 A EP18205178 A EP 18205178A EP 3650757 A1 EP3650757 A1 EP 3650757A1
Authority
EP
European Patent Office
Prior art keywords
burner
gas turbine
gas
hydrogen
fuel
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Withdrawn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
EP18205178.9A
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German (de)
English (en)
Inventor
Erik Wolf
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 EP18205178.9A priority Critical patent/EP3650757A1/fr
Publication of EP3650757A1 publication Critical patent/EP3650757A1/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Withdrawn legal-status Critical Current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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices

Definitions

  • the invention relates to a gas turbine and a method for operating a gas turbine.
  • burner systems have been used for a high fuel flexibility of the gas turbines, which can offer a wide range of fuels from natural gas to hydrogen-rich synthesis gases or alternative fuels.
  • the hydrogen content may typically not exceed 60%.
  • the nitrogen oxide values rise sharply and the reaction and thus the flame speed of the fuel gas mixture increases.
  • the flame speed In order to protect the burner hardware, the flame speed must not exceed a certain value in order to avoid the risk of a flashback into the burner, which would be destroyed in the process.
  • Another difficulty of the burner systems for fuel mixtures is that the combustion properties of the hydrogen-natural gas mixture differ from the combustion properties of the pure natural gas.
  • the proportion of hydrogen in the hydrogen-natural gas mixture also influences the combustion properties.
  • the shape and behavior of the flame changes within the combustion chamber. This can disadvantageously damage the burner and the combustion chamber.
  • the object of the invention is therefore to provide a gas turbine with a burner system and a method for operating the gas turbine which can be operated flexibly in different proportions with hydrogen and conventional fuels and overcomes the problems mentioned.
  • the object is achieved with a gas turbine according to claim 1 and a method for operating a gas turbine according to claim 6.
  • a gas turbine according to the invention comprises at least a first burner for a first fuel gas and at least a second burner for a second fuel gas.
  • the structure of the first burner and the second burner are different.
  • the first burner can be operated with a conventional fuel gas. Natural gas in particular is considered here as a conventional fuel gas.
  • the second burner can be operated with hydrogen.
  • the second burner can be operated with pure hydrogen or with a hydrogen mixture, wherein the mixture can also comprise nitrogen, carbon dioxide and / or water in addition to the hydrogen.
  • the gas turbine which comprises a first and a second burner, is operated such that the first burner is operated with a first fuel and the second burner with a second fuel, the second fuel being hydrogen.
  • Both the first and the second fuel can represent pure components or mixtures of substances.
  • the burners individually by using at least two different burner structures adapt to the properties of the fuel used.
  • the flashback of flames is advantageously avoided by the second burner adapted to the hydrogen.
  • the nitrogen oxide emissions are lower due to the adapted burner.
  • the second burner is a pore burner.
  • Pore burners use microporous structures through which the fuel gas flows, exits finely divided and then mixes and reacts with air. Combustion air and fuel are fed separately, so that advantageously no flashback is possible.
  • the second burner can be an arrangement of macroscopic small burners, similar to micromixing chamber burners or matrix burners. These burners produce a lot of small flames. The combustion can take place without gas premixing. Few nitrogen oxides are therefore advantageously produced. Another advantage is that these small burners are safe against flashback.
  • the second burner can comprise an arrangement of catalytically active material.
  • this type of burner there is a surface reaction between the fuel and the atmospheric oxygen. Few to no nitrogen oxides are therefore advantageously produced.
  • this type of burner is safe against flashback.
  • the second burner can be a DOC burner.
  • These burners are characterized by flameless combustion. The combustion takes place in a volume reaction. Few nitrogen oxides are therefore advantageously produced. It is also advantageous that these burners are safe against flashback.
  • All these types of burners can advantageously be designed such that they are used in a conventional gas turbine. It is also possible to use at least three different types of burners in a gas turbine.
  • the total number of first and second burners is in a range between 5 and 50.
  • the number of burners is predetermined depending on the gas turbine type. The more burners, the fewer the steps of the possible mixing ratios between the first fuel and the second fuel.
  • the first and / or second burner are interchangeable. It is advantageously possible to adapt the gas turbine to new fuels or fuel mixtures with very little adjustments to the gas turbine itself.
  • the gas turbine comprises a control system which sets a first amount of fuel gas for the first burner and / or a second amount of fuel gas for the second burner.
  • the gas turbine can then react advantageously to small fluctuations by means of the control system and adapt the amount of fuel gas accordingly.
  • the hydrogen is produced in a water electrolyser by means of electrolysis. It can be a chlor-alkali electrolysis or an electrolysis with a proton exchange membrane (PEM electrolysis).
  • electrolysis a chlor-alkali electrolysis or an electrolysis with a proton exchange membrane (PEM electrolysis).
  • PEM electrolysis proton exchange membrane
  • electrical energy can advantageously be stored by splitting water into hydrogen and oxygen. The hydrogen can then be stored and, in times with little sun and / or wind, converted into mechanical energy by means of the gas turbine.
  • the first and the second burner can be operated with essentially the same pressure loss. This advantageously makes it possible to replace the burners and to make few or no changes to the operating parameters of the gas turbine, in particular the fuel throughput.
  • FIG. 1 shows schematically a gas turbine with a first and a second burner.
  • the gas turbine 1 comprises a compressor 4, a plurality of first burners 2 and a second burner 3. It also comprises a turbine 5.
  • the gas turbine 1 comprises an air inlet 6, through which air can be fed in for the first burners 2.
  • the gas turbine 1 also includes a hydrogen inlet 7, into which hydrogen can be fed for the second burner 3.
  • the gas turbine further comprises connecting flanges 10, which firmly connect the burners to the turbine 5.
  • the first burner 2 and the second burner 3 can both be connected to the connecting flanges 10.
  • both are the first burner 2 and also the second burner 3 are compatible with the gas turbine and can be connected to the gas turbine without structural changes.
  • the first burners 2 and second burners 3 can thus advantageously be replaced as required, in particular in the case of modernization measures.
  • the second burner 3 is in particular an arrangement of macroscopic small burners. Such a burner creates many small flames. The combustion can take place without gas premixing. Few nitrogen oxides are therefore advantageously produced. Another advantage is that the burner is safe against flashback.
  • the gas turbine 1 is configured as a tube-ring combustor.
  • the gas turbine it is also possible to design the gas turbine with an annular combustor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP18205178.9A 2018-11-08 2018-11-08 Turbine à gaz et procédé de fonctionnement d'une turbine à gaz Withdrawn EP3650757A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP18205178.9A EP3650757A1 (fr) 2018-11-08 2018-11-08 Turbine à gaz et procédé de fonctionnement d'une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18205178.9A EP3650757A1 (fr) 2018-11-08 2018-11-08 Turbine à gaz et procédé de fonctionnement d'une turbine à gaz

