EP1064498B1 - Gasturbinenbrenner - Google Patents
Gasturbinenbrenner Download PDFInfo
- Publication number
- EP1064498B1 EP1064498B1 EP99917770A EP99917770A EP1064498B1 EP 1064498 B1 EP1064498 B1 EP 1064498B1 EP 99917770 A EP99917770 A EP 99917770A EP 99917770 A EP99917770 A EP 99917770A EP 1064498 B1 EP1064498 B1 EP 1064498B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- swirl
- burner
- flow
- combustion
- combustion air
- 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
- 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
- F23D23/00—Assemblies of two or more burners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2206/00—Burners for specific applications
- F23D2206/10—Turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D2210/00—Noise abatement
Definitions
- the invention relates to a gas turbine burner according to the Preamble of claim 1.
- combustion vibrations When operating a burner of a gas turbine, it can Training of combustion vibrations come. It is also known under the terms “combustion chamber hum”, “combustion chamber vibrations”, “combustion-induced pressure pulsations”, “swinging burns”.
- the combustion vibrations are based on an interaction of the supplied per unit time Amount of the combustion air / fuel mixture flowing in the flow channel of the burner, which after an entry is ignited in a combustion chamber and in a flame burns with the current combustion turnover in the Flame. With combustion turnover, the per unit of time is at an amount of combustion air / fuel mixture converted in a flame designated.
- By a change of the combustion turnover can lead to pressure fluctuations in the combustion chamber come to the formation of a stable Can cause pressure vibration.
- the combustion vibrations cause increased noise in addition to increased mechanical and thermal stress from Combustion chamber walls and other combustion system belonging parts.
- a hybrid burner for a gas turbine is known from the EP-0 580 683 B1.
- a hybrid burner has both a diffusion burner, as well as a premix burner. It is therefore both in diffusion mode and in premix mode operated.
- the premix burner of the hybrid burner has one Ring channel for supplying combustion air or from one Combustion air / fuel mixture.
- a swirl device for embossing a swirl on a flow that is the supplied combustion air / fuel mixture or the combustion air in the Ring channel forms. This swirl device is also called a swirl grid designated.
- the diffusion burner of the hybrid burner is arranged coaxially in the ring channel of the premix burner.
- the Diffusion burner has an annular channel Combustion air supply channel in which a fuel supply channel coaxially is arranged.
- the channels of the diffusion burner flow into a nozzle.
- a pilot burner in its combustion air supply duct which is only for the operation of the premix burner is required.
- the Ring channel of the premix burner a combustion air / fuel mixture fed, which is a flow in the ring channel forms which flow a swirl with the help of the swirl grid is imprinted.
- the swirling flow occurs Combustion from the premix burner.
- the combustion will stabilized with the flame of the pilot burner.
- at Diffusion operation of the hybrid burner is via the Combustion air and the fuel supply channel of the Diffusion burner combustion air or fuel to a mixture in the area of the diffusion burner nozzles fed.
- the combustion air / fuel mixture formed during the mixture occurs to a combustion from the Diffusion burner.
- the object of the invention is to provide a gas turbine burner a lower tendency to form combustion vibrations specify.
- the gas turbine burner is directed Problem solved by the features of claim 1.
- Advantageous embodiments are the subject of this back-related subclaims.
- the invention is based on the knowledge that when such a burner is operated, a flow of combustion air forms in the flow channel and is mixed with fuel to form a combustion air / fuel mixture via fuel inlets.
- the fuel is preferably fed into a flow of combustion air that is uniform over the cross section of the flow channel. This has the advantage that the local mixing ratio between combustion air and fuel is essentially uniform over the cross section. With a uniform mixture, the NO x content of the exhaust gas, which arises during the combustion of the combustion air / fuel mixture formed in the mixture, can be influenced.
- a swirl is preferably applied to the flow in the flow channel using a swirl device in order to stabilize the combustion.
