US20110027728A1 - Size scaling of a burner - Google Patents

Size scaling of a burner Download PDF

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Publication number
US20110027728A1
US20110027728A1 US12/935,923 US93592309A US2011027728A1 US 20110027728 A1 US20110027728 A1 US 20110027728A1 US 93592309 A US93592309 A US 93592309A US 2011027728 A1 US2011027728 A1 US 2011027728A1
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Prior art keywords
quarl
burner
section
fuel
flame
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Abandoned
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US12/935,923
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English (en)
Inventor
Vladimir Milosavljevic
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Siemens AG
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Siemens AG
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Publication of US20110027728A1 publication Critical patent/US20110027728A1/en
Abandoned legal-status Critical Current

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    • 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
    • F23R3/346—Feeding into different combustion zones for staged 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00016—Retrofitting in general, e.g. to respect new regulations on pollution
    • 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

Definitions

  • the present invention refers to quarls in a burner preferably for use in gas turbine engines, and more particularly to quarls in a burner adapted to stabilize engine combustion, and further to a burner that use a pilot combustor to provide combustion products to stabilize main lean premixed combustion.
  • Gas turbine engines are employed in a variety of applications including electric power generation, military and commercial aviation, pipeline transmission and marine transportation.
  • fuel and air are provided to a burner chamber where they are mixed and ignited by a flame, thereby initiating combustion.
  • the major problems associated with the combustion process in gas turbine engines, in addition to thermal efficiency and proper mixing of the fuel and the air, are associated to flame stabilization, the elimination of pulsations and noise, and the control of polluting emissions, especially nitrogen oxides (NOx), CO, UHC, smoke and particulated emission
  • flame temperature is reduced by an addition of more air than required for the combustion process itself.
  • the excess air that is not reacted must be heated during combustion, and as a result flame temperature of the combustion process is reduced (below stoichiometric point) from approximately 2300K to 1800 K and below.
  • This reduction in flame temperature is required in order to significantly reduce NOx emissions.
  • a method shown to be most successful in reducing NOx emissions is to make combustion process so lean that the temperature of the flame is reduced below the temperature at which diatomic Nitrogen and Oxygen (N2 and O2) dissociate and recombine into NO and NO2.
  • Swirl stabilized combustion flows are commonly used in industrial gas turbine engines to stabilize combustion by, as indicated above, developing reverse flow (Swirl Induced Recirculation Zone) about the centreline, whereby the reverse flow returns heat and free radicals back to the incoming un-burnt fuel and air mixture.
  • the heat and free radicals from the previously reacted fuel and air are required to initiate (pyrolyze fuel and initiate chain branching process) and sustain stable combustion of the fresh un-reacted fuel and air mixture.
  • Stable combustion in gas turbine engines requires a cyclic process of combustion producing combustion products that are transported back upstream to initiate the combustion process. A flame front is stabilised in a Shear-Layer of the Swirl Induced Recirculation Zone.
  • the amount of air required to reduce the flame temperature from 2300K to 1700-1800 K is approximately twice the amount of air required for stoichiometric combustion. This makes the overall fuel/air ratio ( ⁇ ) very close (around or below 0.5; ⁇ >0.5) or similar to a fuel/air ratio at which lean extinction of the premixed flame occurs. Under these conditions the flame can locally extinguish and re-light in a periodic manner.
  • Radiation heating of the fluid does not produce a sharp gradient; therefore, stability must come from the generation, diffusion and convection of heat into the pre-reacted zone. Diffusion only produces a sharp gradient in laminar flow and not turbulent flows, leaving only convection and energy generation to produce the sharp gradients desired for flame stabilization which is actually heat and free radial gradients. Both, heat and free radial gradients, are generated, diffused and convected by the same mechanisms through recirculating products of combustion within the Swirl Induced Recirculation Zone.
  • An object of the present invention is to present a way to scale the size of a burner.
  • a lean-rich partially premixed low emissions burner for a gas turbine combustor that provides stable ignition and combustion process at all engine load conditions.
  • This burner operates according to the principle of “supplying” heat and high concentration of free radicals from a pilot combustor exhaust to a main flame burning in a lean premixed air/fuel swirl, whereby a rapid and stable combustion of the main lean premixed flame is supported.
  • the pilot combustor supplies heat and supplements a high concentration of free radicals directly to a forward stagnation point and a shear layer of the main swirl induced recirculation zone, where the main lean premixed flow is mixed with hot gases products of combustion provided by the pilot combustor. This allows a leaner mix and lower temperatures of the main premixed air/fuel swirl combustion that otherwise would not be self-sustaining in swirl stabilized recirculating flows during the operating conditions of the burner.
  • the burner utilizes:
  • the disclosed burner provides stable ignition and combustion process at all engine load conditions.
