EP2397764A1 - Brûleur de turbines - Google Patents

Brûleur de turbines Download PDF

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Publication number
EP2397764A1
EP2397764A1 EP10166431A EP10166431A EP2397764A1 EP 2397764 A1 EP2397764 A1 EP 2397764A1 EP 10166431 A EP10166431 A EP 10166431A EP 10166431 A EP10166431 A EP 10166431A EP 2397764 A1 EP2397764 A1 EP 2397764A1
Authority
EP
European Patent Office
Prior art keywords
fuel nozzle
turbine burner
burner according
fuel
blades
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Withdrawn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
EP10166431A
Other languages
German (de)
English (en)
Inventor
Boris Ferdinand Kock
Berthold Köstlin
Bernd Prade
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP10166431A priority Critical patent/EP2397764A1/fr
Priority to US13/699,801 priority patent/US8869535B2/en
Priority to CN201180030001.5A priority patent/CN102947650B/zh
Priority to EP11711862.0A priority patent/EP2583033B1/fr
Priority to PCT/EP2011/054777 priority patent/WO2011157458A1/fr
Publication of EP2397764A1 publication Critical patent/EP2397764A1/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Withdrawn legal-status Critical Current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
    • F23R3/36—Supply of different fuels
    • 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
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00008—Burner assemblies with diffusion and premix modes, i.e. dual mode burners
    • 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
    • F23D2900/00014—Pilot burners specially adapted for ignition of main burners in furnaces or gas turbines
    • 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
    • F23D2900/14—Special features of gas burners
    • F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]
    • 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
    • F23R2900/00004—Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits

Definitions

  • the invention relates to a turbine burner according to the preamble of claim 1.
  • the combustible components of the synthesis gases are essentially CO and H2.
  • the calorific value of the synthesis gas is about 5 to 10 times smaller compared to the calorific value of natural gas.
  • Main constituents in addition to CO and H2 are inert fractions such as nitrogen and / or water vapor and possibly also carbon dioxide. Due to the low calorific value consequently high volume flows of fuel gas must be supplied through the burner of the combustion chamber. As a result, for the combustion of low calorific fuels - e.g. Synthesis gas one or more separate fuel passages must be made available.
  • the synthesis gas is in the burner of the prior art - as in the EP 1 649 219 B1 described over a arranged around the burner axis Ringraumpassage the combustion chamber.
  • the gas is carried out upstream of the burner nozzle through an existing in the burner nozzle nozzle ring with salaried holes, wherein the gas is acted upon by a peripheral speed component.
  • the synthesis gas directly on the nozzle a relatively low Mach number is impressed.
  • there is also only a relatively small intensity with regard to the mixing with the combustion air which encloses the annular fuel flow both from inside and outside.
  • aggravating for a quick mixing of the fuel with the combustion air is the geometric design of the annular gap with a relatively large gap width and a correspondingly large mixing path.
  • the nozzle ring of EP 1 649 219 B1 Anchored holes have been chosen, in particular, for synthesis gases having a relatively high calorific value in order to achieve a sufficiently high pressure loss at the nozzle for acoustic stability, without substantially changing the main dimensions.
  • this embodiment has aerodynamic disadvantages. Thus, discrete jets are generated which can not be sufficiently evened out on the path available up to the burner exit, which leads to increased NO x emissions. In addition, due to the flow separations inside and in front of the nozzle, a considerable total pressure loss occurs, so that this pulse loss is not available as mixing energy.
  • the invention causes a lower pressure drop to occur with the same swirl intensity compared to the nozzle ring of the prior art nozzle.
  • the vanes cause a greater portion of the pressure loss to be applied to the fuel nozzle outlet for the same total pressure loss, resulting in higher acoustic stability in the combustion zone than in the prior art nozzle.
  • the turbine burner after Fig.1 has a secondary supply unit for supplying a secondary fuel or air and for discharging the fuel or air from an opening 6 into a combustion zone 10.
  • the secondary fuel may include natural gas and air.
  • the secondary feed unit has a radius Ri.
  • the secondary supply unit may also include a pilot burner 2, which is designed for a further fuel such as oil.
  • a further, arranged around the pilot burner 2 annular natural gas duct 35 may be provided for supplying natural gas Gn.
  • the natural gas can be diluted with steam or water to control the NOx levels.
  • the secondary supply unit can provide a further annular air duct 30, into which compressor air L 'flows.
  • the secondary supply unit comprises at the downstream end at least one swirl generator, a so-called axial grid 22 for generating a swirl.
  • the axial grid 22 can be arranged in the downstream end of the air duct 30 of the secondary supply unit be.
  • the natural gas Gn of the channel 35 is flowed into the air channel 30 in front of the axial grid 22.
  • the resulting air-natural gas mixture is then introduced by the axial grid 22 twisted into the combustion zone 10.
  • the burner further comprises a primary supply unit having a primary mixing tube 11 and a fuel nozzle 1 with an opening facing the combustion zone, the fuel nozzle outlet 4 for supplying a primary fuel, wherein the fuel nozzle 1 and the primary mixing tube 11 is arranged concentrically around the secondary supply unit.
  • the primary mixing tube 11 and the fuel nozzle 1 have a fluid flow connection. Through the primary mixer tube 11 and the fuel nozzle 1 of the combustion zone 10 synthesis gas is supplied.
  • annular channel 40 Arranged at least partially around the primary supply unit is an annular channel 40 which has a plurality of circumferentially arranged swirlers 45 with or without fuel nozzles. Compressor air L ", into which fuel can be injected by means of the swirlers 45, is flowed through this annular channel 40. The resulting compressor air L" fuel mixture or the air L "is likewise introduced into the combustion zone 10 in a twisted manner.
  • the fuel nozzle 1 has an annular wall 9, which is radially spaced from the Sekundärzu GmbH in the axial direction, so that a gap height h is formed by the annular wall 9 and secondary feed.
  • the fuel nozzle 1 has an inner wall 50 directed toward the secondary feed unit, wherein the inner wall 50 has annularly arranged blades 12 (FIG. Fig.2 ).
  • the blades 12 may be disposed on the outer wall of the secondary feed unit (not shown).
  • the outside wall of the secondary feed unit is understood to be the outside wall of the secondary feed unit directed toward the fuel nozzle.
  • the fuel nozzle 1 also has a fuel nozzle inlet 20 and a fuel nozzle outlet 4.
  • the pressure loss is applied to the fuel nozzle outlet 4. This has the advantage of setting higher acoustic stability in the combustion zone 10, that is, stability versus the known buzz in the combustion zone 10, than in the nozzles of the prior art burner.
  • the pressure loss can also be adjusted in this embodiment on the speed of the synthesis gas or the cross section of the fuel nozzle outlet.
  • the fuel nozzle 1 is formed downstream at least partially conical.
  • the blades 12 have a blade leading edge 51 on the upstream side and a blade trailing edge 60 opposite thereto.
  • the blade leading edge 51 has an axial distance s from the fuel nozzle inlet 20.
