EP3314165B1 - A premixed dual fuel burner with a tapering injection component for main liquid fuel - Google Patents
A premixed dual fuel burner with a tapering injection component for main liquid fuel Download PDFInfo
- Publication number
- EP3314165B1 EP3314165B1 EP16745457.8A EP16745457A EP3314165B1 EP 3314165 B1 EP3314165 B1 EP 3314165B1 EP 16745457 A EP16745457 A EP 16745457A EP 3314165 B1 EP3314165 B1 EP 3314165B1
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- European Patent Office
- Prior art keywords
- burner
- injection component
- fuel
- injection
- liquid fuel
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- 239000000446 fuel Substances 0.000 title claims description 163
- 238000002347 injection Methods 0.000 title claims description 115
- 239000007924 injection Substances 0.000 title claims description 115
- 239000007788 liquid Substances 0.000 title claims description 86
- 230000009977 dual effect Effects 0.000 title claims description 33
- 238000002485 combustion reaction Methods 0.000 claims description 72
- 238000011144 upstream manufacturing Methods 0.000 claims description 20
- 239000007789 gas Substances 0.000 claims description 13
- 239000002737 fuel gas Substances 0.000 claims description 12
- 238000000034 method Methods 0.000 description 17
- 239000000203 mixture Substances 0.000 description 13
- 230000015572 biosynthetic process Effects 0.000 description 11
- 239000012530 fluid Substances 0.000 description 6
- 239000007921 spray Substances 0.000 description 4
- 239000000470 constituent Substances 0.000 description 3
- 230000001419 dependent effect Effects 0.000 description 3
- 230000001154 acute effect Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000008021 deposition Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000013021 overheating Methods 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000011796 hollow space material Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000037361 pathway Effects 0.000 description 1
- 230000002123 temporal effect Effects 0.000 description 1
Images
Classifications
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- 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
- F23C1/00—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air
- F23C1/08—Combustion apparatus specially adapted for combustion of two or more kinds of fuel simultaneously or alternately, at least one kind of fuel being either a fluid fuel or a solid fuel suspended in a carrier gas or air liquid and gaseous fuel
-
- 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
- F23D11/40—Mixing tubes or chambers; Burner heads
-
- 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
- F23D11/40—Mixing tubes or chambers; Burner heads
- F23D11/402—Mixing chambers downstream of the nozzle
-
- 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
- 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
- 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
- F23C2900/07001—Air swirling vanes incorporating fuel injectors
-
- 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
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- 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
- F23C2900/07021—Details of lances
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Description
- The present invention relates to turbomachine components and more particularly to a burner for a dual fuel based combustion chamber for a turbomachine.
- In modern day turbomachines, dual fuel i.e. a liquid fuel and a gaseous fuel, are used advantageously as main fuels in many applications for example in Lean Premix combustions, Dry Low NOx combustions, and so and so forth. In present day turbomachines that employ dual fuel combustion techniques, a burner assembly in a combustion section includes a burner head connected to a swirl generator or swirler that in turn is connected to a mixer or premixing pathway or section. The burner assembly is connected to or assembled with a combustion chamber. In combustion section of the turbomachines that use the dual fuel techniques, the main fuels, distinct from pilot fuel supplies, are mostly both gaseous and liquid.
- The basic technique in such dual fuel combustions is to premix the main fuel with air from a compressor of the turbomachine before igniting the combustion mixture, i.e. mixture of the air from the compressor and the main fuel, in the combustion chamber. Usually the air from the compressor is mixed with the main gaseous fuel, either inside the swirler or just before introduction into the swirler, and then swirled by the swirler to create a swirling flow of the air and the main gaseous fuel. This swirling flow of the pressurized air from the compressor and the main gaseous fuel then enters from the swirler into the premixing section. At the premixing section the pressurized air from the compressor and the main gaseous fuel are allowed to mix well before exiting into the combustion chamber or the combustion space where the combustion mixture undergoes combustion.
- In dual fuel combustors, or combustion sections, the main liquid fuel is discharged by a nozzle positioned at the burner head. The main liquid fuel after exiting the nozzle, preferably in atomized form, enters the swirler and then continues into the premixing section and finally into the combustion chamber where the main liquid fuel participates in the combustion reaction.