  • Some important features related to the inventive burner are: the geometric location of the burner elements; the amount of fuel and air staged within the burner; the minimum amount of active species—radicals generated and required at different engine/burner operating conditions; fuel profile; mixing of fuel and air at different engine operating conditions; imparted level of swirl; multi (minimum double quarl) quarl arrangement.
  • a target in this design/invention is to have uniform mixing profiles at the exit of lean premixing channels.
  • Two distinct combustion zones exist within the burner covered by this disclosure, where fuel is burnt simultaneously at all times. Both combustion zones are swirl stabilized and fuel and air are premixed prior to the combustion process.
  • a main combustion process during which more than 90% of fuel is burned, is lean.
  • a bluff body is not needed in the pilot combustor as the present invention uses un un-quenched flow of radicals directed downstream from a combustion zone of the pilot combustor along a centre line of the pilot combustor, said flow of radicals being released through the full opening area of a throat of the pilot combustor at an exit of the pilot combustor.
  • the main reason why the supporting combustion process in the small pilot combustor could be lean, stoichiometric or rich and still provide stable ignition and combustion process at all engine load conditions is related to combustion efficiency.
  • the combustion process which occurs within the small combustor-pilot, has low efficiency due to the high surface area which results in flame quenching on the walls of the pilot combustor.
  • Inefficient combustion process either being lean, stoichiometric or rich, could generate a large pool of active species—radicals which is necessary to enhance stability of the main lean flame and is beneficial for a successful operation of the present burner design/invention (Note: the flame occurring in the premixed lean air/fuel mixture is herein called the lean flame).
  • Relatively large amount of fuel can be added to the small pilot combustor cooling air which corresponds to very rich equivalence ratios ( ⁇ >3).
  • Swirled cooling air and fuel and hot products of combustion from the small pilot combustor can very effectively sustain combustion of the main lean flame below, at and above LBO limits.
  • the combustion process is very stable and efficient because hot combustion products and very hot cooling air (above 750° C.), premixed with fuel, provide heat and active species (radicals) to the forward stagnation point of the main flame recirculation zone.
  • the small pilot combustor combined with very hot cooling air (above 750° C.) premixed with fuel act as a flameless burner, where reactants (oxygen & fuel) are premixed with products of combustion and a distributed flame is established at the forward stagnation point of the swirl induced recirculation zone.
  • a strong recirculation zone is required to enable transport of heat and free radicals from the previously combusted fuel and air, back upstream towards the flame front.
  • a well established and a strong recirculation zone is required to provide a shear layer region where turbulent flame speed can “match” or be proportional to the local fuel/air mixture, and a stable flame can establish.
  • This flame front established in the shear layer of the main recirculation zone has to be steady and no periodic movements or procession of the flame front should occur.
  • the imparted swirl number can be high, but should not be higher then 0.8, because at and above this swirl number more then 80% of the total amount of the flow will be recirculated back.
  • a further increase in swirl number will not contribute more to the increase in the amount of the recirculated mass of the combustion products, and the flame in the shear layer of the recirculation zone will be subjected to high turbulence and strain which can result in quenching and partial extinction and reignition of the flame.
  • Any type of the swirl generator, radial, axial and axial-radial can be used in the burner, covered by this disclosure. In this disclosure a radial swirler configuration is shown.
  • the burner utilizes aerodynamics stabilization of the flame and confines the flame stabilization zone—the recirculation zone—in the multiple quarl arrangement.
  • the multiple quarl arrangement is an important feature of the design of the provided burner for the following reasons.
  • the quarl (or also called diffuser):
  • FIG. 1 is a simplified cross section schematically showing the burner according to the aspects of the invention enclosed in a housing without any details showing how the burner is configured inside said housing.
  • FIG. 2 is a cross section through the burner schematically showing a section above a symmetry axis, whereby a rotation around the symmetry axis forms a rotational body displaying a layout of the burner.
  • FIG. 3 shows a diagram of stability limits of the flame as a function of the swirl number, imparted level of swirl and equivalence ratio.
  • FIG. 4 a shows a diagram of combustor near field aerodynamics.
  • FIG. 4 b shows a diagram of combustor near field aerodynamics.
  • FIG. 5 shows a diagram of turbulence intensity
  • FIG. 6 shows a diagram of relaxation time as a function of combustion pressure.
  • FIG. 7 illustrates in a perspective view fuel tubes 15 at the inlet of swirler 3 .
  • FIG. 1 the burner is depicted with the burner 1 having a housing 2 enclosing the burner components.
  • FIG. 2 shows for the sake of clarity a cross sectional view of the burner above a rotational symmetry axis.
  • the main parts of the burner are the radial swirler 3 , the multi quarl 4 a , 4 b , 4 c and the pilot combustor 5 .
