EP2780636A1 - Turbomachine combustor assembly and method of operating a turbomachine - Google Patents

Turbomachine combustor assembly and method of operating a turbomachine

Info

Publication number
EP2780636A1
EP2780636A1 EP11855268.6A EP11855268A EP2780636A1 EP 2780636 A1 EP2780636 A1 EP 2780636A1 EP 11855268 A EP11855268 A EP 11855268A EP 2780636 A1 EP2780636 A1 EP 2780636A1
Authority
EP
European Patent Office
Prior art keywords
fluid
turbomachine
zone
combustor
combustor assembly
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Withdrawn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
EP11855268.6A
Other languages
German (de)
English (en)
French (fr)
Inventor
llya Aleksandrovich SLOBODYANSKIY
Sergey Aleksandrovich Stryapunin
Dmitry Vladlenovich Tretyakov
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 EP2780636A1 publication Critical patent/EP2780636A1/en
Withdrawn legal-status Critical Current

Links

Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002Wall structures
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34Feeding into different combustion zones
    • F23R3/346Feeding into different combustion zones for staged combustion

Definitions

  • the subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a turbomachine combustor assembly.
  • gas turbomachines In general, gas turbomachines combust a fuel/air mixture that releases heat energy to form a high temperature gas stream.
  • the high temperature gas stream is channeled to a turbine portion via a hot gas path.
  • the turbine portion converts thermal energy from the high temperature gas stream to mechanical energy that rotates a turbine shaft.
  • the turbomachine may be used in a variety of applications, such as for providing power to a pump, an electrical generator, or aircraft.
  • a turbomachine combustor assembly includes a combustor body having a combustor outlet, and a combustion liner arranged within the combustor body.
  • the combustion liner defines a combustion chamber.
  • An injection nozzle is arranged within the combustor body upstream from the combustion chamber. The injection nozzle is configured and disposed to deliver a first fluid toward the combustion chamber.
  • a fluid module is mounted to the combustor body downstream from the combustion chamber.
  • the fluid module includes a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation.
  • a method of operating a turbomachine includes introducing a first fluid into a combustor assembly to establish a first fluid zone, introducing a second fluid into the combustor assembly to establish a second flame zone down stream of the first fluid zone, introducing a third fluid into the combustor assembly to establish a third fluid zone downstream of the second fluid zone, and combusting one or more of the first, second and third fluids to produce a hot gas stream to establish a first operating mode of the turbomachine.
  • a turbomachine includes a compressor portion, a turbine portion operatively connected to the turbine portion, and a combustor assembly fluidly connected to the compressor portion and the turbine portion.
  • the combustor assembly includes a combustor body, and a combustion liner arranged within the combustor body.
  • the combustion liner defines a combustion chamber.
  • An injection nozzle is arranged within the combustor body upstream from the combustion chamber. The injection nozzle is configured and disposed to introduce a first fluid toward the combustion chamber.
  • a fluid module is mounted to the combustor body downstream from the combustion chamber.
  • the fluid module includes a fluid module body that defines a fluid zone, a first injector member mounted to the fluid module body and configured to deliver a second fluid into the fluid zone at a first orientation, and a second injector member mounted to the fluid module body and configured to deliver a third fluid into the fluid zone at a second orientation that is distinct from the first orientation.
  • FIG. 1 is a schematic diagram of a turbomachine including a combustor assembly having a fluid module in accordance with the exemplary embodiment
  • FIG. 2 is a partial perspective view of the combustor assembly of FIG. i ;
  • FIG. 3 is a partial cross-sectional view of the combustor assembly of
  • FIG. 2
  • FIG. 4 is a schematic partial cross-sectional view of the fluid module in accordance with the exemplary embodiment
  • FIG. 5 is a partial cross-sectional view of the combustor assembly of FIG. 2 illustrating a first operating mode in which fluid mixtures are introduced into first, second, and third fluid zones;
  • FIG. 6 is a partial cross-sectional view of the combustor assembly of FIG. 2 illustrating a second operating mode in which fluid mixtures are introduced into the first and second fluid zones;
  • FIG. 7 is a partial cross-sectional view of the combustor assembly of FIG. 2 illustrating a third operating mode in which a fluid mixture is introduced into the first fluid zone.
  • Turbomachine 2 includes a compressor portion 4 operatively connected to a turbine portion 6.
  • Turbomachine 2 also includes a combustor assembly 8 that fluidly links compressor portion 4 and turbine portion 6.
  • a common compressor/turbine shaft 10 mechanically links compressor portion 4 and turbine portion 6.
  • compressed air is passed into combustor assembly 8, mixed with fuel, and combusted to form hot gases.
  • the hot gases are channeled to turbine portion 6 which converts thermal energy from the hot gases into mechanical rotational energy that is channeled to drive an external component such as a generator, a pump or other mechanically or fluidly driven mechanism.
  • combustor assembly 8 includes a combustor body 20 having an outer surface 22 and an inner surface 24.
  • a combustor liner 30 is arranged within combustor body 20.
  • Combustor liner 30 includes an outer surface portion 32 and an inner surface portion 34. Outer surface portion 32 is spaced from inner surface 24 of combustor body 20 to form a duct or passage 36.
  • Combustor body 20 is also shown to include an upstream portion 37 and a downstream portion 39 between which define a combustion chamber 44.
  • Combustor assembly 8 includes a plurality of injection nozzles, one of which is indicated at 50, supported by combustor body 20 and positioned at upstream portion 37 of combustor liner 30.
  • Injection nozzle 50 injects a first fluid mixture 51 into combustion chamber 44.
