EP3134682A1 - Agencement de brûleur - Google Patents

Agencement de brûleur

Info

Publication number
EP3134682A1
EP3134682A1 EP15788377.8A EP15788377A EP3134682A1 EP 3134682 A1 EP3134682 A1 EP 3134682A1 EP 15788377 A EP15788377 A EP 15788377A EP 3134682 A1 EP3134682 A1 EP 3134682A1
Authority
EP
European Patent Office
Prior art keywords
end plate
burner assembly
recess
radially
annular space
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.)
Granted
Application number
EP15788377.8A
Other languages
German (de)
English (en)
Other versions
EP3134682B1 (fr
Inventor
Olga Deiss
Thomas Grieb
Patrick Lapp
Jens Kleinfeld
Matthias CHLEBOWSKI
Fabian SANDER
Christian Beck
Andreas Böttcher
Patrick Ronald Flohr
Thomas Hauser
Simon Purschke
Günther WALZ
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 EP3134682A1 publication Critical patent/EP3134682A1/fr
Application granted granted Critical
Publication of EP3134682B1 publication Critical patent/EP3134682B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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
    • F23R3/286—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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • 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
    • F23R2900/03043—Convection cooled combustion chamber walls with means for guiding the cooling air flow

Definitions

  • Burner arrangement The invention relates to a burner arrangement, in particular for a gas turbine plant.
  • the object of the invention is to provide said device wei ⁇ terzuentwickeln so forth, even at higher temperature requirements and temperature gradients clearly a high component life is ensured.
  • the invention solves this problem by providing that in such a burner arrangement with a combustion chamber, a plurality of merging into the combustion chamber mixing channels in which initiated during normal operation combustion air and fuel introduced mixed ⁇ who, the mixing channels formed by mixing tubes are axially extending through an annular space defined between a tubular outer wall, a tubular inner wall spaced radially from the outer wall, an upstream annular face plate, and a downstream annular face plate is, wherein the end plates are provided with through holes which receive and / or continue the mixing tubes and both radially inwardly and radially outwardly extending in the direction of the annulus peripheral edge, provided in the downstream annular end plate axial holes in the edge, which are substantially parallel to a normal of the face plate of
  • Annulus extending forth into the end plate and that at least one branching off from the axial bore opening for the removal of cooling air is provided.
  • cooling air can be transported in thermally stressed areas of the burner in a simple manner in order to reduce the temperature during operation or to ensure a more homogeneous temperature distribution there. This measure reduces temperature-induced stresses in the material and extends the life of the component.
  • the at least one opening opens into a chamber or a cooling air pocket which is open towards the annular space.
  • the highest thermal loads of the face plate are found in its radially outer and radially inner edges. It is therefore advantageous if holes are arranged in these areas.
  • the opening opens into an elongated recess which extends from the combustion chamber upstream in the edge of the end plate. stretches.
  • this component is made more flexible at heavily loaded areas and can thus respond better to thermal expansion without the voltage values becoming too great. It is particularly advantageous ⁇ way, therefore, when the recess is disposed radially inside the inner edge, because there the voltage values of the component are the highest. Rinsing with air from the bores serves to avoid dead zones in the well where the hot air stops.
  • the face plate continues to seal against the combustion chamber, it is advantageous if the length of the recess is smaller than the height of the edge.
  • the base of the depression has a cross-sectional profile of the set circle, oval, ellipse, so that sources of increased material tensions, such as e.g. Edges, to be avoided.
  • the openings of two holes open into a depression in such a way that opposite sides of the depression can be cooled by impingement cooling.
  • further openings are arranged in the direction of the annular space in the depression.
  • the further openings can be used as resonator openings.
  • ECM electrochemical erosion
  • EDM spark erosion
  • SLM selective laser melting
  • FIG. 1 shows a schematic sectional view of a burner arrangement
  • FIG. 2 shows an end plate with axial bores in the edge
  • FIG. 3 shows a detailed view of the front plate
  • FIG. 4 shows a further detail view of the front plate
  • FIG. 5 shows a sectional view of the bores in the front plate
  • FIG. 6 shows a front plate with elongated depressions
  • FIG. 7 shows a representation of the internal structures of a front plate
