WO2011032935A2 - Verfahren zum verbrennen wasserstoffreicher, gasförmiger brennstoffe in einem brenner sowie brenner zur durchführung des verfahrens - Google Patents
Verfahren zum verbrennen wasserstoffreicher, gasförmiger brennstoffe in einem brenner sowie brenner zur durchführung des verfahrens Download PDFInfo
- Publication number
- WO2011032935A2 WO2011032935A2 PCT/EP2010/063461 EP2010063461W WO2011032935A2 WO 2011032935 A2 WO2011032935 A2 WO 2011032935A2 EP 2010063461 W EP2010063461 W EP 2010063461W WO 2011032935 A2 WO2011032935 A2 WO 2011032935A2
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- burner
- hydrogen
- rich
- fuel
- isokinetic
- Prior art date
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
- F23D14/02—Premix gas burners, i.e. in which gaseous fuel is mixed with combustion air upstream of the combustion zone
-
- 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
-
- 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
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/9901—Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel
Definitions
- the present invention relates to the field of gas turbine combustion technology. It relates to a method for burning hydrogen-rich, gaseous fuels in a burner of a gas turbine according to the
- CO2 emitted by the atmosphere can be traced back to energy generation, where most of the fossil fuels in power plants generate electricity to be burned.
- a considerable savings potential can be achieved in the energy-producing sector to avoid further increasing CO2 emissions.
- a per se known and technically controllable way to reduce the CO2 emission in combustion power plants consists in the removal of carbon from the incinerating fuels.
- This requires a corresponding fuel pretreatment in which, for example, the partial oxidation of the fuel with oxygen and / or a pretreatment of the fuel is carried out with water vapor.
- Such pre-treated fuels usually contain a large proportion of H2 and CO, and depending on the mixing ratios, they have calorific values, which are generally lower than those of natural gas (NG).
- NG natural gas
- Such synthetically produced gases are therefore referred to as MBtu or LBtu gases, depending on the calorific value.
- the swirling flow forming inside this premix burner becomes liquid and / or gaseous fuel to form as homogeneous a mixture as possible
- fuels with a high hydrogen content as an alternative to or in combination with the combustion of conventional types of fuel, there are special requirements for the structural design of the premix burner systems used. So require synthesis gases for injection into
- Burner systems have a multiple fuel volume flow over comparable burners operated with natural gas, so that significantly
- Combustion of hydrogen-rich fuels is based on a strong dilution of diffusion flames (with inert media such as N2 and / or steam). Often, a reduction in power, i. a reduction in the flame temperature, resorted to.
- the fuel should be kept away from any walls as far as possible.
- Fig. 1 shows one of these ways in which the hydrogen-rich
- the AEV burner 10 which is shown in FIG. 1 as an example of a double-cone burner, has an arrangement of a double cone 11 and a subsequent mixing tube 12 along a burner axis 16. Through tangential slots in the
- Bicone 1 1 combustion air is introduced with twist into the interior of the double cone.
- combustion air is injected at the double cone 1 1 natural gas for a lean premix.
- Liquid fuel can be sprayed axially into the burner via a central nozzle 13.
- the hydrogen-rich fuel is (as the third fuel) injected stepped in the axial direction. This is done in the example shown at two Eindüsorten 14 (in the double cone 1 1) and 15 (in the mixing tube 12).
- a particular challenge for the lean premix burners fueled by hydrogen-rich fuels is the fulfillment of the "forced flashback" criterion, which uses high-energy ignition to specifically initiate a restrike Premix burner for hydrogen-rich fuels has so far met this criterion.
- the object is solved by the entirety of the features of claims 1 and 15.
- the method according to the invention is characterized in that the injection of the hydrogen-rich, gaseous fuel with respect to the combustion air is at least partially isokinetic, i. partly with the same direction and speed with respect to the combustion air.
- a partial isokinetic injection is to be understood as a single injection which, under the practical boundary conditions of a combustion chamber, leads to an injection in the direction and velocity of the combustion air. Practically, as partial isokinetic injection, injection is at the speed of Combustion air +/- 50% to understand. Typically, the isokinetic injection is realized with the speed of the combustion air +/- 20%.
- isokinetic injection at high burner load i. performed at high fuel gas mass flows and high hot gas temperatures near the design point.
- the fuel gas is typically injected at a rate at least twice as high as the speed of the
- Combustion air is.
- Wall surface required. An injection perpendicular to the wall surface or the flow is avoided. The angle between the direction of injection and the vertical is kept> 20 ° during isokinetic injection. As far as a sufficient penetration depth of the fuel gas into the combustion air can be achieved, an angle of 30 ° to 50 ° is selected. The injection vector is inclined by> 20 ° in from the vertical in the flow direction.
