EP2409086A1 - Arrangement de brûleur - Google Patents

Arrangement de brûleur

Info

Publication number
EP2409086A1
EP2409086A1 EP10711179A EP10711179A EP2409086A1 EP 2409086 A1 EP2409086 A1 EP 2409086A1 EP 10711179 A EP10711179 A EP 10711179A EP 10711179 A EP10711179 A EP 10711179A EP 2409086 A1 EP2409086 A1 EP 2409086A1
Authority
EP
European Patent Office
Prior art keywords
sleeve
supply channel
burner
fuel supply
wall
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
EP10711179A
Other languages
German (de)
English (en)
Other versions
EP2409086B1 (fr
Inventor
Karsten Jordan
Tobias Krieger
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 EP10711179.1A priority Critical patent/EP2409086B1/fr
Publication of EP2409086A1 publication Critical patent/EP2409086A1/fr
Application granted granted Critical
Publication of EP2409086B1 publication Critical patent/EP2409086B1/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
    • F23R3/283—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
    • F23D—BURNERS
    • F23D2211/00—Thermal dilatation prevention or compensation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00018—Means for protecting parts of the burner, e.g. ceramic lining outside of the flame tube

Definitions

  • the invention relates to a burner arrangement for firing fluid fuels and in particular to a burner arrangement for a gas turbine plant.
  • burner assemblies for firing fluid fuels are among other gas turbines in power plants and others
  • dual-fuel burners which are provided for the combustion of liquid and gaseous fuels, for example natural gas and fuel oil, optionally or in combination.
  • the burner assemblies are accordingly large in size and have a complex structure with multiple fuel supply channels.
  • a centrally located small sized pilot burner with its own fuel supply and air supply is used to stabilize the flame of a large main burner which is placed around the pilot burner.
  • the large main burner is operated predominantly in lean-mixed operation with excess oxygen in order to achieve more favorable emission values.
  • operation with a lean mixture causes the flame of the main burner at least in certain operating conditions subject to fluctuations, which are compensated by a continuous firing action of the pilot burner.
  • Such a burner arrangement is reproduced, for example, in EP 0 580 683 B1.
  • Gas and oil energy sources are arranged relatively close to each other, dar.
  • a gas annulus feeds the main burner based on the flow direction of the incoming air incoming on the upstream side of the so-called swirl vanes, which impart a mixing swirl to the air flow with the fuel gas, or through the swirl vanes.
  • an oil supply is present, which is usually located closer to the burner outlet, as the gas supply. It comprises an oil ring space and an oil feed channel leading to the annular space, which is arranged in the hub wall located between the gas ring space and the pilot burner.
  • the leading to the oil annulus oil supply channel is further away from the hot air supply channel so that the oil in the oil supply channel hardly undergoes heating and therefore only has a temperature of about 50 ° C.
  • the burner hub experiences strong heating in the area of the gas ring space and, on the other hand, the adjacent oil supply channel is significantly cooler, the wall between the gas ring space and the oil supply channel is subject to a large temperature gradient.
  • the temperature gradient arise thermal stresses that shorten the life of such burner hubs or make the use of a high-quality material with the associated costs required lent. Also in other areas where a cold
  • the present invention therefore has the object to reduce the described thermal stresses in the burner hub of the burner assembly.
  • this is equipped with at least one radial positioning means, which ensures a distance of the sleeve from the wall of the fuel supply channel, the distance can be selected in particular with regard to the maximum allowable heat transfer rate.
  • the at least one radial positioning means of the sleeve is designed as a circumferentially arranged, radially outwardly projecting positioning projection.
  • the gap forms a poorly heat-conducting region in comparison to the surrounding metal of the burner hub, which thermally insulates the metal of the hub from the flowing fuel and thus facilitates the heat exchange between the fuel and the burner.
  • Hub limited.
  • the sleeve can each have at least one circumferential positioning projection in the region of its two ends. As a result, the orientation of the casing device is more reliable and the possible due to the game intervals natural oscillations in the flow of fuel are excluded.
  • the at least one positioning projection of the sleeve can furthermore have an annular groove, which is particularly advantageous when the positioning projection is located in the region of a connection point between the fuel supply channel and a fuel supply pipe.
  • annular groove can then be avoided when welding or soldering the Brennstoffzuschreib- tube with the fuel supply channel, a solid or brazing the positioning projection on the fuel supply channel and / or on the fuel supply pipe.
  • the sleeve may be provided with at least one axial positioning means cooperating with an axial positioning means provided in the fuel supply passage for axially positioning the sleeve (30).
  • an axial positioning of the sleeve without cohesive connection is possible.
  • between the axial positioning of the sleeve and the axial positioning means in the fuel supply channel in particular an axial