  • the burner 1 operates according to the principle of “supplying” heat and high concentration of free radicals from the a pilot combustor 5 exhaust 6 to a main flame 7 burning in a lean premixed air/fuel swirl emerging from a first exit 8 of a first lean premixing channel 10 and from a second exit 9 of a second lean premixing channel 11 , whereby a rapid and stable combustion of the main lean premixed flame 7 is supported.
  • Said first lean premixing channel 10 is formed by and between the walls 4 a and 4 b of the multi quarl.
  • the second lean premixing channel 11 is formed by and between the walls 4 b and 4 c of the multi quarl.
  • the outermost rotational symmetric wall 4 c of the multi quarl is provided with an extension 4 c 1 to provide for the optimal length of the multi quarl arrangement.
  • the first 10 and second 11 lean premixing channels are provided with swirler wings fowling the swirler 3 to impart rotation to the air/fuel mixture passing through the channels.
  • Air 12 is provided to the first 10 and second 11 channels at the inlet 13 of said first and second channels.
  • the swirler 3 is located close to the inlet 13 of the first and second channels.
  • fuel 14 is introduced to the air/fuel swirl through a tube 15 provided with small diffusor holes 15 b located at the air 12 inlet 13 between the swirler 3 wings, whereby the fuel is distributed into the air flow through said holes as a spray and effectively mixed with the air flow. Additional fuel can be added through a second tube 16 emerging into the first channel 10 .
  • the flame 7 is generated as a conical rotational symmetric shear layer 18 around a main recirculation zone 20 (below sometimes abbreviated RZ).
  • the flame 7 is enclosed inside the extension 4 c 1 of the outermost quarl, in this example quarl 4 c.
  • the pilot combustor 5 supplies heat and supplements a high concentration of free radicals directly to a forward stagnation point P and the shear layer 18 of the main swirl induced recirculation zone 20 , where the main lean premixed flow is mixed with hot gases products of combustion provided by the pilot combustor 5 .
  • the pilot combustor 5 is provided with walls 21 enclosing a combustion room for a pilot combustion zone 22 . Air is supplied to the combustion room through fuel channel 23 and air channel 24 .
  • a distributor plate 25 provided with holes over the surface of the plate. Said distributor plate 25 is separated a certain distance from said walls 21 forming a cooling space layer 25 a . Cooling air 26 is taken in through a cooling inlet 27 and meets the outside of said distributor plate 25 , whereupon the cooling air 26 is distributed across the walls 21 of the pilot combustor to effectively cool said walls 21 .
  • the cooling air 26 is after said cooling let out through a second swirler 28 arranged around a pilot quarl 29 of the pilot combustor 5 .
  • Further fuel can be added to the combustion in the main lean flame 7 by supplying fuel in a duct 30 arranged around and outside the cooling space layer 25 a . Said further fuel is then let out and into the second swirler 28 , where the now hot cooling air 26 and the fuel added through duct 30 is effectively premixed.
  • a relatively large amount of fuel can be added to the small pilot combustor 5 cooling air which corresponds to very rich equivalence ratios ( ⁇ >3).
  • Swirled cooling air and fuel and hot products of combustion from the small pilot combustor can very effectively sustain combustion of the main lean flame 7 below, at and above LBO limits.
  • the combustion process is very stable and efficient because hot combustion products and very hot cooling air (above 750° C.), premixed with fuel, provide heat and active species (radicals) to the forward stagnation point P of the main flame recirculation zone 20 .
  • the small pilot combustor 5 combined with very hot cooling air (above 750° C.) premixed with fuel act as a flameless burner, where reactants (oxygen & fuel) are premixed with products of combustion and a distributed flame is established at the forward stagnation point P of the swirl induced recirculation zone 20 .
  • the imparted level of swirl and the swirl number (equation 1) is above the critical one (not lower then 0.6 and not higher then 0.8, see also FIG. 3 ) at which vortex breakdown—recirculation zone 20 —will form and will be firmly positioned within the multi quarl 4 a , 4 b , 4 c arrangement.
  • the forward stagnation point P should be located within the quarl 4 a , 4 b , 4 c and at the exit 6 of the pilot combustor 5 .
  • the swirling flow will extend to the exit of the combustor, which can result in an overheating of subsequent guide vanes of a turbine.
  • the imparted level of swirl (the ratio between tangential and axial momentum) has to be higher then the critical one (0.4-0.6), so that a stable central recirculation zone 20 can form.
  • the critical swirl number, SN is also a function of the burner geometry, which is the reason for why it varies between 0.4 and 0.6. If the imparted swirl number is ⁇ 0.4 or in the range of 0.4 to 0.6, the main recirculation zone 20 , may not form at all or may form and extinguish periodically at low frequencies (below 150 Hz) and the resulting aerodynamics could be very unstable which will result in a transient combustion process.
