EP2436983A1 - Brûleur à rayons - Google Patents

Brûleur à rayons Download PDF

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Publication number
EP2436983A1
EP2436983A1 EP10186365A EP10186365A EP2436983A1 EP 2436983 A1 EP2436983 A1 EP 2436983A1 EP 10186365 A EP10186365 A EP 10186365A EP 10186365 A EP10186365 A EP 10186365A EP 2436983 A1 EP2436983 A1 EP 2436983A1
Authority
EP
European Patent Office
Prior art keywords
nozzle carrier
jet
pilot
jet burner
pilot nozzle
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Withdrawn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
EP10186365A
Other languages
German (de)
English (en)
Inventor
Andreas Böttcher
Olga Deiss
Thomas Grieb
Matthias Hase
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 EP10186365A priority Critical patent/EP2436983A1/fr
Publication of EP2436983A1 publication Critical patent/EP2436983A1/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Withdrawn legal-status Critical Current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
    • F23R3/28—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
    • 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
    • F23R2900/00005—Preventing fatigue failures or reducing mechanical stress in gas turbine components
    • 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
    • F23R2900/00012—Details of sealing 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
    • F23R2900/03282—High speed injection of air and/or fuel inducing internal recirculation

Definitions

  • the invention relates to a jet burner with a jet pilot.
  • a pilot nozzle holder for jet pilot nozzles arranged and fastened in the nozzle carrier for the premixing nozzles undergoes, in particular at the nozzle outlet, also different thermal loads than the nozzle carrier for the premixing nozzles, thereby causing thermal damage at the contact surfaces between premix nozzle carrier and pilot nozzle carrier Tensions can come.
  • the object of the invention is to provide a jet burner with a jet pilot, which avoids these thermal stresses.
  • the labyrinth seal comprises annular formations of the premixing nozzle carrier and the pilot nozzle carrier.
  • the nozzle carriers are thus not only carriers of the labyrinth elements, but themselves form part of the sealing system.
  • a head plate with openings for the pilot nozzles at the second end of the pilot nozzle carrier is arranged to suppress the hot gas entering the jet burner and for fixing pilot nozzles in the combustion chamber direction.
  • 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.
  • premix nozzle carrier comprises jet nozzles arranged in a circle extending from its first end to the second end.
  • pilot nozzle carrier comprises jet nozzles extending from its first end to the second end.
  • At least three jet nozzles are arranged in the pilot nozzle carrier.
  • the jet nozzles are arranged in the pilot nozzle carrier in a plane. It is also conceivable that a jet nozzle in the pilot nozzle carrier on the longitudinal axis of the pilot nozzle carrier and the other jet nozzles are arranged on a concentric ring. By a different arrangement of the pilot nozzles within the alignment plate results in a different number of recirculation zones.
  • fuel pipes open into the jet nozzles.
  • the fuel lances advantageously have a closed tip and upstream of the tip radial openings for the injection of fuel across to an oxidant stream.
  • a gas turbine comprises a jet burner according to the invention.
  • a premixing nozzle carrier having a first flange leaf is formed at its first end, at its second end, in such a way that it is used as part of the jet burner according to the invention.
  • a pilot nozzle carrier is formed with a second flange at its first end, at its second end so that it is used as part of the jet burner according to the invention.
  • a lifetime extension of the jet burner is achieved because thermal stresses and movement disabilities are avoided by thermal decoupling of the jet pilot. Permanent deformations caused by thermal stresses do not occur, which ensures reliable operation of the pilot. Due to a labyrinth seal the hot gas entering the burner is still not possible. Eliminating twisting by using a jet pilot results in less thermal acoustics, suppression of pressure pulsations, generation of small-scale flow structures, and dissipation of acoustically induced heat release fluctuations.
  • the 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) with a first 12 and a second end 13 and a pilot nozzle carrier 4 (pilot jet carrier).
  • Premix nozzles 5 are arranged in a circular manner in the nozzle carrier 3.
  • a head plate 11 closes the interior of the pilot nozzle carrier 4 from the combustion chamber.
  • the openings 6 for the pilot nozzles 7 in the top plate 11 are in the embodiment of FIG. 1 arranged on a line.
  • FIG. 2 shows the pilot nozzle carrier 4, which at a first end 8 has a flange 23, which will be referred to here as the second flange 23 and is closed at the second end 10 with the top plate 11 having openings 6 for the pilot nozzles 7.
  • FIG. 3 shows the pilot nozzle carrier 4 from a different angle and without top plate 11th
  • FIG. 4 shows a section through a jet burner 1 with a jet pilot 2 facing away from the combustion chamber and during operation colder, first end 8 of the pilot nozzle carrier or first end 12 of the Vormischdüsenvics 3.
  • the pilot nozzle carrier 4 is in the central passage opening 25 of the premix nozzle carrier 4 via a first flange 22 on Vormischdüsenvic 3 and a second flange 23 on the pilot nozzle carrier 4, which form a threaded flange 9, fixed on one side and is at its second end 10, that is freely suspended, ie in the exit region.
  • the second end 10 of the pilot nozzle carrier 4 and the second end 13 of the Vormischdüsenitatis 3 form a labyrinth seal 14. Radial and axial movements are possible within this labyrinth seal 14.
  • FIG. 4 further shows an alignment plate 15 for the pilot nozzles 7 at the first end 8 of the pilot nozzle carrier 4.
  • FIG. 5 illustrates the function of the labyrinth seal 14 with room for movements in the radial and axial directions (see arrows).
  • FIG. 6 shows the alignment plate 15 with openings 24 for fixing pilot nozzles 7 in the radial direction relative to a longitudinal axis of the pilot nozzle carrier 4. It serves as a floating bearing and allows thermal shifts in the axial direction.
  • FIG. 7 shows alignment plate 15, pilot nozzle carrier 4 and nozzle carrier 3 in the assembly.
  • a first flange 22 on Vormischdüsenvic 3 and a second flange 23 on the pilot nozzle carrier 4 form a threaded flange 9.
  • the alignment plate 15 rests on the second flange 23 on the pilot nozzle carrier 4.
  • FIG. 8 demonstrates that the fuel supply of the jet pilot 2 takes place as well as usually in the premix burner, ie via fuel lances 16 in a so-called "cross flow" configuration.
  • FIG. 9 shows this in detail, wherein a fuel lance 16 has a closed tip 17 and near the top radial openings 18, can be injected through the fuel 20 in a flowing past the fuel lance 16 air flow 19.
  • FIGS. 10 and 11 show how a different number of recirculation zones 21 is created by a different arrangement of the pilot nozzles 7 within the top plate 11. By changing the nozzle diameter, the flow rate can be adjusted.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP10186365A 2010-10-04 2010-10-04 Brûleur à rayons Withdrawn EP2436983A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10186365A EP2436983A1 (fr) 2010-10-04 2010-10-04 Brûleur à rayons

