EP0619456A1 - Système d'alimentation en carburant pour chambre de combustion - Google Patents

Système d'alimentation en carburant pour chambre de combustion Download PDF

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Publication number
EP0619456A1
EP0619456A1 EP94103408A EP94103408A EP0619456A1 EP 0619456 A1 EP0619456 A1 EP 0619456A1 EP 94103408 A EP94103408 A EP 94103408A EP 94103408 A EP94103408 A EP 94103408A EP 0619456 A1 EP0619456 A1 EP 0619456A1
Authority
EP
European Patent Office
Prior art keywords
channel
flow
supply system
fuel supply
vortex
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
EP94103408A
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German (de)
English (en)
Other versions
EP0619456B1 (fr
Inventor
Yau-Pin Dr. Chyou
Adnan Eroglu
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.)
General Electric Switzerland GmbH
ABB Asea Brown Boveri Ltd
Original Assignee
ABB Management 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 ABB Management AG filed Critical ABB Management AG
Publication of EP0619456A1 publication Critical patent/EP0619456A1/fr
Application granted granted Critical
Publication of EP0619456B1 publication Critical patent/EP0619456B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C7/00—Combustion apparatus characterised by arrangements for air supply
    • F23C7/002—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B01—PHYSICAL OR CHEMICAL PROCESSES OR APPARATUS IN GENERAL
    • B01F—MIXING, e.g. DISSOLVING, EMULSIFYING OR DISPERSING
    • B01F25/00—Flow mixers; Mixers for falling materials, e.g. solid particles
    • B01F25/30—Injector mixers
    • B01F25/31—Injector mixers in conduits or tubes through which the main component flows
    • B01F25/314—Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced at the circumference of the conduit
    • B01F25/3141—Injector mixers in conduits or tubes through which the main component flows wherein additional components are introduced at the circumference of the conduit with additional mixing means other than injector mixers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/0015—Whirl chambers, e.g. vortex valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details
    • F23D14/62—Mixing devices; Mixing tubes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2240/00—Components
    • F05B2240/10—Stators
    • F05B2240/12—Fluid guiding means, e.g. vanes
    • F05B2240/122—Vortex generators, turbulators, or the like, for mixing