  • Figure 8 is a sectional view of the elongated recess
  • FIG 9 is a view along the axis of the recess.
  • the figures show a burner assembly 1 according to an embodiment of the present invention or components thereof.
  • the burner assembly 1 of Figure 1 comprises a
  • Combustion chamber 2 a centrally arranged pilot burner 23, a mixing tube assembly 24 with a plurality of mixing tubes 6, which form mixing channels 3, the coins ⁇ in the combustion chamber 2, the ⁇ a plurality of Brennstoffinj 25, which up to a suitable position in the mixing tubes. 6 protrude, and a mounting plate 26 which receives the mixing tube assembly 24 and serves to fasten the burner assembly 1 to a machine housing, not shown.
  • the mixing tube assembly 24 includes a tubular outer wall 8, a radially spaced from the outer wall 8 arranged tubular inner wall 9, an upstream ring ⁇ shaped end plate 10 and a downstream end plate 11, defining an annular space 7 through which the mixing tubes 6 in the axial Extend direction.
  • the end plate 11 has a both radially inward and radially outward in the direction of the annular space 7 extending peripheral edge 13, 14. Further, the mixing tube assembly 24 includes an annular partition plate 27.
  • the upstream face plate 10 includes a
  • the passage openings 12 define in the present case two bolt holes with mutually different bolt circle diameters, wherein the passage openings 12 of the first bolt circle and the through holes 12 of the second bolt circle are offset in the radial direction from each other. Furthermore, the end plate 10 has a multiplicity of numbers of air channels, not shown in FIG. 1, which extend in the axial direction and are distributed over the annular surface of the front plate 10.
  • the partition plate 27 is analogous to the face plate 10 provided with through ⁇ holes 28 which are aligned with the through holes 12 of the end plate 10 in the axial direction. Further, the partition plate 27 is provided with a plurality of scavenging air channels 29 distributed over the annular surface of the partition plate 27.
  • the downstream arranged face plate 11 comprises analogous to the end plate 10 and the partition plate 27 through holes 12 which are aligned axially with the through holes 12 of the end plate 10 and the through holes 28 of the partition plate 27. Furthermore, axially extending in the front plate 11 de air ducts 30 formed, which connect the annular space 7 with the combustion chamber 2 fluidly.
  • a fuel 5 and combustion air 4 flow through the jet nozzles, i. the mixing tubes 6, and arrive as a fuel-air mixture in the combustion chamber. 2
  • Figure 2 shows the downstream annular end ⁇ plate 11 with through holes 12 and axial holes 15 in the edge 13, 14 both radially inward and radially outward.
  • the bores 15 extend substantially parallel to a normal of the end plate 11 from the annular space 7 into the end plate 11. It can be seen in FIG. 3 that at least one opening 16 branched off from the axial bore 15 is provided for the removal of cooling air 17.
  • FIG. 4 shows how a plurality of bores 15 open into the chamber 18.
  • Figure 5 shows the same again at a different angle and in section.
  • the chambers 18 or cooling air pockets may consist of a combination of holes and cutouts or be made by other manufacturing processes.
  • the placement of the STEL len high temperature at the inner cylindrical surface and the outer cylindrical surface of the end plate lead to a Besse ⁇ ren temperature distribution and thus lower temperature-induced stresses.
  • FIG. 6 shows an embodiment of the invention with elongate depressions 19 which extend from the combustion chamber 2 upstream in the edge 13 of the end plate 11.
  • the depressions are arranged radially inward in the inner edge 13. Its length is smaller than the height of the edge 13th
  • FIG. 7 shows the structures in the interior of the edge 13 of the end plate 11.
  • two holes 15 are assigned to a recess 19.
  • the holes 15 have openings 16 for the removal of cooling air 17.
  • the recess holes 16 and the channels 31 are arranged so that ge ⁇ genüberode sides of the recess 21 may be cooled by Prallküh- lung 19th
  • FIG. 7 also shows that the base 20 of the depression 19 has a cross-sectional profile of the set circle, oval, ellipse. Furthermore, it can be seen in FIG. 7 that further openings 22 are arranged in the direction of the annular space 7 in the depression 19.
  • FIG. 8 shows a view of the same exemplary embodiment with a section through a depression 19. It shows the round base 20 of the recess 19 and the channels 31 which open into the depression 19 coming from the openings 16 of the bores 15, as well as further openings 22 starting from the depressions 19, starting in the annular space 7.
  • Figure 9 shows the view from the combustion chamber side on the edge 13 in a recess along its longitudinal axis. One recognizes the outlets of the channels 31.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)