  • flame stabilization can occur if:
  • Recirculating products which are: source of heat and active species (symbolized by means of arrows 1 a and 1 b ), located within the recirculation zone 20 , have to be stationary in space and time downstream from the mixing section of the burner 1 to enable pyrolysis of the incoming mixture of fuel and air. If a steady combustion process is not prevailing, thermo-acoustics instabilities will occur.
  • Swirl stabilized flames are up to five times shorter and have significantly leaner blow-off limits then jet flames.
  • a premixed or turbulent diffusion combustion swirl provides an effective way of premixing fuel and air.
  • the entrainiment of the fuel/air mixture into the shear layer of the recirculation zone 20 is proportional to the strength of the recirculation zone, the swirl number and the characteristics recirculation zone velocity URZ.
  • the characteristics recirculation zone velocity, URZ can be expressed as:
  • URZ UF/Af ( MR,dF/A,cent/dF/A,SN ),
  • RZ strength ( MR )exp ⁇ 1 ⁇ 2( dF/A/dF/A,cent )( URZ/UF/A )( b/dF/A ),
  • MR should be ⁇ 1.
  • recirculation zones size/length is “fixed” and proportional to 2-2.5 dF/A.
  • the process is initiated and stabilized by means of transporting heat and free radicals 31 from the previously combusted fuel and air, back upstream towards the flame front 7 .
  • the combustion process is very lean, as is the case in lean-partially premixed combustion systems, and as a result the combustion temperature is low, the equilibrium levels of free radicals is also very low.
  • the free radicals produced by the combustion process quickly relax, see FIG. 6 , to the equilibrium level that corresponds to the temperature of the combustion products. This is due to the fact that the rate of this relaxation of the free radicals to equilibrium increases exponentially with increase in pressure, while on the other hand the equilibrium level of free radicals decreases exponentially with temperature decrease.
  • the relaxation time of the free radicals can be short compared to the “transport” time required for the free radicals (symbolized by arrows 31 ) to be convected downstream, from the point where they were produced in the shear layer 18 of the main recirculation zone 20 , back upstream, towards the flame front 7 and the forward stagnation point P of the main recirculation zone 20 .
  • This invention utilizes high non-equilibrium levels of free radicals 32 to stabilize the main lean combustion 7 .
  • the scale of the small pilot combustor 5 is kept small and most of the combustion of fuel occurs in the lean premixed main combustor (at 7 and 18 ), and not in the small pilot combustor 5 .
  • the small pilot combustor 5 can be kept small, because the free radicals 32 are released near the forward stagnation point P of the main recirculation zone 20 . This is generally the most efficient location to supply additional heat and free radicals to swirl stabilized combustion ( 7 ).
  • the time scale between quench and utilization of free radicals 32 is very short not allowing free radicals 32 to relax to low equilibrium levels.
  • the forward stagnation point P of the main-lean re-circulating zone 20 is maintained and aerodynamically stabilized in the quarl ( 4 a ), at the exit 6 of the small pilot combustor 5 .
  • the exit of the small pilot combustor 5 is positioned on the centerline and at the small pilot combustor 5 throat 33 .
  • free radicals 32 are mixed with the products of the lean combustion 31 , highly preheated mixture of fuel and air, from duct 30 and space 25 a , and subsequently with premixed fuel 14 and air 12 in the shear layer 18 of the lean main recirculation zone 20 .
  • the burner utilizes aerodynamics stabilization of the flame and confines the flame stabilization zone—recirculation zone ( 5 ), in the multiple quarl arrangement ( 4 a , 4 b and 4 c ).
  • the multiple quarl (the term multiple quarl is herein sometimes used for multiple quarl sections defining the completed quarl of the burner) arrangement is an important feature of the disclosed burner design for the reasons listed below.
  • the quarl (or sometimes called the diffuser):
  • the main recirculation zone 20 is anchored without a need to anchore the flame to a solid surface/bluff body and in that way a high thermal loading and issues related to the burner mechanical integrity are avoided,
  • quadrature half angle ⁇ and length L is important to control the size and shape of the recirculation zone 20 in conjunction with the swirl number.
  • the length of the recirculation zone 20 is roughly proportional to 2 to 2.5 of the quarl length L,
  • D is quarl throat diameter.
  • the minimum length of the quarl should not be smaller then 0.5 and not longer then 2 (Ref1: The influence of Burner Geometry and Flow Rates on the Stability and Symmetry of Swirl-Stabilized Nonpremixed Flames; V. Milsavljevic et al; Combustion and Flame 80, pages 196-208, 1990),
  • optimal quarl half angle ⁇ (Ref1) should not be smaller then 20 and larger then 25 degrees
  • the quarl (or diffuser) and the imparted swirl provides a possibility of a simple scaling of the disclosed burner geometry for different burner powers.
