EP3617599A1 - Brenner mit verbesserter luft-kraftstoff-mischung - Google Patents

Brenner mit verbesserter luft-kraftstoff-mischung Download PDF

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Publication number
EP3617599A1
EP3617599A1 EP18192157.8A EP18192157A EP3617599A1 EP 3617599 A1 EP3617599 A1 EP 3617599A1 EP 18192157 A EP18192157 A EP 18192157A EP 3617599 A1 EP3617599 A1 EP 3617599A1
Authority
EP
European Patent Office
Prior art keywords
burner
tube
sleeve
mixing
section
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Withdrawn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
EP18192157.8A
Other languages
English (en)
French (fr)
Inventor
Anton Berg
Patrik Jaerling
Atanu Kumar Kundu
Anton Mannerfelt
Arturo Manrique Carrera
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 EP18192157.8A priority Critical patent/EP3617599A1/de
Priority to PCT/EP2019/073051 priority patent/WO2020048856A1/en
Publication of EP3617599A1 publication Critical patent/EP3617599A1/de
Withdrawn legal-status Critical Current

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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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • 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
    • F23R3/02—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
    • 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
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners

Definitions

  • the invention relates to a burner of a gas turbine with a swirler section, where fuel and air are introduced into the burner, a mixing section, to enhance the mixing of fuel and air, and an outlet section, to bring the fuel-air-mixture into the combustion chamber.
  • a representative burner of that kind which was the initiation for the invention, is described in the publication EP 2 815 184 B2 .
  • the swirler section comprises a few swirler vanes to swirl a stream of fuel and air in an axial and circumferential direction into the burner interior. Therefore the swirler vanes comprise several fuel nozzles and are spaced apart from each other in circumferential direction to enable an air stream into the burner interior.
  • the mixing section downstream of the swirler section, comprises a mixing volume to enhance the mixing of fuel and air. At common burners of that kind the mixing section is realized by the usage of a tube.
  • the outlet section which comprises the outlet of the burner to pass the fuel-air-mixture into the combustion chamber.
  • the object of the invention is the enhancement of the fuel-air-mixture.
  • the generic burner is determined for the usage at combustor of a gas turbine. Therefore the burner comprises in the fluid flow sequence a swirler section, a mixing section and an outlet section. Those three sections are generally arranged around a burner axis.
  • the swirler section comprises an air flow passage. Through the air flow passage a stream of air - oxygen containing fluid - can pass into the burner interior. To enable combustion in the combustor with the usage of the burner the necessary fuel is introduced at least partly into the swirler section, more precisely into the stream of air by the usage of a number of first fuel nozzles. Therefore the first fuel nozzles are located in the swirler section and are distributed around the air flow passage and/or within the air flow passage.
  • the specific arrangement and the specific design of the first fuel nozzles are not relevant for the current invention and known solutions from the state of the art could be used.
  • the mixing section is arranged downstream of the swirler section and is realized first of all by the usage of a tube.
  • the tube extends along the axis of the burner and has in general a constant inner and outer diameter. But the shape of the tube could also be different from that with a changing inner and outer diameter along the length of the tube and could have cutouts or additions.
  • Relevant for the mixing section is the generation of a mixing volume, which is defined inside the tube of the mixing section.
  • the mixing volume is downstream of the air fluid passage and conducts the stream of air and fuel from the air fluid passage through the mixing section. While the stream of air and fuel from the swirler section passes the mixing section the mixing of both fluids is enhanced.
  • the outlet section is downstream of the mixing section and comprises a burner outlet.
  • the burner outlet builds the downstream end of the mixing volume and enables the discharge of the mixed stream of air and fuel from the mixing volume into a combustion zone downstream of the burner.
  • the outlet section further comprises an annular bulge.
  • the annular bulge is arranged at the downstream end of the tube and can therefore be realized by a thickening of the tube end.
  • a sleeve supplements the mixing section.
  • the sleeve is arranged radially inwardly of the tube. This arrangement establishes an annular channel between the tube and the sleeve.
  • the arrangement of a sleeve inside of the tube further leads to the defining of the mixing volume inside the sleeve.
  • the mixing section comprises two separated volumes inside and outside the sleeve, wherein one volume, the annular channel, substantially surrounds the other volume, the mixing volume.
