EP1224423B1 - Brenner - Google Patents
Brenner Download PDFInfo
- Publication number
- EP1224423B1 EP1224423B1 EP00972775A EP00972775A EP1224423B1 EP 1224423 B1 EP1224423 B1 EP 1224423B1 EP 00972775 A EP00972775 A EP 00972775A EP 00972775 A EP00972775 A EP 00972775A EP 1224423 B1 EP1224423 B1 EP 1224423B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- swirl
- combustion air
- burner
- blades
- combustion
- 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
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Images
Classifications
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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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
- F23R3/12—Air inlet arrangements for primary air inducing a vortex
- F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
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- 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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
- F23M20/005—Noise absorbing means
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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
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2206/00—Burners for specific applications
- F23D2206/10—Turbines
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2210/00—Noise abatement
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14004—Special features of gas burners with radially extending gas distribution spokes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
- F23D2900/14—Special features of gas burners
- F23D2900/14021—Premixing burners with swirling or vortices creating means for fuel or air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
Definitions
- the invention relates to a burner with a combustion air supply duct.
- the Air intake silencer consists of one of an impermeable Wall enclosed flow line running at subsonic speed flows through a gaseous medium is.
- a device for Suppression of airborne noise emissions arranged in the flow line. This facility is in front of one in the flow direction of the medium arranged sound-transmitting noise source and serves the Suppression of airborne noise emissions against the direction of flow.
- the device has a laval nozzle-like Narrowing of the flow line. Through this laval nozzle-like The velocity of the gaseous medium becomes narrowing accelerated to the speed of sound. So that becomes a Reflection barrier built for airborne sound.
- combustion vibrations In combustion systems, it can develop combustion vibrations come. Such combustion vibrations are described in the article "Combustion-Driven-Oscillations in Industry "by Abbott A. Putnam, American Elsevier, New York 1971. According to the Rayleigh criterion, one is built Combustion vibration with a periodic supply of Heat up an amount of air in a combustion chamber if this Heat supply as a periodic release of combustion power in phase with a natural vibration of the air in the Combustion chamber takes place. Accordingly, the combustion vibration suppressed by an anti-phase power release become. Such combustion vibrations can considerable noise pollution and even mechanical Damage to components of the combustion device to lead.
- US Pat. No. 4,483,138 shows a burner with a combustion air duct, in which one of a number of swirl blades formed swirl blade ring is arranged, where the passage cross-sectional area between two swirl blades narrowed and then an abrupt increase in the cross-sectional area takes place. A decrease in Flow rate is not desirable.
- US Pat. No. 5,451,160 shows a burner with a combustion air duct, in which a number of swirl generator elements is arranged.
- the swirl generator elements are only schematic shown, so that a course of the passage cross section between two swirl generator elements not known is.
- US Pat. No. 5,558,515 shows a burner with a combustion air duct, in which swirl generator elements are arranged, the passage cross-sectional area between two Swirl generator element narrows and an abrupt downstream Enlargement of the cross-sectional area takes place.
- the swirl generator elements have a downstream Tearing edge. After the swirl generator element is a venturi element available, which accelerates the current again.
- the object of the invention is to provide a burner in which a combustion zone into which the burner opens, from one Supply of combustion air for the burner is acoustically decoupled from the flow, with this decoupling at most an acceptable additional pressure loss in the combustion air arises.
- this object is achieved by a burner with a combustion air duct in which one of a number Swirl vane ring formed by swirl vanes arranged in this way is that through the swirl vane ring the average passage speed from passing through the swirl vane ring Combustion air to a Mach number of at least 0.4, in particular at least 0.6, is increased. It points the swirl vane ring on first and second vanes that along the circumferential direction of the swirl vane ring alternate in succession, with the second blades opposing against a flow direction of the combustion air the first blades are offset.
- this object is also achieved by a burner with a combustion air duct, in which a swirl generator formed from a number of swirl generator elements is arranged in such a way that the swirl generator causes the average passage speed of combustion air passed through the swirl generator to a Mach number of at least 0.4, in particular at least 0.6.
- the profile profile of the additional swirl blades is designed so that pressure recovery in the combustion air is brought about. This happens through a gradually widening passage cross section. This gradual expansion is to be designed in such a way that there is no stall along the swirl vanes.