- This swirl is usually uniform over the circumference of the flow channel so as not to impair the uniformity of the flow.
- Studies have shown that the more uniform the flow of a combustion air / fuel mixture supplied for combustion with a burner, the greater the likelihood that combustion vibrations can form when the burner is operated in a combustion system.
- the invention is therefore based on the idea of a gas turbine burner to be designed so that a flow of an educated Combustion air / fuel mixture before supply combustion by imprinting an uneven Swirl is so uneven that the excitation of combustion vibrations when operating the gas turbine burner in a combustion system at least significantly reduced is.
- a flow channel Swirl device with swirl elements available, whereby Deflection surfaces of the swirl elements one at the outflow end Have outflow angle to the main flow direction, the for at least two directly adjacent swirl elements is different. This ensures that the flow after flowing through the swirl device in the circumferential direction emerges at at least two different angles, so that the imprinted swirl of the flow of the combustion air / fuel mixture a circumferentially in Circumferential direction is uneven.
- each swirl element is designed as a swirl blade.
- the burner can be designed, for example, as a hybrid burner of the gas turbine.
- swirl device has at least one such swirl group. More preferred the swirl device is formed from several swirl groups, where neighboring swirl groups have different outflow angles exhibit.
- the swirl device can for example be formed from six swirl groups, each Swirl group can have four swirl elements.
- the burner In order to reduce the amount of NO x compounds formed during combustion, it is desirable to supply fuel into a uniform flow of combustion air to form combustion air / fuel mixture intended for combustion.
- the burner preferably has a fuel inlet through which fuel can be fed into the flow channel upstream of the outflow end. As a result, the fuel is fed into a uniform flow of combustion air flowing in the supply duct in front of the swirl device.
- the hybrid burner 1 shows a burner 1 designed as a hybrid burner 1 a gas turbine not shown.
- the hybrid burner 1 has both a diffusion burner 2 and also a premix burner 3.
- the premix burner 3 has an annular channel 4 with an outer wall 16, which for feeding of combustion air 5 or one Combustion air / fuel mixture 5 is used.
- Located in the ring channel 4 a swirl device 6 with an outflow end 12, which serves to impress a swirl on a flow 7, which flow 7 the supplied combustion air / fuel mixture 5 or forms the combustion air 5 in the ring channel 4.
- the swirl device 6 is also referred to below as a swirl grid 6 designated.
- the swirl grid 6 has several swirl elements 15, each of which is designed as a swirl vane.
- Fuel inlets 13 are arranged upstream of the outflow end 12, can be fed into the annular channel 4 via the fuel 14 and thus the combustion air 5 can be mixed.
- the diffusion burner 2 of the hybrid burner 1 is coaxial in the ring channel 4 of the premix burner 3 arranged.
- the diffusion burner 2 has a combustion air supply duct designed as an annular duct 8, in which a fuel supply channel 9 coaxially is arranged.
- the channels 8 and 9 of the diffusion burner 2 open into a nozzle 10.
- the diffusion burner has 2 in its combustion air supply duct 8 a pilot burner 11, which is for operation of the premix burner 3 is provided.
- combustion air becomes 5 supplied via the ring channel 4, which deal with over the fuel inlets 13 supplied fuel 14 into one Combustion air / fuel mixture mixes.
- the combustion air / fuel mixture 5 forms a flow 7 with a local main flow direction 14.
- the swirl grille 6 becomes the flow 7 in Uneven twist impressed with which the Flow 7 leaves the swirl grille 6 at the outflow end 12 and subsequently emerges from the ring channel 4.
- the combustion air / fuel mixture is ignited and burned 5. With the help of a flame from the pilot burner 11 combustion is stabilized.
- An advantage of the described configuration of the hybrid burner 1 is that, due to the uneven swirl that the flow 7 of the combustion air / fuel mixture 5 supplied to the combustion has, the outflow from the burner itself is uneven, which at least reduces the build-up of combustion vibrations.
