EP1645807A1 - Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur - Google Patents

Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur Download PDF

Info

Publication number
EP1645807A1
EP1645807A1 EP04024186A EP04024186A EP1645807A1 EP 1645807 A1 EP1645807 A1 EP 1645807A1 EP 04024186 A EP04024186 A EP 04024186A EP 04024186 A EP04024186 A EP 04024186A EP 1645807 A1 EP1645807 A1 EP 1645807A1
Authority
EP
European Patent Office
Prior art keywords
burner
air
gas
combustion
fuel
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.)
Withdrawn
Application number
EP04024186A
Other languages
German (de)
English (en)
Inventor
Andreas Heilos
Berthold Köstlin
Bernd Dr. Prade
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP04024186A priority Critical patent/EP1645807A1/fr
Priority to ES05801280T priority patent/ES2354703T3/es
Priority to EP05801280A priority patent/EP1800062B1/fr
Priority to CN2005800346422A priority patent/CN101040149B/zh
Priority to PCT/EP2005/054948 priority patent/WO2006040269A1/fr
Publication of EP1645807A1 publication Critical patent/EP1645807A1/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • 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
    • F23R3/36—Supply of different fuels
    • 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
    • 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
    • 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
    • F23D2900/14241—Post-mixing with swirling means
    • 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
    • F23R2900/00002—Gas turbine combustors adapted for fuels having low heating value [LHV]

