EP2881666A1 - Support de buse en mousse métallique - Google Patents

Support de buse en mousse métallique Download PDF

Info

Publication number
EP2881666A1
EP2881666A1 EP13196216.9A EP13196216A EP2881666A1 EP 2881666 A1 EP2881666 A1 EP 2881666A1 EP 13196216 A EP13196216 A EP 13196216A EP 2881666 A1 EP2881666 A1 EP 2881666A1
Authority
EP
European Patent Office
Prior art keywords
nozzle carrier
plate
passages
hot side
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Withdrawn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
EP13196216.9A
Other languages
German (de)
English (en)
Inventor
Simon Bez
Björn Buchholz
Thomas Grieb
Matthias Hase
Werner Krebs
Berthold Köstlin
Stefan Reich
Marc Tertilt
Jan Wilkes
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
Priority to EP13196216.9A priority Critical patent/EP2881666A1/fr
Publication of EP2881666A1 publication Critical patent/EP2881666A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F23R3/28—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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the invention relates to a nozzle carrier for a jet burner.
  • Jet-stabilized combustion systems where the fuel is burned in a jet flame downstream of the burner, have a simpler premixing zone compared to spin-stabilized systems. Since the pressure difference in the burner is converted exclusively into the axial velocity component, these burners are characterized by a low flashback tendency, which is why even highly reactive combustion mixtures with a higher hydrogen content can be burned with this burner. Furthermore, no spin-induced vortex structures are generated in jet-stabilized combustion systems, which can cause flame instabilities.
  • Such a jet-stabilized burner comprises, for example, a jet carrier with a plurality of nozzles, which can usually be arranged concentrically on one or more rings.
  • the design of the nozzle carrier is usually very solid and therefore associated with high material and processing costs.
  • the nozzle carrier must be coated and cooled.
  • the nozzle carrier is made by forging.
  • this shaping method is very expensive and, on the other hand, is only suitable for the production of simple geometries due to the process.
  • the object of the invention is to further develop said nozzle carrier, so that it is at least easier and cheaper to manufacture.
  • the invention solves this problem by providing that in such a nozzle carrier for a jet burner, comprising a nozzle carrier body comprising a hot side facing a combustion chamber in operation and a cold side facing away from the combustion chamber, between which a peripheral edge extends, wherein passages in Düsenarri notion extend from the cold side to the hot side and form Vormischzonen, the nozzle carrier body is made of metal foam and inner walls of the passages for Vormischzonen are gas-tight.
  • the nozzle carrier is no longer massively forged and machined, but it is a nozzle carrier body made of foamed metal powder. Cavities or breakthroughs (e.g., for premix zone and pilot cone) can be shaped directly upon foaming. This eliminates the editing.
  • a high-temperature resistant material should be used (for example, nickel-based alloy).
  • Metal foam can be made with different pore sizes. Due to the sponge-like structure, it offers a very large surface area, is gas-permeable and combines a low weight with good strength. Similar to any type of insulation material, a sponge structure is well suited to breaking and absorbing frequencies.
  • the passages for the premix zones, in which fuel and combustion air are to mix must be made gas-tight by suitable measures.
  • the inner walls are formed by tubes arranged in the passages for premixing zones. This ensures that no fuel enters the nozzle carrier uncontrolled and away from the premix zones.
  • a plate in particular a metal plate, is firmly connected to the hot side.
  • the temperature in front of the foam can be lowered somewhat or the nozzle carrier made of metal foam can thus be sealed against the penetration of the hot gas from the combustion chamber.
  • the metal plate should be made as thin as possible on the hot side, so that they can forward similar to a membrane vibrations of the burner on the associated metal foam. The vibrations are absorbed and absorbed by the metal foam.
  • a correspondingly shaped enclosure is firmly connected to the peripheral edge.
  • One possibility is, for example, to surround the body of metal foam with a cylinder of a shaped metal plate. Compressor air, which is guided past the nozzle carrier during operation, before it is guided around the burner back wall and into the premixing passages of the nozzle carrier, can thus be conducted better past the nozzle carrier. In addition, the mechanical stability of the nozzle carrier improves.
  • a plate is firmly connected to the cold side. It is expedient if the plate is a metal plate. Fastening elements of the nozzle carrier can be attached to this metal plate by means of which the nozzle carrier can be mounted on a burner back plate (cover plate).
  • At least one cooling tube is incorporated in the metal foam.
  • This cooling tube can already be incorporated during foaming in the metal foam. Through the cooling tube cooling air can be directed through the foam targeted to the plate on the hot side.
  • cooling air holes are provided in the plate on the hot side to divert the cooling air into the combustion chamber can.
  • FIG. 1 shows schematically and by way of example a section through a nozzle carrier 1 for a jet burner, with a nozzle carrier body 2, comprising a combustion chamber during operation facing a hot side 3 and a remote from the combustion chamber cold side 4, between which a circumferential edge 5 extends.
  • Passages 6 in the nozzle carrier body 2 extend from the cold side 4 to the hot side 3. In operation, combustion air flows from the cold side 4 into the passages 6 and mixes with fuel from fuel lances which project into the passages 6. Thus, premix zones are formed in the passages 6.
  • the nozzle carrier body 2 is made of metal foam 7 and the inner walls 8 of the passages 6 for premixing zones are gas-tight, for example by means of metallic tubes 9 for the premixing zone, which are firmly incorporated into the metal foam 7 of the nozzle carrier body 2.
  • FIG. 1 shows two metallic plates 10, 13, between which the metal foam 7 is foamed firmly adhering.
  • the plate 10 on the hot side 3 has a thermal barrier coating 11 in order to lower the temperature in the nozzle carrier 1.
  • the plate 13 connected to the cold side 4 may, for example, have fastening elements (not shown) with which the nozzle carrier 1 can be mounted in, for example, a gas turbine.
  • FIG. 1 a correspondingly shaped, in the example of FIG. 1 hollow cylindrical enclosure 12 which is fixedly connected to the peripheral edge 5 of the nozzle carrier body 2.
  • a cooling tube 14 is incorporated in the metal foam 7.
  • the cooling tube 14 serves to cool the plate 10 on the hot side 3 of the nozzle carrier 1 and allows cooling air 15 targeted, ie without high pressure loss, to lead to the plate 10, where they by additional, introduced into the plate 10 cooling air holes 16 in a Combustion chamber can be derived.
  • FIG. 2 shows FIG. 2 in that a plate 13 does not necessarily have to be provided at least on the cold side 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP13196216.9A 2013-12-09 2013-12-09 Support de buse en mousse métallique Withdrawn EP2881666A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13196216.9A EP2881666A1 (fr) 2013-12-09 2013-12-09 Support de buse en mousse métallique

