EP3134682B1 - Brenneranordnung - Google Patents

Brenneranordnung Download PDF

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Publication number
EP3134682B1
EP3134682B1 EP15788377.8A EP15788377A EP3134682B1 EP 3134682 B1 EP3134682 B1 EP 3134682B1 EP 15788377 A EP15788377 A EP 15788377A EP 3134682 B1 EP3134682 B1 EP 3134682B1
Authority
EP
European Patent Office
Prior art keywords
burner assembly
end plate
depression
edge
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.)
Active
Application number
EP15788377.8A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3134682A1 (de
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/de
Application granted granted Critical
Publication of EP3134682B1 publication Critical patent/EP3134682B1/de
Active 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
    • F23R3/28—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
    • 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
    • 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

  • the invention relates to a burner arrangement, in particular for a gas turbine plant.
  • a burner arrangement in particular for a gas turbine plant.
  • gas turbines there are always higher turbine inlet temperatures in order to achieve increased performance and higher efficiency.
  • appropriate burners must be provided.
  • These burners should also meet the highest requirements in terms of production and service, which is why, among other things, there are also high requirements in terms of service life.
  • components which are exposed to high temperatures or temperature gradients such as, for example, the combustion chamber facing end plate of a burner, experienced during operation high local stresses, which among other things lead to spalling of ceramic coatings and thus to early component failure.
  • document US 2010/300106 A1 describes a burner assembly according to the preamble of claim 1.
  • the object of the invention is to further develop said device, so that a high component life is guaranteed even with higher requirements in terms of temperature and temperature gradients.
  • 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 are mixed in which initiated during normal operation combustion air and fuel introduced, wherein the mixing channels are formed by mixing tubes, axially extending through an annulus defined between a tubular outer wall, a tubular inner wall spaced radially from the outer wall, an upstream annular end plate, and a downstream annular end 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 extend substantially parallel to a normal of the end plate from the annular space forth in 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 easily transported into thermally stressed areas of the burner in order to reduce the temperature during operation or to ensure a more homogeneous temperature distribution. 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 accumulation of material in the combustion chamber near area is reduced.
  • a more homogeneous temperature distribution results.
  • the temperature-induced voltages can be significantly reduced.
  • 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.
  • 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 therefore particularly advantageous if the recess is arranged radially inward in the inner edge, because there the voltage values of the component are 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 bottom of the depression has a cross-sectional profile of the set circle, oval, ellipse, so that sources of increased material stresses, 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
  • the mentioned embodiments of the invention lead, both individually and in combination, to the reduction of voltage peaks and thus to an increased service life of the end plate.
  • the face plate heats up evenly during transient processes and even in stationary operation, a more homogeneous temperature distribution. This leads to lower temperature loads under the same thermal conditions. Thus, they allow a significant lifetime extension of the face plate under the same thermal boundary conditions.
  • the control range increases during operation and there are also cheaper alternatives with regard to materials and coatings.
  • the figures show a burner assembly 1 according to an embodiment of the present invention or components thereof.
  • the burner assembly 1 of FIG. 1 comprises a combustion chamber 2, a centrally located pilot burner 23, a mixing tube assembly 24 having a plurality of mixing tubes 6 forming mixing channels 3 opening into the combustion chamber 2, a plurality of fuel injectors 25 protruding into the mixing tubes 6 to a suitable position , 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 comprises a tubular outer wall 8, a tubular inner wall 9 spaced radially from the outer wall 8, an upstream annular end plate 10 and a downstream face plate 11 defining an annulus 7 through which the mixing tubes 6 extend in the axial 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.
  • the mixing tube assembly 24 includes an annular partition plate 27.
  • the upstream face plate 10 includes a plurality of through holes 12 which receive and / or continue the mixing tubes 6.
  • the passage openings 12 define two hole circles with mutually different pitch circle diameters, wherein the passage openings 12 of the first pitch circle and the passage openings 12 of the second pitch circle are arranged offset from one another in the radial direction.
  • the face plate 10 has a plurality of in the FIG. 1 Air ducts, not shown, which extend in the axial direction and are distributed over the annular surface of the end plate 10.
  • the partition plate 27 is analogous to the end plate 10 is 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. Further, in the face plate 11 are axially extending Air channels 30 are 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
  • FIG. 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.
  • FIG. 3 It can be seen that at least one opening 16 branching off from the axial bore 15 is provided for the removal of cooling air 17.
  • FIG. 4 It can be seen how several holes 15 open into the chamber 18.
  • FIG. 5 shows it 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 at the points of high temperature on the inner cylindrical surface and the outer cylindrical surface of the face plate lead to a better temperature distribution and thus lower temperature-induced stresses.
  • FIG. 6 shows an embodiment of the invention with elongated recesses 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 the structures inside the rim 13 of the end plate 11 are shown.
  • two holes 15 are assigned to a recess 19.
  • the holes 15 have openings 16 for the removal of cooling air 17.
  • This cooling air 17 flows through channels 31 to the recess 19.
  • the openings 16 and the channels 31 are arranged so that opposite sides 21 of the recess 19 can be cooled by impingement cooling.
  • FIG. 7 also shows that the base 20 of the recess 19 has a cross-sectional profile of the set circle, oval, ellipse. Furthermore, in the FIG. 7 to see that 19 further openings 22 are arranged in the direction of the annular space 7 in the recess.
  • FIG. 8 shows a view of the same embodiment with a section through a recess 19. It can be seen the round base 20 of the recess 19 and the channels 31, coming from the openings 16 of the holes 15 coming into the recess 19, and other openings 22, which of the Recesses 19, starting in the annular space 7 open.
  • FIG. 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)
EP15788377.8A 2014-11-03 2015-10-29 Brenneranordnung Active EP3134682B1 (de)

Applications Claiming Priority (2)

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

Publications (2)

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

Family

ID=54366207

Family Applications (1)

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

Country Status (5)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022096210A1 (de) * 2020-11-04 2022-05-12 Siemens Energy Global GmbH & Co. KG Resonatorring, verfahren und brennkorb

Families Citing this family (5)

* 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
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
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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
US9309809B2 (en) * 2013-01-23 2016-04-12 General Electric Company Effusion plate using additive manufacturing methods
US9303873B2 (en) 2013-03-15 2016-04-05 General Electric Company System having a multi-tube fuel nozzle with a fuel nozzle housing
US20150285502A1 (en) * 2014-04-08 2015-10-08 General Electric Company Fuel nozzle shroud and method of manufacturing the shroud
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WO2022096210A1 (de) * 2020-11-04 2022-05-12 Siemens Energy Global GmbH & Co. KG Resonatorring, verfahren und brennkorb

Also Published As

Publication number Publication date
RU2656177C1 (ru) 2018-05-31
US10578305B2 (en) 2020-03-03
US20170227223A1 (en) 2017-08-10
EP3134682A1 (de) 2017-03-01
CN106461226B (zh) 2019-06-28
WO2016071186A1 (de) 2016-05-12
CN106461226A (zh) 2017-02-22

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