EP2162681B1 - Gasturbinenbrenner - Google Patents

Gasturbinenbrenner Download PDF

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Publication number
EP2162681B1
EP2162681B1 EP08774628.5A EP08774628A EP2162681B1 EP 2162681 B1 EP2162681 B1 EP 2162681B1 EP 08774628 A EP08774628 A EP 08774628A EP 2162681 B1 EP2162681 B1 EP 2162681B1
Authority
EP
European Patent Office
Prior art keywords
main
inflow
gas
burner
generators
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.)
Not-in-force
Application number
EP08774628.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2162681A2 (de
Inventor
Matthias Hase
Michael Huth
Robert Angel
Drew Ehlert
James Marshall
Yevgeniy Shteyman
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
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Publication of EP2162681A2 publication Critical patent/EP2162681A2/de
Application granted granted Critical
Publication of EP2162681B1 publication Critical patent/EP2162681B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • F23R3/28—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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14701—Swirling means inside the mixing tube or chamber to improve premixing

Definitions

  • the invention relates to a gas turbine combustor having a plurality of main swirl generators each having an inflow port formed by a main swirler rim.
  • combustion air is usually compressed in a multi-stage compressor and then led to a number of gas turbine burners, which are arranged on a, for example, annularly guided around the turbine axis combustion tube.
  • DLN systems In an effort to perform the combustion in a gas turbine possible NO x -arm, so-called DLN systems have (Dry Low NO x) proved.
  • main swirl generators also referred to as main swirlers
  • main swirlers are arranged around a pilot cone in which fuel - usually natural gas - is strongly swirled with air to produce a stable pilot flame.
  • the main swirlers Through the main swirlers, the compressed air flows and is mixed in the main swirlers with the fuel to burn downstream in the main swirl generator in a combustion tube.
  • the gas heated by the combustion is then fed to a power turbine for work by relaxation.
  • the combustion air compressed in the compressor is usually led to the more radially outboard gas turbine burners, that the compressed air against a flow direction in the main swirlers outside along the gas turbine burners and their Brennermänteln along.
  • the flow of the compressed combustion air has to undergo a reversal of direction and in this case a deflecting edge of the burner jacket facing away from the burner pipe and / or the main swirl generator flow around.
  • the U.S. 4,689,961 describes a combustion chamber equipment mt with swirl generators and a cup-shaped recess with a passage in which the injector and the swirl generator and an inflow means are mounted.
  • the US 2003/0110774 A1 discloses a gas turbine with main swirlers having an inlet opening.
  • a gas turbine burner of the type mentioned above which has an inlet guide means with a flow guide, which extends from one of the inflow openings to an adjacent inflow opening, to which the main swirler edges forming the inflow openings adjoin and which are widened radially outward therefrom.
  • the directional reversal of the compressed combustion air upstream of the inflow openings can be guided along the flow guide surface by the flow guide surface adjoining the inflow openings, so that vortex formation is reduced there.
  • negative pressure zones which favor a backflow within the main swirl generator, can be kept low.
  • the Strömungsleit simulation the Einströmleitffens connects to the inflow openings forming main swirler edges of the main swirler, for this a direct abutment to the main swirler edges is not required, but rather a small mounting gap for successive installation of the main swirler and the Einströmleitschs can remain in the gas turbine combustor. Due to the course of the inflow of an inflow to the adjacent inflow, in particular by a continuous course, a turbulence of the combustion air between the main swirl generators can be counteracted. Due to the radial expansion of the flow guide area, a region radially outside the main spin generators can be blocked to reduce or avoid eddies. The radial direction is in this case based on a center around which the main spin generators are arranged radially.
  • the flow control surface is convexly curved in the direction of the combustion air flowing around, so that the trailing in the arc to the inlet opening flowing combustion air is guided along the curved flow guide.
  • the flow guide surface connects to the main swirl tubes parallel to the course of main swirler tubes of the main swirlers. Due to the parallelism of the connection, an abrupt change of direction in the air flow at the edge between the flow guide surface and the main swirler tube can be avoided.
  • the port does not have to be at the outermost main swirler edge, but may also be radially inside the main swirler rim.
  • the main swirl generators are arranged centrally symmetrically about a pilot burner and the flow guide surface runs radially outside the main swirl generator.
  • a combustion air flow flowing radially outwards into the main spin generators of the gas turbine combustor can be guided in the critical region radially outward of the main swirl generator with little rewiring.
  • the central symmetry may be a circular symmetry, with the main spin generators being arranged in a circular ring. Conceivable, for example, also centrally symmetric polygonal or rosette geometries.