  • the channel 11 should be removed and the shell forming quarl section 4 c should thus substitute the shell previously forming quarl section 4 b , which is taken away; the geometry of the quarl section 4 c should be the same as the geometry of the previously existing quarl section 4 b,
  • Quarl section 4 c should be designed in the same as quarl section 4 b (formed as a thin splitter plate),
  • a new third channel (herein fictively called 11 b and not disclosed) should be arranged outside and surrounding the second channel 11 and a new quarl section 4 d (only shown in the schematic quarl drawing of FIG. 8 ) outside and surrounding the second channel 11 , thus forming an outer wall of the third channel; the shape of the new quad section 4 d should be of a shape similar to the shape of former outmost quarl section 4 c.
  • Burner operation and fuel staging within the burner should stay the same or similar.
  • the igniter 34 As in prior art burners, is placed in the outer recirculation zone, which is illustrated in FIG. 4 b , the fuel/air mixture entering this region must often be made rich in order to make the flame temperature sufficiently hot to sustain stable combustion in this region. The flame then often cannot be propagated to the main recirculation until the main premixed fuel and airflow becomes sufficiently rich, hot and has a sufficient pool of free radicals, which occurs at higher fuel flow rates. When the flame cannot propagate from the outer recirculation zone to the inner main recirculation zone shortly after ignition, it must propagate at higher pressure after the engine speed begins to increase.
  • the present invention also allows for the ignition of the main combustion 7 to occur at the forward stagnation point P of the main recirculation zone 20 .
  • Most gas turbine engines must use an outer recirculation zone, see FIG. 4 b , as the location where the spark, or torch igniter, ignites the engine. Ignition can only occur if stable combustion can also occur; otherwise the flame will just blow out immediately after ignition.
  • the inner or main recirculation zone 22 is generally more successful at stabilizing the flame, because the recirculated gas 31 is transported back and the heat from the combustion products of the recirculated gas 31 is focused to a small region at the forward stagnation point P of the main recirculation zone 20 .
  • the combustion—flame front 7 also expands outwards in a conical shape from this forward stagnation point P, as illustrated in FIG. 2 .
  • This conical expansion downstream allows the heat and free radicals 32 generated upstream to support the combustion downstream allowing the flame front 7 to widen as it moves downstream.
  • the quarl ( 4 a , 4 b , 4 c ), illustrated in FIG. 2 compared to swirl stabilized combustion without the quarl, shows how the quarl shapes the flame to be more conical and less hemispheric in nature.
  • a more conical flame front allows for a point source of heat to initiate combustion of the whole flow field effectively.
  • the combustion process within the burner 1 is staged.
  • lean flame 35 is initiated in the small pilot combustor 5 by adding fuel 23 mixed with air 24 and igniting the mixture utilizing ignitor 34 .
  • ignition equivalence ratio of the flame 35 in the small pilot combustor 5 is adjusted at either lean (below equivalence ratio 1, and at approximately equivalence ratio of 0.8) or rich conditions (above equivalence ratio 1, and at approximately equivalence ratio between 1.4 and 1.6).
  • lean lower equivalence ratio 1, and at approximately equivalence ratio of 0.8
  • rich conditions above equivalence ratio 1, and at approximately equivalence ratio between 1.4 and 1.6.
  • a second-low load stage fuel is added through duct 30 to the cooling air 27 and imparted a swirling motion in swirler 28 .
  • combustion of the main lean flame 7 below, at and above LBO limits, is very effectively sustained.
  • the amount of the fuel which can be added to the hot cooling air can correspond to equivalence ratios>3.
