EP2442029A1 - Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement - Google Patents

Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement Download PDF

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Publication number
EP2442029A1
EP2442029A1 EP10187257A EP10187257A EP2442029A1 EP 2442029 A1 EP2442029 A1 EP 2442029A1 EP 10187257 A EP10187257 A EP 10187257A EP 10187257 A EP10187257 A EP 10187257A EP 2442029 A1 EP2442029 A1 EP 2442029A1
Authority
EP
European Patent Office
Prior art keywords
pilot
plate
top plate
ring
head plate
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Withdrawn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
EP10187257A
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Olga Deiss
Thomas Grieb
Matthias Hase
Alexander Rambach
Meike Wilmsen
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 EP10187257A priority Critical patent/EP2442029A1/fr
Priority to PCT/EP2011/058344 priority patent/WO2012048913A1/fr
Publication of EP2442029A1 publication Critical patent/EP2442029A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/002—Wall structures
    • 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
    • F23R3/34—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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation
    • 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
    • F23R2900/00017—Assembling 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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 top plate device for a pilot nozzle carrier and a pilot nozzle carrier or a jet burner with a pilot nozzle carrier.
  • the invention further relates to a method for producing a pilot nozzle carrier.
  • the top plate of the jet pilot In order to decouple the thermal expansions of the top plate of the jet pilot from the nozzle carrier (jet carrier) for the premix nozzles, this is to be stored freely displaceable. However, the top plate should not jam.
  • the object of the invention is to provide a head plate device for a pilot nozzle holder, which does not jam. Another object of the invention is to provide a corresponding pilot nozzle carrier or a jet burner with such a pilot nozzle carrier. It is another object of the invention to provide a method for producing such a pilot nozzle carrier.
  • the plate (impingement cooling plate) has cooling openings. Through many holes in the impingement cooling plate, the top plate is rebound cooled. The supply of air via a direct central jet.
  • the top plate disc is provided with a thermal barrier coating (TBC) to lower the temperature of the material during operation of the torch.
  • TBC thermal barrier coating
  • the openings for pilot nozzles in the top plate disc hollow-cylindrical nozzle guides in the direction of the plate, wherein the nozzle guides relative to their respective Have axis radial grooves. Small grooves in the nozzle guides allow the flow of cooling air in the direction of the combustion chamber through the gap between the top plate and nozzle and thus lock it for the hot gas entering the jet pilot.
  • the top plate disc has a raised peripheral edge on the side facing the ring.
  • the ring has a raised peripheral edge on the side facing the top plate disc.
  • Elevated peripheral edges allow for quick and accurate assembly of the headstock device components.
  • top plate disc is welded to the ring.
  • the raised peripheral edge has radial bores.
  • the gap between the top plate and nozzle carrier (jet carrier) is blocked against ingress of hot gases from the combustion chamber, since cooling air can flow through the holes and the gap.
  • a pilot nozzle carrier further comprises a hollow cylinder, at one end of which the top plate device is arranged. At its other end, the hollow cylinder has a flange.
  • the pilot nozzle carrier is connected to the premix nozzle carrier (Jet Carrier) of the jet burner via the flange.
  • pilot nozzles are arranged in the openings of the plate and connected to the plate in the pilot nozzle carrier.
  • an alignment plate is arranged on the flange of the pilot nozzle carrier, wherein the alignment plate has openings for fixing pilot nozzles in the radial direction relative to a longitudinal axis of the pilot nozzle carrier.
  • the alignment plate serves as a floating bearing and allows thermal displacements of the central jet nozzles in the axial direction.
  • a jet burner comprises a substantially cylindrical premix nozzle carrier (jet carrier) with a central passage opening and, advantageously, a pilot nozzle carrier according to the invention arranged in the central passage opening.
  • a plate is inserted into a top plate disc and a ring firmly connected to the top plate disc.
  • top plate disc is welded to the ring.
