EP0851990B1 - Brenner, insbesondere für eine gasturbine - Google Patents
Brenner, insbesondere für eine gasturbine Download PDFInfo
- Publication number
- EP0851990B1 EP0851990B1 EP96942244A EP96942244A EP0851990B1 EP 0851990 B1 EP0851990 B1 EP 0851990B1 EP 96942244 A EP96942244 A EP 96942244A EP 96942244 A EP96942244 A EP 96942244A EP 0851990 B1 EP0851990 B1 EP 0851990B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- swirl
- burner
- burner according
- stream
- annular gap
- 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.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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
- F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
- F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
- F23D14/24—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other at least one of the fluids being submitted to a swirling motion
-
- 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
- F23C7/004—Combustion apparatus characterised by arrangements for air supply the air being submitted to a rotary or spinning motion using vanes
-
- 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
- F23D14/26—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid with provision for a retention flame
Definitions
- the invention relates to a burner with one axis and one with respect to this rotationally symmetrical arrangement of one Outer jacket and a coaxial inner jacket, which an annular gap extending from an entry to an exit for carrying a stream of an oxygen-containing Gases defined, with a plurality of arranged in the annular gap Nozzles for supplying a fuel and a swirl grid arranged in the annular gap.
- the invention particularly relates to such Burners for use in a gas turbine.
- EP 0 589 520 A1 and US Patents 5 165 241, 5 251 447, 5 323 604 and 5 351 477 are also of interest.
- Both books concern fans, especially fans of the axial type, which are identified by a rotating swirl grid, which a stream of a gas in Form of a swirl-free stream sucked along an axis and in the form of a swirled, accelerated current emits along the axis.
- a rotating swirl grid which a stream of a gas in Form of a swirl-free stream sucked along an axis and in the form of a swirled, accelerated current emits along the axis.
- the configuration of the burner resembles the configuration of one in many ways Fan, and essential theoretical foundations of a Fans can be used immediately. Really important is an effect in the present case that has anything to do with a swirl moving current along an axis Gases and regardless of how this electricity is provided was occurs.
- This effect is the formation of a Vortex core inside the stream, d. that is, one with one Swirl of moving current tends to become one To form a circular ring so that in a surrounding the axis Central area of a cylindrical tube in which the current is no longer flowing in the direction of the current takes place.
- a burner of the type mentioned in the introduction generally has the purpose of a fuel safely and low in pollutants in one Stream of an oxygen-containing gas, especially in compressed air to burn.
- an oxygen-containing gas especially in compressed air to burn.
- Fuels of this type are e.g. B. gases, which contain elemental hydrogen, for example Gases obtained from coal gasification and natural gases, the high proportions of longer chain hydrocarbons, whose ignition temperatures are significantly lower than that Ignition temperature of methane.
- premix combustion as it has so far been realized, not without problems was, especially because of premature inflammation a mixture of fuel and oxygenated Gas relatively easily does great damage to an affected person Can cause burners.
- a widespread method of Preventing a flashback is a narrowing of the Burner outlet and thus an acceleration of the fuel gas at the exit. In the event of a flashback however, the flame can penetrate far into the burner.
- a burner is specified with a Axis and one with respect to this rotationally symmetrical Arrangement of an outer jacket and an inner jacket coaxial therewith, which one from entry to exit reaching annular gap for guiding a flow of oxygen containing gas defined, with a variety of in the annular gap arranged nozzles for supplying a fuel to the stream and one arranged in the annular gap Swirl grille, the arrangement consisting of the outer jacket and the inner jacket is designed so that the current Annular gap between the swirl grille and the outlet with a essentially constant meridional speed flows through.
- the characteristic of the "essentially constant meridional speed" means that the current to flow through Arranging the current a substantially constant meridional flow cross section must oppose. This In many cases, however, the flow cross-section is not, for example perpendicular to an axis of symmetry of the flow Structure, but according to the Current descriptive vector field at an angle to the axis of symmetry and be dimensioned transversely to the vector field.