- the average speed of passage is the over averaged a duct cross section of the combustion air duct Speed.
- Swirl generators are often used in a burner the combustion air entering the combustion chamber to give a twist which stabilizes the combustion flame.
- the acoustic decoupling thus has an effect at most, slightly negative on the efficiency of one Combustion device in which the burner is integrated is.
- a swirl vane ring in the combustion air duct from swirl blades to generate a swirl in the Combustion air arranged.
- the swirl generator is further preferred formed by the swirl vane ring. So instead additional swirl generator for acoustic decoupling see an already existing swirl vane ring as acoustically decoupling swirl generator.
- additional swirl generator for acoustic decoupling see an already existing swirl vane ring as acoustically decoupling swirl generator.
- the swirl generator elements results as a swirl vane itself an easy to implement measure to reduce the pressure drop in to keep the combustion air small.
- the combustion air when entering the swirl vane ring due to an effective narrowing of the cross section follows due to the blade profiles tapering in the direction of flow again an extension through which a pressure recovery is caused in the combustion air.
- Training the Swirl generator as a swirl vane ring thus has both Advantage that it is an already required means of production of a swirl stabilizing the combustion provided will, as well as a favorable on efficiency effective pressure
- the swirl vane ring preferably has first and second Buckets that run along the circumferential direction of the swirl vane ring alternating successively, the second blades against a flow direction of the Combustion air offset from the first blades are.
- the first blades preferably have one first maximum profile thickness and the second blades one second maximum profile thickness, the first maximum Profile thickness is greater than the second maximum profile thickness.
- the first blades have a first chord length and second blades a second chord length. Preferably the first chord length is smaller than the second Chord length.
- the Shoveling one of the partial rings preferably longer and thinner than the blades of the other part of the ring and that are preferred the blades of that part of the wreath longer and thinner, which is arranged in the flow direction in front of the other partial ring is.
- the two functions of the swirl vane ring are optimized, d. H. both the Function of the swirl generation as well as the function of the acoustic Decoupling can be done by appropriate dimensioning and coordination of the partial wreaths to each other in sufficient Dimensions are met.
- this structure is simple Possibility of a swirl vane ring in a burner like this to retrofit that he subsequently the desired acoustic Decoupling enabled.
- the combustion air duct is preferably annular.
- Fuel is preferably in the combustion air duct inlet, which is before combustion with the combustion air intensely mixed.
- The is more preferred Fuel from at least some of the swirl generator elements einllange.
- Through the intensive mixing of the fuel with the combustion air before combustion (premix burner), will reduce nitrogen oxide emissions reached. This is done by leveling the flame temperature due to the good mixing, because the Nitrogen oxide emission exponentially with the flame temperature increases.
- Another advantage of acoustic decoupling an additional mixing results from the swirl generator of fuel and combustion air because of the pronounced acceleration of the combustion air and the subsequent zone of pressure recovery additional swirls in the combustion air to a further improvement the mixing of combustion air and fuel to lead.
- the swirl generator can also be dimensioned in this way be that on part of the pressure recovery is dispensed with in favor of increased turbulence improved mixing.
- the burner preferably has an additional pilot burner on, through which a combustion of the combustion air duct escaping fuel-combustion air mixture is stabilized.
- the pilot burner work as Diffusion burner, d. H.
- Fuel and combustion air of the Pilot burners are only mixed at the place of combustion, so the burner is also referred to as a hybrid burner, in which both premix combustion and diffusion combustion he follows.
- the burner is a gas turbine burner educated. Especially when it comes to high performance implementation Gas turbines can have very large combustion vibrations Amplitudes and possibly considerable damage effects occur. The flow acoustic decoupling to the combustion air supply system is particularly important here. this applies especially for stationary gas turbines.
- FIG. 1 shows a gas turbine 301 in a longitudinal section. Arranged one behind the other along a turbine axis 302 are a compressor 303, a combustor 305 and a Turbine part 307.
- the combustion chamber 305 opens into the burner 100. This comprises an annular duct-shaped combustion air duct 104 and a central one, from the combustion air duct 104 surrounding pilot burner 106.
