EP1800062A1 - Bruleur destine a la combustion d'un gaz combustible a faible pouvoir calorifique et procede pour faire fonctionner un bruleur - Google Patents

Bruleur destine a la combustion d'un gaz combustible a faible pouvoir calorifique et procede pour faire fonctionner un bruleur

Info

Publication number
EP1800062A1
EP1800062A1 EP05801280A EP05801280A EP1800062A1 EP 1800062 A1 EP1800062 A1 EP 1800062A1 EP 05801280 A EP05801280 A EP 05801280A EP 05801280 A EP05801280 A EP 05801280A EP 1800062 A1 EP1800062 A1 EP 1800062A1
Authority
EP
European Patent Office
Prior art keywords
burner
air
combustion
gas
channel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP05801280A
Other languages
German (de)
English (en)
Other versions
EP1800062B1 (fr
Inventor
Andreas Heilos
Berthold Köstlin
Bernd 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 EP05801280A priority Critical patent/EP1800062B1/fr
Publication of EP1800062A1 publication Critical patent/EP1800062A1/fr
Application granted granted Critical
Publication of EP1800062B1 publication Critical patent/EP1800062B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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.
  • EP 0956475 B1 shows a burner for high calorie fuels, e.g. Natural gas or oil which has a largely homogeneous mixture of high calorific fuels and combustion air.
  • a swirling element is introduced within the air supply annular channel in such a way that the inlet of the high-calorie fuel is arranged downstream of the swirling element within the air channel.
  • the fuel is introduced to achieve a homogeneous mixing by means of a plurality of inlet channels which are arranged in the swirl vanes within the air supply channel. This mixture is then introduced into the combustion chamber for combustion.
  • burners and operating methods for burners have been developed in recent years, which have particularly low emissions of nitrogen oxides (NO x ). It will In many cases, it is important that such burners can be operated not only with one fuel but, if possible, with different fuels, for example oil, natural gas and / or coal gas, either selectively or even in combination, in order to ensure security of supply and supply
  • fuels for example oil, natural gas and / or coal gas
  • Hydrocarbon compounds exist, the combustible components of synthesis gases are substantially 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.
  • a separate fuel gas channel which is designed for a high volume flow of low calorific fuel gas, must be provided.
  • the burner in the combustion chamber associated with the gas turbine for selectively operating a gas and steam turbine plant with a synthesis gas from a gasification or a secondary or substitute fuel, the burner in the combustion chamber associated with the gas turbine as two- or
  • Be designed multi-fuel burner which can be applied to both the synthesis gas and with the secondary fuel, such as natural gas or fuel oil 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. In the method of operating the burner, a fossil fuel is gasified and gassed fossil fuel as synthesis gas of the
  • Gas turbine associated burner is sent 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.
  • a stepped synthesis gas operation is possible, which is adapted to the load of the gas turbine.
  • the object of the invention is a burner for the combustion of low calorific fuel gases, in particular synthesis gases, indicate that 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 the air channel has an orifice region directly fluidically adjacent to the mixing region and wherein in the mouth region, 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 carry out a turbulence gradient increase only in the microscopic range, ie large eddy bales with pronounced trailing regions and in particular with upstream flow components must be avoided, otherwise there is a risk of a flashback in the burner itself.
  • the air duct in this case has an orifice region which is arranged directly adjacent to the mixing region in terms of flow, wherein the swirling element is arranged in the mouth area. It has been found that the arrangement of the swirling element in the immediate vicinity of the mixing region in the mouth region leads to a particularly effective formation of air vortex, so that the generated turbulences propagate to the adjoining mixing region largely trouble-free in the microscopic range. As a result, both a spatial and a temporally largely homogeneous mixture of low calorific fuel gas and combustion air and thus a reduced nitrogen production is achieved. Surprisingly, it has been shown that the exact positioning of the swirling element in the immediate vicinity of the mixing region in the mouth region leads to a particularly effective formation of air vortex, so that the generated turbulences propagate to the adjoining mixing region largely trouble-free in the microscopic range. As a result, both a spatial and a temporally largely homogeneous mixture of low calorific fuel gas and combustion air and
  • Verwirbelungselements in the air duct is particularly critical for the mixing result in the mixing area.
  • 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 region, a significantly improved spatial homogeneity of the fuel gas-air mixture in the mixing region.
  • the microturbulences ensure a particularly intimate mixing while avoiding a flashback.
  • Another advantage of the invention is the arrangement of the swirling element in the immediate vicinity of the mixing area in the mouth region. This leads to a particularly effective turbulence. In order to achieve a good mixing result as far as possible further installations in the wake region of the swirling element should be avoided.
  • the swirling element is designed so that the producible turbulent flow of the Combustion air at Verwirbelungselement has substantially no areas of back-flowing 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 hereby comprises:
  • 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 equally spaced from one another. 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. Preference is given to arranged on adjacent circles
  • the burner is designed so that upstream of the
  • Swirling element swirl vanes are arranged in the air duct. 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, this achieves that a swirling element with the advantageous effects described above on the homogeneity of the mixture of low calorific fuel gas and
  • Combustion air in the mixing area can also be used in conjunction with swirl blades, which ultimately act favorably on the stability of the combustion of the low-calorie combustible gas.
  • at least one of the swirl blades can be formed as a hollow blade, from which, if required, a high-calorie fuel, in particular natural gas, can be introduced into the air duct.
  • a high-calorie fuel in particular natural gas
  • the burner can be designed as a premix or hybrid burner for use in gas turbine systems, 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 supplying fluidic media, two of these channels for supplying a Serving pilot burner and wherein the pilot burner, a pilot flame to maintain combustion is generated.
  • 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 and 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 and 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.
  • 3 shows a swirling element in plan view
  • 4 shows a swirling element in side view
  • 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 includes a
  • 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 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 which substantially improves the quality of mixing between the synthesis gas SG and the combustion air 10 at the flame front, thus ensuring a low pollutant synthesis gas Be ⁇ operation of the burner 1, wherein temperature peaks are avoided and Thus, a reduction of the thermal nitrogen oxide formation is achieved over conventional synthesis gas burners.
  • FIG. 2 shows a burner 1 for burning the low calorie burner
  • Fuel 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 is concentrically surrounded by an air supply annular channel 7.
  • the fuel supply channel 8 is designed for fuels with high calorific value, such for exposure to natural gas or fuel oil.
  • the fuel gas channel 26 is designed for a high volume flow of low-calorie fuel gas SG.
  • the fuel gas channel 26 is in the flow direction of the fuel gas SG viewed downstream 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, wherein one of these swirl blades 5 as
  • Hollow blade 5a may be formed.
  • the swirl blade 5 may, if necessary, an inlet formed by openings for a fuel supply of a have high calorific fuel.
  • 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 swirling element 4 in the air channel 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.
  • 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. This ensures that no flammable combustible gas-air mixture to the swirling element 4 can flow back appreciably and thus no combustion at the swirling element 4 is stabilized, which could have a damage of the swirling element result. A permanent operation of the burner 1 with synthesis gas SG with low nitrogen oxide formation is thus achieved.
  • the burner 1 can be operated via the pilot burner 9 as a diffusion burner, wherein a high-calorie fuel is used. Alternatively, it can also be used as a premix burner; ie a high calorific fuel and combustion air 10 are first mixed and then fed to the combustion. In that case, the pilot burner 9 serves to maintain a pilot flame which stabilizes combustion during premix burner operation with a possibly varying fuel-air ratio. In a synthesis gas operation of the burner 1, 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 A possible particularly advantageous design is shown in FIG. 3 in a plan view of a swirling element 4.
  • the swirling element 4 does not necessarily have to occupy the entire channel height of the air channel 2.
  • FIG 3 which shows a plan view of a swirling element 4 and FIG 4, with a the same reference numerals provided turbulator 4 in a side view, are discussed in more detail:
  • the connecting surface 56 constitutes the lateral surface of a
  • trapezoidal, planar deflection elements 51 are arranged in the interior of the truncated cone.
  • the wide side 51 a of each deflecting element 51 is connected to a web 54.
  • 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, the deflection elements 51 being inclined in the same direction along a circle 55a, 55b, 55c from one circle 55a, 55b, 55c to an adjacent circle 55a, 55b, 55c.
  • 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 local 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).
  • 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.