Definitions

  • the invention relates to a burner for the combustion of a low-calorie combustible gas, with an air duct extending along a burner axis for the supply of combustion air and with a fuel gas channel, which is designed for a high volume flow on low calorific fuel gas, wherein the fuel gas channel and the air duct open in a mixing area ,
  • the invention further relates to a method for operating a burner in which a fossil fuel gasified and gasified fossil fuel fed as a low calorific synthesis gas to the burner, mixed with combustion air to a synthesis gas-air mixture and is burned in a combustion chamber.
  • burners and operating methods for burners have been developed in recent years, which have particularly low emissions of nitrogen oxides (NO X ). It is often emphasized that such burners are not only with a fuel, but possibly with different fuels, such as oil, natural gas and / or coal gas optionally or even operated in combination to increase the security of supply and flexibility in operation. Such burners are described for example in EP 0 276 696 B1.
  • the combustible constituents of synthesis gases are essentially carbon monoxide and hydrogen.
  • the calorific value of the synthesis gas is about 5 to 10 times smaller compared to the calorific value of natural gas.
  • Main constituents in addition to carbon monoxide and hydrogen are inert components such as nitrogen and / or water vapor and possibly also carbon dioxide. Due to the low calorific value consequently high volume flows of fuel gas must be supplied through the burner of the combustion chamber. This has the consequence that for the combustion of low calorific fuels - such as synthesis gas - a separate fuel gas channel, which is designed for a high volume flow of low calorific fuel gas, must be provided.
  • the combustor in the combustor associated with the gas turbine must be designed as a dual or multi-fuel burner which is compatible with both the synthesis gas and the secondary fuel, e.g. Natural gas or fuel oil can be applied as needed.
  • the respective fuel is supplied via a specially constructed fuel passage in the burner of the combustion zone.
  • EP 1 277 920 A1 a method for operating a burner of a gas turbine and a power plant with integrated coal gasification is shown.
  • a fossil fuel is gasified and gaseous fossil fuel is fed as synthesis gas to the burner associated with the gas turbine for combustion.
  • the synthesis gas is divided into a first partial flow and a second partial flow and the partial flows are fed to the burner for combustion separately.
  • the quality of mixing between synthesis gas and combustion air at the flame front is an important influencing variable for avoiding temperature peaks and thus for minimizing the formation of thermal nitrogen oxides.
  • a spatially good mixture of combustion air and synthesis gas is particularly difficult due to the high volume flows of required synthesis gas and the correspondingly large spatial extent of the mixing area.
  • the lowest possible production of nitrogen oxides is an essential requirement for combustion, in particular for combustion in the gas turbine plant of a power plant.
  • the formation of nitrogen oxides increases exponentially rapidly with the combustion flame temperature.
  • An inhomogeneous mixture of fuel and air results in a certain distribution of the flame temperatures in the combustion region. The maximum temperature of such a distribution determined by the said exponential relationship of nitrogen oxide formation and flame temperature significantly the amount of undesirable nitrogen oxides formed.
  • the object of the invention is to provide a burner for the combustion of low-calorie combustion gases, in particular synthesis gases, which leads to a lower nitrogen oxide formation.
  • Another object of the invention is to provide a method of operating a burner in which a low calorie fuel gas is burned.
  • a burner for combustion of a low calorific fuel gas with an extending along a burner axis air duct for the supply of combustion air and a fuel gas channel, which is designed for a high volume flow of low calorific fuel gas is, wherein the fuel gas channel and the air channel open into a mixing region, wherein in the air duct, a swirling element is provided for generating turbulent combustion air.
  • the invention is based on the consideration that in the known burners for combustion of low-calorie combustion gases, the nitrogen oxide formation is too high due to insufficient mixing of the low calorific fuel gas with the combustion air in the mixing area in view of future pollutant limits.
  • a swirling element into the air duct, the degree of turbulence of the air mass flow is increased even before the combustion air is mixed with the low-calorie combustion gas.
  • the invention has recognized that it is particularly important in this context to perform a turbulence gradient increase only in the microscopic range, i. large turbulence bales with pronounced tailing areas and in particular with upstream flow components must be avoided, since otherwise there is a risk of a flashback in the burner itself.
  • a significant advantage of the invention is that a particularly good mixture of combustion air and fuel gas is achieved by the microturbulent flow of combustion air, at the same time caused by the swirling pressure loss is low. It is achieved by the mixture of low-calorie fuel gas and turbulence-prone combustion air in the mixing area a significantly improved spatial homogeneity of the fuel gas-air mixture achieved in the mixing area.
  • the microturbulences ensure a particularly intimate mixing while avoiding a flashback.
  • the air duct preferably has an orifice region which directly adjoins the mixing region in terms of flow is arranged, wherein the swirling element is arranged in the mouth region.
  • the swirling element is therefore designed so that the producible turbulent flow of the combustion air at the swirling element has substantially no areas of backflowing combustion air. In this way, a safe operation of the burner is ensured in the combustion of low-calorie fuel gas and in particular the risk of a flashback in the burner itself prevented.
  • the air channel is formed as an annular channel which surrounds the fuel gas channel concentrically.
  • the swirling element is particularly suitable for use in an annular air duct. There are at least two, preferably three circles provided.
  • the connecting surface is less than half of the area enclosed by the larger boundary ring circular area in the swirling element. Further preferably, the diameter of the larger boundary ring is less than about 1 m, in particular 50 to 80 cm.
  • the swirl element is for use in small flow channels, such as e.g. in the air duct of the burner, suitable.