  • the ratio of distance s and gap height h is greater than 1 and less than 4.
  • the fuel nozzle inlet 20 is designed with a larger gap height h.
  • the maximum utilization of the acceptable pressure loss and the avoidance of parasitic pressure losses takes place at the fuel nozzle outlet 4. This results in stable combustion.
  • the fuel nozzle inlet 20 is also rounded, the rounding having a fuel nozzle inlet radius Re.
  • the rounding points away from a fuel nozzle interior.
  • the ratio of the fuel nozzle inlet radius Re and the gap height h is greater than 0.2 and less than 0.8. This results in a uniform flow acceleration up to the blade inflow edge 51, which causes a minimization of the inlet pressure losses and on the blades 12 a uniform flow profile.
  • this can also be done by a straight nozzle 1 with a straight fuel nozzle inlet 20 are caused by an angle ⁇ 75 ° (not shown).
  • the blade inflow edge 51 has the above-mentioned upstream relative axial distance of about 1 ⁇ s (distance) / h (gap height) ⁇ 4 to the fuel nozzle inlet 20.
  • the nozzle 1 is thus designed such that by reducing the gap height h at the fuel nozzle inlet 20, the axial velocity is increased before the blades 12 and a uniform acceleration of the gas takes place until it leaves the nozzle 1.
  • the gap height h at the fuel nozzle outlet 4 is between 0.1 ⁇ h (gap height) / Ra ⁇ 0.2, where Ra represents the outer fuel nozzle radius Ra, so that a Mach number in the range 0.4 ⁇ Ma ⁇ 0.8 is maintained, resulting in a better acoustic decoupling of the fuel system caused by combustion chamber pressure oscillations.
  • an increase in the mixing energy is associated with the higher Mach number. Due to the smaller gap height h than in the nozzles of the prior art at the nozzle outlet 4 also mixing paths are minimized.
  • the blades 12 additionally have a blade angle of attack ( Fig. 2 ).
  • the blade angle of attack is to be selected in which the highest possible swirl number S is set, but without causing a flow separation at the blade trailing edge 60 and the hub 70, wherein the swirl number S sets the angular momentum current to the axial momentum ratio.
  • the hub 70 that part of the secondary feed unit is referred to, which is located on the axial grid 22 and which represents the inner boundary of the fuel nozzle 1 at the nozzle outlet 4.
  • the swirl number S is in a range of greater than 1.2 and less than 1.7.
  • the ratio of the radius Ri of the secondary feed unit to the outer fuel nozzle radius Ra of the fuel nozzle 1 must be greater than 0.6 and less than 0.8 at the fuel nozzle outlet 4. Since the swirl number S depends on the ratio Ri / Ra, compliance with the ratio, that the synthesis gas flow still follows the contour of the fuel nozzle 1, without detaching itself on the hub side.
  • the fuel-air mixture which flows through the axial grid 22, also has a tangential flow direction 100 (swirl). Also in the fuel nozzle 1, a tangential flow direction 110 is impressed on the synthesis gas stream by an angle of attack of the blades 12. The blade angle can now be arranged so that the tangential flow directions 100 and 110 now have an opposite direction of rotation. For this purpose, the blades 12 and the axial grid 22 must have an opposing arrangement. This causes a significant increase in the mixing intensity due to the increased shear rates in the contact zones of the flows 100 and 110.
  • the relative velocities between the air-fuel mixture and synthesis gas is well above the relative velocities of a co-directional arrangement, which in turn significantly higher mixing of the two streams entails. This in turn has a positive effect on NOx emissions.
  • the air flowing through the annular passage 40 has a twist 120. This is preferably rectified to the swirl flow 100.
  • the fuel nozzle 1, seen in the flow direction after the blades 12 still have holes 130.
  • the air of the annular channel 40 can occur when the burner is not in the synthesis gas operation.
  • an operation of the burner without synthesis gas is possible when fuel is supplied via the pilot burner or fuel via the Ergaspassage 35.
  • no hot gas, which is present in the combustion zone 10 can flow back through the nozzle 1 during operation without synthesis gas.
  • the holes 130 may be formed in the flow direction with an inlet shell (7), which projects into the channel 40.
  • the air L "can be more selectively flowed through the holes 130 into the nozzle 1, thus the hot gas even more targeted to prevent hot gas from the combustion zone 10 flows back into the nozzle 1.
  • FIG. 2 shows a fuel nozzle 1 according to the invention in detail.
  • This nozzle 1 has an inner wall 50.
  • the blades 12 are arranged annularly over the circumference of the inner wall 50.
  • the nozzle 1 is conical over the entire area of the hub 70 (FIG. Fig. 1 ), resulting in a lower gap height h at the fuel nozzle outlet 4 ( Fig. 1 ) than is the case with the nozzles of the prior art.
  • the volume flow of the synthesis gas which must be supplied through the burner according to the invention of the combustion zone 10, can be reduced with the same NOx emissions.
  • the better acoustic stability allows for an extended operating range of the burner according to the invention in terms of load and fuel quality.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP10166431A 2010-06-18 2010-06-18 Brûleur de turbines Withdrawn EP2397764A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP10166431A EP2397764A1 (fr) 2010-06-18 2010-06-18 Brûleur de turbines
US13/699,801 US8869535B2 (en) 2010-06-18 2011-03-29 Turbine burner having premixing nozzle with a swirler
CN201180030001.5A CN102947650B (zh) 2010-06-18 2011-03-29 透平燃烧器
EP11711862.0A EP2583033B1 (fr) 2010-06-18 2011-03-29 Brûleur de turbines
PCT/EP2011/054777 WO2011157458A1 (fr) 2010-06-18 2011-03-29 Brûleur de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10166431A EP2397764A1 (fr) 2010-06-18 2010-06-18 Brûleur de turbines