- Also known are burners with a central fuel lance to provide for gaseous and/or liquid fuel. One configuration of a cylindrical central fuel lance is known from the patent publication
US 2010/0273117 A1 , which covers the features specified in the preamble ofclaim 1. - Further,
US 5,791,894 A shows a conical inner body within a premix burner, to generate a swirl about an axis by swirling of a medium around the inner body. The inner body may comprise optinally also a bore to provide liquid fuel and/or air to a front region of the combustion space. - However, there are some disadvantages in the scheme of presently known dual fuel burners and as described above. Firstly, discharging of the main liquid fuel at the burner head interferes with the swirl generation performed by the swirler by increasing the aerodynamic disturbances inside the swirler. Furthermore, the aerodynamic disturbances also adversely affect an axial flow of the combustion mixture and/or its components, i.e. flow of the combustion mixture and/or its constituents from a burner head side of the burner towards the combustion chamber. Secondly, since the main liquid fuel is discharged before the swirler or just at the beginning of the swirler, in some cases parts of the main liquid fuel get deposited on surfaces of inside walls of the swirler and/or the premixing section. This deposition of the main liquid fuel residues leads to clogging of the interiors of the swirler and especially the interiors of the premixing section. The clogging results in loss of efficiency and in most cases the turbomachine operation is required to be stopped to clean the main liquid fuel residues deposited on surfaces of inside walls of the swirler and/or the premixing section.
- Furthermore, as a result of the clogging and the aerodynamic disturbances, as mentioned above, a flow of combustion mixture and/or components of the combustion mixture is jeopardized which leads into increased possibility of formation of recirculation zones within burner interiors such as the premixing section. The formation of the recirculation zones within the burner interiors is undesirable, as it may result into overheating of the burner components for example the premixing section and/or the swirler. A continued problem of overheating over an extended period of time may result into damaging of the parts of the burner components i.e. the premixing section, the swirler, etc. Moreover, as a result of the formation of the undesired recirculation zones within the premixing section, efficiency of the turbomachines in operation is reduced.
- An object of the present technique is to obviate the above mentioned disadvantages and to ensure that recirculation zones for the combustion are formed at a desired spatial position in the combustion chamber or the combustion space. It is undesirable to allow formation of the recirculation zone within the premixing section of the burner. Achieving this object increases the combustion efficiency and thus the efficiency of the overall turbomachine, elongates operational life of the components of the burner and associated structures that may otherwise get over heated due to formation or extension of recirculation zones at undesirable spatial positions within the burner interiors, and stabilizes the combustion reaction due to control on the recirculation zone formation and its spatial position in the combustion chamber.
- The above objects are achieved by a premixed dual fuel burner according to
claim 1 of the present technique. Advantageous embodiments of the present technique are provided in dependent claims. Features ofclaim 1 may be combined with features of dependent claims, and features of dependent claims can be combined together. - According to the present technique, a premixed dual fuel burner for a combustion chamber of a turbomachine is presented. The premixed dual fuel burner, hereinafter referred to as the burner, includes a burner head, a burner interior, a swirler, a premixing section and an injection component. The swirler is arranged in series between the burner head and the premixing section. The burner head includes a burner head end. The burner interior is elongated along a main axis of the burner and is formed of an upstream side and a downstream side. The upstream side is disposed between the burner head and the downstream side. The upstream side is fluidly connected to the downstream side, i.e. the upstream side and the downstream side are continuous and together form the burner interior. A part of the burner interior enclosed by the swirler is the upstream side of the burner interior and the other part of the burner interior enclosed by the premixing section is the downstream side of the burner interior. The swirler includes an inlet section. The inlet section is configured to introduce air and a main gas fuel into the burner interior. The premixing section has a burner outlet through which the premixing side is configured to be arranged or fixed or assembled with the combustion chamber such that the downstream side is fluidly connected to the combustion chamber.