  • the flow guide extends from a radially outwardly facing portion to a radially inwardly facing, located at the inflow opening portion. The flow can thus be guided during an entire direction reversal of the flow guide.
  • the flow guide surface has a central symmetry at a radially outer region and deviates from the central symmetry in a region lying radially further inward and is adapted to the shape of the main swirler edges.
  • the flow guide is expediently annular, in particular annular continuously guided around the main swirl generator, whereby a uniform inflow from all sides in the gas turbine burner can be achieved.
  • the flow guide surface is advantageously arranged like a bead in the inflow direction in front of the main swirl generators.
  • the bead may be shaped in the form of a U-bend with legs arranged downstream, with respect to the flow direction in the main swirl generators.
  • the section facing outwards forms a centrally symmetrical surface, in particular an annular surface, and the section facing inward has a surface adapted to an annular shape of the main swirler, then a flow around the main swirler with low turbulence can be achieved.
  • the flow guide extends with at least substantially uniform curvature from the outwardly facing portion to the inwardly facing portion.
  • the uniform curvature is in this case given by a circular section line between the flow guide surface and a plane oriented in the radial direction, the radial direction relating to the center around which the main spin generators are arranged.
  • the uniform curvature need not be present in any plane in the radial direction. It is sufficient if realized in a single radial plane is, for example, in a plane that passes through the above-mentioned center and between the main swirlers. Conveniently, the curvature is uniform in each plane passing between the main spin generators.
  • the Einströmleitsch connects a running around the main swirler burner shell with the main swirl generators.
  • the flow in this area is already low vortex.
  • the vortex freedom can be maintained at least substantially up to the main swirl generators.
  • the connection advantageously consists directly at the main swirler edge or in the immediate vicinity or at the inflow opening.
  • the inflow conducting means closes a gap between a burner jacket extending around the main swirler and the main swirl generators.
  • a small mounting gap between the burner jacket and the main swirl generators remain, for example, up to a gap width of 2 mm.
  • the flow guide is guided between the main swirl generator.
  • a gap between the main swirl generators or the main swirler edges can be at least partially closed.
  • the curvature of the flow guide surface is from the radially outward suitably section to the radially inwardly facing portion expediently evenly.
  • the flow guide surface is led to the radial depth of the main swirler axes of the main swirl generators between the main swirl generators. It can thus a gap between the main swirl generators completely - if necessary, except for the mounting gap - are closed.
  • a simple mountability of the inflow and the main swirl generators can be achieved when the Einströmleitsch is guided in its radially inner portion radially outward to the main swirler edges. Conveniently, it is aligned in the immediate vicinity of the main swirler edges in the axial direction, so that the main swirler or the Einströmleitstoff can be easily inserted for mounting in the axial direction.
  • the gas turbine combustor has an outer and an inner burner jacket which respectively surrounds the main swirl generator and to which the inflow conducting means in each case adjoin in the jacket direction.
  • the combustion air can be guided along a large radius of curvature of the flow guide, so that a large negative pressure along this flow can be counteracted.
  • the jacket direction here is the direction of the shells at the location of the connection and in particular the axial direction of the gas turbine burner, so that the flow guide surface is aligned in the axial direction at the connection to at least the outer burner jacket, expediently both burner shrouds.
  • the inlet guide means has two legs pointing in the inflow direction, which are in particular brought together in parallel downstream of the inlet opening, a stable construction can be achieved and easy mountability of the Einströmleitstoffs can be achieved.
  • the inflow conducting means in the region of the flow guiding face is expediently made in several parts in the tangential direction.
  • FIG. 1 shows a gas turbine combustor 2 in a longitudinal section with a combustion tube 4.
  • the gas turbine combustor 2 comprises a pilot burner with a pilot cone 8, around the annular eight main swirler 10 are arranged.
  • Each of the main swirlers 10 has a main swirl tube 12 within which a premix blade 14 is arranged with a number of radially outwardly directed vanes.
  • a fuel-carrying premix gas passage 16 communicates with unillustrated premix bores through which the fuel is forced into the interior of the main swirler tube 12.
  • the fuel is fed through feeds 18 to each main swirler 10 and within of the main swirler tube 12 is mixed with compressed combustion air.
  • a flow profile of the gas turbine burner 2 flowing around the combustion air is shown by solid arrows 20.
  • the combustion air initially flows around the gas turbine burner 2 counter to a flow direction 22, which is related to the premix flow within the main swirl generator 10. It flows along a burner jacket 24 which surrounds all of the main swirlers 10 of the gas turbine combustor 2, and then flows in an arc around an edge 26 of the burner jacket 24 towards an inflow port 28 of each main swirler 10.