- a simple calculation model provides which does not have to explicitly take the current into account, one good approximation to determine the flow cross section along the arrangement to be flowed through: into the arrangement Tori inscribed, which covers both the surface of the The outer jacket and the surface of the inner jacket tangentially touch.
- the points are at which such Torus touches the outer jacket or the inner jacket a circle on the outer jacket or a circle on the inner jacket.
- One is clamped between these two circles Truncated cone surface; this has an area, which in a good approximation of the effective flow cross-section at the location of the Corresponds to the truncated cone.
- Computer programs are also available on a commercial basis With which flows through practically any shape Arrangements are predictable.
- the relevantly experienced and working people are, for example, the computer programs TASCFLOW and FLUENT known.
- a such a computer program used to use one of the simple calculation model described above Optimize structure is; there are of course no fundamental ones Objections, the present case with a three-dimensional Treat model.
- the invention is based on the knowledge that the guarantee a constant meridional speed for the Current behind the swirl grid, i.e. H. ensuring one constant rate of propagation of the current along the axis or in a radial-axial with respect to the axis Level, stabilizing itself in a special way on the current and the mixture of oxygen to be formed in this stream containing gas and the fuel affects.
- This measure ensures that disruptions due to non-ideal flow to the burner can be suppressed.
- a necessary pressure drop across the burner has to set, is to a large extent between the Entry and the swirl grille dismantled. That is also the danger prevents disturbances in the Electricity arise.
- the outer jacket is particularly important designed in such a way that at the entrance Lip or a rounded funnel opens; the inner jacket is at the entrance especially with a rounded Edge. This contributes to homogenization of the current passing through the burner and avoids that disturbances that formed in the stream in front of the burner have to continue into the burner.
- those arranged in the annular gap Nozzles for supplying a fuel are arranged in the swirl grille are.
- the swirl grid from hollow guide vanes in which the nozzles are arranged.
- the burner is designed such that one of the swirl grille, a radius of the outer jacket and a radius of the inner jacket to determine both radii on Exit, defined swirl number, which can be calculated as Quotient between an angular momentum as dividend and one Product of a meridional impulse and the radius of the Outer jacket as a divisor, with the angular momentum and the meridional Impulse characterize the current at the outlet, if which flows towards the entrance without swirl, is smaller than one critical swirl number, which is determined by the radii.
- the requirement that the corresponding design of the burner is known as the "hub criterion of Strscheletzky ".
- the swirl number is off characteristic quantities of the current, namely the size of a meridional component of its momentum as well as its size its angular momentum, which is essentially from the swirl grid is determined, it can be calculated that the swirl number is nevertheless a characteristic parameter of the burner itself is. This results from the fluid mechanics similarity relationships.
- critical swirl number has been coined on based on the observation that located near the axis a current moving with a swirl along the axis forms a so-called vortex core, d. H. an area, from which the current is essentially displaced. root cause centrifugal forces are one example.
- the diameter this vortex core is amenable to calculation; please refer the books cited. Basically, the diameter increases of the vortex core with increasing swirl number. Should be now the current move in a circular ring which defines is by the radius of the outer jacket of the burner as the outer radius and the radius of the inner jacket as the inner radius, so can only ensure that the flow against the inner jacket be if the to the given outer radius and the given swirl radius of the vortex core is smaller than the inner radius.
- the critical swirl number is in this Context defined as the twist number at which the radius of the vortex core of the current exactly the inner radius, d. H. corresponds to the radius of the inner jacket.
- the swirl number of the burner defined as explained is preferred chosen significantly smaller than the critical swirl number; in particular, the number of swirls of the burner is between 75% and 97% of the critical swirl number and lies particularly preferably at about 90% of the critical swirl number.
- the number of swirls of the burner is between 75% and 97% of the critical swirl number and lies particularly preferably at about 90% of the critical swirl number.
- the burner of any configuration is preferably provided with a pilot burner.
