EP2615373A1 - System und Verfahren für die Zufuhr eines Arbeitsfluids zu einem Brenner - Google Patents

System und Verfahren für die Zufuhr eines Arbeitsfluids zu einem Brenner Download PDF

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Publication number
EP2615373A1
EP2615373A1 EP13150587.7A EP13150587A EP2615373A1 EP 2615373 A1 EP2615373 A1 EP 2615373A1 EP 13150587 A EP13150587 A EP 13150587A EP 2615373 A1 EP2615373 A1 EP 2615373A1
Authority
EP
European Patent Office
Prior art keywords
working fluid
combustor
combustion chamber
compressor
distribution manifold
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Withdrawn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
EP13150587.7A
Other languages
English (en)
French (fr)
Inventor
Lucas John Stoia
Roy Marshall Washam
Patrick Benedict Melton
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 Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2615373A1 publication Critical patent/EP2615373A1/de
Withdrawn legal-status Critical Current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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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

Definitions

  • the present invention generally involves a system and method for supplying a working fluid to a combustor.
  • Combustors are commonly used in industrial and power generation operations to ignite fuel to produce combustion gases having a high temperature and pressure.
  • gas turbines typically include one or more combustors to generate power or thrust.
  • a typical gas turbine used to generate electrical power includes an axial compressor at the front, one or more combustors around the middle, and a turbine at the rear.
  • Ambient air may be supplied to the compressor, and rotating blades and stationary vanes in the compressor progressively impart kinetic energy to the working fluid (air) to produce a compressed working fluid at a highly energized state.
  • the compressed working fluid exits the compressor and flows through one or more nozzles into a combustion chamber in each combustor where the compressed working fluid mixes with fuel and ignites to generate combustion gases having a high temperature and pressure.
  • the combustion gases expand in the turbine to produce work. For example, expansion of the combustion gases in the turbine may rotate a shaft connected to a generator to produce electricity.
  • combustion gas temperatures generally improve the thermodynamic efficiency of the combustor.
  • higher combustion gas temperatures also promote flashback or flame holding conditions in which the combustion flame migrates towards the fuel being supplied by the nozzles, possibly causing severe damage to the nozzles in a relatively short amount of time.
  • higher combustion gas temperatures generally increase the disassociation rate of diatomic nitrogen, increasing the production of nitrogen oxides (NO X ).
  • a lower combustion gas temperature associated with reduced fuel flow and/or part load operation (turndown) generally reduces the chemical reaction rates of the combustion gases, increasing the production of carbon monoxide and unburned hydrocarbons.
  • one or more fuel injectors also known as late lean injectors, may be circumferentially arranged around the combustion chamber downstream from the nozzles. A portion of the compressed working fluid exiting the compressor may flow through the fuel injectors to mix with fuel to produce a lean fuel-air mixture. The lean fuel-air mixture may then be injected into the combustion chamber for additional combustion to raise the combustion gas temperature and increase the thermodynamic efficiency of the combustor.
  • the late lean injectors are effective at increasing combustion gas temperatures without producing a corresponding increase in the production of NO X .
  • the pressure and flow of the compressed working fluid exiting the compressor may vary substantially around the circumference of the combustion chamber.
  • the fuel-air ratio flowing through the late lean injectors can vary considerably, mitigating the beneficial effects otherwise created by the late lean injection of fuel into the combustion chamber.
  • Previous attempts have been made to achieve a more uniform flow of working fluid through the late lean injectors. For example, scoops or shrouds have been installed over a portion of the fuel injectors to more evenly regulate the flow of working fluid through the fuel injectors.
  • an improved system and method for reducing the variation in the pressure and/or flow of the working fluid flowing through the late lean injectors would be useful.
  • One embodiment of the present invention is a system for supplying a working fluid to a combustor that includes a fuel nozzle and a combustion chamber downstream from the fuel nozzle.
  • a plurality of fuel injectors are circumferentially arranged around the combustion chamber downstream from the fuel nozzle.
  • a combustor casing circumferentially surrounds at least a portion of the combustion chamber.
  • a distribution manifold encloses the plurality of fuel injectors, and a plenum passes through the combustor casing to provide fluid communication for a working fluid to flow to the distribution manifold.
  • Another embodiment of the present invention is a system for supplying a working fluid to a combustor that includes a compressor and a combustor downstream from the compressor.
  • the combustor includes a combustion chamber and a plurality of fuel injectors circumferentially arranged around the combustion chamber.
  • a combustor casing surrounds at least a portion of the combustor to contain a working fluid flowing from the compressor to the combustor.
  • a distribution manifold encloses the plurality of fuel injectors, and a plenum passes through the combustor casing to provide fluid communication for a portion of the working fluid to flow to the distribution manifold.
  • the present invention may also include a method for supplying a working fluid to a combustor.
  • the method includes flowing a working fluid from a compressor through a combustion chamber, diverting a portion of the working fluid into a plenum, and flowing the diverted portion of the working fluid outside of the compressor and the combustor.
  • the method further includes flowing the diverted portion of the working fluid through a combustor casing that circumferentially surrounds at least a portion of the combustion chamber and flowing the diverted portion of the working fluid through a distribution manifold that encloses a plurality of fuel injectors circumferentially arranged around the combustion chamber.
  • Various embodiments of the present invention include a system and method for supplying a working fluid to a combustor.
  • the system includes multiple late lean injectors that circumferentially surround a combustion chamber.
  • the system diverts or flows a portion of the working fluid from a common location and routes the diverted portion of the working fluid to a distribution manifold that surrounds the late lean injectors.
