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EP2601447A2 - Chambre de combustion de turbine à gaz - Google Patents

Chambre de combustion de turbine à gaz

Info

Publication number
EP2601447A2
EP2601447A2 EP11725735.2A EP11725735A EP2601447A2 EP 2601447 A2 EP2601447 A2 EP 2601447A2 EP 11725735 A EP11725735 A EP 11725735A EP 2601447 A2 EP2601447 A2 EP 2601447A2
Authority
EP
European Patent Office
Prior art keywords
pilot
fuel nozzle
main
opening
combustion chamber
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Withdrawn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
EP11725735.2A
Other languages
German (de)
English (en)
Inventor
Bernd Prade
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP11725735.2A priority Critical patent/EP2601447A2/fr
Publication of EP2601447A2 publication Critical patent/EP2601447A2/fr
Withdrawn legal-status Critical Current

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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous 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

Definitions

  • the present invention relates to a gas turbine combustor according to the preamble of claim 1.
  • a gas turbine combustor wherein premix combustion takes place is provided with a pilot burner for combustion in addition to the main burners for premix combustion.
  • the pilot burner serves to stabilize the combustion.
  • the diffusion flame or premixed flame produced by the pilot is a pilot flame for the main burner ver ⁇ expended to produce a fuel-rich flame is stabilized by WO combustion.
  • a pilot burner may optionally have a cone at the outlet, where ⁇ is facilitated by the stabilization of the pilot flame.
  • the main burners are arranged at regular intervals around the pilot burner. High outputs of such a gas turbine combustor require high turbine inlet temperatures, which result from a high flame temperature. With regard to the formation of CO and NOx values, it is necessary to keep the flame temperature ⁇ ture and the residence time of the gas in the combustion chamber in egg nem permissible range.
  • the high temperatures in the gas turbine require a high flame temperature, which also affect the NOx values and increase them.
  • the mean flame temperature is in the range
  • the object of the present invention is therefore to specify a gas turbine combustion chamber which can be operated with an increased flame temperature and thus improved efficiency and without the disadvantages described above.
  • Fig. 1 shows schematically a longitudinal section through a
  • Fig. 2 shows schematically a cross section, which is perpendicular to the longitudinal section, through a gas turbine ⁇ combustion chamber according to the prior art.
  • FIG. 3 schematically shows a side view of OF INVENTION ⁇ to the invention pilot cone in a first embodiment.
  • Fig. 4 shows schematically a cross section, which is perpendicular to the longitudinal section, through the erfindungsge ⁇ Permitted gas turbine combustor of the first embodiment.
  • FIG. 5 shows schematically a side view of a erfin ⁇ inventive pilot cone in a second embodiment.
  • FIG. 6 schematically shows a side view of OF INVENTION ⁇ to the invention pilot cone in a third embodiment.
  • Fig. 7 shows schematically a cross section, which is perpendicular to the longitudinal section, through the erfindungsge ⁇ Permitted gas turbine combustor of the third embodiment.
  • Fig. 8 shows schematically a longitudinal section through a gas turbine combustor according to the invention in a fourth embodiment.
  • Fig. 9 schematically shows a cross-section which is perpendicular to the longitudinal section through a fiction, ⁇ modern gas turbine combustor in a fifth embodiment.
  • Fig. 1 and Fig. 2 show a gas turbine combustor according to the prior art.
  • the gas turbine combustor in this case has a pilot fuel nozzle, which is arranged in the middle section of a cylinder 2.
  • the cylinder 2 opens at its end to a combustion chamber (not shown).
  • the Pi ⁇ lotbrennstoffdüse includes a fuel nozzle 1, as well as around the outer periphery of the fuel nozzle radially spaced a 1 zy ⁇ -cylindrical outer casing 9.
  • a pilot swirler 5 is arranged ⁇ .
  • a pilot cone 4 with inside 11 and outside 12 is arranged on the combustion chamber side of the pilot fuel nozzle.
  • the pilot cone 4 has an opening 6 within the front region of the Zy ⁇ Linders. 2
  • main burners are attached ⁇ associates in respect to the radial direction around the pilot fuel nozzle.
  • Each main burner includes a main nozzle 7, and a disposed with a gap around the outer periphery of the main nozzle 7 in question around the outer cylinder 20.
  • main swirlers 21 are arranged ⁇ . Such a main burner produces a main mixture by mixing fuel with air, which is separated from the main burner in the direction of the combustion chamber (not shown) is ejected.
  • pilot cone 4 a mixed pilot flame (pilot mixture) is formed by mixing air and pilot fuel, so that the fuel present in the mixture from the main burners is ignited and thus the mixture (main mixture) coming from the main burner is burned.
  • 3 and 4 now show a first embodiment of the invention.
  • turbulence generators in the form of projections are mounted on the inside 11 of the pilot cone 4 (FIGS. 3 and 4). These are mounted above all in the region of the opening 6 of the pilot cone 4.
  • the hump 30 Kgs ⁇ NEN also be attached to the outer side 12 of the pilot cone 4 (not shown).
  • the humps 30 are preferably mounted at uniform intervals over the entire circumference of the opening 6 of the pilot cone 4 (FIG. 4). Instead of the hump 30 also Dimples or dents may be mounted (not ge ⁇ shows).
  • the turbulence generators cause better mixing and thus improved CO values. Thereby, even with a short residence time and a short mixing path of the combustion gas in the combustion chamber (not shown) with high flame temperatures, good NO x values are obtained. Other measures for reducing the NOx values can thus be dispensed with. Thus, no impairment of the operation, for example in base load longer exists.
  • Fig. 5 shows a second embodiment of the inven ⁇ tion.
  • a single strip ring 33 is provided as a turbulence generator which dseite over the entire circumference of the Au 12 in the region of the opening 6 of the pilot cone 4 is arranged ⁇ is.
  • it is also possible to provide strips which are spaced apart over the circumference of the outer side 12 in the region of the opening 6 of the pilot cone 4. are arranged.
  • the strip ring 33 is arranged at an angle of 30 ° to 60 ° to the outer side 12 of the pilot cone 4.
  • the strips may be arranged at such an angle. This results in a particularly good mixing of pilot mixture and main mixture and thus a particularly good combustion.
  • Fig. 6 and Fig. 7 now show a third embodiment of the invention.
  • the turbulence generators are designed as trapezoidal strips 35, which are arranged on the opening 6 over the entire circumference of the opening 6, wherein the trapezoidal strips 35 are arranged alternately at an angle of - / + 30 ° to the pilot cone 4. Even so, the naturalmi ⁇ research pilot mixture and main mixture can be significantly increased.
  • Turbulence generators may, for example, also be sharp, straight edge vanes, corners or prisms placed at a predetermined angle over the entire circumference of the opening 6 on the pilot cone 4 (not shown).
  • the sharp edge points towards the combustion chamber (not shown).
  • such wings with different angles alternately (not shown), in particular at an angle of +/- 30 ° to the pilot cone 4, be arranged.
  • Fig. 8 shows another embodiment of an OF INVENTION ⁇ to the invention gas turbine combustor.
  • the gas turbine combustor has an axial direction A.
  • Each of the main burners also has main nozzles 7 and an outer cylinder 20 arranged with a clearance around the outer periphery of the main nozzle 7 in question.
  • extension tubes 230 are formed to extend the openings of the outer cylinders 20 such that the extension tubes 230 radially constrict and widen circumferentially such that each extension tube 230 merges with the adjacent extension tube 230. This results in an annular main nozzle opening 240.
  • the annular main nozzle opening 240 extends in the axial direction A to the opening 6 of the pilot cone 4.
  • 240 turbulence generators for example projection 30 are arranged on the inside 111 of the ring ⁇ shaped main nozzle opening.
  • 4 turbulence generators are mounted on the réellesei ⁇ te 11 and / or the outer side 12 of the pilot cone. This causes a better manubulence ⁇ tion and thus improved CO values than in such a configuration of the gas turbine without turbulence generators.
  • Fig. 9 shows a fifth example of a gas turbine combustor according to the invention.
  • This has an axial direction A.
  • Each of the main burners has main nozzles 7 and an outer cylinder 20 (Fig. 8) arranged with a clearance around the outer circumference of the main nozzle 7 in question.
  • turbulence generators for example bosses 30, are arranged on an inner side 260 of the extension tubes 250 in the region of the outlet opening of the extension tubes 250.
  • 4 turbulence generators are attached to the inner side 11 and / or the outer side 12 of the Pi ⁇ lotkonus. This results in better mixing and thus improved CO values than in such a configuration of the gas turbine without turbulence generators.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Abstract