- the pilot burner 106 is as a diffusion burner executed in the fuel 114 and Compressor air 112 mixed in a combustion zone 311 and be burned.
- fuel 114 of the combustion air 112 admixed from the compressor 303.
- the combustion air 112 initially mixes intimately with the Fuel 114 before it is also in the combustion zone 311 burns within the combustion chamber 305. This so-called Premixed combustion is achieved through the diffusion combustion of the Pilot burner 106 stabilized.
- burning in the Combustion chamber 305 generates hot exhaust gas 315, which the Turbine part 307 is fed.
- Blading shown in turbine part 307 is the energy one of the hot exhaust gases 315 in rotational energy is not closer shown turbine shaft implemented.
- Fluctuations in the combustion flame 313 result in Propagation of sound waves within the combustion chamber 305, that are reflected from the combustion chamber walls and in place the combustion 311 in turn fluctuations in the flame 313 cause. This interaction can cause a certain combustion chamber vibration at certain frequencies of the fluctuations build up in the combustion chamber 305 that too significant noise or even damage of components of the gas turbine 301 can lead. These combustion vibrations also spread through the combustion air duct 104 out. Through the combustion air duct 104 thus an additional volume to the combustion chamber 305 coupled, through which the formation of combustion chamber vibrations can also be favored. In addition Components upstream of the combustion chamber 305 also below Exposed to damaging vibrations.
- the combustion air duct 104 flow acoustic to decouple from the combustion chamber 305.
- a simple and acceptable from the pressure loss Possibility of acoustic decoupling of the combustion chamber 305 and combustion air duct 104 by means of a 2 shows the burner 100.
- FIG. 2 shows partially cut open and in perspective one burner 100 directed along a focal axis 98 an inner wall 101 and an outer wall 102 is an annular channel Combustion air duct 104 is formed. This encloses a centrally arranged, not shown in detail Pilot burner 106.
- a swirl generator 109 designed as a swirl vane ring arranged. This is made of swirl blades Swirl generator elements 108 are formed.
- the swirl blades 108 are in their position by adjusting screws 110 in the Outer wall 102 adjustable.
- the swirl vane ring 109 is thereby alternating along its circumferential direction U. successive, different swirl blades 108 educated.
- a first swirl vane 108B follows a second swirl vane 108A each.
- the first swirl blades 108B are opposite the second swirl blades 108a staggered and both shorter and thicker. This is explained in more detail below with reference to FIG 3. Out some, preferably all of the swirl blades 108 is by means of one running inside the swirl vane 108, here invisible fuel channel fuel 114 over Openings, in particular around the blade leading edge, let into the combustion air duct 104. By the Combustion air duct 104 flows combustion air 112. This mixes intensively with the fuel 114 Dimensioning of the swirl blades 108 becomes the combustion air 112 accelerated to a Mach number above 0.4. This creates a reflection barrier for sound waves built up.
- FIG. 3 shows a cross section of three of the swirl blades 108 namely, second swirl blades 108A and an intermediate one first swirl vane 108B.
- the first swirl vane 108B has a leading edge point 200B, a trailing edge point 202B, a skeleton line 204B, a maximum Profile thickness 206B and an adjustment engagement 208B.
- each second swirl vane 108A has one Blade leading edge point 208A, a blade trailing edge point 202A, a skeleton line 204A, a maximum profile thickness 206A and an adjustment engagement 208A.
- Combustion air 112 flows along the flow direction 210 between the first Swirl vane 108B and one of the second swirl vanes 108A therethrough.
- the first is along this flow direction 210 Swirl vane 108B opposite second swirl vane 108A set back so that there is a distance L1 between the Tangents to the respective blade leading edge points 200B, 200A results.
- a passage cross section F1 for the between Combustion air 112 flowing through the swirl blades 108 shrinks down to a maximum narrowing caused by a minimum distance L4 between the first swirl vane 108B and the second swirl vane 108A. After this maximum constriction, the passage cross section increases F2 again and so moderately that it is not to a stall and thus to pressure losses due to comes from vortex formation. This will result in a high pressure recovery ensured in the combustion air 112.
- the combustion air enters the trailing edge points 202B, 202A 112 again between the two blades 108.