- This pilot burner comprises in particular a pilot burner arranged in the inner jacket, which delivers a small, stable burning flame where the mixture formed in the burner itself ignite from oxygen-containing gas and fuel can. This is important when regulating the fuel supply and thus a regulation of heat production the burner is desired. It has been shown that premix combustion without stabilization only in one relative narrow operating range, characterized by a relative exact chemical composition, stable is. Will, however, with an appropriate pilot burner provided additional stabilization, one can important extension of the operating area for practical operation can be achieved.
- the burner is particularly qualified for use in a Combustion device of a gas turbine and is in particular qualified for a gas turbine that is relatively flammable Fuels are to be burned.
- the burner is by no means limited to the combustion of gaseous Fuels; in principle, the burner can be in the appropriate Design with any flowable fuel, especially operated with heating oil and the like become.
- the burner shown in FIG. 1 is with respect to axis 1 rotationally symmetrical. It has an outer jacket 2 and one too this coaxial inner jacket 3. Neither the outer jacket 2 nor the inner jacket 3 must each be made in one piece; it is very possible and, for example, for the sake of rational production, advantageous, the outer jacket 2 and / or the inner jacket 3, as shown, from several parts put together. Define the outer jacket 2 and the inner jacket 3 an annular gap 4, which from an inlet 5 to an outlet 6 from a stream 7 (represented by arrows) an oxygen-containing gas is flowed through.
- An annular swirl 8 is arranged, consisting of a plurality of guide vanes 8, which one of the stream 7 Swirl imprints; this means that the stream 7 behind the Swirl grid 8 makes a helical movement about axis 1 executes. So he doesn't just have velocity vectors, those in radial-axial with respect to axis 1 Layers lie and accordingly according to the professional Terminology is meridional; the speed vectors have components behind the swirl grille 8, the tangential to axis 1 or to circles, their centers lie on axis 1 and lie in planes, which are oriented perpendicular to axis 1 are. Such tangential components can be according to the relevant terminology also referred to as "peripheral components become.
- the guide vanes 8 have nozzles 9 through which the Stream 7 is supplied with a fuel, in particular a combustible gas becomes. This initially mixes with the electricity without ignition, and the mixture formed ignites only in the area of the exit 6. The is accordingly Burner a premix burner.
- An essential feature of the burner is that the arrangement designed in such a way from the outer jacket 2 and the inner jacket 3 is that the current 7 the annular gap 4 between the swirl grid 8 and the outlet 6 with a substantially constant meridional Speed flows through.
- stream 7 in its direction of propagation, i.e. H. in a with respect to axis 1 meridional direction, no acceleration or experience delay.
- This requires a careful design, in particular of the outer casing 2 and the inner shell 3, since it may be desirable and in the illustrated Example is realized that the current 7 itself not just moved parallel to axis 1, but a part executes a movement directed radially inwards to axis 1. This inward movement must be balanced by an appropriate extension of the respective distance between the outer jacket 2 and the inner jacket 3; This is clearly recognizable from the drawing.
- the annular gap 4 narrows significantly; this narrowing results mainly from the fact that the Stream 7 is partly led radially inwards to axis 1, so that it is sufficient between the outer jacket 2 and the inner jacket 3 Maintain a largely constant distance.
- the outer jacket 2 is supportive in the area of the entrance 5 expanded approximately like a funnel, so that it becomes 5 opens like a rounded funnel or lip, and the inner jacket 3 has a rounded at the inlet 5 Edge 10.
- nozzles 9 which serve to deliver the fuel, has already been pointed out. These nozzles 9 are in the guide vanes 8 arranged, thus a particularly homogeneous interference to ensure the fuel in stream 7 without detaching the flow from the guide vanes 8 is coming.
- the fuel is supplied to the nozzles 9 through a fuel line 11 and an annular one and arranged on the inside of the inner jacket 3 fuel distribution space 12. From this fuel distribution room 12 Fuel through channels (not shown) in the inner jacket 3 and the guide vanes 8 flow to the nozzles 9.