L'invention concerne une chambre de combustion de turbine à gaz comprenant: - un injecteur de combustible pilote qui est disposé dans la partie centrale d'un cylindre (2) qui s'ouvre à une extrémité en direction d'une chambre de combustion, l'injecteur de combustible pilote comprenant un injecteur de combustible (1) ainsi qu'un revêtement extérieur (9) cylindrique espacé radialement autour du pourtour extérieur de l'injecteur de combustible (1), et un élément de tourbillonnement pilote (5) étant disposé entre l'injecteur de combustible (1) et le revêtement extérieur (9), - plusieurs brûleurs principaux qui sont disposés autour de l'injecteur de combustible pilote par rapport à la direction radiale, - un cône pilote (4) pourvu d'un côté intérieur (11) et d'un côté extérieur (12), le cône pilote (4) étant disposé sur l'injecteur de combustible pilote du côté chambre de combustion et présentant une ouverture (6) du côté chambre de combustion de sorte qu'une flamme pilote est formée par le mélange d'air et de combustible pilote dans le cône pilote (4) pour allumer un combustible injecté par les brûleurs principaux, le cône pilote (4) présentant sur son côté intérieur (11) et/ou son côté extérieur (12) des générateurs de turbulence.
EP11725735.2A 2010-08-02 2011-06-15 Chambre de combustion de turbine à gaz Withdrawn EP2601447A2 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11725735.2A EP2601447A2 (fr) 2010-08-02 2011-06-15 Chambre de combustion de turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP10171601A EP2416070A1 (fr) 2010-08-02 2010-08-02 Chambre de combustion de turbine à gaz
EP11725735.2A EP2601447A2 (fr) 2010-08-02 2011-06-15 Chambre de combustion de turbine à gaz
PCT/EP2011/059901 WO2012016748A2 (fr) 2010-08-02 2011-06-15 Chambre de combustion de turbine à gaz