  • a third part and full load stage fuel 15 a is gradually added to the air 12 , which is the main air flow to the main flame 7 .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
US12/935,923 2008-04-01 2009-03-26 Size scaling of a burner Abandoned US20110027728A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP08006666.5 2008-04-01
EP08006666A EP2107311A1 (de) 2008-04-01 2008-04-01 Größenskalierung eines Brenners
PCT/EP2009/053555 WO2009121776A1 (en) 2008-04-01 2009-03-26 Size scaling of a burner

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EP (2) EP2107311A1 (de)
CN (1) CN101981379B (de)
ES (1) ES2417158T3 (de)
RU (1) RU2455570C1 (de)
WO (1) WO2009121776A1 (de)

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US8794217B1 (en) * 2013-02-07 2014-08-05 Thrival Tech, LLC Coherent-structure fuel treatment systems and methods
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US20230288067A1 (en) * 2020-08-25 2023-09-14 Siemens Energy Global GmbH & Co. KG Combustor for a gas turbine

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US9366443B2 (en) * 2013-01-11 2016-06-14 Siemens Energy, Inc. Lean-rich axial stage combustion in a can-annular gas turbine engine
JP6086860B2 (ja) * 2013-11-29 2017-03-01 三菱日立パワーシステムズ株式会社 ノズル、燃焼器、及びガスタービン

Citations (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2787120A (en) * 1950-08-05 1957-04-02 Leduc Rene Plural annular coaxial combustion chambers
US3299632A (en) * 1964-05-08 1967-01-24 Rolls Royce Combustion chamber for a gas turbine engine
US3866413A (en) * 1973-01-22 1975-02-18 Parker Hannifin Corp Air blast fuel atomizer
US3937011A (en) * 1972-11-13 1976-02-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Fuel injector for atomizing and vaporizing fuel
US4062182A (en) * 1974-12-21 1977-12-13 Mtu Motoren-Und Turbinen-Union Gmbh Combustion chamber for gas turbine engines
US4204402A (en) * 1976-05-07 1980-05-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduction of nitric oxide emissions from a combustor
US4569295A (en) * 1983-01-18 1986-02-11 Stubinen Utveckling Ab Process and a means for burning solid fuels, preferably coal, turf or the like, in pulverized form
US4701124A (en) * 1985-03-04 1987-10-20 Kraftwerk Union Aktiengesellschaft Combustion chamber apparatus for combustion installations, especially for combustion chambers of gas turbine installations, and a method of operating the same
US4845940A (en) * 1981-02-27 1989-07-11 Westinghouse Electric Corp. Low NOx rich-lean combustor especially useful in gas turbines
US4955191A (en) * 1987-10-27 1990-09-11 Kabushiki Kaisha Toshiba Combustor for gas turbine
US5040371A (en) * 1988-12-12 1991-08-20 Sundstrand Corporation Fuel injectors for use with combustors
US5054280A (en) * 1988-08-08 1991-10-08 Hitachi, Ltd. Gas turbine combustor and method of running the same
US5069029A (en) * 1987-03-05 1991-12-03 Hitachi, Ltd. Gas turbine combustor and combustion method therefor
US5081844A (en) * 1989-03-15 1992-01-21 Asea Brown Boveri Ltd. Combustion chamber of a gas turbine
US5094082A (en) * 1989-12-22 1992-03-10 Sundstrand Corporation Stored energy combustor
US5131334A (en) * 1991-10-31 1992-07-21 Monro Richard J Flame stabilizer for solid fuel burner
US5237812A (en) * 1992-10-07 1993-08-24 Westinghouse Electric Corp. Auto-ignition system for premixed gas turbine combustors
US5240410A (en) * 1991-12-30 1993-08-31 Industrial Technology Research Institute Dual fuel low nox burner
US5284438A (en) * 1992-01-07 1994-02-08 Koch Engineering Company, Inc. Multiple purpose burner process and apparatus
US5319935A (en) * 1990-10-23 1994-06-14 Rolls-Royce Plc Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection
US5321948A (en) * 1991-09-27 1994-06-21 General Electric Company Fuel staged premixed dry low NOx combustor
US5323614A (en) * 1992-01-13 1994-06-28 Hitachi, Ltd. Combustor for gas turbine
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
US5407347A (en) * 1993-07-16 1995-04-18 Radian Corporation Apparatus and method for reducing NOx, CO and hydrocarbon emissions when burning gaseous fuels
US5411394A (en) * 1990-10-05 1995-05-02 Massachusetts Institute Of Technology Combustion system for reduction of nitrogen oxides
US5477685A (en) * 1993-11-12 1995-12-26 The Regents Of The University Of California Lean burn injector for gas turbine combustor
US5628192A (en) * 1993-12-16 1997-05-13 Rolls-Royce, Plc Gas turbine engine combustion chamber
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
US5802854A (en) * 1994-02-24 1998-09-08 Kabushiki Kaisha Toshiba Gas turbine multi-stage combustion system
US6109038A (en) * 1998-01-21 2000-08-29 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel assembly