  • pilot nozzles are welded to the plate.
  • FIG. 1 shows schematically and by way of example a jet burner 1 with a jet pilot 2.
  • the jet burner 1 comprises a nozzle carrier 3 for premixing nozzles (jet carrier) and a pilot nozzle carrier 4.
  • Premix nozzles 5 are arranged in a circle in the nozzle carrier 3.
  • a top plate device 6 closes the interior of the pilot nozzle carrier 4 with respect to the combustion chamber.
  • the openings 7 for the pilot nozzles 8 in the top plate device 6 are in the embodiment of FIG. 1 arranged on a line.
  • FIG. 2 shows the jet pilot 2
  • the pilot nozzle carrier 4 is formed as a hollow cylinder 9 having at one end a flange 10 for attachment of the jet pilot 2 and the pilot nozzle carrier 4 on the nozzle carrier 3 for premixing nozzles.
  • FIG. 2 At the other end of the pilot nozzle carrier 4, a head plate device 6. Pilot nozzle carrier 4 and head plate device 6 are provided at their radially outer sides with cooling air openings 11, 12. The upstream part of the pilot nozzles 8 and their arrangement in the pilot nozzle carrier 4 are in FIG. 2 also shown.
  • FIG. 3 shows an exploded view of a jet pilot 2 with a top plate disc 13, a plate 14, a ring 15, three pilot nozzles 8, a hollow cylinder 9 with flange 10 and an alignment plate 16th
  • Top plate disc 13, plate 14 and ring 15 form the top plate device 6.
  • the top plate disc 13 has a Edge 17 with cooling air openings 12 and hollow cylindrical nozzle guides 18, which have radial grooves 19 relative to their respective axis.
  • the plate 14 has in the embodiment of FIG. 3 three openings 20 for pilot nozzles 8 and further cooling holes 21 for impingement cooling of the top plate disc 13.
  • the supply of cooling air via a direct central jet along the axis of the hollow cylinder 9.
  • the top plate 13 is hot gas side coated with TBC.
  • the ring 15 has in the embodiment of FIG. 3 on the head plate disc 13 side facing a raised peripheral edge 22nd
  • the impact cooling plate 14 which serves as a piston and permits thermal displacements in the radial direction, is inserted into the top plate disk 13. Thereafter, the piston chamber is closed by means of a welded connection via the ring 15.
  • the pilot nozzles 8 are now firmly connected to the impingement cooling plate 14.
  • the hollow cylinder 9 of the pilot nozzle carrier 4 is firmly welded to the ring 15 and screwed over the flange 10 to the jet carrier (nozzle carrier) 3.
  • the alignment plate 16 with openings 23 for fixing pilot nozzles 8 in the radial direction relative to a longitudinal axis of the pilot nozzle carrier 4 is screwed onto the flange 10. It serves as a floating bearing and allows thermal displacements of the pilot nozzles 8 in the axial direction.
  • FIG. 4 shows a section through a combustion chamber-side part of a jet burner 1 with Vormischdüsenvic 3 and pilot nozzle carrier 4 according to the invention.
  • the top plate disc 13 is welded to the ring 15. A portion 25 between the top plate disc 13 and the ring 15 is defined.
  • the mounted between the top plate disc 13 and ring 15 plate 14 with openings 20 for pilot nozzles 8 is displaceable in this region 25 in the radial direction 26 and fixed in the axial direction.
  • the ring 15 is welded to the hollow cylinder 9 27.
  • the plate 14 is with the pilot nozzles 8 welded.
  • the top plate disc has nozzle guides 18 with grooves 19.
  • FIG. 5 shows a detailed view of the top plate device 6 and the cooling air streams 29, 30, 31 in the top plate device 6.
  • Air 29 strikes the plate 14 and penetrates through the cooling holes 21 in the space between the plate 14 and head plate disc 13 a. Through the grooves 19 in the nozzle guides 18 of the top plate disc 13, the air 30 penetrates into the gap 32 between the pilot nozzle 8 and nozzle guide 18 and flows in the direction of the combustion chamber from 31. Thus, the gap 32 between the top plate and nozzle is blocked.
  • the space between the pilot nozzle carrier 4 and the premixing nozzle carrier 3 (jet carrier) is flushed through radial bores in the hollow cylinder 9 of the pilot nozzle carrier 4.
  • the blocking of the gap between top plate device 6 and premix nozzle carrier 3 takes place by means of air flow through cooling air openings 12 in the edge of the top plate device 6.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP10187257A 2010-10-12 2010-10-12 Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement Withdrawn EP2442029A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP10187257A EP2442029A1 (fr) 2010-10-12 2010-10-12 Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement
PCT/EP2011/058344 WO2012048913A1 (fr) 2010-10-12 2011-05-23 Plaque supérieure refroidie par impact à découplage thermique pour un pilote de projection