  • the deflection elements associated with a circle are equal to one another spaced. This achieves a uniform turbulence over the entire connecting surface and thus brings about a particularly homogeneous mixing of the low-calorie combustible gas, in particular of the synthesis gas, with the combustion air in the mixing region.
  • each deflection element tapers from the connection surface to a tear-off edge for generating vertebrae.
  • it has approximately trapezoidal or triangular shape.
  • Preferred dimensions of the associated at a respective circle deflecting elements are inclined in the same direction. Preferably arranged on adjacent circles deflecting elements are inclined in opposite directions. This arrangement of the deflection causes a homogenization over larger areas of the air flow takes place in addition to the local good mixing by the turbulence. This is particularly important to ensure turbulence in the microscopic range at the confluence of the low calorific fuel gas and the combustion air in the mixing area with regard to achieving a homogeneous synthesis gas combustion air mixture during burner operation.
  • the burner is designed such that swirl vanes are arranged in the air duct upstream of the swirling element. This ensures that the combustion air in the air duct is already pre-impounded by means of a swirl blade, before the swirling combustion air flow through the swirling element experiences a turbulence increase in the microscopic range downstream of the swirling element. Furthermore, it is thereby achieved that a swirling element having the above-described advantageous effects on the homogeneity of the mixture of low-calorie combustion gas and combustion air in the mixing region also in connection with swirl blades can be used, which ultimately act favorably on the stability of the combustion of the low-calorie fuel gas.
  • At least one of the swirl vanes is designed as a hollow blade, from which, if necessary, a high-calorie fuel, in particular natural gas, can be introduced into the air duct.
  • a high-calorie fuel in particular natural gas
  • This embodiment makes it possible to use a uniform injection of high-calorie fuel, such as in a natural gas operation of the burner, from a swirl blade designed as a hollow blade with a further homogenizing effect on the fuel / air mixture in combination with the above-mentioned advantages.
  • the burner is thus advantageously designed for various operating conditions and operating materials, so that optionally gaseous fuels with completely different specific calorific values, for example natural gas and coal gas, can be used.
  • high calorific fuel e.g.
  • Natural gas the swirl blades are used for injection of high calorific fuel (premix combustion), while operating with a low calorie fuel gas of the fuel gas channel, which is designed for a high volume flow of fuel gas, is supplied with synthesis gas.
  • the burner is thus designed to operate selectively with a synthesis gas from a gasifier and a secondary or substitute fuel as a dual or multi-fuel burner, which is compatible with both the synthesis gas and the secondary fuel, e.g. high-calorie natural gas or fuel oil can be applied as needed.
  • the respective fuel is supplied to the combustion zone via a respective fuel passage, optionally the fuel gas channel in the synthesis gas mode or the hollow blade in the natural gas mode.
  • the burner as a premix or hybrid burner for use in gas turbine plants, with an air supply channel, in particular an annular channel, which encloses at least three further, in particular concentric to the air supply channel arranged annular channels for the supply of fluidic media, two of these channels are used to supply a pilot burner and wherein a pilot flame for maintaining the combustion can be generated by the pilot burner.
  • the object directed to a method according to the invention is achieved by a method for operating a burner in which a fossil fuel gasified and gasified fossil fuel fed as a low calorific synthesis gas to the burner, and the combustion air mixed into a synthesis gas-air mixture and in a combustion chamber is burned, and immediately before the mixture of the synthesis gas with the combustion air, the degree of turbulence of the air mass flow is increased.
  • a fossil fuel gasified and gasified fossil fuel fed as a low calorific synthesis gas to the burner, and the combustion air mixed into a synthesis gas-air mixture and in a combustion chamber is burned, and immediately before the mixture of the synthesis gas with the combustion air, the degree of turbulence of the air mass flow is increased.
  • microturbulences are generated.
  • this is used in the operation of a burner of a gas turbine.
  • the power plant 24 comprises a gas turbine plant 25 with a gasification plant 23 upstream of the gas turbine plant 25 for a fossil fuel B.
  • the gas turbine plant 25 comprises a compressor 14, a combustion chamber 16 and a turbine 18 connected downstream of the combustion chamber 16.
  • the compressor 14 and the turbine 18 are coupled together via a common rotor shaft 15.
  • Downstream of the turbine 18, an electric generator 19 is coupled via a generator shaft 22 to the turbine.
  • the combustion chamber 16 comprises a combustion chamber 17 and a burner 1 projecting into the combustion chamber 17 for combustion of a low-calorie combustible gas SG, which is obtained from the gasification device 23 by gasification of the fossil fuel B.
  • air 10 is sucked into the compressor 14 and is highly compressed there.
  • the compressed air 10 is then supplied as combustion air 10 to the burner 1 and mixed with the low-calorie fuel gas SG.
  • the resulting fuel gas-air mixture is burned in the combustion chamber 17, with very hot combustion gases.
  • the hot combustion gases are fed to the turbine 18 where they relax to perform work and put both the compressor-side rotor shaft 15 and the generator shaft 22 in rotation. In this way, electric power is generated, which the generator 19 emits for distribution in an electrical network.
  • the partially cooled and expanded combustion gases are discharged as exhaust gas 20.
  • These exhaust gases 20 are polluting, in particular nitrogen oxides are present in the exhaust gas, which form at the high combustion temperatures in the combustion chamber 17.
  • Increased nitrogen oxide emission also occurs when the fuel gas / air mixture is not mixed sufficiently homogeneously or experiences a temporal or spatial change in the mixture field. This generally leads to an unfavorable mixture of the low-calorie combustible gas SG with the combustion air 10 and to a considerable increase in the nitrogen oxide formation rate in the combustion process.