- the deviation of the velocity component of the fuel gas and the combustion air in the plane of the burner wall should be less than +/- 20 °. In the design point, for example, a deviation of less than +/- 10 ° is achieved.
- Combustion air in each plane should be less than +/- 20 °. In the design point, for example, a deviation of less than +/- 10 ° is achieved for each plane.
- Isokinetic injection can be carried out either in burners with swirling flow, for example in a double-cone burner, or in swirl-free burned-through burners.
- a further embodiment of the method according to the invention is characterized in that in a partially isokinetic manner the
- hydrogen-rich, gaseous fuel is injected through elongated rounded openings in the combustion air.
- the main axis of the oblong rounded openings is aligned parallel to the local air flow and the hydrogen-rich, gaseous fuel through the elongated rounded openings with a relation to the perpendicular to the swirl air flow in
- the inclination is> 20 °.
- an angle of 30 ° to 50 ° is selected.
- the velocity component of the injection of the fuel gas parallel to the plane of the burner wall should ideally be identical to the velocity component of the combustion air in this plane. In practice, deviations can not be avoided.
- the deviation of the velocity component of the fuel gas and the combustion air in the plane of the burner wall should be less than +/- 20 °. In the design point, for example, a deviation of less than +/- 10 ° is achieved. Accordingly, the alignment of the main axis of the oblong rounded opening can not be perfectly perfect for all operating states
- the deviation between the direction of flow and the orientation of the main axis should be less than +/- 20 °. in the
- Design point for example, a deviation of less than +/- 10 ° is reached.
- An oblong rounded opening is an opening which has a larger extent in one direction than in a second, perpendicularly oriented direction.
- An oblong rounded opening is for example a slot or an oval.
- the elongated rounded opening can be designed as an ellipse.
- the elongated ones rounded openings formed with an axis of symmetry in its greatest longitudinal extent. It has a so-called main axis which extends in the largest longitudinal direction and a minor axis, which is at right angles to the main axis occidentalrecht.
- the major axis is typically also an axis of symmetry of the oblong rounded opening.
- a further improvement can be achieved in that the burner wall immediately downstream of the elongated rounded openings through a
- An embodiment of the method according to the invention is characterized in that the hydrogen-rich, gaseous fuel is injected through elongated, rounded openings in a partially isokinetic manner into the swirling air flow of the combustion air of a double-cone burner. It is the
- Main axis of the elongated rounded openings in each case aligned parallel to the local swirl air flow.
- the hydrogen-rich, gaseous fuel is injected through the elongated, rounded openings, for example, with an inclination directed perpendicular to the swirl air flow in swirl air flow direction.
- the inclination is> 20 °.
- an angle of 30 ° to 50 ° is selected.
- the deviation of the velocity component of the fuel gas and the combustion air in the plane of the burner wall should be less than +/- 20 °. In the design point, for example, a deviation of less than +/- 10 ° is achieved. Accordingly, the alignment of the main axis of the oblong rounded opening can not be perfectly perfect for all operating states Alignment guaranteed. The deviation between the direction of flow and the orientation of the main axis should be less than +/- 20 °. in the
- Design point for example, a deviation of less than +/- 10 0 reached.
- the ratio of the major axis to the minor axis of the oblong rounded openings is greater than 2: 1. Practically, a range of 2: 1 to 5: 1 is well feasible. In a typical embodiment, the major axis to minor axis ratio of the elongated rounded openings is 3: 1.
- the cross-sectional area of the elongated, rounded openings corresponds to the cross-sectional area of circular openings with a
- the elongated rounded openings are close to the
- Output of the double cone arranged.
- this connection is for example referred to as the rear third of the longitudinal expansion of the burner in the main flow direction; typically, proximity is even limited to the rear fifth of the burner.
- a further improvement can be achieved in that the double cone immediately downstream of the elongated rounded openings through a
- Another embodiment of the invention is characterized in that hydrogen-rich, gaseous fuel protrudes through elongated, rounded openings at an opening in the interior of the double cone in the axial direction,
- Fuel lance is injected into the swirl air stream.
- the fuel lance is typically designed as a so-called long fuel lance. This is a lance that extends at least into the downstream half of the double cone. It is also conceivable within the scope of the invention that in the axial direction
- a mixing tube is arranged downstream of the double cone, and that the hydrogen-rich, gaseous fuel is injected through elongated rounded openings in the wall of the mixing tube in the swirling air flow.