Publications (1)

Publication Number Publication Date
EP2601447A2 true EP2601447A2 (fr) 2013-06-12

Family

ID=43479914

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10171601A Withdrawn EP2416070A1 (fr) 2010-08-02 2010-08-02 Chambre de combustion de turbine à gaz
EP11725735.2A Withdrawn EP2601447A2 (fr) 2010-08-02 2011-06-15 Chambre de combustion de turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP10171601A Withdrawn EP2416070A1 (fr) 2010-08-02 2010-08-02 Chambre de combustion de turbine à gaz

Country Status (6)

Country Link
US (1) US9194587B2 (fr)
EP (2) EP2416070A1 (fr)
JP (1) JP5657794B2 (fr)
CN (1) CN103119369B (fr)
RU (1) RU2566866C2 (fr)
WO (1) WO2012016748A2 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6037736B2 (ja) * 2012-09-11 2016-12-07 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器およびこれを備えたガスタービン機関
US9528704B2 (en) * 2014-02-21 2016-12-27 General Electric Company Combustor cap having non-round outlets for mixing tubes
US9528702B2 (en) 2014-02-21 2016-12-27 General Electric Company System having a combustor cap
JP6723768B2 (ja) 2016-03-07 2020-07-15 三菱重工業株式会社 バーナアセンブリ、燃焼器、及びガスタービン
JP6692847B2 (ja) * 2018-03-26 2020-05-13 三菱重工業株式会社 ガスタービン燃焼器及びこれを備えたガスタービン機関
JP7096182B2 (ja) * 2019-02-27 2022-07-05 三菱重工業株式会社 ガスタービン燃焼器及びガスタービン
KR102583224B1 (ko) * 2022-01-26 2023-09-25 두산에너빌리티 주식회사 클러스터가 구비된 연소기 및 이를 포함하는 가스 터빈
CN115030837B (zh) * 2022-08-10 2022-11-08 中国空气动力研究与发展中心低速空气动力研究所 一种喷口降噪装置
US12130016B1 (en) * 2023-05-31 2024-10-29 General Electric Company Turbine engine including a combustor
CN117515592A (zh) * 2023-12-04 2024-02-06 浙江燃创透平机械有限公司 一种径向分级低排放燃烧器及燃烧室

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Publication number Priority date Publication date Assignee Title
US3736746A (en) * 1971-08-13 1973-06-05 Gen Electric Recirculating annular slot fuel/air carbureting system for gas turbine combustors
IL93630A0 (en) * 1989-03-27 1990-12-23 Gen Electric Flameholder for gas turbine engine afterburner
US5575153A (en) * 1993-04-07 1996-11-19 Hitachi, Ltd. Stabilizer for gas turbine combustors and gas turbine combustor equipped with the stabilizer
JP3435833B2 (ja) 1993-09-17 2003-08-11 株式会社日立製作所 燃焼器
WO1999006767A1 (fr) * 1997-07-31 1999-02-11 Siemens Aktiengesellschaft Brûleur
US6122916A (en) * 1998-01-02 2000-09-26 Siemens Westinghouse Power Corporation Pilot cones for dry low-NOx combustors
US6038861A (en) * 1998-06-10 2000-03-21 Siemens Westinghouse Power Corporation Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors
JP2001254946A (ja) * 2000-03-14 2001-09-21 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器
JP4508474B2 (ja) * 2001-06-07 2010-07-21 三菱重工業株式会社 燃焼器
JP5173393B2 (ja) * 2007-12-21 2013-04-03 三菱重工業株式会社 ガスタービン燃焼器
US8113000B2 (en) * 2008-09-15 2012-02-14 Siemens Energy, Inc. Flashback resistant pre-mixer assembly
US8661779B2 (en) * 2008-09-26 2014-03-04 Siemens Energy, Inc. Flex-fuel injector for gas turbines
RU99596U1 (ru) 2010-06-16 2010-11-20 Николай Валентинович Стуценко Горелочное устройство

Non-Patent Citations (1)

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Title
See references of WO2012016748A2 *

Also Published As

Publication number Publication date
US9194587B2 (en) 2015-11-24
JP5657794B2 (ja) 2015-01-21
EP2416070A1 (fr) 2012-02-08
CN103119369A (zh) 2013-05-22
RU2013109306A (ru) 2014-09-10
US20130125550A1 (en) 2013-05-23
CN103119369B (zh) 2016-03-09
JP2013535651A (ja) 2013-09-12
WO2012016748A3 (fr) 2013-03-21
WO2012016748A2 (fr) 2012-02-09
RU2566866C2 (ru) 2015-10-27

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