  • the invention provides a remedy in which it proposes a solution that significantly improves the quality of mixing between the synthesis gas SG and the combustion air 10 at the flame front, thus ensuring a low-emission synthesis gas operation of the burner 1, wherein temperature peaks are avoided and thus a Lowering of the thermal nitrogen oxide formation compared to conventional synthesis gas burners is achieved.
  • FIG. 2 shows a burner 1 for combustion of the low-calorie combustible gas SG according to the invention.
  • the burner 1 is approximately rotationally symmetrical with respect to an axis 12.
  • a directed along the axis 12 pilot burner 9 with a fuel supply channel 8 and this concentrically enclosing air supply annular channel 7 is concentrically surrounded by a fuel ring channel 3.
  • the fuel supply channel and the fuel ring channel 3 are designed for fuels with high calorific value, such as for exposure to natural gas or fuel oil.
  • the fuel ring channel 3 is concentrically enclosed by a fuel gas channel 26 which is at a high volume flow low calorie fuel gas SG is designed.
  • the fuel gas channel 26 is viewed downstream in the flow direction of the fuel gas SG partially concentrically enclosed by an air supply annular channel 2.
  • an air supply annular channel 2 In the air supply annular channel 2 is a - schematically illustrated - ring of swirl vanes 5 is installed. At least one of these swirl blades 5 is formed as a hollow blade 5a. It has an inlet 6 formed by several openings for a fuel supply of a high-calorie fuel.
  • the fuel ring channel 3 opens into this hollow blade 5a. Downstream of the swirl vane ring 5 is a - shown schematically - swirling element 4 is installed in the air duct 2.
  • the fuel gas channel 26 and the air channel 2 each open into a common mixing region 27, where the low-calorie fuel gas SG is mixed intensively with the combustion air 10.
  • the turbulence element 4 in the air duct 2 provides for the generation of turbulent combustion air 10, so that a good mixing result in the mixing region 27 and thus a low-emission synthesis gas operation of the burner 1 is achieved. It is particularly advantageous for the mixing result if, as shown in FIG. 2, the air duct 2 has an opening region 28 directly fluidically adjacent to the mixing region 27, wherein the swirling element 4 is arranged in the mouth region.
  • the swirling element 4 is designed such that the producible turbulent flow of the combustion air 10 at the swirling element 4 has substantially no regions of combustion air 10 flowing back.
  • the burner 1 can optionally be operated via the pilot burner 9 as a diffusion burner, with a high-calorific Fuel 11 is used. Frequently, however, it is also used as a premix burner; ie high calorific fuel 11 and combustion air 10 are first mixed and then fed to the combustion.
  • the pilot burner 9 serves to maintain a pilot flame, which stabilizes the combustion during premix burner operation with a possibly changing fuel-air ratio.
  • the fuel 11 is introduced from the fuel channel 3 into a hollow blade 5a of the swirl vane ring 5 in the premixing mode of the burner 1 and introduced from there via the inlet 6 into the combustion air 10 in the air channel 2.
  • the low-calorie synthesis gas SG with the combustion air 10 is first transferred downstream into the mixing region 27 where it is intimately mixed and burned in a combustion zone (not shown).
  • FIG. 3 which shows a plan view of a swirling element 4
  • FIG. 4 which shows a swirling element 4 provided with the same reference number in a side view
  • each web 54 From an inner boundary ring 52 lead distributed over the ring circumference a plurality of webs 54 to an outer boundary ring 53.
  • the center of the outer boundary ring 53 lies on the axis of symmetry 59 of the inner boundary ring 52 and the webs 54 are directed normal to the inner boundary ring 52.
  • the connecting surface 56 represents the lateral surface of a truncated cone between the inner delimiting ring 52 and the outer delimiting ring 53.
  • Arranged on each web 54 are trapezoidal plane deflection elements 51 pointing in the interior of the truncated cone.
  • the wide side 51 a of each deflecting element 51 is connected to a web 54.
  • the deflection elements are arranged at equal distances from each other along three concentric circles 55a, 55b, 55c, which are concentric with the axis of symmetry 59.
  • the deflection elements 51 are inclined relative to a normal one of the connection axis 56, wherein the deflection elements 51 in each case are guided along a circle 55a, 55b, 55c in the same direction, by a circle 55a, 55b, 55c to an adjacent circle 55a, 55b, 55c are inclined in opposite directions.
  • the combustion air 10 is impressed on a microturbulence, which continues into the mixing region 27 inside.
  • the volumetric flows of low calorific fuel gas SG and turbulent combustion air 10 out of the air duct 2 which are introduced into the mixing region 27 are mixed particularly intensively and homogeneously by these microturbulences in the combustion air 10.
  • the inclination of the deflection elements 51 characterizes the main flow of the combustion air 10 in addition to secondary flows 58, which in addition to the locally good mixing due to the turbulence, a homogenization of the fuel gas-air mixture over the entire cross-sectional area of the mixing region 27 (see FIG 2) favor.
  • This embodiment of the swirling element 4 which only influences the air flow in the air duct 2 during the synthesis gas operation, has the consequence that the pressure loss caused by the turbulence is particularly low.
  • the burner 1 of the invention is therefore particularly suitable for operation in a power plant 24 with integrated gasification of a fossil fuel to a synthesis gas SG, for example coal gas.
  • the burner 1 is arranged in a combustion chamber 16 of a gas turbine plant 25.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP04024186A 2004-10-11 2004-10-11 Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur Withdrawn EP1645807A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP04024186A EP1645807A1 (fr) 2004-10-11 2004-10-11 Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur
ES05801280T ES2354703T3 (es) 2004-10-11 2005-09-30 Quemador para la combustión de un gas de combustión de bajo poder calorífico y método para operar un quemador.
EP05801280A EP1800062B1 (fr) 2004-10-11 2005-09-30 Bruleur destine a la combustion d'un gaz combustible a faible pouvoir calorifique et procede pour faire fonctionner un bruleur
CN2005800346422A CN101040149B (zh) 2004-10-11 2005-09-30 用于燃烧低热值燃气的燃烧器和燃烧器的工作方法
PCT/EP2005/054948 WO2006040269A1 (fr) 2004-10-11 2005-09-30 Bruleur destine a la combustion d'un gaz combustible a faible pouvoir calorifique et procede pour faire fonctionner un bruleur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04024186A EP1645807A1 (fr) 2004-10-11 2004-10-11 Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur

Publications (1)

Publication Number Publication Date
EP1645807A1 true EP1645807A1 (fr) 2006-04-12

Family

ID=34926939

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04024186A Withdrawn EP1645807A1 (fr) 2004-10-11 2004-10-11 Brûleur pour gas à faible capacité calorifique et méthode d'utilisation d'un tel brûleur
EP05801280A Expired - Fee Related EP1800062B1 (fr) 2004-10-11 2005-09-30 Bruleur destine a la combustion d'un gaz combustible a faible pouvoir calorifique et procede pour faire fonctionner un bruleur

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05801280A Expired - Fee Related EP1800062B1 (fr) 2004-10-11 2005-09-30 Bruleur destine a la combustion d'un gaz combustible a faible pouvoir calorifique et procede pour faire fonctionner un bruleur

Country Status (4)

Country Link
EP (2) EP1645807A1 (fr)
CN (1) CN101040149B (fr)
ES (1) ES2354703T3 (fr)
WO (1) WO2006040269A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2161502A1 (fr) 2008-09-05 2010-03-10 Siemens Aktiengesellschaft Brûleur à prémélange pour un combustible pauvre et riche
EP2169307A1 (fr) 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Buse à combustible
EP2629011A1 (fr) 2008-09-29 2013-08-21 Siemens Aktiengesellschaft Buse de combustible
WO2014114533A1 (fr) * 2013-01-24 2014-07-31 Siemens Aktiengesellschaft Système de brûleur possédant des éléments de turbulence