- Another embodiment of the inventive method is characterized in that the injection of the hydrogen rich, gaseous
- Fuel with respect to the combustion air isokinetic, i. with the same direction and speed.
- the combustion air enters the interior of the double cone through louvers in the double cone, and the hydrogen-rich, gaseous
- Fuel is in the area of the louvers isokinetic in the incoming
- a comb injector is a hollow body having substantially the structure of a comb through which the fuel gas is introduced and distributed, as well as hollow tines emanating from this hollow body, through which the fuel gas is directed to Eindüseö réelleen at the ends of the tines.
- a comb injector may be a wedge-shaped tapered hollow body having on the side of the wedge tip a series of injection openings through which the fuel gas is injected.
- the structure of this embodiment corresponds in principle to that of the trailing edge of an air-cooled turbine blade
- a piggyback injector mounted on the double cone.
- a piggyback injector is one on the side of the air supply to a half shell of a Double cone attached hollow body through which the fuel gas is supplied. This hollow body tapers in the flow direction in a wedge shape. From the downstream edge is fuel gas via a series of injection openings
- the burner according to the invention is characterized in that the burner means for partially isokinetic or isokinetic injection of a
- An embodiment of the burner according to the invention is characterized in that the means for partially isokinetic or isokinetic injection of a hydrogen-rich gaseous fuel in the combustion air entering the burner elongated rounded openings comprise that the major axis of the elongated rounded openings in each case parallel to the local air flow is aligned, and that the elongated, rounded openings and / or bores or holes leading to the elongated, rounded openings are formed so that the hydrogen-rich, gaseous fuel through the elongated, rounded openings with respect to the perpendicular to the local air flow in Air flow direction directed inclination is injected.
- Burner wall executed.
- feeds are suitable, which lead normal to the burner surface through the burner wall and are designed with a deflection in the region of the elongated rounded openings.
- the inclination is> 20 °.
- the ratio of the major axis to the minor axis of the oblong rounded openings is greater than 2: 1. Practically, a range of 2: 1 to 5: 1 is well feasible. In a typical
- the ratio of the major axis to the minor axis of the elongated rounded openings is 3: 1.
- the cross-sectional area of the elongated, rounded openings corresponds to the cross-sectional area of circular openings with a
- the oblong rounded openings are arranged in the vicinity of the outlet of the burner.
- Double-cone burner The double-cone burner according to the invention is characterized in that the double-cone burner has a double cone and means for partially isokinetic or isokinetic injection of a hydrogen-rich, gaseous fuel into the combustion air entering the double cone, and that the injection means to a fuel supply for
- An embodiment of the inventive double-cone burner is characterized in that the means for partially isokinetic or isokinetic injection of a hydrogen-rich, gaseous fuel in the in the
- Double cone entering combustion air elongated rounded openings include that the major axis of the oblong rounded openings is aligned parallel to the local swirl air flow, respectively, and that the elongated rounded openings are formed so that the hydrogen rich, gaseous fuel is injected through the elongated, rounded openings with an inclination directed perpendicular to the swirl air flow in swirl air flow direction.
- the inclination is> 20 °.
- the ratio of the major axis to the minor axis of the oblong rounded openings is greater than 2: 1. Practically, a range of 2: 1 to 5: 1 is advantageous. In a typical
- the ratio of the major axis to the minor axis of the elongated rounded openings is 3: 1.
- the cross-sectional area of the elongated, rounded openings corresponds to the cross-sectional area of circular openings with a
- the oblong rounded openings are arranged in the vicinity of the outlet of the double cone.
- the oblong rounded openings are close to the exit of one adjoining the double cone
- a further embodiment of the double-cone burner according to the invention is characterized in that the double cone has louvers for the entry of combustion air into the interior of the double cone, and that the means for partially isokinetic or isokinetic injection of a hydrogen-rich, gaseous fuel into the combustion air entering the double cone a plurality of arranged in the region of the louvers and tangentially oriented fuel nozzles comprises.
- the fuel nozzles are part of a Kamminjektors or a seated on the double cone piggyback.
- fuel lance be provided with elongated rounded openings.
- Ambient air understood, but for example, a mixture of air and recirculated exhaust gases, or mixed with an inert gas air mixture.
- Fig. 1 in longitudinal section a double cone burner AEV type for three different fuels with axially stepped injection of a hydrogen-rich, gaseous fuel;
- FIG. 2 is a perspective side view of a burner for MBtu fuel with round gas injection openings at the burner outlet for the injection of hydrogen rich, gaseous
- FIG. 3 in a section in the plan view (Fig. 3a) and in section (Fig.
