EP2728258A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

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Publication number
EP2728258A1
EP2728258A1 EP12191049.1A EP12191049A EP2728258A1 EP 2728258 A1 EP2728258 A1 EP 2728258A1 EP 12191049 A EP12191049 A EP 12191049A EP 2728258 A1 EP2728258 A1 EP 2728258A1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
gas turbine
mixing section
combustor
downstream
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Withdrawn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
EP12191049.1A
Other languages
German (de)
English (en)
Inventor
Andrea Ciani
Adnan Eroglu
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.)
General Electric Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Priority to EP12191049.1A priority Critical patent/EP2728258A1/fr
Publication of EP2728258A1 publication Critical patent/EP2728258A1/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Withdrawn legal-status Critical Current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
    • F23R3/002—Wall structures
    • 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
    • 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 the technology of gas turbines. It refers to a gas turbine according to the preamble of claim 1.
  • Fig. 1 shows in a perspective view a stationary gas turbine of the applicant of the well-known type GT26.
  • the gas turbine 10 of Fig. 1 comprises a rotor 11 surrounded by a casing, a compressor 13, which compresses air entering the gas turbine 10 through an air intake 12, a ring of first burners 14 with a first fuel supply 14a, a first (high pressure) turbine 16, a ring of second burners 15 with a second fuel supply 15a, a second (low pressure) turbine 16', and an exhaust gas outlet 17 for releasing the exhaust gas either into a stack or a heat recovery steam generator of an associated water/steam cycle in case of a combined cycle power plant CCPP.
  • a gas turbine of the type shown in Fig. 1 is called to have a sequential combustion, due to the sequential arrangement of a first and a second combustion chamber with first and second burners.
  • FIG.2 A typical design of the second burner/combustion chamber (second combustor) arrangement, which is known in the art (see for example document EP 2 169 314 A2 or EP 2 423 599 A2 ) is illustrated in Fig.2 .
  • the second (SEV) combustor of Fig. 2 comprises a second burner/injector 15 axially connected to a combustion chamber 18.
  • the hot gas flow entering the burner section (from the left side in Fig. 2 ; see arrow) is fed with fuel by means of fuel supply 15a via the injector (e.g. a lance) through injection holes 15b, flows along a mixing section 32, and leaves the burner section at its exit to expand into the combustion chamber 18.
  • the interface between the burner section 15, 32 and combustion chamber 18 is characterized by a sudden cross-sectional area change (i.e. backward facing step) comprising a perpendicular front panel 19 extending from the exit of the burner section to inner liner 21 and outer liner 20.
  • the mechanical interface is at the front panel seal, separating the burner front panel 19 from the liners 20 and 21.
  • the transition between burner section 15, 32 and combustion chamber 18 is located at the periphery of the burner front panel 19.
  • the front panel 19 is flat and a large portion of the combustion chamber 18 is therefore occupied by recirculation bubbles 22.
  • the leakages were minimised with seals between front panel 19 and liners 20, 21.
  • they are completely bypassing the flame and the decreased turbine inlet temperature due to bypassing air needs to be compensated with higher flame temperature.
  • the leakages may also locally quench the flame and increase the part load CO emissions.
  • the gas turbine according to the invention comprises a compressor, a first combustor downstream of said compressor, a first turbine, a second combustor downstream of said first turbine, and a second turbine downstream of said second combustor, whereby said second combustor comprises a plurality of burners having a mixing section, which opens downstream into a wider combustion chamber. It is characterized in that the transition between the mixing section and the combustion chamber is continuous.
  • the transition between the mixing section and the combustion chamber is streamlined.
  • the mixing section and the combustion chamber are assembled from at least two parts, which are joined at a split plane.
  • said split plane is located at the exit of said mixing section.
  • said split plane is located upstream of the exit of said mixing section.
  • said burners inject fuel in an injection plane perpendicular to the flow direction within said mixing section, and that said split plane coincides with said injection plane.
  • said combustion chamber has an annular layout.
  • said combustion chamber has a can layout.
  • a basic idea of the present invention is to minimize the second (SEV) burner pressure drop and associated emissions by means of a smoother transition between burner section and combustion chamber.
  • An additional measure is to move the split plane and hence the position of the associated leakages upstream.
  • the transition between burner mixing section 32 and combustion chamber 24 of a gas turbine 30 with sequential combustion is done with a smoothed, especially streamlined, geometry of the outer liner 25 and inner liner 26.
  • the split between burner 15, mixing section 32 and combustion chamber 24 can be located at the mixing section 32 exit (split plane 29), so that leakages 27 are entering into the flame and participate in the fuel/air reaction.
  • Both measures can be used separately or in combination. Both measures can be applied to combustion chambers with annular or can layout.
  • the split could be even positioned at the injection plane 31, with the leakages 28 being mixed with the injected fuel, which is particularly suitable for a can layout.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP12191049.1A 2012-11-02 2012-11-02 Turbine à gaz Withdrawn EP2728258A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP12191049.1A EP2728258A1 (fr) 2012-11-02 2012-11-02 Turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12191049.1A EP2728258A1 (fr) 2012-11-02 2012-11-02 Turbine à gaz

Publications (1)

Publication Number Publication Date
EP2728258A1 true EP2728258A1 (fr) 2014-05-07

Family

ID=47216089

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12191049.1A Withdrawn EP2728258A1 (fr) 2012-11-02 2012-11-02 Turbine à gaz

Country Status (1)

Country Link
EP (1) EP2728258A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0623786A1 (fr) * 1993-04-08 1994-11-09 ABB Management AG Chambre de combustion
US20020187448A1 (en) * 2001-06-09 2002-12-12 Adnan Eroglu Burner system
EP2169314A2 (fr) 2008-09-30 2010-03-31 Alstom Technology Ltd Procédé pour réduire les émissions d'une combustion séquentielle dans une turbine à gaz et chambre de combustion pour une telle turbine à gaz
US20110030375A1 (en) * 2009-08-04 2011-02-10 General Electric Company Aerodynamic pylon fuel injector system for combustors
EP2423599A2 (fr) 2010-08-27 2012-02-29 Alstom Technology Ltd Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à l'exécution du procédé

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0623786A1 (fr) * 1993-04-08 1994-11-09 ABB Management AG Chambre de combustion
US20020187448A1 (en) * 2001-06-09 2002-12-12 Adnan Eroglu Burner system
EP2169314A2 (fr) 2008-09-30 2010-03-31 Alstom Technology Ltd Procédé pour réduire les émissions d'une combustion séquentielle dans une turbine à gaz et chambre de combustion pour une telle turbine à gaz
US20110030375A1 (en) * 2009-08-04 2011-02-10 General Electric Company Aerodynamic pylon fuel injector system for combustors
EP2423599A2 (fr) 2010-08-27 2012-02-29 Alstom Technology Ltd Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à l'exécution du procédé

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

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