- the Blade trailing edge points 202B, 202A are shown by the Distance L3 spaced apart.
- the first swirl blades 108B both have a greater maximum profile thickness than 206B also a shorter chord 204B compared to the maximum profile thicknesses 206A or 204A second swirl blades 108A.
- This alternating Vane design in the swirl vane ring 109 enables both the setting of a sufficiently high swirl Stabilization of a combustion as well as desired acoustic decoupling effect by accelerating the combustion air 112 and then pressure recovery.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
- Air Supply (AREA)
Abstract
Description
Gleichzeitig wird der Profilverlauf der zusätzlichen Drallschaufeln so gestaltet, daß ein Druckrückgewinn in der Verbrennungsluft bewirkt wird. Dies geschieht durch einen sich allmählich erweiternden Durchtrittsquerschnitt. Dabei ist diese allmähliche Erweiterung so auszugestalten, daß es nicht zu einem Strömungsabriß entlang der Drallschaufeln kommt.
- FIG 1
- eine Gasturbine,
- FIG 2
- einen Brenner und
- FIG 3
- Drallschaufeln eines Drallschaufelkranzes.
Claims (13)
- Brenner (100) mit einem Verbrennungsluftkanal (104), in dem ein aus einer Anzahl von Drallschaufeln (108) gebildeter Drallschaufelkranz (109) zur Erzeugung eines die Verbrennung stabilisierenden Dralles in der Verbrennungsluft (112) angeordnet ist,
wobei der Drallschaufelkranz (109) aus ersten Drallschaufeln (108B) und aus zweiten Drallschaufeln (108A) gebildet ist, die entlang der Umfangsrichtung (U) des Drallschaufelkranzes (109) wechselnd aufeinander folgen,
wobei die zweiten Drallschaufeln (108A) entgegen einer Strömungsrichtung (210) der Verbrennungsluft (112) gegenüber den ersten Drallschaufeln (108B) versetzt sind,
so dass durch den Drallerzeuger (109) die mittlere Durchtrittsgeschwindigkeit von durch den Drallschaufelkranz (109) durchgeleiteter Verbrennungsluft (112) auf eine Machzahl von mindestens 0,4 erhöhbar ist. - Brenner (100) mit einem Verbrennungsluftkanal (104), in dem ein aus einer Anzahl von Drallerzeugerelementen (108) gebildeter Drallerzeuger (109) angeordnet ist,
wobei durch den Drallerzeuger (109) eine Erhöhung der Durchtrittsgeschwindigkeit durch eine Verengung eines freien Durchtrittsquerschnittes (F1) für die Verbrennungsluft (112) und ein anschließender Druckrückgewinn in der Verbrennungsluft (112) durch einen sich allmählich so erweiternden freien Durchtrittsquerschnitt (F2) bewirkt wird, so daß die Verbrennungsluft (112) im wesentlichen frei von einem Strömungsabriß zwischen den Drallerzeugerelementen (108) strömt, und
so dass die mittlere Durchtrittsgeschwindigkeit von durch den Drallerzeuger (109) durchgeleiteter Verbrennungsluft (112) auf eine Machzahl von mindestens 0,4 erhöht ist. - Brenner (100) nach Anspruch 2,
bei dem im Verbrennungsluftkanal (104) ein Drallschaufelkranz (109) aus Drallschaufeln (108) zur Erzeugung eines die Verbrennung stabilisierenden Dralles in der Verbrennungsluft (112) angeordnet ist. - Brenner (100) nach Anspruch 3,
bei dem der Drallerzeuger (109) durch den Drallschaufelkranz (109) gebildet ist, wobei die Drallerzeugerelemente (108) durch die Drallschaufeln (108) gebildet sind. - Brenner (100) nach Anspruch 4,
bei dem der Drallschaufelkranz (109) aus ersten Drallschaufeln (108B) und aus zweiten Drallschaufeln (108A) gebildet ist, die entlang der Umfangsrichtung (U) des Drallschaufelkranzes (109) wechselnd aufeinander folgen,