  • annular channel is closed at the upstream end. As result there is substantially no fluid connection between the air flow passage in the swirler section and the annular channel in the mixing section. In contrast the annular channel is open at the downstream end. As result the burner outlet connects the downstream end of both separated volumes, the mixing volume inside the sleeve and the annular channel outside the sleeve, so that one common stream of mixed air and fuel is discharged through the burner outlet of the outlet section.
  • the annular channel needs a sufficient size to enable its positive effect on the mixing of air and fuel.
  • the annular channel should have preferably a cross-sectional area of at least 10% of the cross-sectional area defined by the mixing volume.
  • Particular preferred the cross-sectional area defined by the annular channel is at least 20% of the cross-sectional area of the mixing volume.
  • the annular channel should not be to oversized compared to the mixing volume, so that the stream of air and fluid from the air flow passage is not hindered by a to small size of the mixing volume. Therefore the cross-sectional area defined by the annular channel should not exceed 50% of the cross-sectional area of the mixing volume. Particular preferred the cross-sectional area of the annular channel should be not more than 40% of the cross-sectional area defined by the mixing volume.
  • the swirler section At the swirler section air and fuel is introduced into the interior of the burner more precisely in the air flow passage.
  • the swirler section comprises advantageous two or more swirler vanes, which are distributed in circumference. Those swirler vanes could be arranged at the beginning of the air flow passage and/or within the air flow passage.
  • the swirler vanes are designed to increase a circumferential velocity component which leads to a better mixing of fuel and air especially in the downstream mixing section.
  • first fuel nozzles needs to be arranged at the swirler section, which are used to inject at least a portion of fuel in the swirler section.
  • the first fuel nozzles are distributed in the swirler section in axial direction and/or in circumferential direction. Thereby it is particularly advantageous if the first fuel nozzles are arranged within the swirler vanes.
  • the first fuel nozzles could be used to introduce a first kind of fuel into the burner.
  • the burner comprises preferably at the bulge at the downstream side of the burner a plurality of second fuel nozzles distributed around the circumference of the bulge.
  • the second fuel nozzles with an injection direction into the combustion chamber pointing at least radially outwardly.
  • a best mixture of air and fuel at the burner outlet could be archived if fuel is further introduced into the annular channel. Therefore it is an advantage if the tube and/or the bulge comprise a plurality of third fuel nozzles distributed at around its circumference. Accordingly the third fuel nozzles need to be angled at least radially inwardly. With the third fuel nozzles it is possible to introduce the first and/or the second kind of fuel. Dependent on the to be burned fuels also a different third kind of fuel could be introduced into the annular channel with the third fuel nozzles.
  • the length of the sleeve within the mixing section could be different. It is advantageous if the upstream side the sleeve starts at about the end of the swirler section. At the downstream side the sleeve with the open end of the annular channel the sleeve comprises a downstream end. Thereby the downstream end should preferably extend close to the burner outlet and therefore the downstream end is preferably located in the outlet section. The sleeve could extend exactly to the end of the burner or the downstream end has a certain distance to the burner outlet.
  • the burner with the inventive sleeve makes it possible to add further fourth fuel nozzles in the sleeve distributed around the circumference of the sleeve.
  • the fourth fuel nozzles could be used to introduce fuel into the mixing volume and/or into the annular channel.
  • the fourth fuel nozzles are arranged at the downstream end of the sleeve and in particular angled about parallel to the burner axis (which includes an angle to the burner axis up to 15°) to introduce the fuel into the combustion chamber located the downstream of the burner.
  • the air openings are formed to guide air at least partially in circumference and axially into the annular channel.
  • the sleeve is in connection with the tube by the usage of several connectors.
  • the connectors are at least firmly attached to the tube and to the sleeve. Thereby they are distributed at least in circumference. It is possible to use those connectors only at one axial position along the length of the mixing section, but it is also possible to arrange the connectors axially offset with each other at two or more times. In this case the sleeve could be made as one piece together with the tube. But it is also possible, for example, to weld the tube and/or the sleeve to the connectors.
  • spacers are used to keep a certain distance between the tube and the sleeve. Therefore several spacers are distributed at least in circumference, whereby they are connected with the tube and are in contact with the sleeve.
  • the fuel lines extend through the complete length of the sleeve from the upstream end to the downstream end to fourth fuel nozzles, respectively.