- the geometry of the arrangement of the swirl grille 8, the outer jacket 2 and the inner jacket 3 is, as already detailed above explained, chosen such that a swirl number, which essential indicators of the current 7 determines if this in meridional direction at the entry 5 in the ring channel 4, is smaller than a critical swirl number, which is results from the radius of the outer jacket 2 and the radius of the Inner jacket 3 at the outlet 6.
- the critical swirl number is defined in such a way that a cylindrical flow through along a channel with the stated radius of the outer jacket 2 the axis 1 flows, forms a vortex core, so a area surrounding axis 1 from which the current displaces which has a radius that is the radius of the inner jacket 3 at outlet 6 corresponds.
- the geometric structure of the burner has been worked out with the help of common mathematical models.
- the default for defining the structure is in that the flow cross sections over the entire relevant ring channel 4 must be constant.
- the structure of the simple calculation model was then developed using the commercially available computer program TASCFLOW regarding the desired consistency of the flow cross section optimized via the ring channel 4.
- the inflammable mixture is ignited in stream 7 outside the burner.
- a pilot burner is provided for this 13 with one inside the inner jacket 3 arranged pilot burner 13. This delivers a small one Flame, which ensures that the combustible mixture ignited in the stream 7.
- a flame on the pilot burner 13 to ignite and maintain is an igniter 14 intended. In the event that from a special pilot burner 13, 14 is taken for granted a modified igniter to ignite the mixture to provide.
- FIG 2 shows a schematic illustration of a gas turbine with a compressor part 15 for suction and compression of Air, a combustion part 16, to which the compressed air is supplied which is also the one intended for combustion Receives fuel, and a turbine part 17, in which the of the compressor part 15 and compressed in the combustion part 16 additional heated electricity with submission of mechanical work is relaxed.
- the burner shown in FIG 1 is provided for installation in a combustion part 16 together with a A number of similar burners.
- the burner according to the invention is characterized by features with which a current passing through the burner Gases in a particularly favorable manner for the intended purpose being affected.
- the burner is characterized by a particularly stable operation and particularly avoids operational Disturbances due to non-ideal inflow or through flashbacks.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pre-Mixing And Non-Premixing Gas Burner (AREA)
- Gas Burners (AREA)
Description
- In FIG 1
- einen Längsschnitt durch einen Brenner;
- in FIG 2
- ein Schema einer Gasturbine
Claims (12)
- Brenner mit einer Achse (1) und einer bezüglich dieser rotationssymmetrischen Anordnung aus einem Außenmantel (2) und einem dazu koaxialen Innenmantel (3), welche einen von einem Eintritt (5) zu einem Austritt (6) reichenden Ringspalt (4) zur Führung eines Stromes (7) eines Sauerstoff enthaltenden Gases definiert, mit einer Vielzahl von in dem Ringspalt (4) angeordneten Düsen (9) zur Zuführung eines Brennstoffes zu dem Strom (7) sowie einem in dem Ringspalt (4) angeordneten Drallgitter (8), dadurch gekennzeichnet, daß die Anordnung aus dem Außenmantel (2) und dem Innenmantel (3) derart gestaltet ist, daß der Strom (7) den Ringspalt (4) zwischen dem Drallgitter (8) und dem Austritt (6) mit einer im wesentlichen konstanten meridionalen Geschwindigkeit durchfließt.
- Brenner nach Anspruch 1, bei dem die Anordnung aus dem Außenmantel (2) und dem Innenmantel (3) derart gestaltet ist, daß sich der Ringspalt (4) zwischen dem Eintritt (5) und dem Drallgitter (8) verengt.
- Brenner nach Anspruch 2, bei dem der Außenmantel (2) sich am Eintritt (5) nach Art einer Lippe öffnet.
- Brenner nach Anspruch 2 oder 3, bei dem der Innenmantel (3) am Eintritt (5) eine abgerundete Kante (10) hat.