Definitions

  • the invention relates to a fuel supply system for a combustion chamber with premix combustion, in which a gaseous and / or liquid fuel is injected as a secondary flow into a gaseous, channeled main flow, the secondary flow having a substantially smaller mass flow than the main flow, and the flow through which the premix channel has curved walls having,
  • the mixing of fuel into a combustion air flow flowing in a premixing duct generally takes place by means of radial injection of the fuel into the duct by means of cross-jet mixers.
  • the momentum of the fuel is so low that an almost complete mixing takes place only after a distance of approximately 100 channel heights.
  • Venturi mixers are also used.
  • the injection of the fuel via grid arrangements is also known.
  • spraying in front of special swirl bodies is also used.
  • the devices operating on the basis of transverse jets or stratified flows either have very long mixing distances result or require high injection pulses.
  • premixing under high pressure and substoichiometric mixing ratios there is a risk of the flame flashing back or even of self-ignition of the mixture.
  • Flow separations and dead water zones in the premixing tube, thick boundary layers on the walls or possibly extreme speed profiles over the cross-section through which the flow is flowing can be the cause of auto-ignition in the tube or form paths through which the flame can strike back from the downstream combustion zone into the premixing tube.
  • the geometry of the premixing section must therefore be given the greatest attention.
  • the invention is therefore based on the object of providing, in a combustion chamber with premix combustion, a measure with which an intimate mixing of combustion air and fuel is achieved within a very short distance with a uniform speed distribution in the mixing zone.
  • the measure should also be suitable for retrofitting existing premix combustion chambers.
  • the new static mixer which is represented by the 3-dimensional vortex generators, it is possible to achieve extremely short mixing distances in the combustion chamber with a low pressure drop.
  • the generation of longitudinal vortices without a recirculation area results in a rough mixing of the two streams after a full vortex revolution, while fine mixing due to turbulent flow and molecular diffusion processes occurs after a distance that corresponds to a few channel heights.
  • the advantage of vortex generators can be seen in their particular simplicity in every respect.
  • the element consisting of three walls with flow around it is completely problem-free.
  • the roof surface can be joined with the two side surfaces in a variety of ways.
  • the element can also be fixed to flat or curved channel walls in the case of weldable materials by simple weld seams. From a fluidic point of view, the element has a very low pressure drop when flowing around and it creates vortices without a dead water area.
  • the element due to its generally hollow interior, the element can be cooled in a variety of ways and with various means.
  • the two side surfaces enclosing the arrow angle ⁇ form an at least approximately sharp connecting edge with one another, which together with the longitudinal edges of the roof surface forms a tip, the flow cross-section is hardly impaired by blocking.
  • the sharp connecting edge is the exit-side edge of the vortex generator and it runs perpendicular to the channel wall with which the side surfaces are flush, then the non-formation of a wake area is advantageous.
  • a vortex generator generated two identical opposite vortices.
  • a vortex generator essentially consists of three free-flowing triangular surfaces. These are a roof surface 10 and two side surfaces 11 and 13. In their longitudinal extent, these surfaces run at certain angles in the direction of flow.
  • the side walls of the vortex generator which consist of right-angled triangles, are fixed with their long sides on a channel wall 21, preferably gas-tight. They are oriented so that they form a joint on their narrow sides, including an arrow angle ⁇ .
  • the joint is designed as a sharp connecting edge 16 and is vertical to that channel wall 21 with which the side surfaces are flush.
  • the two side surfaces 11, 13 enclosing the arrow angle ⁇ are symmetrical in shape, size and orientation in FIG. 1 and are arranged on both sides of an axis of symmetry 17. This axis of symmetry 17 is rectified like the channel axis.
  • the roof surface 10 lies with a very narrow edge 15 running transversely to the flow through the channel on the same channel wall 21 as the side walls 11, 13. Its longitudinal edges 12, 14 are flush with the longitudinal edges of the side surfaces projecting into the flow channel.
  • the roof surface extends at an angle of inclination ⁇ to the channel wall 21. Its longitudinal edges 12, 14 form a tip 18 together with the connecting edge 16.
  • the vortex generator can also be provided with a bottom surface with which it is fastened in a suitable manner to the channel wall 21.
  • a floor area is not related to the mode of operation of the element.
  • the connecting edge 16 of the two side surfaces 11, 13 forms the downstream edge of the vortex generator.
  • the edge 15 of the roof surface 10 which runs transversely to the flow through the channel is thus the edge which is first acted upon by the channel flow.
  • the vortex generator works as follows: When flowing around edges 12 and 14, the main flow is converted into a pair of opposing vortices. Their vortex axes lie in the axis of the main flow. The number of swirls and the location of the vortex breakdown (if the latter is desired at all) are determined by appropriate selection of the angle of attack ⁇ and the arrow angle ⁇ . With increasing angles, the vortex strength or the swirl number becomes increased and the location of the vortex burst moves upstream into the area of the vortex generator itself. Depending on the application, these two angles ⁇ and ⁇ are predetermined by the structural conditions and by the process itself. Then only the length L of the element and the height h of the connecting edge 16 need to be adjusted (FIG. 4).
  • FIG. 2 shows a so-called half "vortex generator" based on a vortex generator according to FIG. 1, in which only one of the two side surfaces of the vortex generator 9a is provided with the arrow angle ⁇ / 2.
  • the other side surface is straight and oriented in the direction of flow.
  • only one vortex is generated on the arrowed side. Accordingly, there is no vortex-neutral field downstream of the vortex generator, but a dall is imposed on the flow.
  • the vortex generators are mainly used on the one hand as a mixer of two flows.
  • the main flow in the form of combustion air attacks the transverse inlet edges 15 in the direction of the arrow.
  • the secondary flow in the form of a gaseous and / or liquid fuel has a substantially smaller mass flow than the main flow. It is introduced into the main flow in the immediate area of the vortex generators.
  • the introduction into the flow channel of the gaseous and / or liquid fuel to be mixed into the combustion air can be designed in many ways according to FIG. 5.
  • the outflow of the fuel into the combustion air can take place via the staggered arrangement in the longitudinal edges 12 and 14 (or at least in their immediate area) are.
  • the fuel is first introduced here through means, not shown, through the channel wall 21 into the hollow interior of the vortex generator. From the wall bores 22c, it thus arrives directly into the vortex which arises and which rises in the injection region. There are defined flow conditions here.