  • the axial positioning of the sleeve may be formed as at least one abutting edge on an end face of the positioning projection.
  • the axial positioning means in the fuel supply channel is then designed as a counteranglement edge.
  • FIG. 1 shows a burner arrangement known from EP 0 580 683 B1
  • FIG. 2 shows a known embodiment of the burner hub of a burner arrangement
  • FIG. 3 shows a schematically exaggerated sequence of the thermally induced voltage in the burner hub according to the prior art from FIG. 2,
  • FIG. 5 shows an enlarged partial cross-sectional view from FIG. 4.
  • FIG. 1 shows a burner arrangement according to the prior art, which can optionally be used in conjunction with a plurality of similar arrangements, for example in the combustion chamber of a gas turbine plant.
  • the pilot burner system comprises a central oil feed 1 (medium G) with an oil nozzle 5 arranged at its end and an inner gas supply channel 2 (medium F) arranged concentrically around the central oil feed 1. This in turn is surrounded by a concentrically arranged around the axis of the burner inner air supply channel 3 (Medium E).
  • a suitable ignition system may be arranged, for which many embodiments are known and whose illustration has therefore been omitted here.
  • the inner air supply channel 3 has a swirl blading 6 in its end region.
  • the pilot burner system can, in a manner known per se, ie predominantly as a diffusion burner operated. Its task is to maintain the main burner in a stable burner, since it is mostly operated with a mixture of mats to reduce the emission of pollutants, which requires stabilization of its flame by means of a diffusion flame or a flame based on a less lean mixture.
  • the main burner system has a concentric with the pilot burner system arranged and obliquely on this incoming outer air supply annular duct system 4.
  • This air supply ring channel system 4 is also provided with a swirl blading 7.
  • the swirl blading 7 consists of hollow blades with outlet nozzles 11 in the flow cross-section of the air supply annular channel system 4 (medium A). These are fed from a gas supply line 19 and a gas ring channel 9 through openings 10.
  • the burner has an oil supply line 23, which opens into an oil ring channel 13, which in turn has outlet nozzles 14 in the region or downstream of the swirl blading 7.
  • the burner hub 18 has, as an integrally formed cast part, welded cast plugs 17, with which the auxiliary openings, which served to remove the mandrels, are closed.
  • FIG. 3 shows a schematically exaggerated sequence of the thermally induced stresses in the burner hub according to the prior art from FIG. Due to the stresses, the wall 21 between the gas ring space 9 and the oil supply line 23 is deformed.
  • This deformation of the metallic cast and / or welded burner hub 18 is due to the temperature gradient in the wall between the oil supply channel 23, flows through the oil at a temperature of about 50 0 C, and the gas annulus 9, due to the heating by the compressor air in the air supply channel 4 (medium A in Fig.l) is heated to about 420 0 C.
  • the shielding wall is realized in the form of a sleeve 30 inserted into the oil supply channel 23, which prevents direct contact of the cold oil flowing along the flow path in the oil supply channel 23 with the wall 21 between the gas ring chamber 9 and the oil supply line 23.
  • the oil itself can be used in the simplest case, provided that no ignition is to be feared, since in this case no sealing of the intermediate space 38 against the flow path of the oil is required.
  • FIG. 5 shows an enlarged partial cross-sectional view of the tubular section 37 of the oil supply channel 23 and the sleeve 30 introduced therein for clarification.
  • the positioning projection 33 is disposed in a common groove cutout of the tubular portion 37 and a corresponding groove groove of the oil supply pipe 32. Like the groove cutout of the tubular section 37, the groove cutout of the oil feed tube 32 also has a mating edge 50 which cooperates with an abutment edge 51 of the positioning projection 33. In this way, the sleeve 30 is centered by the positioning projection 33 not only in the oil supply passage 23, but also secured in the direction of the longitudinal axis Y.
  • All positioning projections 33, 35 preferably have a diameter dimensioned such that there is a sufficient distance between the walls of the cavity 30 and cylindrical outer surfaces of the positioning projections, which serves to compensate for different thermal expansions.
  • the sleeve 30 is positioned on the one hand exactly enough in the radial direction and on the other hand never jammed during operation. The stresses occurring as a result of jamming in the burner hub 18 are thus effectively avoided.
  • the thermal expansion of the sleeve 30 in the axial direction Y is designed free of tension causing jamming.
  • positioning projection 33 located in the Nutausfräsungen of the tubular section 37 and the oil supply pipe 32 positioning projection 33 is dimensioned such that a predetermined clearance d between the Jacobanoßkante 50 in the Nutausfräsung the oil supply pipe 32 and the corresponding abutment edge 51 of the positioning projection 33rd is present, which allows a thermal expansion of the sleeve in the axial direction without thereby voltages in the axial direction Y would be built.
  • the invention has been described in the context of the embodiment with reference to a specific oil supply channel, it can also be used in other fuel supply channels.
  • the sleeve need not have a round cross-section, but may also have a polygonal cross-section.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)
  • Gas Burners (AREA)