  • the first fluid mixture passes along a longitudinal axis of combustor assembly 8.
  • the longitudinal axis should be understood to describe an axis of combustor assembly that extends between upstream portion 37 and downstream portion 39.
  • combustor assembly 8 includes a fluid module 60 mounted at downstream portion 39 of combustor body 20.
  • Fluid module 60 includes a fluid module body 62 that defines a fluid zone 64.
  • Fluid module 60 also includes an inlet section 67 and an outlet section 69.
  • Outlet section 69 joins with a transition piece 75.
  • Transition piece 75 includes a duct 77 that delivers products of combustion to turbine portion 6. As will be discussed more fully below, duct 77 defines a combustion area 79.
  • fluid module 60 includes a plurality of first injector members 84 arranged in an annular array upstream relative to an annular array of a plurality of second injector members 86.
  • the plurality of first injector members 84 receives fuel via a first fluid supply conduit 89 provided in combustor body 20.
  • First fluid supply conduit 89 includes a first fluid inlet 90 that is configured to receive a first fluid.
  • the first fluid could be a fuel, an inert gas or other liquid or gaseous mixture.
  • the plurality of second injector members receive a second fluid through a second fluid supply conduit 92 provided on combustor body 20.
  • Second fluid supply conduit 92 includes a second fluid inlet 93 that is configured to receive a second fluid.
  • the second fluid could be fuel, an inert gas or other liquid or gaseous mixture.
  • first and second fluids may be substantially identical or may be distinct one from the other depending upon desired operation parameters.
  • each of the first and second injector members 84 and 86 include corresponding first and second third fluid inlets 96 and 97.
  • Third fluid inlets may provide air from compressor portion 4 to each of the fist and second injector members 84, 86 or some other liquid or gaseous mixture that is mixed with corresponding ones of the first and second fluids.
  • each first injector member 84 includes a first injector body 108 mounted to fluid module body 62 at a first orientation.
  • First injector body 108 includes a third fluid passage 1 10 that is fluidly coupled to third fluid inlet 96 and a first fluid passage 112.
  • First fluid passage 1 12 extends within third fluid passage 1 10 and is fluidly coupled to first fluid supply conduit 89.
  • Each first injector member 84 is configured to introduce a second fluid mixture 1 19 into combustion zone 64. More specifically, each first injector member 84 is oriented to deliver a stream of the second fluid mixture that may include the first fluid and the third fluid along a radial axis into combustion zone 64.
  • radial axis describes an axis that is substantially perpendicular to the longitudinal axis of the combustor assembly.
  • Each second injector member 86 includes a second injector body 130 mounted to fluid module body 62.
  • Second injector body 130 includes a second third fluid passage 132 that is fluidly coupled to second third fluid inlet 97 and a second fluid passage 134.
  • Second fluid passage 134 extends within second third fluid passage 132 and is fluidly coupled to second fluid supply conduit 92.
  • Each second injector member 86 is configured to introduce a third fluid mixture 141 toward combustion area 79. More specifically, each second injector member 86 is oriented to deliver a mixture of the second and third fluids along an axis that is angled relative to the longitudinal axis and the radial axis.
  • Each second injector member 86 is configured to deliver a third fluid mixture stream 142 downstream from second fluid mixture 1 19.
  • Third fluid mixture may include both the second and third fluids.
  • combustor assembly 8 can be operated in one of a plurality of modes depending upon a desired power output.
  • combustor assembly 8 can be selectively operated in a first or base load mode in which first fluid mixture 51 defines a first combustible mixture and is combusted in a first fluid zone 154, second fluid mixture 119 defines a second combustible mixture and is combusted in a second fluid zone 157, and third fluid mixture 142 defines a third combustible mixture and is combusted in a third fluid zone 160 such as shown in FIG. 5.
  • the three fluid zones 154, 157, and 159 lead to more complete combustion and establish a prolonged residence time of the fluid mixtures that leads to a more uniform heat release that results in lower combustion dynamics.
  • the second mixture could include any air and/or inert gas to promote more complete combustion of the first and third mixtures.
  • Combustor assembly 8 can also be selectively operated in a second or first off-peak mode such as when desired power output is between about 40% and 70% of base load.
  • the third fluid mixture does not contain any combustibles and may represent air or a mixture of inert gases. Alternatively, the third fluid mixture may simply be discontinued.
  • the first and second fluid zones 154 and 157 are active such as shown in FIG. 6.
  • Combustor assembly 8 may also be operated in a third mode such as when desired power output is between about 20% and 40% of base load. In the third mode, only first fluid zone 154 is active.
  • the second and third fluid mixtures do not contain combustibles and may represent air or an inert gas mixture. Alternatively the second and third fluid mixtures may simply be discontinued.
  • the combustor assembly of the exemplary embodiment allows for the selective introduction of fluid mixtures into various positions along a combustion path.
  • the fluid mixtures can all represent combustible mixtures or can represent mixtures of air or other inert fluids.
  • Inert fluids can be introduced downstream from combustible fluids or may be introduced upstream of combustible fluids to facilitate more complete combustion. The introduction of inert fluids upstream of a combustion event has been shown to reduce undesirable emissions.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP11855268.6A 2011-11-17 2011-11-17 Turbomachine combustor assembly and method of operating a turbomachine Withdrawn EP2780636A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2011/000908 WO2013073984A1 (en) 2011-11-17 2011-11-17 Turbomachine combustor assembly and method of operating a turbomachine