  • the inflow opening 28 is surrounded by the main swirler edge 30 of the corresponding main swirler 10 facing away from the combustion tube 4.
  • the gas turbine combustor 2 is provided with an inlet flow means 36 which extends annularly around all the main swirlers 10 within the burner jacket 24 and adjoins the main swirler banks 30 of the main swirler 10 substantially in parallel.
  • the outer return flow 32 can be at least largely eliminated, whereby the inner return flow 34 is significantly reduced and thus the flow through the main spin generators 10 is made uniform.
  • FIG. 2 A more efficient embodiment of the invention is in FIG. 2 shown.
  • the following description of the following exemplary embodiments is essentially limited to the differences from the exemplary embodiment FIG. 1 which is referred to with regard to features and functions that remain the same.
  • Substantially identical components are basically numbered with the same reference numerals.
  • An inflow guide means 38 has a convexly curved flow guide surface 40, which adjoins the main swirler tube 12 in a substantially parallel manner in the region of the inflow opening 28. Radially outward, the flow guide surface 40 widens and adjoins the burner jacket 24 so as to connect the main spin generators 10 to the burner jacket 24.
  • the Einströmleit Structure 40 is also curved so that it is radially aligned in the region of the burner jacket 24 and at the inlet opening 28 is substantially aligned axially.
  • the Einströmleitstoff 38 closes a gap 42 between the main spin generators 10 and the burner jacket 24 and this - as explained in detail to the embodiment of Figures 3 to 6 - between the main swirl generator 10 and the main swirler 30. However, for ease of assembling, a small gap may remain between the inflow guide 28 and the main swirler tube 12.
  • FIGS. 3 to 6 show a further gas turbine burner 44 with a very efficient inflow conducting means 46.
  • FIG. 4 11 shows a perspective top view of the gas turbine combustor 44 and the inflow guide 46
  • FIGS. 3 and 5 show the inflow guide in a section taken in the axial direction of the gas turbine combustor 44
  • FIG. 6 shows a section of the Ausströmleitstoffs 46 in a plan view in the axial direction or flow direction 22nd
  • the inflow guide means 46 has a bead-like flow guide surface 48 which is arranged in the inflow direction 22 in front of the main swirl generators 10 and which comprises the main swirler edges 30 of FIG Main spin generator 10 with an outer burner shell 50, which also surrounds the main swirler 10 connects.
  • the radially outer burner jacket 50 serves to guide the combustion air a little way outside the inner burner jacket 24 in order to create a not too narrow curvature of the flow deflection.
  • the connection of the flow guide surface 48 to the outer, axially extending burner shell 50 is in the shell direction or in the axial direction, so that a flow guide from the outer burner shell 50 passes substantially seamlessly onto the flow guide surface 48.
  • the compressor air from a radially outwardly facing portion 52 to a radially inwardly facing portion 54 which terminates at the inflow opening 28, guided by the flow in this flow with substantially uniform curvature flow guide 48 to the inlet opening 28 vortex.
  • the Einströmleitstoff 46 is here, as in FIG. 4 is annularly passed around all of the main spin generators 10 and engages radially inwardly between the main spin generators 10 and their main swirler edges 30 to define both a gap 58 between the outer burner shell 50 and the main swirler tube 12 and the gap 42 between the inner burner shell 24 and Close main swirler tube 12. A backflow of combustion air through these gaps 42, 58 to the inlet opening 28 is thus at least largely avoided, with a small mounting gap 60 may remain between the main swirler tube 12 and the Einströmleitstoff 46.
  • the flow directing surface 48 is drawn radially inward between the main swirlers 10 up to the level of main swirler axes 56 of the main swirlers 10 to inhibit the flow of combustion air between the main swirlers 10.
  • the inflow guide 46 with its radially inner portion 54 is guided radially outward past the main swirler edges 30 and extends there in the axial direction, so that the main swirler 10 can be inserted in the axial direction for installation in the gas turbine burner 44.
  • the radially outer portion 52 is guided radially inside the outer burner jacket 52 and there also in the shell direction or axial direction, so that the Einströmleitsch 46 can be inserted into the burner jacket 50.
  • the inflow guide means 46 comprises an inner leg 62 and an outer leg 64, which are brought together in parallel in the flow direction 22 on the inner burner jacket 24 and are fastened to the burner jacket 24.
  • the gas turbine combustor 44 For mounting the gas turbine combustor 44 in a gas turbine, the gas turbine combustor 44 includes a retainer 66 having retention members 68 which are passed through the flow guide surface 48 and secured to the burner shrouds 24, 50. For easy manufacture and assembly of the inflow guide 46, it is divided into a plurality of segments 70, between each of which a holding element 68 is passed.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP08774628.5A 2007-07-09 2008-07-02 Gasturbinenbrenner Not-in-force EP2162681B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US95882207P 2007-07-09 2007-07-09
PCT/EP2008/058491 WO2009007283A2 (de) 2007-07-09 2008-07-02 Gasturbinenbrenner