  • the system reduces variations in the pressure and/or flow rate of the diverted working fluid at each late lean injector to produce a more uniform fuel-air mixture injected into the combustion chamber.
  • Fig. 1 provides a simplified cross-section view of a system 10 according to one embodiment of the present invention.
  • the system 10 may be incorporated into a gas turbine 12 having a compressor 14 at the front, one or more combustors 16 radially disposed around the middle, and a turbine 18 at the rear.
  • the compressor 14 and the turbine 18 typically share a common rotor 20 connected to a generator 22 to produce electricity.
  • the compressor 14 may be an axial flow compressor in which a working fluid 24, such as ambient air, enters the compressor 14 and passes through alternating stages of stationary vanes 26 and rotating blades 28.
  • a compressor casing 30 contains the working fluid 24 as the stationary vanes 26 and rotating blades 28 accelerate and redirect the working fluid 24 to produce a continuous flow of compressed working fluid 24.
  • the majority of the compressed working fluid 24 flows through a compressor discharge plenum 32 to the combustor 16.
  • the combustor 16 may comprise any type of combustor known in the art.
  • a combustor casing 34 may circumferentially surround some or all of the combustor 16 to contain the compressed working fluid 24 flowing to the combustor 16.
  • One or more fuel nozzles 36 may be radially arranged in an end cover 38 to supply fuel to a combustion chamber 40 downstream from the fuel nozzles 36.
  • Possible fuels include, for example, one or more of blast furnace gas, coke oven gas, natural gas, vaporized liquefied natural gas (LNG), hydrogen, and propane.
  • the compressed working fluid 24 may flow from the compressor discharge plenum 32 along the outside of the combustion chamber 40 before reaching the end cover 38 and reversing direction to flow through the fuel nozzles 36 to mix with the fuel.
  • the mixture of fuel and compressed working fluid 24 flows into the combustion chamber 40 where it ignites to generate combustion gases having a high temperature and pressure.
  • the combustion gases flow through a transition piece 42 to the turbine 18.
  • the turbine 18 may include alternating stages of stators 44 and rotating buckets 46.
  • the first stage of stators 44 redirects and focuses the combustion gases onto the first stage of turbine buckets 46.
  • the combustion gases expand, causing the turbine buckets 46 and rotor 20 to rotate.
  • the combustion gases then flow to the next stage of stators 44 which redirects the combustion gases to the next stage of rotating turbine buckets 46, and the process repeats for the following stages.
  • Fig. 2 provides a simplified side view of the combustor 16 shown in Fig. 1 according to one embodiment of the present invention.
  • the combustor 16 includes a plurality of fuel injectors 50 circumferentially arranged around the combustion chamber 40 downstream from the fuel nozzles 36.
  • the fuel injectors 50 may receive the same or a different fuel than supplied to the fuel nozzles 36 and mix the fuel with a portion of the compressed working fluid 24 before injecting the mixture into the combustion chamber 40. In this manner, the fuel injectors 50 supply a lean mixture of fuel and air for additional combustion to raise the temperature, and thus the efficiency, of the combustor 16.
  • a distribution manifold 52 encloses the fuel injectors 50 to shield the fuel injectors 50 from direct impingement by the compressed working fluid 24 flowing out of the compressor 14.
  • the distribution manifold 52 may circumferentially surround at least a portion of the combustion chamber 40 inside of the combustor casing 34 to contain a portion of the compressed working fluid 24 diverted from a common source and supplied to the fuel injectors 50.
  • a plenum 54 may connect the distribution manifold 52 to a common source of the diverted compressed working fluid 24 to provide fluid communication for the diverted working fluid 24 to flow to the distribution manifold 52. For example, as shown more clearly in Fig.
  • the plenum 54 may include an upstream portion 56 configured to receive or divert a portion of the working fluid 24 from the compressor 14.
  • the upstream portion 56 may pass through the compressor casing 30 so that at least a portion of the plenum 54 extends outside of the compressor 14 and combustor 16 before passing through the combustor casing 32 to connect to the distribution manifold 52.
  • the plenum 54 may separate into a plurality of branch lines 58 before or after passing through the combustor casing 34.
  • the branch lines 58 may include, for example, piping or flexible hoses so that each branch line 58 provides a separate fluid communication with the distribution manifold 52.
  • the plenum 54 may divert a portion of the compressed working fluid 24 at or close to the discharge pressure of the compressor 14 and deliver this diverted compressed working fluid 24 directly to the fuel injectors 50 inside the distribution manifold 52 with little or no pressure drop in the compressed working fluid 24.
  • the system 10 shown and described with respect to Figs. 1 and 2 may also provide a method for supplying the working fluid 24 to the combustor 16.
  • the method may include flowing the working fluid 24 from the compressor 14 through the combustion chamber 40 and diverting a portion of the working fluid 24 into the plenum 54.
  • the method may further include flowing the diverted portion of the working fluid 24 outside of the compressor 14 and the combustor 16, through the combustor casing 34 that circumferentially surrounds at least a portion of the combustion chamber 40, and through the distribution manifold 52 that encloses the fuel injectors 50 circumferentially arranged around the combustion chamber 40.
  • the method may further include flowing the diverted portion of the working fluid 24 through the compressor casing 30, circumferentially around at least a portion of the combustion chamber 40 inside of the distribution manifold 52, and/or separating the diverted portion of the working fluid 24 into the branch lines 58 before or after passing through the combustor casing 34.
  • the various embodiments of the present invention may provide one or more technical advantages over existing late lean injection systems.
  • the systems and methods described herein may reduce variations in the pressure and/or flow of the working fluid 24 through each fuel injector 50.
  • the various embodiments require less analysis to achieve the desired fuel-air ratio through the fuel injectors 50 and enhance the intended ability of the fuel injectors 50 achieve the desired efficiency and reduced emissions from the combustor 16.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13150587.7A 2012-01-13 2013-01-09 System und Verfahren für die Zufuhr eines Arbeitsfluids zu einem Brenner Withdrawn EP2615373A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/349,886 US20130180253A1 (en) 2012-01-13 2012-01-13 System and method for supplying a working fluid to a combustor