- Brenner nach einem der vorhergehenden Ansprüche, bei dem die Düsen (9) in dem Drallgitter (8) angeordnet sind.
- Brenner nach Anspruch 5, bei dem das Drallgitter (8) aus Leitschaufeln (8) besteht und die Düsen (9) in den Leicschaufeln (8) angeordnet sind.
- Brenner nach einem der vorhergehenden Ansprüche, bei dema) das Drallgitter (8), ein Radius des Außenmantels (2) und ein Radius des Innenmantels (3), welche Radien am Austritt (6) bestimmt sind, eine Drallzahl definieren, welche ein Quotient zwischen einem Drehimpuls als Dividend und einem Produkt aus einem meridionalen Impuls und dem Radius des Außenmantels (2) als Divisor ist, wobei der Drehimpuls und der meridionale Impuls den Strom (7) am Austritt (6) charakterisieren, wenn dieser den Eintritt (5) ohne Drall anströmt;b) die Drallzahl kleiner ist als eine kritische Drallzahl, welche bestimmt ist durch die Radien.
- Brenner nach Anspruch 7, bei dem die Drallzahl zwischen 75 Prozent und 97 Prozent der kritischen Drallzahl beträgt.
- Brenner nach Anspruch 8, bei dem die Drallzahl etwa 90 Prozent der kritischen Drallzahl beträgt.
- Brenner nach einem der vorhergehenden Ansprüche, welcher eine Pilotbrenneinrichtung (13,14) hat.
- Brenner nach Anspruch 10, bei dem die Pilotbrenneinrichtung (13,14) einen in dem Innenmantel (3) angeordneten Pilotbrenner (13) umfaßt.
- Brenner nach einem der vorhergehenden Ansprüche, welcher in einem Verbrennungsteil (16) einer Gasturbine (15,16,17) eingesetzt ist.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19535287 | 1995-09-22 | ||
DE19535287 | 1995-09-22 | ||
PCT/DE1996/001756 WO1997011311A2 (de) | 1995-09-22 | 1996-09-17 | Brenner, insbesondere für eine gasturbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0851990A2 EP0851990A2 (de) | 1998-07-08 |
EP0851990B1 true EP0851990B1 (de) | 2001-12-05 |
Family
ID=7772905
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP96942244A Expired - Lifetime EP0851990B1 (de) | 1995-09-22 | 1996-09-17 | Brenner, insbesondere für eine gasturbine |
Country Status (7)
Country | Link |
---|---|
US (1) | US6038864A (de) |
EP (1) | EP0851990B1 (de) |
JP (1) | JP3939756B2 (de) |
DE (1) | DE59608389D1 (de) |
ES (1) | ES2169273T3 (de) |
RU (1) | RU2156405C2 (de) |
WO (1) | WO1997011311A2 (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2019020350A1 (de) | 2017-07-27 | 2019-01-31 | Siemens Aktiengesellschaft | Gasturbinenbrenner mit vorgemischten strahlflammen |
Families Citing this family (20)
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JP4130475B2 (ja) * | 1996-09-09 | 2008-08-06 | シーメンス アクチエンゲゼルシヤフト | 空気内で燃料を燃焼する装置とその方法 |
DE59801583D1 (de) * | 1997-07-17 | 2001-10-31 | Siemens Ag | Brenneranordnung für eine feuerungsanlage, insbesondere eine gasturbinenbrennkammer |
US6161387A (en) * | 1998-10-30 | 2000-12-19 | United Technologies Corporation | Multishear fuel injector |
DE10104695B4 (de) * | 2001-02-02 | 2014-11-20 | Alstom Technology Ltd. | Vormischbrenner für eine Gasturbine |
US6551098B2 (en) * | 2001-02-22 | 2003-04-22 | Rheem Manufacturing Company | Variable firing rate fuel burner |
US6539721B2 (en) | 2001-07-10 | 2003-04-01 | Pratt & Whitney Canada Corp. | Gas-liquid premixer |