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2169308A1 (fr) * 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Alimentation en carburant et procédé d'injection du carburant
EP2312215A1 (fr) * 2008-10-01 2011-04-20 Siemens Aktiengesellschaft Brûleur et procédé de fonctionnement d'un brûleur
CN101581449B (zh) * 2009-06-25 2010-12-29 上海应用技术学院 一种生物质气天然气混烧低NOx烧嘴及其应用
DE102009038845A1 (de) * 2009-08-26 2011-03-03 Siemens Aktiengesellschaft Drallschaufel, Brenner und Gasturbine
CN103134078B (zh) 2011-11-25 2015-03-25 中国科学院工程热物理研究所 一种阵列驻涡燃料-空气预混器
JP5889754B2 (ja) * 2012-09-05 2016-03-22 三菱日立パワーシステムズ株式会社 ガスタービン燃焼器
FR3011911B1 (fr) 2013-10-14 2015-11-20 Cogebio Bruleur de gaz pauvre
DE102014207428A1 (de) * 2014-04-17 2015-10-22 Siemens Aktiengesellschaft Brenner mit Drallschaufel
DE102018114870B3 (de) 2018-06-20 2019-11-28 Deutsches Zentrum für Luft- und Raumfahrt e.V. Brennersystem und Verfahren zur Erzeugung von Heißgas in einer Gasturbinenanlage
CN109237514B (zh) * 2018-08-08 2024-02-23 中国华能集团有限公司 一种用于燃气轮机的双管路气体燃料燃烧器
CN109489069A (zh) * 2018-11-28 2019-03-19 中国华能集团有限公司 一种燃气轮机多种气体燃料混烧燃烧器结构及使用方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4833878A (en) * 1987-04-09 1989-05-30 Solar Turbines Incorporated Wide range gaseous fuel combustion system for gas turbine engines
EP0276696B1 (fr) 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
US5451160A (en) * 1991-04-25 1995-09-19 Siemens Aktiengesellschaft Burner configuration, particularly for gas turbines, for the low-pollutant combustion of coal gas and other fuels
DE4409918A1 (de) * 1994-03-23 1995-09-28 Abb Management Ag Brenner zum Betrieb einer Brennkammer
US6148603A (en) * 1995-12-29 2000-11-21 Asea Brown Boveri Ag Method of operating a gas-turbine-powered generating set using low-calorific-value fuel
EP1277920A1 (fr) 2001-07-19 2003-01-22 Siemens Aktiengesellschaft Méthode pour opérer une chambre de combustion d'une turbine a gaz et centrale

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH609438A5 (fr) * 1976-02-27 1979-02-28 Fascione Pietro
JPS5913822A (ja) * 1982-07-14 1984-01-24 Mitsui Eng & Shipbuild Co Ltd 低発熱量ガスの燃焼方法および低発熱量ガス用バ−ナ
US4930430A (en) * 1988-03-04 1990-06-05 Northern Engineering Industries Plc Burners
CN2107591U (zh) * 1991-11-07 1992-06-17 鞍山钢铁公司 自动火焰可调烧嘴
JP4127858B2 (ja) * 1996-12-20 2008-07-30 シーメンス アクチエンゲゼルシヤフト 液体燃料用バーナ

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0276696B1 (fr) 1987-01-26 1990-09-12 Siemens Aktiengesellschaft Brûleur hybride pour fonctionnement en prémélange au gaz et/ou au mazout, notamment pour turbines à gaz
US4833878A (en) * 1987-04-09 1989-05-30 Solar Turbines Incorporated Wide range gaseous fuel combustion system for gas turbine engines
US5451160A (en) * 1991-04-25 1995-09-19 Siemens Aktiengesellschaft Burner configuration, particularly for gas turbines, for the low-pollutant combustion of coal gas and other fuels
DE4409918A1 (de) * 1994-03-23 1995-09-28 Abb Management Ag Brenner zum Betrieb einer Brennkammer
US6148603A (en) * 1995-12-29 2000-11-21 Asea Brown Boveri Ag Method of operating a gas-turbine-powered generating set using low-calorific-value fuel
EP1277920A1 (fr) 2001-07-19 2003-01-22 Siemens Aktiengesellschaft Méthode pour opérer une chambre de combustion d'une turbine a gaz et centrale