US6201029B1 (en) * 1996-02-13 2001-03-13 Marathon Oil Company Staged combustion of a low heating value fuel gas for driving a gas turbine
US6209325B1 (en) * 1996-03-29 2001-04-03 European Gas Turbines Limited Combustor for gas- or liquid-fueled turbine
US6272840B1 (en) * 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
US6354072B1 (en) * 1999-12-10 2002-03-12 General Electric Company Methods and apparatus for decreasing combustor emissions
US6488496B1 (en) * 2001-09-06 2002-12-03 Hauck Manufacturing Co. Compact combination burner with adjustable spin section
US6684641B2 (en) * 1999-12-15 2004-02-03 Osaka Gas Co., Ltd. Fluid distributor, burner device, gas turbine engine, and cogeneration system
US6769903B2 (en) * 2000-06-15 2004-08-03 Alstom Technology Ltd Method for operating a burner and burner with stepped premix gas injection
US20040219466A1 (en) * 2003-05-02 2004-11-04 Marino John A. Aggregate dryer burner with compressed air oil atomizer
US6820411B2 (en) * 2002-09-13 2004-11-23 The Boeing Company Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion
US20040255589A1 (en) * 2003-06-19 2004-12-23 Shouhei Yoshida Gas turbine combustor and fuel supply method for same
US20050106520A1 (en) * 2003-09-05 2005-05-19 Michael Cornwell Device for stabilizing combustion in gas turbine engines
US20070113555A1 (en) * 2004-08-27 2007-05-24 Richard Carroni Mixer Assembly
US20080083224A1 (en) * 2006-10-05 2008-04-10 Balachandar Varatharajan Method and apparatus for reducing gas turbine engine emissions
US7621131B2 (en) * 2003-06-06 2009-11-24 Rolls-Royce Deutschland Ltd & Co. Kg Burner for a gas-turbine combustion chamber
US8033112B2 (en) * 2008-04-01 2011-10-11 Siemens Aktiengesellschaft Swirler with gas injectors

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1150640A (fr) * 1956-05-18 1958-01-16 Perfectionnements aux chambres de combustion notamment pour aéronefs
JP3673009B2 (ja) * 1996-03-28 2005-07-20 株式会社東芝 ガスタービン燃焼器
US5983642A (en) * 1997-10-13 1999-11-16 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel tube with concentric members and flow regulating
UA68446C2 (en) * 2002-02-18 2004-08-16 Res And Production Complex Of Combustion chamber of gas turbine of power unit
EP1659339A1 (de) * 2004-11-18 2006-05-24 Siemens Aktiengesellschaft Verfahren zum Anfahren eines Brenners

Patent Citations (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2787120A (en) * 1950-08-05 1957-04-02 Leduc Rene Plural annular coaxial combustion chambers
US3299632A (en) * 1964-05-08 1967-01-24 Rolls Royce Combustion chamber for a gas turbine engine
US3937011A (en) * 1972-11-13 1976-02-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Fuel injector for atomizing and vaporizing fuel
US3866413A (en) * 1973-01-22 1975-02-18 Parker Hannifin Corp Air blast fuel atomizer
US4062182A (en) * 1974-12-21 1977-12-13 Mtu Motoren-Und Turbinen-Union Gmbh Combustion chamber for gas turbine engines
US4204402A (en) * 1976-05-07 1980-05-27 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Reduction of nitric oxide emissions from a combustor
US4845940A (en) * 1981-02-27 1989-07-11 Westinghouse Electric Corp. Low NOx rich-lean combustor especially useful in gas turbines
US4569295A (en) * 1983-01-18 1986-02-11 Stubinen Utveckling Ab Process and a means for burning solid fuels, preferably coal, turf or the like, in pulverized form
US4701124A (en) * 1985-03-04 1987-10-20 Kraftwerk Union Aktiengesellschaft Combustion chamber apparatus for combustion installations, especially for combustion chambers of gas turbine installations, and a method of operating the same
US5069029A (en) * 1987-03-05 1991-12-03 Hitachi, Ltd. Gas turbine combustor and combustion method therefor
US4955191A (en) * 1987-10-27 1990-09-11 Kabushiki Kaisha Toshiba Combustor for gas turbine
US5054280A (en) * 1988-08-08 1991-10-08 Hitachi, Ltd. Gas turbine combustor and method of running the same
US5040371A (en) * 1988-12-12 1991-08-20 Sundstrand Corporation Fuel injectors for use with combustors
US5081844A (en) * 1989-03-15 1992-01-21 Asea Brown Boveri Ltd. Combustion chamber of a gas turbine
US5094082A (en) * 1989-12-22 1992-03-10 Sundstrand Corporation Stored energy combustor
US5411394A (en) * 1990-10-05 1995-05-02 Massachusetts Institute Of Technology Combustion system for reduction of nitrogen oxides
US5319935A (en) * 1990-10-23 1994-06-14 Rolls-Royce Plc Staged gas turbine combustion chamber with counter swirling arrays of radial vanes having interjacent fuel injection
US5321948A (en) * 1991-09-27 1994-06-21 General Electric Company Fuel staged premixed dry low NOx combustor