- Another advantage is that the flow 7 has a swirl with which the combustion is stabilized.
- the combustion air 5 upstream of the outflow end 12 forms a uniform flow 7.
- the arrangement of the fuel inlets 13 allows the uniform flow 7 of the combustion air 5 to be fed and mixed upstream with fuel 14, as a result of which a uniform mixture between the combustion air 5 and the fuel 14 can be achieved. This makes it possible to reduce the amount of NO x compounds formed during the combustion.
- FIG. 2 shows a view of the swirl elements 15 of the ring channel 4 of the premix burner 3 which are developed in the circumferential direction, the direction 17 shown in FIG. 1 perpendicular to the outer wall 16 of the ring channel 4 being selected as the viewing direction.
- the swirl elements 15 each have a deflection surface 18.
- the deflection surfaces 18 each form an outflow angle ⁇ with the local main flow direction 14 (see also FIG. 1).
- the deflection surfaces 18 of two adjacent swirl elements 20 and 21 have different outflow angles ⁇ 1 and ⁇ 2 .
- the flow 7 leaves the swirl grille 6 at the outflow end 12 with a swirl impressed unevenly in the circumferential direction.
- the swirl elements 20 and the swirl elements 21 are each combined to form a swirl group which have the outflow angle ⁇ 1 and ⁇ 2 .
- the invention is characterized by a burner in which in a flow of combustion air or a combustion air / fuel mixture a combustion is supplied, wherein the flow is an uneven swirl in the circumferential direction is imprinted.
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)
- Air Supply (AREA)
Description
Weiter bevorzugt ist jedes Drallelement als eine Drallschaufel ausgebildet. Der Brenner kann beispielsweise als Hybridbrenner der Gasturbine ausgebildet sein.
- FIG 1
- ein als Hybridbrenner ausgeführter Brenner für eine Gasturbine und
- FIG 2
- eine Ansicht der in Umfangsrichtung abgewickelten Drallelemente des Ringkanals des Vormischbrenners.
Claims (4)
- Brenner
mit einer Strömung (7),
mit einer Drallvorrichtung (6) zur Aufprägung eines Dralls auf die Strömung (7),
wobei
die Strömung (7) durch ein Gemisch aus Brennstoff und Verbrennungsluft gebildet ist,
die Strömung (7) in einem Strömungskanal geführt ist, und
die Drallvorrichtung in dem Strömungskanal (4) angeordnet ist, und
der Brenner ein Gasturbinenbrenner ist, und
der Brenner ein Vormischbrenner (3) ist, und
jedes einer Anzahl von Drallelementen (15) der Drallvorrichtung (6) eine Umlenkfläche (18) mit einem an deren Abströmende (12) vorgesehenen Abströmwinkel (α) zu einer Hauptströmungsrichtung (14) aufweist,
wobei die Abströmwinkel (α) zumindest zweier benachbarter Drallelemente (15) unterschiedlich sind,
so dass die Drallvorrichtung (6) zur Aufprägung eines über den Umfang des Ringkanals (4) ungleichmäßigen Dralls auf die Strömung (7) ausgebildet ist. - Brenner nach Anspruch 1,
dadurch gekennzeichnet, dass die Drallvorrichtung (6) aus mehreren Drallgruppen (20,21) gebildet ist, wobei jede Drallgruppe (20,21) mehrere Drallelemente (15) mit gleichem Abströmwinkel (α1 bzw. α2) aufweist, und wobei die Drallelemente (15) benachbarter Drallgruppen (20,21) unterschiedliche Abströmwinkel ((α1,α2) aufweisen. - Brenner nach Anspruch 1 oder 2,
gekennzeichnet durch dessen Ausführung als Hybridbrenner. - Brenner nach Anspruch 1,
dadurch gekennzeichnet, dass