Publications (1)

Publication Number Publication Date
EP2397764A1 true EP2397764A1 (fr) 2011-12-21

Family

ID=43086876

Family Applications (2)

Application Number Title Priority Date Filing Date
EP10166431A Withdrawn EP2397764A1 (fr) 2010-06-18 2010-06-18 Brûleur de turbines
EP11711862.0A Active EP2583033B1 (fr) 2010-06-18 2011-03-29 Brûleur de turbines

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP11711862.0A Active EP2583033B1 (fr) 2010-06-18 2011-03-29 Brûleur de turbines

Country Status (4)

Country Link
US (1) US8869535B2 (fr)
EP (2) EP2397764A1 (fr)
CN (1) CN102947650B (fr)
WO (1) WO2011157458A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015040228A1 (fr) * 2013-09-23 2015-03-26 Siemens Aktiengesellschaft Brûleur pour turbine à gaz et procédé de réduction des vibrations thermoacoustiques dans une turbine à gaz

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2312215A1 (fr) * 2008-10-01 2011-04-20 Siemens Aktiengesellschaft Brûleur et procédé de fonctionnement d'un brûleur
US10731861B2 (en) * 2013-11-18 2020-08-04 Raytheon Technologies Corporation Dual fuel nozzle with concentric fuel passages for a gas turbine engine
EP2993406A1 (fr) 2014-09-03 2016-03-09 Siemens Aktiengesellschaft Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz
DE102021002508A1 (de) 2021-05-12 2022-11-17 Martin GmbH für Umwelt- und Energietechnik Düse zum Einblasen von Gas in eine Verbrennungsanlage mit einem Rohr und einem Drallerzeuger, Rauchgaszug mit einer derartigen Düse und Verfahren zur Verwendung einer derartigen Düse

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999004196A1 (fr) * 1997-07-17 1999-01-28 Siemens Aktiengesellschaft Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz
DE19757617A1 (de) * 1997-12-23 1999-03-25 Siemens Ag Verbrennungssystem sowie Brenner eines Verbrennungssystems
WO2006053866A1 (fr) * 2004-11-18 2006-05-26 Siemens Aktiengesellschaft Procede pour mettre en marche un bruleur
EP1649219B1 (fr) 2003-07-25 2008-05-07 Ansaldo Energia S.P.A. Bruleur de turbine a gaz
US20090025394A1 (en) * 2005-09-30 2009-01-29 Ansaldo Energia S.P.A Method For Starting A Gas Turbine Equipped With A Gas Burner, And Axial Swirler For Said Burner

Family Cites Families (4)

* 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
DE19549143A1 (de) 1995-12-29 1997-07-03 Abb Research Ltd Gasturbinenringbrennkammer
US7685823B2 (en) 2005-10-28 2010-03-30 Power Systems Mfg., Llc Airflow distribution to a low emissions combustor
US8393891B2 (en) * 2006-09-18 2013-03-12 General Electric Company Distributed-jet combustion nozzle

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999004196A1 (fr) * 1997-07-17 1999-01-28 Siemens Aktiengesellschaft Agencement de bruleurs pour une installation de chauffe, notamment une chambre de combustion de turbine a gaz
DE19757617A1 (de) * 1997-12-23 1999-03-25 Siemens Ag Verbrennungssystem sowie Brenner eines Verbrennungssystems
EP1649219B1 (fr) 2003-07-25 2008-05-07 Ansaldo Energia S.P.A. Bruleur de turbine a gaz
WO2006053866A1 (fr) * 2004-11-18 2006-05-26 Siemens Aktiengesellschaft Procede pour mettre en marche un bruleur
US20090025394A1 (en) * 2005-09-30 2009-01-29 Ansaldo Energia S.P.A Method For Starting A Gas Turbine Equipped With A Gas Burner, And Axial Swirler For Said Burner

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015040228A1 (fr) * 2013-09-23 2015-03-26 Siemens Aktiengesellschaft Brûleur pour turbine à gaz et procédé de réduction des vibrations thermoacoustiques dans une turbine à gaz

Also Published As

Publication number Publication date
CN102947650A (zh) 2013-02-27
WO2011157458A1 (fr) 2011-12-22
CN102947650B (zh) 2014-12-17
EP2583033B1 (fr) 2014-06-25
US20130074506A1 (en) 2013-03-28
US8869535B2 (en) 2014-10-28
EP2583033A1 (fr) 2013-04-24

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