CH709640A8 - Systems and methods for coherence reduction in a combustion system with first and second combustion chamber of a gas turbine. - Google Patents

Systems and methods for coherence reduction in a combustion system with first and second combustion chamber of a gas turbine. Download PDF

Info

Publication number
CH709640A8
CH709640A8 CH00713/15A CH7132015A CH709640A8 CH 709640 A8 CH709640 A8 CH 709640A8 CH 00713/15 A CH00713/15 A CH 00713/15A CH 7132015 A CH7132015 A CH 7132015A CH 709640 A8 CH709640 A8 CH 709640A8
Authority
CH
Switzerland
Prior art keywords
combustion chamber
fuel
nozzle set
fuel nozzle
combustion
Prior art date
Application number
CH00713/15A
Other languages
German (de)
Other versions
CH709640A2 (en
Inventor
Sarah Lori Crothers
Joseph Vincent Citeno
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of CH709640A2 publication Critical patent/CH709640A2/en
Publication of CH709640A8 publication Critical patent/CH709640A8/en

Links

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
    • F23R3/346—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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • 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
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Feeding And Controlling Fuel (AREA)

Abstract

Ein System enthält eine Gasturbine (10) mit einer ersten Brennkammer (17) und einer zweiten Brennkammer (21). Die erste Brennkammer (17) enthält einen ersten Brennstoffdüsensatz (18) und mehrere erste Einspritzzapfen (14). Die mehreren ersten Einspritzzapfen (14) sind in einer ersten Konfiguration stromaufwärts des ersten Brennstoffdüsensatzes (18) an einem ersten Brennstoffweg entlang angeordnet, und die mehreren ersten Einspritzzapfen (14) sind zum Leiten eines Brennstoffs zu dem ersten Brennstoffdüsensatz (18) eingerichtet. Das System enthält ferner die zweite Brennkammer (21) mit einem zweiten Brennstoffdüsensatz (18) und mehreren zweiten Einspritzzapfen (15). Die mehreren zweiten Einspritzzapfen (15) sind in einer zweiten Konfiguration stromaufwärts des zweiten Brennstoffdüsensatzes (18) an einem zweiten Brennstoffweg entlang angeordnet, und die mehreren zweiten Einspritzzapfen (15) sind zum Leiten des Brennstoffs zu dem zweiten Brennstoffdüsensatz (18) eingerichtet. Die zweite Konfiguration hat relativ zu der ersten Konfiguration wenigstens einen Unterschied. Mit dem System erfolgt die Steuerung der Verbrennungsdynamik und/oder der modalen Kopplung der Verbrennungsdynamik, um die Möglichkeit einer unerwünschten Mitschwingungsantwort (z.B. eines Resonanzverhaltens) von Bauteilen in dem Turbinensystem zu reduzieren.A system includes a gas turbine (10) having a first combustion chamber (17) and a second combustion chamber (21). The first combustion chamber (17) includes a first fuel nozzle set (18) and a plurality of first injection pins (14). The plurality of first injection pins (14) are disposed in a first configuration upstream of the first fuel nozzle set (18) along a first fuel path, and the plurality of first injection pins (14) are configured to direct a fuel to the first fuel nozzle set (18). The system further includes the second combustion chamber (21) having a second fuel nozzle set (18) and a plurality of second injection pins (15). The plurality of second injection pins (15) are disposed in a second configuration upstream of the second fuel nozzle set (18) along a second fuel path, and the plurality of second injection pins (15) are configured to direct the fuel to the second fuel nozzle set (18). The second configuration has at least one difference relative to the first configuration. The system is used to control the combustion dynamics and / or the modal coupling of the combustion dynamics to reduce the possibility of an undesirable co-resonant response (e.g., resonance behavior) of components in the turbine system.

CH00713/15A 2014-05-28 2015-05-21 Systems and methods for coherence reduction in a combustion system with first and second combustion chamber of a gas turbine. CH709640A8 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/288,974 US20150345794A1 (en) 2014-05-28 2014-05-28 Systems and methods for coherence reduction in combustion system

Publications (2)

Publication Number Publication Date
CH709640A2 CH709640A2 (en) 2015-11-30
CH709640A8 true CH709640A8 (en) 2016-01-15

Family

ID=54481590

Family Applications (1)

Application Number Title Priority Date Filing Date
CH00713/15A CH709640A8 (en) 2014-05-28 2015-05-21 Systems and methods for coherence reduction in a combustion system with first and second combustion chamber of a gas turbine.