US6698208B2 (en) | 2001-12-14 | 2004-03-02 | Elliott Energy Systems, Inc. | Atomizer for a combustor |
US6786047B2 (en) | 2002-09-17 | 2004-09-07 | Siemens Westinghouse Power Corporation | Flashback resistant pre-mix burner for a gas turbine combustor |
US6848260B2 (en) | 2002-09-23 | 2005-02-01 | Siemens Westinghouse Power Corporation | Premixed pilot burner for a combustion turbine engine |
EP1645805A1 (de) * | 2004-10-11 | 2006-04-12 | Siemens Aktiengesellschaft | Brenner für fluidische Brennstoffe und Verfahren zum Betreiben eines derartigen Brenners |
US7370466B2 (en) * | 2004-11-09 | 2008-05-13 | Siemens Power Generation, Inc. | Extended flashback annulus in a gas turbine combustor |
EP1944547A1 (de) | 2007-01-15 | 2008-07-16 | Siemens Aktiengesellschaft | Steuerverfahren zur Kraftstoffspaltung |
US20080276622A1 (en) * | 2007-05-07 | 2008-11-13 | Thomas Edward Johnson | Fuel nozzle and method of fabricating the same |
US8113000B2 (en) * | 2008-09-15 | 2012-02-14 | Siemens Energy, Inc. | Flashback resistant pre-mixer assembly |
EP2312215A1 (de) | 2008-10-01 | 2011-04-20 | Siemens Aktiengesellschaft | Brenner und Verfahren zum Betrieb eines Brenners |
EP2236934A1 (de) | 2009-03-18 | 2010-10-06 | Siemens Aktiengesellschaft | Brenneranordnung |
EP2264370B1 (de) * | 2009-06-16 | 2012-10-10 | Siemens Aktiengesellschaft | Brenneranordnung für eine Verfeuerungsanlage zum Verfeuern fluidischer Brennstoffe und Verfahren zum Betrieb einer solchen Brenneranordnung |
US8387393B2 (en) * | 2009-06-23 | 2013-03-05 | Siemens Energy, Inc. | Flashback resistant fuel injection system |
WO2012118397A1 (ru) * | 2011-02-28 | 2012-09-07 | Открытое Акционерное Общество "Силовые Машины - Зтл, Лмз, Электросила, Энергомашэкспорт" (Оао "Силовые Машины") | Горелка |
US9046262B2 (en) * | 2011-06-27 | 2015-06-02 | General Electric Company | Premixer fuel nozzle for gas turbine engine |
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-
1996
- 1996-09-17 JP JP51231697A patent/JP3939756B2/ja not_active Expired - Lifetime
- 1996-09-17 EP EP96942244A patent/EP0851990B1/de not_active Expired - Lifetime
- 1996-09-17 DE DE59608389T patent/DE59608389D1/de not_active Expired - Lifetime
- 1996-09-17 RU RU98107628/06A patent/RU2156405C2/ru active IP Right Revival
- 1996-09-17 WO PCT/DE1996/001756 patent/WO1997011311A2/de active IP Right Grant
- 1996-09-17 ES ES96942244T patent/ES2169273T3/es not_active Expired - Lifetime
-
1998
- 1998-03-23 US US09/047,164 patent/US6038864A/en not_active Expired - Lifetime
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2019020350A1 (de) | 2017-07-27 | 2019-01-31 | Siemens Aktiengesellschaft | Gasturbinenbrenner mit vorgemischten strahlflammen |
Also Published As
Publication number | Publication date |
---|---|
US6038864A (en) | 2000-03-21 |
RU2156405C2 (ru) | 2000-09-20 |
DE59608389D1 (de) | 2002-01-17 |
ES2169273T3 (es) | 2002-07-01 |
JP2000512723A (ja) | 2000-09-26 |
JP3939756B2 (ja) | 2007-07-04 |
WO1997011311A3 (de) | 1997-05-15 |
EP0851990A2 (de) | 1998-07-08 |
WO1997011311A2 (de) | 1997-03-27 |
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