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13196216.9A EP2881666A1 (fr) 2013-12-09 2013-12-09 Support de buse en mousse métallique

Publications (1)

Publication Number Publication Date
EP2881666A1 true EP2881666A1 (fr) 2015-06-10

Family

ID=49726612

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13196216.9A Withdrawn EP2881666A1 (fr) 2013-12-09 2013-12-09 Support de buse en mousse métallique

Country Status (1)

Country Link
EP (1) EP2881666A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106016362A (zh) * 2016-05-16 2016-10-12 中国科学院工程热物理研究所 一种燃气轮机柔和燃烧室及其控制方法
EP3195905A1 (fr) * 2016-01-22 2017-07-26 Extinctium Buse silencieuse de diffusion de gaz
WO2022058369A1 (fr) * 2020-09-18 2022-03-24 Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de chambre de combustion

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2122653A1 (de) * 1970-05-08 1971-12-09 Dunlop Holdings Ltd Stabilisierter Düsenbrenner
US5764850A (en) * 1996-04-04 1998-06-09 Phoenix Solutions Co. Silicon carbide foam electric heater for heating gas directed therethrough
WO2005061855A1 (fr) * 2003-12-20 2005-07-07 Mtu Aero Engines Gmbh Composant de turbine a gaz
DE102006029586A1 (de) * 2006-06-20 2007-12-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Einblaskopf, Mischungsraum und Triebwerk
DE102007063539A1 (de) * 2007-12-21 2009-06-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennkammervorrichtung
EP2442029A1 (fr) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement
DE102010043336A1 (de) * 2010-11-03 2012-05-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennkammervorrichtung
DE102010043337A1 (de) * 2010-11-03 2012-05-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Fluidzuführungsvorrichtung