Abstract

L'invention porte sur un arrangement de brûleur pour une installation de chauffe destinée à brûler des combustibles fluides. L'arrangement de brûleur comporte un moyeu de brûleur (18), au moins une gaine d'amenée d'air (3, 4) et, pour chaque type de combustible, au moins une gaine d'amenée de combustible (9, 13, 19, 23), la ou les gaines d'amenée de combustible (9, 13, 19, 23) étant au moins partiellement réalisées dans le moyeu de brûleur (18). Dans au moins une gaine d'amenée de combustible (23), on a disposé une paroi (30) formant écran, qui se trouve à une certaine distance de la paroi (21) de la gaine d'amenée de combustible (23), de sorte qu'entre la paroi (21) de la gaine d'amenée de combustible (23) et la paroi (30) formant écran, il se forme un espace intermédiaire (38), qui n'appartient pas à la trajectoire d'écoulement du combustible qui passe par la gaine d'amenée de combustible (23). Le manchon (30) est muni d'au moins un organe radial de positionnement (33, 35), lequel garantit une certaine distance (s) du manchon (30) à la paroi (21) de la gaine d'amenée de combustible (23), et le ou les organes radiaux de positionnement (33, 35) du manchon (3) sont réalisés sous forme d'au moins un ergot de positionnement (33,35), disposé d'une manière circonférentielle, dépassant radialement vers l'extérieur.
EP10711179.1A 2009-03-18 2010-03-11 Arrangement de brûleur pour une turbine à gaz Active EP2409086B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10711179.1A EP2409086B1 (fr) 2009-03-18 2010-03-11 Arrangement de brûleur pour une turbine à gaz

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09155441A EP2236934A1 (fr) 2009-03-18 2009-03-18 Agencement de brûleur
PCT/EP2010/053060 WO2010121864A1 (fr) 2009-03-18 2010-03-11 Arrangement de brûleur
EP10711179.1A EP2409086B1 (fr) 2009-03-18 2010-03-11 Arrangement de brûleur pour une turbine à gaz

Publications (2)

Publication Number Publication Date
EP2409086A1 true EP2409086A1 (fr) 2012-01-25
EP2409086B1 EP2409086B1 (fr) 2013-11-13