Publications (2)

Publication Number Publication Date
EP2162681A2 EP2162681A2 (de) 2010-03-17
EP2162681B1 true EP2162681B1 (de) 2016-08-31

Family

ID=40229140

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08774628.5A Not-in-force EP2162681B1 (de) 2007-07-09 2008-07-02 Gasturbinenbrenner

Country Status (7)

Country Link
US (2) US8387394B2 (zh)
EP (1) EP2162681B1 (zh)
JP (1) JP5064562B2 (zh)
KR (1) KR101493256B1 (zh)
CN (1) CN101688670B (zh)
RU (1) RU2478877C2 (zh)
WO (1) WO2009007283A2 (zh)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2162681B1 (de) * 2007-07-09 2016-08-31 Siemens Aktiengesellschaft Gasturbinenbrenner
US8371123B2 (en) * 2009-10-28 2013-02-12 General Electric Company Apparatus for conditioning airflow through a nozzle
US20130025285A1 (en) * 2011-07-29 2013-01-31 General Electric Company System for conditioning air flow into a multi-nozzle assembly
US8904797B2 (en) * 2011-07-29 2014-12-09 General Electric Company Sector nozzle mounting systems
US9291102B2 (en) * 2011-09-07 2016-03-22 Siemens Energy, Inc. Interface ring for gas turbine fuel nozzle assemblies
JP5984445B2 (ja) * 2012-03-23 2016-09-06 三菱日立パワーシステムズ株式会社 燃焼器
JP6318443B2 (ja) * 2013-01-22 2018-05-09 三菱日立パワーシステムズ株式会社 燃焼器、及び回転機械
WO2014137412A1 (en) * 2013-03-05 2014-09-12 Rolls-Royce Corporation Gas turbine engine fuel air mixer
US9328664B2 (en) 2013-11-08 2016-05-03 Siemens Energy, Inc. Transition support system for combustion transition ducts for turbine engines
JP6602004B2 (ja) * 2014-09-29 2019-11-06 川崎重工業株式会社 燃料噴射器及びガスタービン
US10920986B2 (en) 2014-10-06 2021-02-16 Mitsubishi Power, Ltd. Gas turbine combustor base plate configuration
CN107575889B (zh) * 2017-09-05 2023-05-16 中国联合重型燃气轮机技术有限公司 燃气轮机的燃料喷嘴
CN107726313B (zh) * 2017-09-28 2019-05-24 上海交通大学 可拆卸式可控排气组分的预混柴油燃烧器
DE102018205874A1 (de) 2018-04-18 2019-10-24 Siemens Aktiengesellschaft Brenner mit selektiver Anpassung des Bohrungsmusters für die Gaseindüsung
KR102340397B1 (ko) * 2020-05-07 2021-12-15 두산중공업 주식회사 연소기 및 이를 포함하는 가스 터빈

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Also Published As

Publication number Publication date
US20130269352A1 (en) 2013-10-17
KR101493256B1 (ko) 2015-02-16
CN101688670B (zh) 2013-05-15
CN101688670A (zh) 2010-03-31
KR20100047239A (ko) 2010-05-07
WO2009007283A2 (de) 2009-01-15
EP2162681A2 (de) 2010-03-17
JP2010532860A (ja) 2010-10-14
WO2009007283A3 (de) 2009-04-30
US8973369B2 (en) 2015-03-10
US8387394B2 (en) 2013-03-05
RU2010104444A (ru) 2011-08-20
US20100275605A1 (en) 2010-11-04
JP5064562B2 (ja) 2012-10-31
RU2478877C2 (ru) 2013-04-10

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