EP2236934A1 - Agencement de brûleur - Google Patents

Agencement de brûleur Download PDF

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Publication number
EP2236934A1
EP2236934A1 EP09155441A EP09155441A EP2236934A1 EP 2236934 A1 EP2236934 A1 EP 2236934A1 EP 09155441 A EP09155441 A EP 09155441A EP 09155441 A EP09155441 A EP 09155441A EP 2236934 A1 EP2236934 A1 EP 2236934A1
Authority
EP
European Patent Office
Prior art keywords
sleeve
fuel supply
burner
supply channel
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.)
Withdrawn
Application number
EP09155441A
Other languages
German (de)
English (en)
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 EP09155441A priority Critical patent/EP2236934A1/fr
Priority to PCT/EP2010/053060 priority patent/WO2010121864A1/fr
Priority to ES10711179.1T priority patent/ES2437090T3/es
Priority to US13/255,117 priority patent/US9057524B2/en
Priority to RU2011142000/06A priority patent/RU2491478C2/ru
Priority to CN201080012440.9A priority patent/CN102388270B/zh
Priority to EP10711179.1A priority patent/EP2409086B1/fr
Publication of EP2236934A1 publication Critical patent/EP2236934A1/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Withdrawn legal-status Critical Current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
    • F23R3/283—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.
  • Gas turbine engines are used in power plants and other large-scale engine applications, among other things, with burner assemblies for firing fluid fuels.
  • burner assemblies for firing fluid fuels.
  • so-called dual-fuel burners are used, 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, thereby achieving 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 for example in EP 0 580 683 B1 reproduced.
  • a challenge in these burners are the resulting by an uneven thermal distribution mechanical stresses in the walls of the metallic housing, the so-called hub in which the Zubigringkanäle the gas and oil fuels are arranged relatively close together, represents a gas ring space feeds the main burner based on the flow direction of the incoming air on the input side upstream 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 annulus and a leading to the annulus oil supply channel, which is located in the located between the gas annulus and the pilot burner hub wall.
  • gas Since gas has a lower density compared to oil, it requires a larger cross-section, whereby the dimensioning of the gas supply is much greater than the oil supply. Therefore, the part of the burner hub with the gas supply to a larger air duct facing outer surface than the oil supply.
  • the air supply is done with pre-compressed air that has passed through a compressor, whereby this supplied air has a temperature due to the compression, which already reaches over 400 ° C. Consequently, the area of the burner hub with the gas supply is heated rapidly to a temperature in the range of over 400 ° C and remains at this operating temperature.
  • 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.
  • a cold fuel is led through a hot hub area, such voltages occur.
  • the present invention therefore has the object to reduce the described thermal stresses in the burner hub of the burner assembly.
  • a burner arrangement according to the invention for a combustion system for firing fluid fuels comprises a burner hub, at least one air supply channel and for each fuel type at least one fuel supply channel, wherein the at least one fuel supply channel is at least partially formed in the burner hub.
  • Disposed in at least one fuel supply passageway is a shielding wall spaced from the wall of the fuel supply passageway so that a gap not belonging to the flow path of the fuel flowing through the fuel supply passageway is formed between the wall of the fuel supply passageway and the shielding wall.
  • 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 limits the heat exchange between the fuel and the burner hub.
  • the shielding wall can be formed in a structurally simple embodiment of the invention by an introduced into the fuel supply duct sleeve.
  • it can be equipped with at least one radial positioning means, which ensures a distance of the sleeve from the wall of the fuel supply channel, wherein the distance can be selected in particular with regard to the maximum allowable heat transfer rate can be.
  • the at least one radial positioning means of the sleeve can, for example, be designed as a circularly arranged, radially outwardly projecting positioning projection.
  • the sleeve can each have at least one circumferential positioning projection in the region of its two ends.
  • 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.
  • an annular groove By means of the annular groove can then be avoided when welding or soldering the fuel supply pipe to the fuel supply channel, a hard soldering or soldering the positioning projection on the fuel supply channel and / or 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 channel for axially positioning the sleeve (30).
  • an axial positioning of the sleeve without cohesive connection is possible.
  • an axial clearance be present, which allows a thermal expansion of the sleeve in the axial direction, without causing voltages are generated.
  • 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 assembly according to the prior art, which may 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 possible embodiments are known and its representation has therefore been omitted here.
  • the inner air supply channel 3 has a twist blading 6 in its end region.
  • the pilot burner system can be operated in a manner known per se, ie predominantly as a diffusion burner. Its task is to maintain the main burner in a stable burner, since it is usually operated with a lean mixture to reduce the emission of pollutants, which requires stabilizing 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 annular 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.
  • FIG. 2 shows an embodiment of the burner hub 18 of a burner assembly according to the prior art in cross section.