Abstract

L'invention concerne un brûleur (1) destiné à la combustion d'un gaz combustible à faible pouvoir calorifique (SG). Ce brûleur (1) comprend un canal d'air (2) qui s'étend le long d'un axe (12) du brûleur et qui sert à acheminer de l'air de combustion (10), ainsi qu'un canal de gaz combustible (26) dimensionné pour un haut débit volumétrique de gaz à faible pouvoir calorifique (SG), ce canal de gaz combustible (26) et ce canal d'air (2) débouchant dans une zone de mélange (27). Selon l'invention, pour que la combustion de gaz de synthèse dans ce brûleur (1) génère de faibles émissions d'oxydes d'azote, un élément de turbulence (4) est placé dans le canal d'air (2) pour produire un air de combustion (10) turbulent. Cet élément de turbulence est disposé dans une zone d'ouverture (28) directement en communication fluidique avec la zone de mélange (27). L'invention concerne en outre un procédé pour faire fonctionner un brûleur à gaz de synthèse (1). Ce procédé consiste à augmenter de façon significative le degré de turbulence du flux massique d'air sur une échelle microscopique juste avant le mélange du gaz de synthèse (SG) avec l'air de combustion (10) pour permettre l'obtention d'un mélange gaz de synthèse-air homogène dans le temps et dans l'espace.
EP05801280A 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 Expired - Fee Related EP1800062B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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

Applications Claiming Priority (3)

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
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
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

Publications (2)

Publication Number Publication Date
EP1800062A1 true EP1800062A1 (fr) 2007-06-27
EP1800062B1 EP1800062B1 (fr) 2010-11-03

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 Before (1)

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

Country Status (4)

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

Cited By (2)

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WO2015055916A1 (fr) 2013-10-14 2015-04-23 Cogebio Brûleur de gaz pauvre
EP3584501A1 (fr) 2018-06-20 2019-12-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de brûleur et procédé de production de gaz chaud dans une installation de turbine à gaz

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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
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Publication number Priority date Publication date Assignee Title
WO2015055916A1 (fr) 2013-10-14 2015-04-23 Cogebio Brûleur de gaz pauvre
EP3584501A1 (fr) 2018-06-20 2019-12-25 Deutsches Zentrum für Luft- und Raumfahrt e.V. Système de brûleur et procédé de production de gaz chaud dans une installation de turbine à gaz

Also Published As

Publication number Publication date
WO2006040269A1 (fr) 2006-04-20
CN101040149B (zh) 2010-06-16
ES2354703T3 (es) 2011-03-17
CN101040149A (zh) 2007-09-19
EP1645807A1 (fr) 2006-04-12
EP1800062B1 (fr) 2010-11-03

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