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10187257A EP2442029A1 (fr) 2010-10-12 2010-10-12 Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement

Publications (1)

Publication Number Publication Date
EP2442029A1 true EP2442029A1 (fr) 2012-04-18

Family

ID=43719421

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10187257A Withdrawn EP2442029A1 (fr) 2010-10-12 2010-10-12 Plaque frontale refroidie par impact dotée d'un découplage thermique pour un pilote de rayonnement

Country Status (2)

Country Link
EP (1) EP2442029A1 (fr)
WO (1) WO2012048913A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014139738A1 (fr) * 2013-03-13 2014-09-18 Siemens Aktiengesellschaft Brûleur à jet de gaz comportant un canal de refroidissement dans la plaque de base
EP2881666A1 (fr) * 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Support de buse en mousse métallique
EP3002518A1 (fr) * 2014-09-30 2016-04-06 Alstom Technology Limited Panneau avant de chambre de combustion
EP2647912A3 (fr) * 2012-04-05 2017-03-29 General Electric Company Système et procédé pour supporter des buses de carburant à l'intérieur d'une chambre de combustion
EP3184902A1 (fr) * 2015-12-21 2017-06-28 General Electric Company Module couvercle de chambre de combustion et son système de maintien

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013204309A1 (de) * 2013-03-13 2014-09-18 Siemens Aktiengesellschaft Strahlbrenner
CN113028449B (zh) * 2021-02-26 2023-03-17 中国空气动力研究与发展中心设备设计与测试技术研究所 一种燃气发生器流线型燃料分流盘

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4408461A (en) * 1979-11-23 1983-10-11 Bbc Brown, Boveri & Company Limited Combustion chamber of a gas turbine with pre-mixing and pre-evaporation elements
US4914918A (en) * 1988-09-26 1990-04-10 United Technologies Corporation Combustor segmented deflector
US5271219A (en) * 1990-09-01 1993-12-21 Rolls-Royce Plc Gas turbine engine combustor
FR2825778A1 (fr) * 2001-06-06 2002-12-13 Snecma Moteurs Liaison coulissante entre un systeme d'injection d'une chambre de combustion et un fond de cette chambre de combustion
US20090188255A1 (en) * 2008-01-29 2009-07-30 Alstom Technologies Ltd. Llc Combustor end cap assembly
US20100058766A1 (en) * 2008-09-11 2010-03-11 Mcmahan Kevin Weston Segmented Combustor Cap

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4408461A (en) * 1979-11-23 1983-10-11 Bbc Brown, Boveri & Company Limited Combustion chamber of a gas turbine with pre-mixing and pre-evaporation elements
US4914918A (en) * 1988-09-26 1990-04-10 United Technologies Corporation Combustor segmented deflector
US5271219A (en) * 1990-09-01 1993-12-21 Rolls-Royce Plc Gas turbine engine combustor
FR2825778A1 (fr) * 2001-06-06 2002-12-13 Snecma Moteurs Liaison coulissante entre un systeme d'injection d'une chambre de combustion et un fond de cette chambre de combustion
US20090188255A1 (en) * 2008-01-29 2009-07-30 Alstom Technologies Ltd. Llc Combustor end cap assembly
US20100058766A1 (en) * 2008-09-11 2010-03-11 Mcmahan Kevin Weston Segmented Combustor Cap

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2647912A3 (fr) * 2012-04-05 2017-03-29 General Electric Company Système et procédé pour supporter des buses de carburant à l'intérieur d'une chambre de combustion
US10088163B2 (en) 2013-03-13 2018-10-02 Siemens Aktiengesellschaft Jet burner with cooling duct in the base plate
CN105102893A (zh) * 2013-03-13 2015-11-25 西门子公司 在基板中具有冷却通道的喷射燃烧器
CN105102893B (zh) * 2013-03-13 2017-06-06 西门子公司 在基板中具有冷却通道的喷射燃烧器
WO2014139738A1 (fr) * 2013-03-13 2014-09-18 Siemens Aktiengesellschaft Brûleur à jet de gaz comportant un canal de refroidissement dans la plaque de base
EP2881666A1 (fr) * 2013-12-09 2015-06-10 Siemens Aktiengesellschaft Support de buse en mousse métallique
EP3002518A1 (fr) * 2014-09-30 2016-04-06 Alstom Technology Limited Panneau avant de chambre de combustion
CN105465830A (zh) * 2014-09-30 2016-04-06 阿尔斯通技术有限公司 燃烧器前面板
US10107496B2 (en) 2014-09-30 2018-10-23 Ansaldo Energia Switzerland AG Combustor front panel
CN105465830B (zh) * 2014-09-30 2020-06-05 安萨尔多能源瑞士股份公司 燃烧器前面板
EP3184902A1 (fr) * 2015-12-21 2017-06-28 General Electric Company Module couvercle de chambre de combustion et son système de maintien
JP2017142048A (ja) * 2015-12-21 2017-08-17 ゼネラル・エレクトリック・カンパニイ 燃焼器キャップモジュールおよびそのための保持システム
US10429073B2 (en) 2015-12-21 2019-10-01 General Electric Company Combustor cap module and retention system therefor
JP7076943B2 (ja) 2015-12-21 2022-05-30 ゼネラル・エレクトリック・カンパニイ 燃焼器キャップモジュールおよびそのための保持システム

Also Published As

Publication number Publication date
WO2012048913A1 (fr) 2012-04-19

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