  • the fuel lines pass through the tube and the connectors and/or the spacers and then through the sleeve down to the fourth fuel nozzles. If the fuel lines cross the spacers it could be acceptable if a part of the fuel is lost in the contact of the spacer at the sleeve into the annular channel.
  • a further variation of the mixing in the mixing volume and in the annular channel could be reached by the implementation of several mixing openings arranged in the sleeve distributed in circumference. Obviously the mixing openings pass through the sleeve to connect the annular channel with the mixing volume. Here it is advantageous to form shape of the mixing volume so that air from the annular channel is guided into the mixing volume at least partially in circumference and axially.
  • Another solution offers the guidance of air, more precisely a mixture of air and fuel, from the mixing volume into the annular channel by a shape of the mixing openings which guide the air at least partially in circumference and axially into the annular channel.
  • the shape of the downstream end of the sleeve can be varied. Thereby it is advantageous if the downstream end has a corrugated shape around the circumference.
  • the distance between the tube and the downstream end of the tube varies in a repeating manner.
  • the least distance between the sleeve and the tube should be lower than 0,5 times the medium distance by the uses of a corrugated shape.
  • the most distance should be at least 1,5 times the medium distance. It is particular advantageous, if the least distance is less than 0,25 and/or the most distance is more than 2 times the medium distance between the sleeve and the tube.
  • the inventive burner enables the building of a new inventive combustor by the usage of a burner according the preceding description.
  • the advantage combustor comprises further a combustion chamber, wherein the burner is arranged upstream of the combustion chamber.
  • the burner is arranged upstream of the combustion chamber.
  • the burner comprises second fuel nozzles arranged in the bulge and/or fourth fuel nozzles arranged in the downstream end of the sleeve
  • the fuel nozzles are preferably designed to conduct the fuel into the combustion chamber.
  • FIG 1 an example for a burner 01 according the invention is shown in a perspective view.
  • the burner 01 extends along a burner axis 10 and could be divided into three different parts. Thereby it noteworthy, that there is no strict separation between the three parts and it is not relevant to define a dividing plane along the burner axis 10.
  • the first part at the upstream end is build by a swirler section 02.
  • air and fuel more precisely a first kind of fuel, are introduced into the burner. Therefore the swirler section 02 comprises in this example 4 swirler vanes 04, which define an air flow passage 03.
  • the air flow passage 03 starts at the free space between the swirler vanes 04, where air can pass freely the swirler vanes, and goes up to the downstream end of the swirler section 02.
  • a mixing section 12 builds the second part of the burner 01 and is arranged downstream of the swirler section 02.
  • the swirler section 12 is build first of all by a tube 24, which is in this example cylindrical.
  • the tube 24 surrounds a mixing volume 13 as a free space inside the mixing section, which follows directly the air flow passage 03 to guide the stream of air and fuel - while mixing them - to the downstream of the burner 01 located combustion chamber 09.
  • the mixing section 12 is followed by the outlet section 32.
  • a bulge 34 is arranged at the outlet section 32, which 34 is an extension of the tube 24 just with an enlarged outer diameter.
  • the mixing volume 13 goes downstream into the outlet section 32 up to a burner outlet 33.
  • the burner outlet 33 is the interface to a combustion chamber 09 downstream of the burner 01, whereby the stream of air and fuel is emitted from the burner 01 into the combustion chamber 09.
  • the key feature for the invention is the integration of a sleeve 14 in the mixing section 12 to divide the free space inside the tube 24 into the mixing volume 13 located inside the sleeve 14 and an annular channel 23 defined by the tube 24 on the outer side and by the sleeve 14 on the inner side.
  • the sleeve 14 extend on the downstream side up to a free downstream end 16, which 16 is located in the outlet section 32 in axial direction close to the burner outlet 33.
  • FIG. 2 shows an longitudinal cross section through the example of the burner 01 as shown in fig. 1 .
  • the swirler section 02 On the left hand side of the drawing there is the swirler section 02 with the swirler vanes 03 shown. Starting from the swirler vanes 04 the air flow passage 03 extends as free space up the downstream end of the swirler section.
  • the swirler vanes 03 are formed to guide the stream of air and fuel, which flows first of all in an axial direction, partly in circumferential direction to enhance the mixing of air and fuel.
  • Each of the swirler vanes 04 comprises several first fuel nozzles 05, which 05 are distributed further along the axial extent of the swirler vanes 04.
  • the swirler section 02 is followed downstream by the mixing section 12 with the tube 24. Downstream of the mixing section 12 the outlet section 32 with the annular bulge 34 is located and shown on the right hand side of the drawing.
  • the bulge 24 comprises in this example the same inner diameter as the tube 24 but with an increased outer diameter compared to the tube 24.