Country Status (5)

Country Link
US (1) US20150345794A1 (en)
JP (1) JP2015224867A (en)
CN (1) CN105318354A (en)
CH (1) CH709640A8 (en)
DE (1) DE102015107767A1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9845956B2 (en) * 2014-04-09 2017-12-19 General Electric Company System and method for control of combustion dynamics in combustion system
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

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6269646B1 (en) * 1998-01-28 2001-08-07 General Electric Company Combustors with improved dynamics
US20070107437A1 (en) * 2005-11-15 2007-05-17 Evulet Andrei T Low emission combustion and method of operation
US7966820B2 (en) * 2007-08-15 2011-06-28 General Electric Company Method and apparatus for combusting fuel within a gas turbine engine
US7578130B1 (en) * 2008-05-20 2009-08-25 General Electric Company Methods and systems for combustion dynamics reduction
US20100192578A1 (en) * 2009-01-30 2010-08-05 General Electric Company System and method for suppressing combustion instability in a turbomachine
US20110072826A1 (en) * 2009-09-25 2011-03-31 General Electric Company Can to can modal decoupling using can-level fuel splits
JP2011111964A (en) * 2009-11-26 2011-06-09 Mitsubishi Heavy Ind Ltd Gas turbine combustor
US20110131998A1 (en) * 2009-12-08 2011-06-09 Vaibhav Nadkarni Fuel injection in secondary fuel nozzle
US20110173983A1 (en) * 2010-01-15 2011-07-21 General Electric Company Premix fuel nozzle internal flow path enhancement
US8418468B2 (en) * 2010-04-06 2013-04-16 General Electric Company Segmented annular ring-manifold quaternary fuel distributor
EP2698582B1 (en) * 2011-03-16 2017-11-22 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor and gas turbine
US8966909B2 (en) * 2012-08-21 2015-03-03 General Electric Company System for reducing combustion dynamics

Also Published As

Publication number Publication date
CH709640A2 (en) 2015-11-30
DE102015107767A1 (en) 2015-12-03
JP2015224867A (en) 2015-12-14
CN105318354A (en) 2016-02-10
US20150345794A1 (en) 2015-12-03

Similar Documents

Publication Publication Date Title
CH709637A8 (en) Systems and methods for varying injectors for coherence reduction in a combustion system with first and second combustion chamber of a gas turbine.
de Saint-Cyr et al. Argumentation update in YALLA (yet another logic language for argumentation)
Čanađija et al. A gradient elasticity model of Bernoulli–Euler nanobeams in non-isothermal environments
AT522344A5 (en) Method and device for model-based optimization of a technical facility
GB2557599B (en) Gas turbine engine fuel supply system having de-priming and re-priming sub-systems
Nguyen et al. Certain properties related to well posedness of switching diffusions
CH706867A8 (en) System and method for reducing combustion dynamics.
WO2015148412A3 (en) Methods for producing cyclic and acyclic ketones
CH709640A8 (en) Systems and methods for coherence reduction in a combustion system with first and second combustion chamber of a gas turbine.
WO2013177178A3 (en) Business process analytics
AT515988A3 (en) Luminaire, arrangement for a grid ceiling, method for mounting a lamp, method for dismantling a lamp, as well as dismantling tool
CH707575A8 (en) Combustion chamber with aerodynamic struts.
SG11201800280SA (en) Computer implemented method, system and computer program product for simulating the behavior of a knitted fabric at yarn level
Gavryushkin et al. Reducibilities among equivalence relations induced by recursively enumerable structures
MX390781B (en) A COMPOSITION, A METHOD FOR PREPARING SAID COMPOSITION, A METHOD FOR PREPARING A RIGIDIZED FABRIC, THE RIGIDIZED FABRIC THUS OBTAINED, A FILTRATION DEVICE, METHODS FOR MANUFACTURING THE FILTRATION DEVICE, INSTALLATION, PROCESS AND USE OF SAID FILTRATION DEVICE FOR FILTRATION OF A LIQUID METAL OR AN ALLOY THEREOF.
EP3093771A3 (en) Methods and systems for transforming fault tree diagrams of engineering systems
MX2017005264A (en) Method for automatically validating data against a predefined data specification.
Li Asymptotic behavior and multiplicity for a diffusive Leslie–Gower predator–prey system with Crowley–Martin functional response
AT517050A3 (en) Heating channel unit, method for producing a heating channel unit and Umbuganlage
AR109403A1 (en) THERMAL INJECTION SYSTEM AND METHOD OF USE OF THE SAME
FR3045011B1 (en) MULTI-AXIAL TURBOJET AND BACK PART OF AIRCRAFT PROVIDED WITH SUCH TURBOJETS
DK3500323T3 (en) Safety needle with deformable needle for injector pin
BR112019004653A2 (en) knitted surfaces and method for obtaining
AT513535A3 (en) Method for functional testing of an arrangement for dynamic fuel consumption measurement
BR112018004621A2 (en) automatic primer application system

Legal Events

Date Code Title Description
PK Correction

Free format text: BERICHTIGUNG ERFINDER

PK Correction

Free format text: ERFINDER BERICHTIGT.

NV New agent

Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH

AZW Rejection (application)