  • the fuel can also be injected from wall bores 22a, which are located in the channel wall 21 along the edge 15 of the vortex generator.
  • the injection angle is then selected so that the fuel flows around the roof surface of the vortex generator as a film before it is mixed in.
  • This "cold" film forms a protective layer against a hot main current for the roof surface.
  • This solution according to is particularly well suited for dual operation, in which both gaseous and liquid fuel are mixed into the main flow and later burned.
  • the liquid fuel, here oil is then injected through a single bore (not shown) which opens directly at the edge 15, preferably at the same injection angle as the gas. This oil also spreads over the surface of the roof as a protective film before it is atomized.
  • a slot (not shown here) could also be used.
  • Wall bores 22b can also be provided downstream of the vortex generators, through which the fuel is blown into the ascending vortex.
  • the fuel can also be injected from a single hole which is made in the area of the tip 18 of the vortex generator.
  • the agent is injected directly into the fully developed vertebra and also in its ascending branch.
  • FIG. 3 shows, in simplified form, a combustion chamber with a channel 20 through which an annular flow flows.
  • an equal number of vortex generators according to FIG. Generators lie in the same radial. If the same heights h are assumed for opposite vortex generators, FIG. 3 shows that the vortex generators on the inner channel ring 21b have a smaller arrow ⁇ . In the longitudinal section in FIG. 4 it can be seen that this could be compensated for by a larger angle of attack ⁇ if swirl-like vortices are desired in the inner and outer ring cross section. In this solution, as indicated in FIG. 3, two vortex pairs, each with small vertebrae, are generated, which leads to a shorter mixing length.
  • the liquid fuel is injected here via a central fuel lance 24, the mouth of which is located downstream of the vortex generators 9 in the area of the tip 18 thereof.
  • the gaseous fuel is injected twice according to the methods described in FIG. 5.
  • the injected fuel is dragged along by the vortices and mixed with the main flow. It follows the helical course of the vertebrae and is evenly finely distributed in the chamber downstream of the vertebrae. This reduces the risk of impinging jets on the opposite wall and the formation of so-called "hot spots" - in the case of the radial injection of fuel into an undisturbed flow mentioned at the beginning.
  • the fuel injection can be kept flexible and adapted to other boundary conditions. In this way, the same injection pulse can be maintained throughout the load range. Since the mixing is determined by the geometry of the vortex generators and not by the machine load, in this case the gas turbine output, the burner configured in this way works optimally even under partial load conditions.
  • the combustion process is optimized by adjusting the ignition delay time of the fuel and mixing time of the vortices, which ensures a minimization of emissions.
  • the effective mixing results in a good temperature profile over the cross section through which the flow is flowing and also reduces the possibility of the occurrence of thermoacoustic instability. Due to their presence alone, the vortex generators act as a damping measure against thermoacoustic vibrations.
  • the gaseous fuel can be injected through wall bores which are fed from ring lines provided in the interior of the channel.
  • central lances for liquid fuel can also be provided be, a plurality of which is distributed over the circumference of the ring channel.
  • Fig. 6 shows a configuration like Fig. 3, but with smaller radii of the ring walls and large channel height. The height of the opposing vortex generators is very different.
  • the height h of the connecting edge 16 will be coordinated with the channel height H or the height of the channel part which is assigned to the vortex generator in such a way that the vortex generated immediately downstream of the vortex generator already reaches such a size that the full channel height H is filled, which leads to a uniform speed distribution in the applied cross section.
  • Another criterion that can influence the ratio h / H to be selected is the pressure drop that occurs when the vortex generator flows around. It goes without saying that the pressure loss coefficient also increases with a larger ratio h / H.
  • the connecting edges of two opposite vortex generators are offset by half a division.
  • the vortex structure downstream of the vortex generators is changed such that the vortices generated on the same side have the same direction of rotation and may merge into one large vortex that fills the entire channel cross section in the corresponding angular sector.
  • this allows the mixing quality to be improved and, on the other hand, a longer lifespan of the vortex can be achieved.
  • This solution offers the possibility, not shown, of raising the height of the inner vortex generators so that their tips can engage between the side walls of the two opposite vortex generators.
  • FIG. 9 four vortex generators 9 are strung together on the wall 21a in the circumferential direction in such a way that no gaps are left on the channel wall.
  • the mode of operation of the elements in such a network corresponds to that of the outer vortex generators in FIG. 3.
  • the arrangement consists of 4 groups of 3 vortex generators 9a each according to FIG. 2. In one group the three vortex generators are equipped with increasing height. All vortices generated are the same rotation.
  • FIG. 13 shows a variant with vortex generators 9 which is particularly suitable as an exchange unit in cylindrical premixing chambers. It is also designed for dual operation, which means that both liquid and gaseous fuel can be mixed into the combustion air.
  • the kit which can be inserted axially into the premixing tube (not shown) consists of a central lance 27 which is provided with vortex generators 9 at its end.
  • the liquid fuel passes through an oil line 29 arranged in the central lance 28 to the injection head, from which it is injected into the channel via nozzles.
  • the nozzles are directed in the direction of the arrow in the symmetry line of the vortex generators.
  • the fuel is captured by the rising vortices.
  • the gaseous fuel which is also fed to the central lance, passes via hollow ribs 27 into a gas ring 28, with which the system is centered and fixed in the tube. The fuel is added to the main flow from this gas ring 28.
  • the invention is not limited to the examples described and shown. With regard to the arrangement of the vortex generators in the network, many combinations are possible without leaving the scope of the invention.
  • the introduction of the secondary flow into the main flow can also be carried out in a variety of ways.
  • the variant according to FIG. 9 is also suitable, for example, in combustion chambers of the "can" principle.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical Kinetics & Catalysis (AREA)
EP94103408A 1993-04-08 1994-03-07 Système d'alimentation en carburant pour chambre de combustion Expired - Lifetime EP0619456B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH01088/93A CH687832A5 (de) 1993-04-08 1993-04-08 Brennstoffzufuehreinrichtung fuer Brennkammer.
CH1088/93 1993-04-08