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10186365A EP2436983A1 (fr) 2010-10-04 2010-10-04 Brûleur à rayons

Publications (1)

Publication Number Publication Date
EP2436983A1 true EP2436983A1 (fr) 2012-04-04

Family

ID=43629699

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10186365A Withdrawn EP2436983A1 (fr) 2010-10-04 2010-10-04 Brûleur à rayons

Country Status (1)

Country Link
EP (1) EP2436983A1 (fr)

Cited By (3)

* 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
WO2016160010A1 (fr) * 2015-04-01 2016-10-06 Siemens Energy, Inc. Injecteur de carburant à prémélange destiné à être utilisé dans un moteur à turbine à combustion
CN110566947A (zh) * 2019-09-16 2019-12-13 浙江力聚热水机有限公司 一种超低氮预混燃气燃烧器及其燃烧方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
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
US5103632A (en) * 1990-01-29 1992-04-14 Sundstrand Corporation Seal for a stored energy combustor
US5339635A (en) * 1987-09-04 1994-08-23 Hitachi, Ltd. Gas turbine combustor of the completely premixed combustion type

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4100733A (en) * 1976-10-04 1978-07-18 United Technologies Corporation Premix combustor
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
US5339635A (en) * 1987-09-04 1994-08-23 Hitachi, Ltd. Gas turbine combustor of the completely premixed combustion type
US5103632A (en) * 1990-01-29 1992-04-14 Sundstrand Corporation Seal for a stored energy combustor

Cited By (4)

* 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
US10088163B2 (en) 2013-03-13 2018-10-02 Siemens Aktiengesellschaft Jet burner with cooling duct in the base plate
WO2016160010A1 (fr) * 2015-04-01 2016-10-06 Siemens Energy, Inc. Injecteur de carburant à prémélange destiné à être utilisé dans un moteur à turbine à combustion
CN110566947A (zh) * 2019-09-16 2019-12-13 浙江力聚热水机有限公司 一种超低氮预混燃气燃烧器及其燃烧方法

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