US5131334A (en) * 1991-10-31 1992-07-21 Monro Richard J Flame stabilizer for solid fuel burner
US5240410A (en) * 1991-12-30 1993-08-31 Industrial Technology Research Institute Dual fuel low nox burner
US5284438A (en) * 1992-01-07 1994-02-08 Koch Engineering Company, Inc. Multiple purpose burner process and apparatus
US5323614A (en) * 1992-01-13 1994-06-28 Hitachi, Ltd. Combustor for gas turbine
US5237812A (en) * 1992-10-07 1993-08-24 Westinghouse Electric Corp. Auto-ignition system for premixed gas turbine combustors
US5407347A (en) * 1993-07-16 1995-04-18 Radian Corporation Apparatus and method for reducing NOx, CO and hydrocarbon emissions when burning gaseous fuels
US5394688A (en) * 1993-10-27 1995-03-07 Westinghouse Electric Corporation Gas turbine combustor swirl vane arrangement
US5477685A (en) * 1993-11-12 1995-12-26 The Regents Of The University Of California Lean burn injector for gas turbine combustor
US5628192A (en) * 1993-12-16 1997-05-13 Rolls-Royce, Plc Gas turbine engine combustion chamber
US5802854A (en) * 1994-02-24 1998-09-08 Kabushiki Kaisha Toshiba Gas turbine multi-stage combustion system
US5647215A (en) * 1995-11-07 1997-07-15 Westinghouse Electric Corporation Gas turbine combustor with turbulence enhanced mixing fuel injectors
US6201029B1 (en) * 1996-02-13 2001-03-13 Marathon Oil Company Staged combustion of a low heating value fuel gas for driving a gas turbine
US6209325B1 (en) * 1996-03-29 2001-04-03 European Gas Turbines Limited Combustor for gas- or liquid-fueled turbine
US6109038A (en) * 1998-01-21 2000-08-29 Siemens Westinghouse Power Corporation Combustor with two stage primary fuel assembly
US6354072B1 (en) * 1999-12-10 2002-03-12 General Electric Company Methods and apparatus for decreasing combustor emissions
US6684641B2 (en) * 1999-12-15 2004-02-03 Osaka Gas Co., Ltd. Fluid distributor, burner device, gas turbine engine, and cogeneration system
US6951097B2 (en) * 1999-12-15 2005-10-04 Osaka Gas Co., Ltd. Fluid distributor, burner apparatus, gas turbine engine and co-generation system
US6272840B1 (en) * 2000-01-13 2001-08-14 Cfd Research Corporation Piloted airblast lean direct fuel injector
US6769903B2 (en) * 2000-06-15 2004-08-03 Alstom Technology Ltd Method for operating a burner and burner with stepped premix gas injection
US6488496B1 (en) * 2001-09-06 2002-12-03 Hauck Manufacturing Co. Compact combination burner with adjustable spin section
US6820411B2 (en) * 2002-09-13 2004-11-23 The Boeing Company Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion
US20040219466A1 (en) * 2003-05-02 2004-11-04 Marino John A. Aggregate dryer burner with compressed air oil atomizer
US7621131B2 (en) * 2003-06-06 2009-11-24 Rolls-Royce Deutschland Ltd & Co. Kg Burner for a gas-turbine combustion chamber
US20040255589A1 (en) * 2003-06-19 2004-12-23 Shouhei Yoshida Gas turbine combustor and fuel supply method for same
US20050106520A1 (en) * 2003-09-05 2005-05-19 Michael Cornwell Device for stabilizing combustion in gas turbine engines
US20070113555A1 (en) * 2004-08-27 2007-05-24 Richard Carroni Mixer Assembly
US20080083224A1 (en) * 2006-10-05 2008-04-10 Balachandar Varatharajan Method and apparatus for reducing gas turbine engine emissions
US8033112B2 (en) * 2008-04-01 2011-10-11 Siemens Aktiengesellschaft Swirler with gas injectors

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20122154A1 (it) * 2012-12-17 2014-06-18 Ansaldo Energia Spa Gruppo bruciatore, camera di combustione comprendente detto gruppo bruciatore e metodo per alimentare detto gruppo bruciatore
WO2014097153A1 (en) * 2012-12-17 2014-06-26 Ansaldo Energia S.P.A. Burner assembly, combustion chamber comprising said burner assembly and method for supplying fuel to said burner assembly
US8794217B1 (en) * 2013-02-07 2014-08-05 Thrival Tech, LLC Coherent-structure fuel treatment systems and methods
US9145803B2 (en) 2013-02-07 2015-09-29 Thrival Tech, LLC Coherent-structure fuel treatment systems and methods
US9441581B2 (en) 2013-02-07 2016-09-13 Thrivaltech, Llc Coherent-structure fuel treatment systems and methods
US20150159877A1 (en) * 2013-12-06 2015-06-11 General Electric Company Late lean injection manifold mixing system
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles
US20230288067A1 (en) * 2020-08-25 2023-09-14 Siemens Energy Global GmbH & Co. KG Combustor for a gas turbine

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ES2417158T3 (es) 2013-08-06
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EP2263044B1 (de) 2013-05-15
EP2263044A1 (de) 2010-12-22
EP2107311A1 (de) 2009-10-07
CN101981379B (zh) 2012-06-20
RU2455570C1 (ru) 2012-07-10
WO2009121776A1 (en) 2009-10-08

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