Family

ID=40943837

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09155441A Withdrawn EP2236934A1 (fr) 2009-03-18 2009-03-18 Agencement de brûleur
EP10711179.1A Active EP2409086B1 (fr) 2009-03-18 2010-03-11 Arrangement de brûleur pour une turbine à gaz

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09155441A Withdrawn EP2236934A1 (fr) 2009-03-18 2009-03-18 Agencement de brûleur

Country Status (6)

Country Link
US (1) US9057524B2 (fr)
EP (2) EP2236934A1 (fr)
CN (1) CN102388270B (fr)
ES (1) ES2437090T3 (fr)
RU (1) RU2491478C2 (fr)
WO (1) WO2010121864A1 (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6210810B2 (ja) * 2013-09-20 2017-10-11 三菱日立パワーシステムズ株式会社 デュアル燃料焚きガスタービン燃焼器
US20160116168A1 (en) * 2014-10-27 2016-04-28 Solar Turbines Incorporated Robust insulated fuel injector for a gas turbine engine
CN108310926B (zh) * 2018-04-25 2024-01-19 大连恒通和科技有限公司 燃烧尾气处理及热量回收装置
US10982856B2 (en) * 2019-02-01 2021-04-20 Pratt & Whitney Canada Corp. Fuel nozzle with sleeves for thermal protection
JPWO2023013310A1 (fr) * 2021-08-05 2023-02-09

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276696B1 (fr) * 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
DE59204270D1 (de) 1991-04-25 1995-12-14 Siemens Ag Brenneranordnung, insbesondere für gasturbinen, zur schadstoffarmen verbrennung von kohlegas und anderen brennstoffen.
US5423173A (en) * 1993-07-29 1995-06-13 United Technologies Corporation Fuel injector and method of operating the fuel injector
EP0851990B1 (fr) 1995-09-22 2001-12-05 Siemens Aktiengesellschaft Bruleur, en particulier pour turbine a gaz
US5761907A (en) * 1995-12-11 1998-06-09 Parker-Hannifin Corporation Thermal gradient dispersing heatshield assembly
DE19905996A1 (de) * 1999-02-15 2000-08-17 Abb Alstom Power Ch Ag Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer
DE19905995A1 (de) * 1999-02-15 2000-08-17 Asea Brown Boveri Brennstofflanze zum Eindüsen von flüssigen und/oder gasförmigen Brennstoffen in eine Brennkammer sowie Verfahren zum Betrieb einer solchen Brennstofflanze
US6182437B1 (en) * 1999-06-24 2001-02-06 Pratt & Whitney Canada Corp. Fuel injector heat shield
US6761035B1 (en) * 1999-10-15 2004-07-13 General Electric Company Thermally free fuel nozzle
US6543235B1 (en) * 2001-08-08 2003-04-08 Cfd Research Corporation Single-circuit fuel injector for gas turbine combustors
US6823677B2 (en) * 2002-09-03 2004-11-30 Pratt & Whitney Canada Corp. Stress relief feature for aerated gas turbine fuel injector
EP1701095B1 (fr) * 2005-02-07 2012-01-18 Siemens Aktiengesellschaft Ecran thermique
US8166763B2 (en) * 2006-09-14 2012-05-01 Solar Turbines Inc. Gas turbine fuel injector with a removable pilot assembly
US8015815B2 (en) * 2007-04-18 2011-09-13 Parker-Hannifin Corporation Fuel injector nozzles, with labyrinth grooves, for gas turbine engines

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2010121864A1 *

Also Published As

Publication number Publication date
ES2437090T3 (es) 2014-01-08
WO2010121864A1 (fr) 2010-10-28
RU2491478C2 (ru) 2013-08-27
CN102388270B (zh) 2014-07-09
EP2409086B1 (fr) 2013-11-13
US20110314826A1 (en) 2011-12-29
EP2236934A1 (fr) 2010-10-06
RU2011142000A (ru) 2013-04-27
US9057524B2 (en) 2015-06-16
CN102388270A (zh) 2012-03-21

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