Publications (1)

Publication Number Publication Date
EP2615373A1 true EP2615373A1 (de) 2013-07-17

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EP13150587.7A Withdrawn EP2615373A1 (de) 2012-01-13 2013-01-09 System und Verfahren für die Zufuhr eines Arbeitsfluids zu einem Brenner

Country Status (5)

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US (1) US20130180253A1 (de)
EP (1) EP2615373A1 (de)
JP (1) JP2013145107A (de)
CN (1) CN103206725A (de)
RU (1) RU2013100409A (de)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US10260424B2 (en) 2016-03-24 2019-04-16 General Electric Company Transition duct assembly with late injection features
US11022038B2 (en) * 2017-05-04 2021-06-01 General Electric Company Compressor circumferential fluid distribution system
US11371709B2 (en) 2020-06-30 2022-06-28 General Electric Company Combustor air flow path

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1074792A1 (de) * 1999-07-31 2001-02-07 Rolls-Royce Plc Turbinenbrennkammeranordnung
US6192688B1 (en) * 1996-05-02 2001-02-27 General Electric Co. Premixing dry low nox emissions combustor with lean direct injection of gas fule
US20110179803A1 (en) * 2010-01-27 2011-07-28 General Electric Company Bled diffuser fed secondary combustion system for gas turbines

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US2984970A (en) * 1956-07-31 1961-05-23 Gen Electric Thrust augmenting system
FR2122308B1 (de) * 1971-01-19 1976-03-05 Snecma Fr
US4918925A (en) * 1987-09-30 1990-04-24 General Electric Company Laminar flow fuel distribution system
KR930013441A (ko) * 1991-12-18 1993-07-21 아더 엠.킹 다수의 연소기들을 포함한 가스터어빈 연소장치
US5573396A (en) * 1994-11-03 1996-11-12 Astec Industries, Inc. Low emissions burner
US5782076A (en) * 1996-05-17 1998-07-21 Westinghouse Electric Corporation Closed loop air cooling system for combustion turbines
US5771696A (en) * 1996-10-21 1998-06-30 General Electric Company Internal manifold fuel injection assembly for gas turbine
US20030024234A1 (en) * 2001-08-02 2003-02-06 Siemens Westinghouse Power Corporation Secondary combustor for low NOx gas combustion turbine
US8387398B2 (en) * 2007-09-14 2013-03-05 Siemens Energy, Inc. Apparatus and method for controlling the secondary injection of fuel
US8281594B2 (en) * 2009-09-08 2012-10-09 Siemens Energy, Inc. Fuel injector for use in a gas turbine engine
US8438852B2 (en) * 2010-04-06 2013-05-14 General Electric Company Annular ring-manifold quaternary fuel distributor

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6192688B1 (en) * 1996-05-02 2001-02-27 General Electric Co. Premixing dry low nox emissions combustor with lean direct injection of gas fule
EP1074792A1 (de) * 1999-07-31 2001-02-07 Rolls-Royce Plc Turbinenbrennkammeranordnung
US20110179803A1 (en) * 2010-01-27 2011-07-28 General Electric Company Bled diffuser fed secondary combustion system for gas turbines

Also Published As

Publication number Publication date
CN103206725A (zh) 2013-07-17
US20130180253A1 (en) 2013-07-18
RU2013100409A (ru) 2014-07-20
JP2013145107A (ja) 2013-07-25

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