jedes Drallelement (15) als Drallschaufel ausgebildet ist.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19812322 | 1998-03-20 | ||
DE19812322 | 1998-03-20 | ||
PCT/DE1999/000614 WO1999049264A1 (de) | 1998-03-20 | 1999-03-08 | Brenner und verfahren zur reduzierung von verbrennungsschwingungen beim betrieb |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1064498A1 EP1064498A1 (de) | 2001-01-03 |
EP1064498B1 true EP1064498B1 (de) | 2002-11-13 |
Family
ID=7861710
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP99917770A Expired - Lifetime EP1064498B1 (de) | 1998-03-20 | 1999-03-08 | Gasturbinenbrenner |
Country Status (5)
Country | Link |
---|---|
US (1) | US6374593B1 (de) |
EP (1) | EP1064498B1 (de) |
JP (1) | JP2002507717A (de) |
DE (1) | DE59903398D1 (de) |
WO (1) | WO1999049264A1 (de) |
Families Citing this family (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1096201A1 (de) * | 1999-10-29 | 2001-05-02 | Siemens Aktiengesellschaft | Brenner |
DE10040869A1 (de) * | 2000-08-21 | 2002-03-07 | Alstom Power Nv | Verfahren und Vorrichtung zur Unterdrückung von Strömungswirbeln innerhalb einer Strömungskraftmaschine |
US6539721B2 (en) * | 2001-07-10 | 2003-04-01 | Pratt & Whitney Canada Corp. | Gas-liquid premixer |
EP1342953A1 (de) * | 2002-03-07 | 2003-09-10 | Siemens Aktiengesellschaft | Gasturbine |
EP1342952A1 (de) * | 2002-03-07 | 2003-09-10 | Siemens Aktiengesellschaft | Brenner, Verfahren zum Betrieb eines Brenners und Gasturbine |
US6898938B2 (en) * | 2003-04-24 | 2005-05-31 | General Electric Company | Differential pressure induced purging fuel injector with asymmetric cyclone |
DE10345440A1 (de) * | 2003-09-30 | 2005-05-12 | Siemens Ag | Verfahren, Computerprogramm mit Programmcode-Mitteln und Computerprogramm-Produkt zur Analyse von Einflussgrößen auf einen Brennvorgang in einer Brennkammer unter Verwendung eines trainierbaren, statistischen Modells |
ITTO20040309A1 (it) * | 2004-05-13 | 2004-08-13 | Ansaldo Energia Spa | Metodo per controllare un combustore a gas di una turbina a gas |
EP1645805A1 (de) * | 2004-10-11 | 2006-04-12 | Siemens Aktiengesellschaft | Brenner für fluidische Brennstoffe und Verfahren zum Betreiben eines derartigen Brenners |
EP1659339A1 (de) * | 2004-11-18 | 2006-05-24 | Siemens Aktiengesellschaft | Verfahren zum Anfahren eines Brenners |
US7874138B2 (en) * | 2008-09-11 | 2011-01-25 | Siemens Energy, Inc. | Segmented annular combustor |
US20120103237A1 (en) * | 2010-11-03 | 2012-05-03 | Ronny Jones | Tiltable multiple-staged coal burner in a horizontal arrangement |
US10641176B2 (en) | 2016-03-25 | 2020-05-05 | General Electric Company | Combustion system with panel fuel injector |
US10584880B2 (en) | 2016-03-25 | 2020-03-10 | General Electric Company | Mounting of integrated combustor nozzles in a segmented annular combustion system |
US10830442B2 (en) | 2016-03-25 | 2020-11-10 | General Electric Company | Segmented annular combustion system with dual fuel capability |
US10563869B2 (en) | 2016-03-25 | 2020-02-18 | General Electric Company | Operation and turndown of a segmented annular combustion system |
US10584876B2 (en) | 2016-03-25 | 2020-03-10 | General Electric Company | Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system |
US11428413B2 (en) | 2016-03-25 | 2022-08-30 | General Electric Company | Fuel injection module for segmented annular combustion system |