wobei die zweiten Drallschaufeln (108A) entgegen einer Strömungsrichtung (210) der Verbrennungsluft (112) gegenüber den ersten Drallschaufeln (108B) versetzt sind. - Brenner (100) nach Anspruch 1 oder 5,
bei dem die ersten Drallschaufeln (108B) eine erste maximale Profildicke (206B) und die zweiten Drallschaufeln (108A) eine zweite maximale Profildicke (206A) aufweisen,
wobei die erste maximale Profildicke (206B) größer ist als die zweite maximale Profildicke (206A). - Brenner (100) nach Anspruch 1 oder 6,
bei dem die ersten Drallschaufeln (108B) eine erste Profilsehnenlänge (204B) und die zweiten Drallschaufeln (108A) eine zweite Profilsehnenlänge (204A) aufweisen,
wobei die erste Profilsehnenlänge (204B) kleiner ist als die zweite Profilsehnenlänge (204A). - Brenner (100) Anspruch 1,
bei dem die Erhöhung der Durchtrittsgeschwindigkeit durch eine Verengung eines freien Durchtrittsquerschnittes (F1) für die Verbrennungsluft (112) und ein anschließender Druckrückgewinn in der Verbrennungsluft (112) durch einen sich allmählich so erweiternden freien Durchtrittsquerschnitt (F2) bewirkt wird, daß die Verbrennungsluft (112) im wesentlichen frei von einem Strömungsabriß zwischen den Drallerzeugerelementen (108) strömt. - Brenner (100) nach einem der vorhergehenden Ansprüche,
bei dem der Verbrennungsluftkanal (104) ringförmig ausgebildet ist. - Brenner (100) nach einem der vorhergehenden Ansprüche,
bei dem in den Verbrennungsluftkanal (104) Brennstoff (114) einlaßbar ist, der sich dabei vor einer Verbrennung mit der verbrennungsluft (112) intensiv vermischt. - Brenner (100) nach Anspruch 10,
bei dem der Brennstoff (114) aus zumindest einigen der Drallerzeugerelemente (108) einlaßbar ist. - Brenner (100) nach einem der vorhergehenden Ansprüche,
der einen zusätzlichen Pilotbrenner (106) umfaßt, durch den eine Verbrennung des aus dem Verbrennungsluftkanal (104) austretenden Brennstoff/Verbrennungsluftgemisches stabilisierbar ist. - Brenner (100) nach einem der vorhergehenden Ansprüche,
der als ein Gasturbinenbrenner (100) ausgebildet ist.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP00972775A EP1224423B1 (de) | 1999-10-29 | 2000-10-16 | Brenner |
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP99121577 | 1999-10-29 | ||
EP99121577A EP1096201A1 (de) | 1999-10-29 | 1999-10-29 | Brenner |
PCT/EP2000/010167 WO2001033138A1 (de) | 1999-10-29 | 2000-10-16 | Brenner |
EP00972775A EP1224423B1 (de) | 1999-10-29 | 2000-10-16 | Brenner |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1224423A1 EP1224423A1 (de) | 2002-07-24 |
EP1224423B1 true EP1224423B1 (de) | 2004-09-15 |
Family
ID=8239298
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99121577A Withdrawn EP1096201A1 (de) | 1999-10-29 | 1999-10-29 | Brenner |
EP00972775A Expired - Lifetime EP1224423B1 (de) | 1999-10-29 | 2000-10-16 | Brenner |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99121577A Withdrawn EP1096201A1 (de) | 1999-10-29 | 1999-10-29 | Brenner |
Country Status (6)
Country | Link |
---|---|
US (1) | US6688109B2 (de) |
EP (2) | EP1096201A1 (de) |
JP (1) | JP4567266B2 (de) |
CN (1) | CN1143980C (de) |
DE (1) | DE50007809D1 (de) |
WO (1) | WO2001033138A1 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
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DE102004059882A1 (de) * | 2004-12-10 | 2006-06-22 | Rolls-Royce Deutschland Ltd & Co Kg | Magervormischbrenner mit integriertem Stützbrenner |