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2161502A1 (fr) 2008-09-05 2010-03-10 Siemens Aktiengesellschaft Brûleur à prémélange pour un combustible pauvre et riche
EP2169307A1 (fr) 2008-09-29 2010-03-31 Siemens Aktiengesellschaft Buse à combustible
EP2629011A1 (fr) 2008-09-29 2013-08-21 Siemens Aktiengesellschaft Buse de combustible
US8959922B2 (en) 2008-09-29 2015-02-24 Siemens Aktiengesellschaft Fuel nozzle with flower shaped nozzle tube
WO2014114533A1 (fr) * 2013-01-24 2014-07-31 Siemens Aktiengesellschaft Système de brûleur possédant des éléments de turbulence

Also Published As

Publication number Publication date
CN101040149A (zh) 2007-09-19
EP1800062A1 (fr) 2007-06-27
CN101040149B (zh) 2010-06-16
ES2354703T3 (es) 2011-03-17
WO2006040269A1 (fr) 2006-04-20
EP1800062B1 (fr) 2010-11-03

Similar Documents

Publication Publication Date Title
EP1800062B1 (fr) Bruleur destine a la combustion d'un gaz combustible a faible pouvoir calorifique et procede pour faire fonctionner un bruleur
EP1723369B1 (fr) Bruleur a premelange et procede pour bruler un gaz pauvre
EP0675322B1 (fr) Brûleur à prémélange
EP0781967B1 (fr) Chambre de combustion annulaire pour turbine à gaz
DE4426351B4 (de) Brennkammer für eine Gasturbine
EP2329196B1 (fr) Brûleur et procédé d'utilisation d'un brûleur
DE102010017779B4 (de) Radiale Einlassleitschaufeln für einen Brenner
DE4411623A1 (de) Vormischbrenner
DE102008037480A1 (de) Mager vorgemischte Dual-Fuel-Ringrohrbrennkammer mit Radial-Mehrring-Stufendüse
DE102010037412B4 (de) Zweibrennstoffdüse für eine Turbomaschine
EP1504222B1 (fr) Bruleur a premelange
DE102008003300A1 (de) Brennstoffflexibler dreifach gegenläufiger Verwirbler und Verfahren zu dessen Benutzung
EP0687860A2 (fr) Chambre de combustion à allumage automatique
DE19510744A1 (de) Brennkammer mit Zweistufenverbrennung
EP0956475A2 (fr) Bruleur pour solides fluides, procede pour actionner un bruleur et element de tourbillonnement
EP2171353A1 (fr) Brûleur à prémélange et procédé de fonctionnement d'un brûleur à prémélange
WO2015150114A1 (fr) Brûleur, turbine à gaz munie dudit brûleur et injecteur de combustible
CH699911B1 (de) Brennkammer und Verfahren zum Mischen eines Druckluftstroms.
WO2012016748A2 (fr) Chambre de combustion de turbine à gaz
DE102005038662B4 (de) Brennkopf und Verfahren zur Verbrennung von Brennstoff
DE102004027702A1 (de) Injektor für Flüssigbrennstoff sowie gestufter Vormischbrenner mit diesem Injektor
WO2006015968A1 (fr) Bruleur, turbine a gaz et fonctionnement du bruleur
DE4415916A1 (de) Verfahren und Vorrichtung zur Verbrennung eines fließfähigen Brennstoffs
EP2808610A1 (fr) Chambre de combustion d'une turbine à gaz avec injection tangentielle comme injection pauvre tardive
DE112010003677B4 (de) Verfahren zum verbrennen wasserstoffreicher, gasförmiger brennstoffe in einem brenner sowie brenner zur durchführung des verfahrens

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

AKX Designation fees paid
STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20061013

REG Reference to a national code

Ref country code: DE

Ref legal event code: 8566