US10520194B2 (en) | 2016-03-25 | 2019-12-31 | General Electric Company | Radially stacked fuel injection module for a segmented annular combustion system |
US10605459B2 (en) | 2016-03-25 | 2020-03-31 | General Electric Company | Integrated combustor nozzle for a segmented annular combustion system |
US10641491B2 (en) | 2016-03-25 | 2020-05-05 | General Electric Company | Cooling of integrated combustor nozzle of segmented annular combustion system |
US11156362B2 (en) | 2016-11-28 | 2021-10-26 | General Electric Company | Combustor with axially staged fuel injection |
US10690350B2 (en) | 2016-11-28 | 2020-06-23 | General Electric Company | Combustor with axially staged fuel injection |
KR102245798B1 (ko) * | 2019-09-17 | 2021-04-28 | 두산중공업 주식회사 | 연료 노즐 어셈블리 및 이를 포함하는 가스 터빈의 연소기 |
US11371702B2 (en) | 2020-08-31 | 2022-06-28 | General Electric Company | Impingement panel for a turbomachine |
US11994292B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus for turbomachine |
US11994293B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus support structure and method of manufacture |
US11614233B2 (en) | 2020-08-31 | 2023-03-28 | General Electric Company | Impingement panel support structure and method of manufacture |
US11460191B2 (en) | 2020-08-31 | 2022-10-04 | General Electric Company | Cooling insert for a turbomachine |
US11255545B1 (en) | 2020-10-26 | 2022-02-22 | General Electric Company | Integrated combustion nozzle having a unified head end |
US11802693B2 (en) * | 2021-04-16 | 2023-10-31 | General Electric Company | Combustor swirl vane apparatus |
US11598526B2 (en) * | 2021-04-16 | 2023-03-07 | General Electric Company | Combustor swirl vane apparatus |
US11767766B1 (en) | 2022-07-29 | 2023-09-26 | General Electric Company | Turbomachine airfoil having impingement cooling passages |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3663189D1 (en) * | 1985-03-04 | 1989-06-08 | Siemens Ag | Burner disposition for combustion installations, especially for combustion chambers of gas turbine installations, and method for its operation |
KR100234569B1 (ko) | 1991-04-25 | 1999-12-15 | 피터 토마스 | 석탄가스 및 다른연료의 저공해 연소를 위한 버너장치 |
US5365865A (en) * | 1991-10-31 | 1994-11-22 | Monro Richard J | Flame stabilizer for solid fuel burner |
US5388536A (en) * | 1992-03-25 | 1995-02-14 | Chung; Landy | Low NOx burner |
US5676538A (en) * | 1993-06-28 | 1997-10-14 | General Electric Company | Fuel nozzle for low-NOx combustor burners |
US5415114A (en) * | 1993-10-27 | 1995-05-16 | Rjc Corporation | Internal air and/or fuel staged controller |
WO1999006767A1 (de) * | 1997-07-31 | 1999-02-11 | Siemens Aktiengesellschaft | Brenner |
US5966937A (en) * | 1997-10-09 | 1999-10-19 | United Technologies Corporation | Radial inlet swirler with twisted vanes for fuel injector |
-
1999
- 1999-03-08 US US09/646,612 patent/US6374593B1/en not_active Expired - Fee Related
- 1999-03-08 EP EP99917770A patent/EP1064498B1/de not_active Expired - Lifetime
- 1999-03-08 JP JP2000538190A patent/JP2002507717A/ja not_active Abandoned
- 1999-03-08 WO PCT/DE1999/000614 patent/WO1999049264A1/de active IP Right Grant
- 1999-03-08 DE DE59903398T patent/DE59903398D1/de not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
EP1064498A1 (de) | 2001-01-03 |
WO1999049264A1 (de) | 1999-09-30 |
DE59903398D1 (de) | 2002-12-19 |
JP2002507717A (ja) | 2002-03-12 |
US6374593B1 (en) | 2002-04-23 |
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