  • the function of the bulge 34 is to enable the mounting inside the combustor on the head end side of the combustion chamber 09.
  • the bulge 34 comprises an annular fuel line 36 and in connection with the fuel line 36 several second fuel nozzles 35. Those second fuel nozzles 35 are arranged on the downstream end of the outlet section 32 and are formed to inject the fuel partly in axial direction and partly radially outwards into the combustion chamber 09.
  • the tube 24 comprises several air openings 27, which 27 break through the tube 24 and is distributed around the circumference of the tube 24.
  • the air openings 27 are formed to guide the air from outside of the tube to the inside of the tube partially in axial direction and partly in circumferential direction.
  • On the upper side of the drawing a few air openings 27 spaced apart from each other in axial direction are shown.
  • the inventive sleeve 14 is arranged inside the tube 24 and extends downstream into the bulge 34 close to the burner outlet 33. With the sleeve 14 the free space inside the tube 24 (and bulge 34) is divided into the mixing volume 13 defined by the sleeve 14 and the annular channel 23 defined between the tube 24 on the radial outer side and sleeve 14 on the radial inner side.
  • annular channel 23 is closed at the upstream side, so that there is in particular no fluid connection to the air flow passage 03.
  • the annular channel 23 is open, so that both streams of air and fuel pass through the mixing volume 13 first and second through the annular channel 23 together the burner outlet 33.
  • the drawing shows further different solutions to connect the sleeve 14 with the tube 24.
  • a connector 26a is used to solidly connect the sleeve 14 with the tube 24. This will increase the stability of the solution, but the thermal expansion needs to be considered.
  • the solid connection could be realized by an integral forming of the mixing section 12 with the tube 24 and the sleeve 14 as one piece. It is also possible, for example, to weld the connector 26a at the tube 24 and/or at the sleeve 14.
  • a different kind of a connector 26b is shown at the end of the tube 24 on the lower side of the drawing.
  • This connector 26b formed like a strap will increase the flexibility especially in radial direction, so that different thermal expansion in radial direction could not destroy the connection between the tube 24 and the sleeve 14.
  • spacers 28, which 28 is shown on the upper side of the drawing could be solidly connected to the tube 24 but are only in contact to the sleeve 14. With this solution the concentricity of the sleeve 14 to the tube 24 could be ensured but compared to the connectors 26 thermal stress because of different thermal expansion is avoided.
  • the drawing shows different solutions to guide air from the outside of the burner 01 into the mixing section 12.
  • a plurality of mixing openings 17 could be arranged in the sleeve 14, whereby the mixing openings 17 are also distributed in circumferential direction.
  • the mixing openings 17 could be arranged two or more times along the axis of the burner.
  • the mixing openings are formed to guide air from the annular channel 23 into the mixing volume 13 partly in axial direction and also partly in circumferential direction.
  • air lines 18 are used for another solution to guide air into the mixing volume 13 within the connector 26a and the spacer 28.
  • the air lines 18 pass through the tube 24 and next though the connector 26a respectively through the spacer 28 and then through the sleeve 14.
  • the burner further comprises third fuel nozzles 15 and fourth fuel nozzles 25.
  • the third fuel nozzles 15 are arranged at the downstream end 16 of the sleeve 14 pointing downstream parallel to the burner axis 10 into the combustion chamber 09.
  • the fuel supply is realized by the integration of a branched fuel line partly through the tube 24, next to a connector 26b and partly through the sleeve 14.
  • To induct fuel into the annular channel 23 several fourth fuel nozzles 25 are arranged into the bulge 34, which each point into the annular channel 23 partly in axial direction and partly in circumferential direction.
  • the fuel nozzles 25 are in fluid connection with a further annular fuel line 37 inside the bulge 34.
  • the sleeve 64 inside the tube 74 again divides the space into the mixing volume 63 and the annular channel 73.
  • the difference to the solution shown in the fig. 1 is characterized by the shape of the free downstream end 66 of the sleeve 13.
  • the sleeve 64 in this example features a corrugated downstream end 66.
  • the distance between the downstream end 66 of the sleeve 64 and the annular bulge 84 varies between about 0,4 and about 2,0 of the medium distance between the sleeve 64 and the tube 74.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP18192157.8A 2018-09-03 2018-09-03 Brenner mit verbesserter luft-kraftstoff-mischung Withdrawn EP3617599A1 (de)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP18192157.8A EP3617599A1 (de) 2018-09-03 2018-09-03 Brenner mit verbesserter luft-kraftstoff-mischung
PCT/EP2019/073051 WO2020048856A1 (en) 2018-09-03 2019-08-29 Burner with improved air-fuel mixing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP18192157.8A EP3617599A1 (de) 2018-09-03 2018-09-03 Brenner mit verbesserter luft-kraftstoff-mischung