Abstract

L'invention concerne un agencement de brûleur (1) présentant une chambre de combustion (2), et une multitude de canaux de mélange (3) qui débouchent dans la chambre de combustion (2) et dans lesquels de l'air de combustion (4) introduit et du combustible (5) introduit sont mélangés pendant un fonctionnement conforme à l'utilisation. Les canaux de mélange (3) sont formés par des tubes de mélange (6) qui s'étendent axialement à travers un espace annulaire (7), qui est défini entre une paroi externe (8) tubulaire, une paroi interne (9) tubulaire disposée à une certaine distance radiale de la paroi externe (8), une plaque frontale (10) annulaire disposée en amont et une plaque frontale (11) annulaire disposée en aval. Les plaques frontales (10, 11) sont pourvues d'ouvertures de passage (12), qui logent ou prolongent les tubes de mélange (6) et qui présentent, tant radialement vers l'intérieur que radialement vers l'extérieur, un bord (13, 14) périphérique s'étendant dans le sens de l'espace annulaire (7). Des trous axiaux (15) sont réalisés dans la plaque frontale (11) annulaire disposée en aval, dans le bord (13, 14) et s'étendent de manière sensiblement parallèle à une perpendiculaire de la plaque frontale (11) à partir de l'espace annulaire (7) dans la plaque frontale (11). Au moins une ouverture (16) déviant du trou axial (15) est destinée à évacuer l'air de refroidissement (17).
EP15788377.8A 2014-11-03 2015-10-29 Agencement de brûleur Active EP3134682B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014222402 2014-11-03
PCT/EP2015/075053 WO2016071186A1 (fr) 2014-11-03 2015-10-29 Agencement de brûleur

Publications (2)

Publication Number Publication Date
EP3134682A1 true EP3134682A1 (fr) 2017-03-01
EP3134682B1 EP3134682B1 (fr) 2018-08-22

Family

ID=54366207

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15788377.8A Active EP3134682B1 (fr) 2014-11-03 2015-10-29 Agencement de brûleur

Country Status (5)

Country Link
US (1) US10578305B2 (fr)
EP (1) EP3134682B1 (fr)
CN (1) CN106461226B (fr)
RU (1) RU2656177C1 (fr)
WO (1) WO2016071186A1 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106287816B (zh) * 2016-08-12 2019-01-18 中国航空工业集团公司沈阳发动机设计研究所 一种干式低排放燃烧器
KR102178876B1 (ko) 2017-10-20 2020-11-13 주식회사 엘지화학 이차전지용 양극활물질의 제조방법 및 이를 이용하는 이차전지
CN108816128A (zh) * 2018-05-22 2018-11-16 徐州腾睿智能装备有限公司 一种用于地表水径流净化植物栽培块药剂注入混合装置
CN109611891B (zh) * 2018-12-16 2020-11-06 中国航发沈阳发动机研究所 一种干低排放燃烧器
DE102020213836A1 (de) * 2020-11-04 2022-05-05 Siemens Energy Global GmbH & Co. KG Resonatorring, Verfahren und Brennkorb
US11719438B2 (en) 2021-03-15 2023-08-08 General Electric Company Combustion liner

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US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
DE69306025T2 (de) 1992-03-30 1997-05-28 Gen Electric Konstruktion eines Brennkammerdomes
US5377483A (en) 1993-07-07 1995-01-03 Mowill; R. Jan Process for single stage premixed constant fuel/air ratio combustion
US7322795B2 (en) * 2006-01-27 2008-01-29 United Technologies Corporation Firm cooling method and hole manufacture
CN101206029B (zh) 2006-12-21 2010-12-08 中国科学院工程热物理研究所 一种微型燃气轮机燃烧室喷嘴
US8438853B2 (en) 2008-01-29 2013-05-14 Alstom Technology Ltd. Combustor end cap assembly
US20100236248A1 (en) 2009-03-18 2010-09-23 Karthick Kaleeswaran Combustion Liner with Mixing Hole Stub
US8495881B2 (en) * 2009-06-02 2013-07-30 General Electric Company System and method for thermal control in a cap of a gas turbine combustor
RU2010132334A (ru) * 2010-08-03 2012-02-10 Дженерал Электрик Компани (US) Топливное сопло для турбинного двигателя и охлаждающий кожух для охлаждения внешней части цилиндрического топливного сопла турбинного двигателя
JP5438727B2 (ja) 2011-07-27 2014-03-12 株式会社日立製作所 燃焼器、バーナ及びガスタービン
EA021650B1 (ru) 2011-08-29 2015-08-31 Геннадий Борисович Варламов Многокамерная газовая горелка трубчатого типа
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US9562689B2 (en) * 2012-08-23 2017-02-07 General Electric Company Seal for fuel distribution plate
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Also Published As

Publication number Publication date
CN106461226A (zh) 2017-02-22
US10578305B2 (en) 2020-03-03
US20170227223A1 (en) 2017-08-10
WO2016071186A1 (fr) 2016-05-12
CN106461226B (zh) 2019-06-28
EP3134682B1 (fr) 2018-08-22
RU2656177C1 (ru) 2018-05-31

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