- FIG. 6 shows the isokinetic injection according to FIG. 4 by means of a
- Figure 7 shows in side view (Figure 7a) and upstream (Figure 7b) another embodiment for the isokinetic injection of hydrogen rich gaseous fuel with additional partial isokinetic injection via elliptical openings in a long fuel lance;
- hydrogen-rich fuel with H2 »50% can be achieved in that the gas injection openings 18 in FIG. 2 are characterized by elongated, rounded openings,
- elliptical opening 24 is reproduced in the double-cone burner 20 'of FIG. 3 in plan view (FIG. 3 a) and in section (FIG. 3 b).
- the elliptical openings 24 are characterized by the following characteristic properties:
- the main axis is aligned with the local swirl air flow 23, which is formed by the double cone from the incoming combustion air 17.
- the cross-sectional area of the elliptical openings 24 corresponds to the
- This type of injection is ultimately an injection into a Querströmu but can be described as “partially isokinetic", because thereby due to the inclination, the shape and the dimensions of the opening
- effusion cooling immediately downstream of the elongated, rounded openings 24 significantly reduces the tendency of the injectors to hold the flame. This is done by corresponding, finely distributed outflow holes 25, as shown in Fig. 3a. Effusion cooling allows the use of larger fuel jets, resulting in greater penetration, better mixing and less NOx (as well as less dilution by N2 or steam).
- the fuel is injected into the louvers of a double-cone burner (e.g., of the EV or AEV type), the
- Injection direction is precisely aligned with the local air flow and the
- the hydrogen-rich fuel is injected in stages (in the present example of FIG. 4, two stages 28 and 29 available). This ensures that the fuel injection is almost isokinetic over the entire load range and increases the flexibility of operation.
- FIG. 5 and FIG. 6 show two ways of achieving the desired isokinetic injection:
- a comb injector 31 is inserted to expose the hydrogen-rich fuel 19 from the center of the air slot 26
- the fuel to be injected can also be introduced directly through a plenum integrated in the shell of the double cone 1 1 and injected through the trailing edge of the shell.
- the burner parts for the premixing of natural gas and the injection of liquid fuels such as oil remain unaffected so that the burners can operate as a three-fuel burner.
- inventive burner are shown schematically. On the left in the figure, a top view of the burner in the direction of flow is shown. He has in this example a simple right-angled flow cross-section, which is limited by the burner walls 1.
- section A - A the longitudinal extent of the burner 2 is shown in the flow direction.
- the combustion air 17 flows parallel to the burner axis 16 through the twist-free burner 2.
- the hydrogen-rich, gaseous fuel 19 is isokinetically injected through the oblong rounded openings 24 through the burner wall 1 in the combustion air 17 at an angle ⁇ to the flow normal.
- the flow normal 4 is the perpendicular to the air flow direction, which in the example parallel to
- the elongated, rounded openings 24 in this example are elongated holes having a length to width ratio of about 2: 1.
- the effusion cooling 3 of the burner wall is injected through a field of effusion holes 25 through the cooling air.
- Burners are selected with a circular cross-section. This can be flowed through without swirling or swirling. LIST OF REFERENCE NUMBERS
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- General Engineering & Computer Science (AREA)
Abstract
Description
Claims
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE112010003677.2T DE112010003677B4 (de) | 2009-09-17 | 2010-09-14 | Verfahren zum verbrennen wasserstoffreicher, gasförmiger brennstoffe in einem brenner sowie brenner zur durchführung des verfahrens |
US13/405,396 US8549860B2 (en) | 2009-09-17 | 2012-02-27 | Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH01438/09 | 2009-09-17 | ||
CH01438/09A CH701905A1 (de) | 2009-09-17 | 2009-09-17 | Verfahren zum Verbrennen wasserstoffreicher, gasförmiger Brennstoffe in einem Brenner sowie Brenner zur Durchführung des Verfahrens. |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US13/405,396 Continuation US8549860B2 (en) | 2009-09-17 | 2012-02-27 | Method for combusting hydrogen-rich, gaseous fuels in a burner, and burner for performing said method |