- The injection component has a tapering structure positioned along the main axis. The tapering structure of the injection component extends from the burner head into the burner interior. The injection component has a burner head side and an injection side. The injection component tapers from the burner head side to the injection side along the main axis. The injection component includes at least one liquid fuel outlet at the injection side. The injection component is configured to introduce a main liquid fuel into the burner interior through the at least one liquid fuel outlet. The main liquid fuel introduced in the burner interior by the injection component via the liquid fuel outlet is directed towards the combustion chamber. The injection side of the injection component is disposed in the burner interior.
- Besides, at least one of the at least one liquid fuel outlet is at a side - i.e. a side face of the tapering - of the injection side of the injection component. Thus, the liquid fuel outlet is angled in respect of an axial direction of the burner.
- The injection component is particularly a fuel lance.
- The tapering structure of the injection component minimizes aerodynamic disturbances in the burner interior, and thus ensuring efficient functioning of the swirler in generating swirl which in turn aids in achieving a desired spatial position of a central recirculation zone, preferably the central recirculation zone or the main recirculation zone is formed and limited completely within the combustion chamber, and thus minimizing possibilities of a flashback into the burner interior. Furthermore, the tapering structure of the injection component facilitates an axial velocity, i.e. along the main axis, of the combustion mixture i.e. the main fuel gas and the air mixture exiting from the swirler into the premixing section and continuing further into the combustion chamber. The facilitation of the axial velocity results from directed flow of the combustion mixture and/or its constituents along the tapering structure. The tapering form of the injection component acts as a guide to the flow of main gas fuel and air facilitating the axial flow direction. This also helps in achieving the desired spatial position of the recirculation zone, which is preferably positioned in the combustion chamber and outside the premixing section. The positioning of the recirculation zone outside the premixing zone and within the combustion chamber minimizes possibilities of a flashback into the burner interior for example into the premixing section interior.
- Furthermore, by introducing the main liquid fuel via the liquid fuel outlet on the injection component extending into the burner interior and by directing the main liquid fuel towards the combustion chamber, it is ensured that deposition of residues of the main liquid fuel is minimized in inner walls of the swirler and/or the premixing section, and thus clogging of the burner cavity enclosed by the swirler and/or the premixing section is at least partially prevented which in turn leads to proper swirl action by the swirler and/or proper fuel premixing action by the premixing section and which subsequently also helps in formation of the recirculation zone at the desired spatial position and in increasing efficiency of the turbomachine.
- In an embodiment of the burner, the tapering structure of the injection component is a conical structure. The conical structure has preferably a regular geometrical shape i.e. the conical structure is symmetrical about a longitudinal axis of the conical structure. The tapering of the structure is smooth and gradual. The regular conical structure helps in further reduction of the aerodynamic disturbances in the burner interior. Moreover, the conical shape being a regular shape is easy to manufacture and assemble.
- In another embodiment of the burner, the tapering structure of the injection component is arranged coaxially to the main axis. The longitudinal axis of the conical structure overlaps with the main axis. This adds symmetry to the burner interior and this facilitates the further reduction of the aerodynamic disturbances in the burner interior.
- In another embodiment of the burner, a first distance is between 20% and 80% of a second distance. The first distance is a distance measured along the main axis between the at least one liquid fuel outlet and the burner head end. The second distance is a distance measured along the main axis between the burner outlet of the premixing section and the burner head end, in other words a length of the burner interior along the main axis. Thus, the main liquid fuel is transported, confined within the injection component, at least partially through parts of the burner interior that are enclosed by the swirler and/or the premixing section and is delivered into the burner interior at a desired position within the burner interior depending on a ratio of the first and the second distances. By maintaining a proper ratio of the first and the second distances, the main liquid fuel is ejected or injected out into the burner interior at a desirable position in the burner interior thus at least partially decreasing the risk of spraying the liquid fuel on surfaces of the inner walls of the swirler and/or the premixing section.
- In another embodiment of the burner, the injection component is configured to be longitudinally adjustable along the main axis such that a position of the at least one liquid fuel outlet of the injection component is changeable from a first location along the main axis to a second location along the main axis. Thus a desirable position in the burner interior to eject or inject out the main liquid fuel can be adjusted during an operation of the turbomachine and/or may be set as desired between two operations of the turbomachine.