Publications (2)

Publication Number Publication Date
EP0619456A1 true EP0619456A1 (fr) 1994-10-12
EP0619456B1 EP0619456B1 (fr) 1997-10-08

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EP94103408A Expired - Lifetime EP0619456B1 (fr) 1993-04-08 1994-03-07 Système d'alimentation en carburant pour chambre de combustion

Country Status (6)

Country Link
US (1) US5658358A (fr)
EP (1) EP0619456B1 (fr)
JP (1) JP3527278B2 (fr)
CH (1) CH687832A5 (fr)
DE (1) DE59404243D1 (fr)
RU (1) RU2118756C1 (fr)

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DE19507088A1 (de) * 1995-03-01 1996-09-05 Abb Management Ag Vormischbrenner
DE19512645A1 (de) * 1995-04-05 1996-10-10 Bmw Rolls Royce Gmbh Vorrichtung zur Kraftstoffaufbereitung für eine Brennkammer
EP0745809A1 (fr) * 1995-06-02 1996-12-04 ABB Management AG Générateur de tourbillons pour chambre de combustion
EP0718561A3 (fr) * 1994-12-24 1997-04-23 Abb Management Ag Brûleur
EP0775869A2 (fr) 1995-11-23 1997-05-28 Abb Research Ltd. Brûleur à prémélange
DE10250208A1 (de) * 2002-10-28 2004-06-03 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Flammenstabilisierung für mager vorgemischte Brenner für Flüssigbrennstoff in Gasturbinenbrennkammern mittels Turbolatorelementen im Hauptstrom
EP2112433A1 (fr) 2008-04-23 2009-10-28 Siemens Aktiengesellschaft Chambre de mélange
EP2253888A1 (fr) * 2009-05-14 2010-11-24 Alstom Technology Ltd Brûleur d'une turbine à gaz
DE102013018146A1 (de) * 2013-12-04 2015-06-11 Astrium Gmbh Einspritzelement für eine Raketenbrennkammer
WO2015134009A1 (fr) * 2014-03-05 2015-09-11 Siemens Aktiengesellschaft Moteur à turbine à gaz avec système de mélange statique de flux d'échappement de compresseur