  • the burner hub 18 has, as an integrally formed casting, welded cast plugs 17, with which the auxiliary openings are closed, which were used to remove the mandrels.
  • annular spaces 9 and 13 are arranged.
  • the annular spaces 9 and 13 each have a plurality of outlet openings 10 and 14, through which the respective fuel (medium B or medium C in FIG. 1 ) is emptied into the combustion chamber 24.
  • FIG. 3 is a schematically exaggerated sequence of thermally induced stresses in the burner hub of the prior art FIG. 2 shown. 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 passage 23 through which oil flows at a temperature of about 50 ° C, and the gas annulus 9, due to the heating by the compressor air in the air supply channel 4 (medium A in Fig.1 ) is heated to about 420 ° C.
  • FIG. 4 shows a detail of a cross section through an embodiment of the burner assembly according to the invention.
  • the burner assembly comprises a burner hub 18 in which a gas annulus 9 with a gas supply channel 19 (in FIG. 4 not shown) and an oil annulus 13 with an oil supply channel 23 are arranged.
  • the basic structure of the burner assembly corresponds to that with reference to the FIGS. 1 and 2 described structure. It will therefore only the differences to the FIGS. 1 and 2 described burner structure described.
  • a shielding wall 30 is arranged in the oil supply channel 23 such that a gap 38 is formed between the wall between the gas ring space 9 and the oil supply line 23 on the one hand and the shielding wall 30 on the other hand.
  • This space 38 thermally isolates the flow path of the oil formed by the inner surface of the shielding wall 30 from the wall 21 between the gas annulus 9 and the oil supply line 23, since the medium in the gap, such as air or hardly or hardly flowing oil, a much lower
  • the thermal conductivity of air is 0.023 W / mK and that of oil is about 0.15 W / mK (at room temperature).
  • the thermal conductivity of metals is two to three orders of magnitude higher.
  • the gap 38 can therefore be considered an adiabatic acting thermal shielding can be seen.
  • the amount of the distance s between the wall 21 and the shielding wall 30 may be used constructively to set a desired heat transfer rate.
  • 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 space 9 and the oil supply line 23.
  • the outer diameter of the sleeve 30 is dimensioned smaller by a predetermined amount than the inner diameter of the oil supply channel 23, so that between the inserted sleeve 30 and the wall 21, a gap 38 is formed, in which a medium having a substantially lower thermal conductivity than the metal Burner hub 18 is located.
  • 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.
  • the sleeve 30 is designed as a sleeve 30 which can be inserted into an opening in a tubular section 37 of the oil supply channel 23.
  • the sleeve 30 has for this purpose at its upstream end a preferably circular, annular positioning projection 33 which serves as a spacer for radially centering the sleeve body in the cavity 23 and at the same time the function of a Abutting edge carries 53 which abuts against a complementary, in the region of the opening of the tubular projection 37 existing abutment edge 52 of a corresponding Nutausfräsung and thus determines the position of the sleeve 30 in the axial direction.
  • FIG. 5 shows for clarity an enlarged partial cross-sectional view of the tubular section 37 of the oil supply channel 23 and the sleeve 30 inserted therein.
  • the sleeve 30 has at its upstream positioned end a positioning projection 33 with an annular groove 36. are.
  • the annular groove 36 is located in the oil supply passage 23 inserted sleeve 30 in the amount of the plane in which the opening of the tubular section 37 is executed.
  • the welding seam 31 is located in the region of the annular groove 36 during the welding of the tubular section 37 with an oil supply pipe 32, so that when the two pipe ends 30 are joined, the positioning projection 33, and thus the sleeve 30, is not welded or burnt.
  • the positioning protrusion 33 is disposed in a common groove groove of the tubular portion 37 and a corresponding groove groove of the oil supply pipe 32.
  • the groove groove of the oil supply pipe 32 also has a counter abutment edge 50 which cooperates with a 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.
  • positioning projection 35 (FIG. Figure 4 ) disposed near the downstream end of the sleeve 30.
  • positioning projection 35 is preferably designed as an annular Vietnamese Surpriseder projection and extends with its preferably cylindrically configured outer diameter up to the wall of the cavity 38 so that it also contributes to the centering of the sleeve 30.
  • 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 located positioning projection 33 is dimensioned such that a predetermined clearance d between the Jacobanoßungskante 50 in the Nutausfräsung the oil supply pipe 32 and the corresponding abutment edge 51 of the positioning projection 33 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 sleeve 30 can be mounted in the burner assembly according to the invention by passing through the opening of the tubular section 37 of the fuel supply channel 23 to be connected to a fuel supply pipe 32 until abutment of the abutment edge 53 of the positioning projection 33 against the abutment edge 52 in the groove cut of the pipe executed portion 37 is inserted into the fuel supply passage 23. Thereafter, the fuel supply pipe 32 is placed on the placed upstream end of the tubular portion 37 and connected by a welding method with the tubular portion 37, wherein the annular groove 36 prevents a firm welding of the sleeve on the fuel supply pipe 32 and / or the tubular portion 37.
  • 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. Also, the sleeve does not need to have no 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)
EP09155441A 2009-03-18 2009-03-18 Agencement de brûleur Withdrawn EP2236934A1 (fr)