Publications (1)

Publication Number Publication Date
EP3650757A1 true EP3650757A1 (fr) 2020-05-13

Family

ID=64267669

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18205178.9A Withdrawn EP3650757A1 (fr) 2018-11-08 2018-11-08 Turbine à gaz et procédé de fonctionnement d'une turbine à gaz

Country Status (1)

Country Link
EP (1) EP3650757A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838029A (en) * 1986-09-10 1989-06-13 The United States Of America As Represented By The Secretary Of The Air Force Externally vaporizing system for turbine combustor
US5133180A (en) * 1989-04-18 1992-07-28 General Electric Company Chemically recuperated gas turbine
US20050210881A1 (en) * 2004-03-29 2005-09-29 General Electric Company System and method for co-production of hydrogen and electrical energy
DE102011052931A1 (de) * 2010-09-08 2012-03-08 General Electric Co. System und Verfahren zum Produzieren wasserstoffreichen Brennstoffes
EP2664764A2 (fr) * 2012-05-17 2013-11-20 General Electric Company Système et procédé de production d'un combustible riche en hydrogène

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4838029A (en) * 1986-09-10 1989-06-13 The United States Of America As Represented By The Secretary Of The Air Force Externally vaporizing system for turbine combustor
US5133180A (en) * 1989-04-18 1992-07-28 General Electric Company Chemically recuperated gas turbine
US20050210881A1 (en) * 2004-03-29 2005-09-29 General Electric Company System and method for co-production of hydrogen and electrical energy
DE102011052931A1 (de) * 2010-09-08 2012-03-08 General Electric Co. System und Verfahren zum Produzieren wasserstoffreichen Brennstoffes
EP2664764A2 (fr) * 2012-05-17 2013-11-20 General Electric Company Système et procédé de production d'un combustible riche en hydrogène

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