Publications (1)

Publication Number Publication Date
EP2780636A1 true EP2780636A1 (en) 2014-09-24

Family

ID=46506614

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11855268.6A Withdrawn EP2780636A1 (en) 2011-11-17 2011-11-17 Turbomachine combustor assembly and method of operating a turbomachine

Country Status (4)

Country Link
US (1) US20140238034A1 (zh)
EP (1) EP2780636A1 (zh)
CN (1) CN103917826B (zh)
WO (1) WO2013073984A1 (zh)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9297534B2 (en) 2011-07-29 2016-03-29 General Electric Company Combustor portion for a turbomachine and method of operating a turbomachine
US20150052905A1 (en) * 2013-08-20 2015-02-26 General Electric Company Pulse Width Modulation for Control of Late Lean Liquid Injection Velocity
US10060629B2 (en) * 2015-02-20 2018-08-28 United Technologies Corporation Angled radial fuel/air delivery system for combustor
US10480792B2 (en) * 2015-03-06 2019-11-19 General Electric Company Fuel staging in a gas turbine engine
CN114353121B (zh) * 2022-01-18 2022-12-20 上海交通大学 一种用于燃气轮机的多喷嘴燃料注入方法

Family Cites Families (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2398654A (en) * 1940-01-24 1946-04-16 Anglo Saxon Petroleum Co Combustion burner
US3872664A (en) * 1973-10-15 1975-03-25 United Aircraft Corp Swirl combustor with vortex burning and mixing
DE2629761A1 (de) * 1976-07-02 1978-01-05 Volkswagenwerk Ag Brennkammer fuer gasturbinen
US4265615A (en) * 1978-12-11 1981-05-05 United Technologies Corporation Fuel injection system for low emission burners
US4420929A (en) * 1979-01-12 1983-12-20 General Electric Company Dual stage-dual mode low emission gas turbine combustion system
US4928481A (en) * 1988-07-13 1990-05-29 Prutech Ii Staged low NOx premix gas turbine combustor
JP3335713B2 (ja) * 1993-06-28 2002-10-21 株式会社東芝 ガスタービン燃焼器
JP2950720B2 (ja) * 1994-02-24 1999-09-20 株式会社東芝 ガスタービン燃焼装置およびその燃焼制御方法
JPH0988628A (ja) * 1995-09-26 1997-03-31 Toshiba Corp 再熱型ガスタービンプラント
US5571247A (en) * 1995-11-13 1996-11-05 Butler; Virginia L. Self containing enclosure for protection from killer bees
JP3619626B2 (ja) * 1996-11-29 2005-02-09 株式会社東芝 ガスタービン燃焼器の運転方法
CA2225263A1 (en) * 1997-12-19 1999-06-19 Rolls-Royce Plc Fluid manifold
US6311471B1 (en) * 1999-01-08 2001-11-06 General Electric Company Steam cooled fuel injector for gas turbine
US6453658B1 (en) * 2000-02-24 2002-09-24 Capstone Turbine Corporation Multi-stage multi-plane combustion system for a gas turbine engine
US20030150216A1 (en) * 2001-07-03 2003-08-14 O'beck John Timothy Gas turbine
JP2007113888A (ja) * 2005-10-24 2007-05-10 Kawasaki Heavy Ind Ltd ガスタービンエンジンの燃焼器構造
DE102006016037A1 (de) * 2006-04-05 2007-10-11 Robert Bosch Gmbh Verfahren zum Betreiben einer Brennkraftmaschine
EP1847778A1 (en) * 2006-04-21 2007-10-24 Siemens Aktiengesellschaft Pre-mix combustion system for a gas turbine and method of operating the same
US7886545B2 (en) * 2007-04-27 2011-02-15 General Electric Company Methods and systems to facilitate reducing NOx emissions in combustion systems
US8387398B2 (en) * 2007-09-14 2013-03-05 Siemens Energy, Inc. Apparatus and method for controlling the secondary injection of fuel
US7886539B2 (en) * 2007-09-14 2011-02-15 Siemens Energy, Inc. Multi-stage axial combustion system
US7665309B2 (en) * 2007-09-14 2010-02-23 Siemens Energy, Inc. Secondary fuel delivery system
US8176739B2 (en) * 2008-07-17 2012-05-15 General Electric Company Coanda injection system for axially staged low emission combustors