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CN104549097B (zh) * 2008-11-26 2017-04-12 卡尔冈碳素公司 在污水/循环水紫外消毒系统中混合部件的使用方法和装置
ES2462974T3 (es) 2010-08-16 2014-05-27 Alstom Technology Ltd Quemador de recalentamiento
US9435537B2 (en) * 2010-11-30 2016-09-06 General Electric Company System and method for premixer wake and vortex filling for enhanced flame-holding resistance
US8863525B2 (en) * 2011-01-03 2014-10-21 General Electric Company Combustor with fuel staggering for flame holding mitigation
US9297532B2 (en) * 2011-12-21 2016-03-29 Siemens Aktiengesellschaft Can annular combustion arrangement with flow tripping device
GB2500873A (en) * 2012-03-22 2013-10-09 Corac Energy Technologies Ltd Pipeline compression system
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US9358557B2 (en) * 2013-12-20 2016-06-07 Young Living Essential Oils, Lc Liquid diffuser
EP2993404B1 (fr) * 2014-09-08 2019-03-13 Ansaldo Energia Switzerland AG Mélangeur de gaz ou d'air de dilution pour une chambre de combustion d'une turbine à gaz
EP3301368A1 (fr) 2016-09-28 2018-04-04 Siemens Aktiengesellschaft Générateur de turbulence, ensemble chambre de combustion et turbine à gaz avec mélange d'air/carburant amélioré
RU2685629C2 (ru) * 2017-05-24 2019-04-22 Шор Борис Иосифович Активатор жидкости
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KR102164619B1 (ko) * 2019-04-08 2020-10-12 두산중공업 주식회사 연소기 및 이를 포함하는 가스터빈
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EP0520163A2 (fr) * 1991-06-26 1992-12-30 BDAG Balcke-Dürr Aktiengesellschaft Dispositif pour la combustion des matières combustibles

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0718561A3 (fr) * 1994-12-24 1997-04-23 Abb Management Ag Brûleur
US5918465A (en) * 1995-02-03 1999-07-06 Bmw Rolls-Royce Gmbh Flow guiding body for a gas turbine combustion chamber
WO1996023981A1 (fr) * 1995-02-03 1996-08-08 Bmw Rolls-Royce Gmbh Corps de guidage de l'ecoulement pour chambres de combustion de turbines a gaz
DE19507088B4 (de) * 1995-03-01 2005-01-27 Alstom Vormischbrenner
DE19507088A1 (de) * 1995-03-01 1996-09-05 Abb Management Ag Vormischbrenner
EP0730121A3 (fr) * 1995-03-01 1998-03-11 Abb Research Ltd. Brûleur à prémélange
DE19512645A1 (de) * 1995-04-05 1996-10-10 Bmw Rolls Royce Gmbh Vorrichtung zur Kraftstoffaufbereitung für eine Brennkammer
EP0745809A1 (fr) * 1995-06-02 1996-12-04 ABB Management AG Générateur de tourbillons pour chambre de combustion
EP0775869A2 (fr) 1995-11-23 1997-05-28 Abb Research Ltd. Brûleur à prémélange
EP0775869A3 (fr) * 1995-11-23 1998-03-11 Abb Research Ltd. Brûleur à prémélange
US5791892A (en) * 1995-11-23 1998-08-11 Abb Research Ltd. Premix burner
DE10250208A1 (de) * 2002-10-28 2004-06-03 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Flammenstabilisierung für mager vorgemischte Brenner für Flüssigbrennstoff in Gasturbinenbrennkammern mittels Turbolatorelementen im Hauptstrom
DE10250208A9 (de) * 2002-10-28 2004-12-23 Rolls-Royce Deutschland Ltd & Co Kg Vorrichtung zur Flammenstabilisierung für mager vorgemischte Brenner für Flüssigbrennstoff in Gasturbinenbrennkammern mittels Turbolatorelementen im Hauptstrom
EP2112433A1 (fr) 2008-04-23 2009-10-28 Siemens Aktiengesellschaft Chambre de mélange
US8424310B2 (en) 2008-04-23 2013-04-23 Siemens Aktiengesellschaft Mixing chamber
EP2253888A1 (fr) * 2009-05-14 2010-11-24 Alstom Technology Ltd Brûleur d'une turbine à gaz
US9726377B2 (en) 2009-05-14 2017-08-08 Ansaldo Energia Switzerland AG Burner of a gas turbine
DE102013018146A1 (de) * 2013-12-04 2015-06-11 Astrium Gmbh Einspritzelement für eine Raketenbrennkammer
DE102013018146B4 (de) * 2013-12-04 2021-02-25 Arianegroup Gmbh Einspritzelement für eine Raketenbrennkammer
WO2015134009A1 (fr) * 2014-03-05 2015-09-11 Siemens Aktiengesellschaft Moteur à turbine à gaz avec système de mélange statique de flux d'échappement de compresseur

Also Published As

Publication number Publication date
CH687832A5 (de) 1997-02-28
EP0619456B1 (fr) 1997-10-08
US5658358A (en) 1997-08-19
JPH0771758A (ja) 1995-03-17
JP3527278B2 (ja) 2004-05-17
DE59404243D1 (de) 1997-11-13
RU2118756C1 (ru) 1998-09-10

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