Publications (2)
Publication Number | Publication Date |
---|---|
WO2011032935A2 true WO2011032935A2 (de) | 2011-03-24 |
WO2011032935A3 WO2011032935A3 (de) | 2012-03-29 |
Family
ID=41446342
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2010/063461 WO2011032935A2 (de) | 2009-09-17 | 2010-09-14 | Verfahren zum verbrennen wasserstoffreicher, gasförmiger brennstoffe in einem brenner sowie brenner zur durchführung des verfahrens |
Country Status (4)
Country | Link |
---|---|
US (1) | US8549860B2 (de) |
CH (1) | CH701905A1 (de) |
DE (1) | DE112010003677B4 (de) |
WO (1) | WO2011032935A2 (de) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
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CN111649352B (zh) * | 2020-06-02 | 2021-08-06 | 中国人民解放军国防科技大学 | 一种自持式流体振荡器及火箭基组合循环发动机 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0321809B1 (de) | 1987-12-21 | 1991-05-15 | BBC Brown Boveri AG | Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner |
WO1993017279A1 (en) | 1992-02-26 | 1993-09-02 | United Technologies Corporation | Premix gas nozzle |
EP0780629A2 (de) | 1995-12-21 | 1997-06-25 | ABB Research Ltd. | Brenner für einen Wärmeerzeuger |
EP1070915A1 (de) | 1999-07-22 | 2001-01-24 | Asea Brown Boveri AG | Vormischbrenner |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
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CH678757A5 (de) * | 1989-03-15 | 1991-10-31 | Asea Brown Boveri | |
DE4304213A1 (de) * | 1993-02-12 | 1994-08-18 | Abb Research Ltd | Brenner zum Betrieb einer Brennkraftmaschine, einer Brennkammer einer Gasturbogruppe oder Feuerungsanlage |
DE4416650A1 (de) * | 1994-05-11 | 1995-11-16 | Abb Management Ag | Verbrennungsverfahren für atmosphärische Feuerungsanlagen |
GB9410233D0 (en) * | 1994-05-21 | 1994-07-06 | Rolls Royce Plc | A gas turbine engine combustion chamber |
US5813232A (en) * | 1995-06-05 | 1998-09-29 | Allison Engine Company, Inc. | Dry low emission combustor for gas turbine engines |
DE59709281D1 (de) * | 1997-11-25 | 2003-03-13 | Alstom | Brenner zum Betrieb eines Wärmeerzeugers |
EP0981016B1 (de) * | 1998-08-19 | 2004-01-07 | ALSTOM (Switzerland) Ltd | Brenner zum Betrieb einer Brennkammer |
EP1504222B1 (de) * | 2002-05-16 | 2007-07-11 | Alstom Technology Ltd | Vormischbrenner |
US7000403B2 (en) * | 2004-03-12 | 2006-02-21 | Power Systems Mfg., Llc | Primary fuel nozzle having dual fuel capability |
JP4913746B2 (ja) | 2004-11-30 | 2012-04-11 | アルストム テクノロジー リミテッド | 予混合バーナー内の水素を燃焼する方法及び装置 |
ATE480737T1 (de) * | 2005-06-17 | 2010-09-15 | Alstom Technology Ltd | Brenner zur vormischartigen verbrennung |
DE102005061486B4 (de) | 2005-12-22 | 2018-07-12 | Ansaldo Energia Switzerland AG | Verfahren zum Betreiben einer Brennkammer einer Gasturbine |
EP2058590B1 (de) | 2007-11-09 | 2016-03-23 | Alstom Technology Ltd | Verfahren zum Betrieb eines Brenners |
US8104286B2 (en) * | 2009-01-07 | 2012-01-31 | General Electric Company | Methods and systems to enhance flame holding in a gas turbine engine |
-
2009
- 2009-09-17 CH CH01438/09A patent/CH701905A1/de unknown
-
2010
- 2010-09-14 WO PCT/EP2010/063461 patent/WO2011032935A2/de active Application Filing
- 2010-09-14 DE DE112010003677.2T patent/DE112010003677B4/de active Active
-
2012
- 2012-02-27 US US13/405,396 patent/US8549860B2/en active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0321809B1 (de) | 1987-12-21 | 1991-05-15 | BBC Brown Boveri AG | Verfahren für die Verbrennung von flüssigem Brennstoff in einem Brenner |
WO1993017279A1 (en) | 1992-02-26 | 1993-09-02 | United Technologies Corporation | Premix gas nozzle |
EP0780629A2 (de) | 1995-12-21 | 1997-06-25 | ABB Research Ltd. | Brenner für einen Wärmeerzeuger |
EP1070915A1 (de) | 1999-07-22 | 2001-01-24 | Asea Brown Boveri AG | Vormischbrenner |
Also Published As
Publication number | Publication date |
---|---|
DE112010003677A5 (de) | 2012-12-13 |
US8549860B2 (en) | 2013-10-08 |
US20120210727A1 (en) | 2012-08-23 |
DE112010003677B4 (de) | 2023-10-26 |
CH701905A1 (de) | 2011-03-31 |
WO2011032935A3 (de) | 2012-03-29 |
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