US8701418B2 (en) * 2009-01-07 2014-04-22 General Electric Company Late lean injection for fuel flexibility
US8707707B2 (en) * 2009-01-07 2014-04-29 General Electric Company Late lean injection fuel staging configurations
US8112216B2 (en) * 2009-01-07 2012-02-07 General Electric Company Late lean injection with adjustable air splits
RU2506499C2 (ru) * 2009-11-09 2014-02-10 Дженерал Электрик Компани Топливные форсунки газовой турбины с противоположными направлениями завихрения
US8707708B2 (en) * 2010-02-22 2014-04-29 United Technologies Corporation 3D non-axisymmetric combustor liner
US8752386B2 (en) * 2010-05-25 2014-06-17 Siemens Energy, Inc. Air/fuel supply system for use in a gas turbine engine
EP2742291B1 (en) * 2011-08-11 2020-07-08 General Electric Company System for injecting fuel in a gas turbine engine
US9097424B2 (en) * 2012-03-12 2015-08-04 General Electric Company System for supplying a fuel and working fluid mixture to a combustor
US9551492B2 (en) * 2012-11-30 2017-01-24 General Electric Company Gas turbine engine system and an associated method thereof
US20150167980A1 (en) * 2013-12-18 2015-06-18 Jared M. Pent Axial stage injection dual frequency resonator for a combustor of a gas turbine engine
US20150316266A1 (en) * 2014-04-30 2015-11-05 Siemens Aktiengesellschaft Burner with adjustable radial fuel profile
US10480791B2 (en) * 2014-07-31 2019-11-19 General Electric Company Fuel injector to facilitate reduced NOx emissions in a combustor system
US10060629B2 (en) * 2015-02-20 2018-08-28 United Technologies Corporation Angled radial fuel/air delivery system for combustor

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
None *
See also references of WO2013073984A1 *

Also Published As

Publication number Publication date
US20140238034A1 (en) 2014-08-28
CN103917826B (zh) 2016-08-24
WO2013073984A1 (en) 2013-05-23
CN103917826A (zh) 2014-07-09

Similar Documents

Publication Publication Date Title
US9140454B2 (en) Bundled multi-tube nozzle for a turbomachine
EP2626635B1 (en) Combustor assembly with trapped vortex cavity
US9297534B2 (en) Combustor portion for a turbomachine and method of operating a turbomachine
JP5606776B2 (ja) 燃焼システムにおいて燃料ノズルを熱的に保護するための方法及びシステム
EP2405201B1 (en) Injection nozzle for a turbomachine
EP2738355B1 (en) A gas turbine engine system and an associated method thereof
US8161750B2 (en) Fuel nozzle for a turbomachine
US8297059B2 (en) Nozzle for a turbomachine
US20110083444A1 (en) Low btu fuel injection system
KR20190025497A (ko) 사전 혼합 연료 분사기 및 가스 터빈 연소기에서의 사용 방법
EP3102877B1 (en) Combustor
US20150107255A1 (en) Turbomachine combustor having an externally fueled late lean injection (lli) system
EP2664854B1 (en) Secondary combustion system
US20140238034A1 (en) Turbomachine combustor assembly and method of operating a turbomachine
EP2587159B1 (en) Fuel injection assembly for use in turbine engines and method of assembling same
KR20190048905A (ko) 연료 노즐, 이를 포함하는 연소기 및 가스 터빈
US8863526B2 (en) Fuel injector
US20130111918A1 (en) Combustor assembly for a gas turbomachine
KR102021129B1 (ko) 연료 노즐, 이를 포함하는 연소기 및 가스 터빈
KR20190048904A (ko) 연료 노즐, 이를 포함하는 연소기 및 가스 터빈
WO2024116966A1 (ja) ガスタービンの運転方法

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20140617

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20180604

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20181016