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2122653A1 (de) * 1970-05-08 1971-12-09 Dunlop Holdings Ltd Stabilisierter Düsenbrenner
US5764850A (en) * 1996-04-04 1998-06-09 Phoenix Solutions Co. Silicon carbide foam electric heater for heating gas directed therethrough
WO2005061855A1 (fr) * 2003-12-20 2005-07-07 Mtu Aero Engines Gmbh Composant de turbine a gaz
DE102006029586A1 (de) * 2006-06-20 2007-12-27 Deutsches Zentrum für Luft- und Raumfahrt e.V. Einblaskopf, Mischungsraum und Triebwerk
DE102007063539A1 (de) * 2007-12-21 2009-06-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennkammervorrichtung
EP2442029A1 (fr) * 2010-10-12 2012-04-18 Siemens Aktiengesellschaft Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement
DE102010043336A1 (de) * 2010-11-03 2012-05-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennkammervorrichtung
DE102010043337A1 (de) * 2010-11-03 2012-05-16 Deutsches Zentrum für Luft- und Raumfahrt e.V. Fluidzuführungsvorrichtung

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3195905A1 (fr) * 2016-01-22 2017-07-26 Extinctium Buse silencieuse de diffusion de gaz
FR3046943A1 (fr) * 2016-01-22 2017-07-28 Extinctium Buse silencieuse de diffusion de gaz.
CN106016362A (zh) * 2016-05-16 2016-10-12 中国科学院工程热物理研究所 一种燃气轮机柔和燃烧室及其控制方法
WO2022058369A1 (fr) * 2020-09-18 2022-03-24 Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de chambre de combustion

Similar Documents

Publication Publication Date Title
EP2010773B1 (fr) Aube de turbine
DE69919298T2 (de) Kühlstruktur für eine Gasturbinenbrennkammer
EP3526519B1 (fr) Pointe de brûleur comprenant un système de conduit d'air et un système de conduit de combustible pour un brûleur et procédé de fabrication associé
DE60224141T2 (de) Gasturbine und Brennkammer dafür
EP2954262B1 (fr) Brûleur à jet de gaz comportant un canal de refroidissement dans la plaque de base
DE112014001594B4 (de) Brennkammer und Gasturbine
EP2423599A2 (fr) Procédé de fonctionnement d'un agencement de brûleur ainsi qu'agencement de brûleur destiné à l'exécution du procédé
DE112009000822T5 (de) Brennerkomponente und Verfahren zur Herstellung
WO2010066516A2 (fr) Lance à combustible pour brûleur
EP2881666A1 (fr) Support de buse en mousse métallique
DE112019004946T5 (de) Brennerkomponente, Brenner, Gasturbine und Herstellungsverfahren für Brennerkomponente
EP3219918A1 (fr) Dispositif de refroidissement de plateformes d'une couronne d'aubes directrices d'une turbine à gaz
EP2442029A1 (fr) Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement
WO2010136029A2 (fr) Utilisation d'une buse à compensation de hauteur
EP3018412B1 (fr) Récupérateur et Brûleur à Récupération
EP3559556B1 (fr) Pointe de brûleur destinée à être montée dans un brûleur comprenant un système de conduit d'air et un système de conduit de combustible et procédé de fabrication associé
DE2815916C2 (de) Ringbrennkammer mit Brennstoff-Vorverdampfung für Gasturbinentriebwerke
DE10341515A1 (de) Anordnung zur Kühlung hoch wärmebelasteter Bauteile
DE102019117868B4 (de) Düsenvorrichtung und Heißgasschweißanlage
EP2270397A1 (fr) Chambre de combustion de turbine à gaz et turbine à gaz
WO2020157190A1 (fr) Composant à gaz chaud pour turbines à gaz et procédé de fabrication d'un composant à gaz chaud pour turbines à gaz de ce type
EP2864705B1 (fr) Refroidissement d'une chambre de combustion
EP1577614B1 (fr) Arrangement d'une structure de support et d'un bouclier thermique d'un turbine à gaz
EP3593048B1 (fr) Chambre de combustion de type silo et procédé pour ré-équiper ladite chambre
DE10037776A1 (de) Brennkammer für ein Flüssigkeitsraketentriebwerk

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: 20131209

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

AX Request for extension of the european patent

Extension state: BA ME

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: 20151211