EA039073B1 (ru) * | 2020-09-07 | 2021-11-30 | Некоммерческое Акционерное Общество "Алматинский Университет Энергетики И Связи Имени Гумарбека Даукеева" | Двухъярусная горелка |
Families Citing this family (39)
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JP4161493B2 (ja) * | 1999-12-10 | 2008-10-08 | ソニー株式会社 | エッチング方法およびマイクロミラーの製造方法 |
US6968692B2 (en) | 2002-04-26 | 2005-11-29 | Rolls-Royce Corporation | Fuel premixing module for gas turbine engine combustor |
DE10233161B4 (de) * | 2002-07-22 | 2012-01-05 | Alstom Technology Ltd. | Brenner und Pilotbrenner |
EP1394471A1 (de) * | 2002-09-02 | 2004-03-03 | Siemens Aktiengesellschaft | Brenner |
DE10348604A1 (de) * | 2003-10-20 | 2005-07-28 | Rolls-Royce Deutschland Ltd & Co Kg | Kraftstoffeinspritzdüse mit filmartiger Kraftstoffplatzierung |
DE102004015186A1 (de) * | 2004-03-29 | 2005-10-20 | Alstom Technology Ltd Baden | Gasturbinen-Brennkammer und zugehöriges Betriebsverfahren |
US8104285B2 (en) * | 2005-09-30 | 2012-01-31 | Ansaldo Energia S.P.A. | Gas turbine equipped with a gas burner and axial swirler for the burner |
US8769960B2 (en) | 2005-10-21 | 2014-07-08 | Rolls-Royce Canada, Ltd | Gas turbine engine mixing duct and method to start the engine |
US7490471B2 (en) * | 2005-12-08 | 2009-02-17 | General Electric Company | Swirler assembly |
EP1821035A1 (de) * | 2006-02-15 | 2007-08-22 | Siemens Aktiengesellschaft | Gasturbinenbrenner und Verfahren zum Mischen von Brennstoff und Luft in einem Wirbelbereich eines Gasturbinenbrenners |
EP1892469B1 (de) * | 2006-08-16 | 2011-10-05 | Siemens Aktiengesellschaft | Drallerzeugerkanal und Brenner für eine Gasturbine |
US20080078182A1 (en) * | 2006-09-29 | 2008-04-03 | Andrei Tristan Evulet | Premixing device, gas turbines comprising the premixing device, and methods of use |
US7631500B2 (en) * | 2006-09-29 | 2009-12-15 | General Electric Company | Methods and apparatus to facilitate decreasing combustor acoustics |
EP1918638A1 (de) * | 2006-10-25 | 2008-05-07 | Siemens AG | Brenner, insbesondere für eine Gasturbine |
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-
1999
- 1999-10-29 EP EP99121577A patent/EP1096201A1/de not_active Withdrawn
-
2000
- 2000-10-16 WO PCT/EP2000/010167 patent/WO2001033138A1/de active IP Right Grant
- 2000-10-16 CN CNB008151075A patent/CN1143980C/zh not_active Expired - Fee Related
- 2000-10-16 JP JP2001534984A patent/JP4567266B2/ja not_active Expired - Fee Related
- 2000-10-16 DE DE50007809T patent/DE50007809D1/de not_active Expired - Lifetime
- 2000-10-16 EP EP00972775A patent/EP1224423B1/de not_active Expired - Lifetime
-
2002
- 2002-04-26 US US10/133,926 patent/US6688109B2/en not_active Expired - Lifetime
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102004059882A1 (de) * | 2004-12-10 | 2006-06-22 | Rolls-Royce Deutschland Ltd & Co Kg | Magervormischbrenner mit integriertem Stützbrenner |
EA039073B1 (ru) * | 2020-09-07 | 2021-11-30 | Некоммерческое Акционерное Общество "Алматинский Университет Энергетики И Связи Имени Гумарбека Даукеева" | Двухъярусная горелка |
Also Published As
Publication number | Publication date |
---|---|
WO2001033138A1 (de) | 2001-05-10 |
CN1143980C (zh) | 2004-03-31 |
CN1384908A (zh) | 2002-12-11 |
JP2003513223A (ja) | 2003-04-08 |
JP4567266B2 (ja) | 2010-10-20 |
EP1096201A1 (de) | 2001-05-02 |
US20020174656A1 (en) | 2002-11-28 |
DE50007809D1 (en) | 2004-10-21 |
US6688109B2 (en) | 2004-02-10 |
EP1224423A1 (de) | 2002-07-24 |
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