Publications (1)

Publication Number Publication Date
EP3617599A1 true EP3617599A1 (de) 2020-03-04

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ID=63490276

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18192157.8A Withdrawn EP3617599A1 (de) 2018-09-03 2018-09-03 Brenner mit verbesserter luft-kraftstoff-mischung

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EP (1) EP3617599A1 (de)
WO (1) WO2020048856A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111829787B (zh) * 2020-06-23 2022-07-22 江苏大学 一种能实现多重混合的可视化燃烧实验平台

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3973395A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Low emission combustion chamber
US6019596A (en) * 1997-11-21 2000-02-01 Abb Research Ltd. Burner for operating a heat generator
US6210152B1 (en) * 1998-09-16 2001-04-03 Abb Research Ltd. Burner for a heat generator and method for operating the same
US20020189257A1 (en) * 2000-12-11 2002-12-19 Christian Steinbach Premix burner arrangement for operating a combustion chamber field of technology
US20040139748A1 (en) * 2000-10-11 2004-07-22 Alstom (Switzerland) Ltd. Burner
EP3290804A1 (de) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Brenner mit kraftstoff- und luftzufuhr in einer wand des brenners
EP2815184B1 (de) 2012-04-10 2018-08-29 Siemens Aktiengesellschaft Brenner

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3973395A (en) * 1974-12-18 1976-08-10 United Technologies Corporation Low emission combustion chamber
US6019596A (en) * 1997-11-21 2000-02-01 Abb Research Ltd. Burner for operating a heat generator
US6210152B1 (en) * 1998-09-16 2001-04-03 Abb Research Ltd. Burner for a heat generator and method for operating the same
US20040139748A1 (en) * 2000-10-11 2004-07-22 Alstom (Switzerland) Ltd. Burner
US20020189257A1 (en) * 2000-12-11 2002-12-19 Christian Steinbach Premix burner arrangement for operating a combustion chamber field of technology
EP2815184B1 (de) 2012-04-10 2018-08-29 Siemens Aktiengesellschaft Brenner
EP3290804A1 (de) * 2016-08-31 2018-03-07 Siemens Aktiengesellschaft Brenner mit kraftstoff- und luftzufuhr in einer wand des brenners

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