Priority Applications (7)

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
ES10711179.1T ES2437090T3 (es) 2009-03-18 2010-03-11 Disposición de quemador para una turbina de gas
US13/255,117 US9057524B2 (en) 2009-03-18 2010-03-11 Shielding wall for a fuel supply duct in a turbine engine
RU2011142000/06A RU2491478C2 (ru) 2009-03-18 2010-03-11 Горелочное устройство
CN201080012440.9A CN102388270B (zh) 2009-03-18 2010-03-11 燃烧器装置
EP10711179.1A EP2409086B1 (fr) 2009-03-18 2010-03-11 Arrangement de brûleur pour une turbine à gaz

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP2236934A1 true EP2236934A1 (fr) 2010-10-06

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 After (1)

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

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
KR20240013799A (ko) * 2021-08-05 2024-01-30 미츠비시 파워 가부시키가이샤 가스 터빈 연소기 및 가스 터빈

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0580683B1 (fr) 1991-04-25 1995-11-08 Siemens Aktiengesellschaft Bruleur, en particulier pour turbines a gaz, pour la combustion peu polluante du gaz de houille et d'autres combustibles
WO2001001041A1 (fr) * 1999-06-24 2001-01-04 Pratt & Whitney Canada Corp. Bouclier thermique pour injecteur de carburant

Family Cites Families (12)

* 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
US5423173A (en) * 1993-07-29 1995-06-13 United Technologies Corporation Fuel injector and method of operating the fuel injector
JP3939756B2 (ja) * 1995-09-22 2007-07-04 シーメンス アクチエンゲゼルシヤフト 特にガスタービン用のバーナ
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
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

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0580683B1 (fr) 1991-04-25 1995-11-08 Siemens Aktiengesellschaft Bruleur, en particulier pour turbines a gaz, pour la combustion peu polluante du gaz de houille et d'autres combustibles
WO2001001041A1 (fr) * 1999-06-24 2001-01-04 Pratt & Whitney Canada Corp. Bouclier thermique pour injecteur de carburant

Also Published As

Publication number Publication date
RU2491478C2 (ru) 2013-08-27
RU2011142000A (ru) 2013-04-27
CN102388270A (zh) 2012-03-21
CN102388270B (zh) 2014-07-09
US20110314826A1 (en) 2011-12-29
US9057524B2 (en) 2015-06-16
WO2010121864A1 (fr) 2010-10-28
ES2437090T3 (es) 2014-01-08
EP2409086B1 (fr) 2013-11-13
EP2409086A1 (fr) 2012-01-25

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