- In another embodiment of the burner, the at least one liquid fuel outlet is positioned in the upstream side of the burner interior. This provides an embodiment in which, if so desired for a particular mode of operation of the turbomachine, the main liquid fuel can be injected out of the liquid fuel outlet before the premixing section.
- In another embodiment of the burner, the at least one liquid fuel outlet is positioned in the downstream side of the burner interior. This provides an embodiment in which, if so desired for a particular mode of operation of the turbomachine, the main liquid fuel can be injected out of the liquid fuel outlet into the burner interior enclosed by the premixing section. Furthermore, this embodiment ensures that spraying of the liquid fuel on surfaces of the inner wall of the swirler and at least a part of the surfaces of the inner wall of the premixing section are minimized.
- In another embodiment of the burner, one of the at least one liquid fuel outlet is at an end of the injection side of the injection component, particularly at a tip of the injection component. The end is the most axial position of the injection component. This ensures that a spray or a fluid stream of the main liquid fuel is directed along the main axis towards the combustion chamber. According to the invention a further one - also called "first additional outlet" - of the at least one liquid fuel outlet is at a side of the injection side of the injection component. The first additional outlet is configured to introduce the main liquid fuel into the burner interior. The first additional outlet is at a side of the injection side of the injection component. This provides an additional direction in which an additional spray or an additional fluid stream of the main liquid fuel is directed towards the combustion chamber. This additional direction is at an acute angle to the main axis and is directed towards the combustion chamber.
- According to the invention, the at least one liquid fuel outlet is at a side of the injection side of the injection component. This ensures that a spray or a fluid stream of the main liquid fuel is directed towards the combustion chamber along an angle to the main axis. This direction is at an acute angle to the main axis and is directed towards the combustion chamber. In a related embodiment, the injection component includes a second additional outlet configured to introduce the main liquid fuel into the burner interior. The second additional outlet is at an end of the injection side of the injection component. This provides an additional direction, i.e. along the main axis, in which an additional spray or an additional fluid stream of the main liquid fuel is directed towards the combustion chamber.
- In another embodiment of the burner, the inlet section of the swirler includes at least one air inlet and at least one main fuel gas inlet. Thus the main gas fuel and the air from a compressor of the turbomachine may be introduced into the burner interior separately at the swirler. In an alternate embodiment, the main gas fuel and the air from the compressor may be introduced via a common inlet.
- In another embodiment of the burner, the at least one air inlet and/or the at least one main fuel gas inlet is arranged tangentially along the swirler with respect to the main axis. This provides a commonly used embodiment of the swirler and thus the burner of the present technique may be realized, operated and manufactured with ease.
- In another embodiment of the burner, the swirler has a conical frustum shape having a top side and a bottom side. A cross-section of the conical frustum increases from the top side towards the bottom side. The top side is connected to the burner head and the bottom side is connected to the pre-mixing section. This provides another commonly used embodiment of the swirler and thus the burner of the present technique may be realized, operated and manufactured with ease.
- According to the invention, the premixed dual fuel burner has a radial width - taken in a radial direction in respect of an axis of the burner - of the injection component that reduces over an axial distance D by only or less than D/10, preferably less than D/15. In other embodidment the radial width may reduce by less than D/20.
- In another embodiment of the burner, the premixing section has a part of the premixing section which surrounds the burner outlet of the premixing section. The part of the premixing section includes an external pilot. The external pilot is configured to introduce a pilot fuel into the combustion chamber. This aids in formation an external recirculation zone in the combustion chamber and thus aiding in lean combustion. Furthermore the present technique may be implemented in turbomachines that use Dry Low NOx combustions.
- The present technique is further described hereinafter with reference to illustrated embodiments shown in the accompanying drawing, in which:
- FIG 1
- schematically illustrates a cross-sectional view of an exemplary embodiment of a premixed dual fuel burner including an injection component,
- FIG 2
- schematically illustrates a cross-sectional view of the injection component of the embodiment depicted in
FIG 1 , - FIG 3
- schematically illustrates a cross-sectional view of another exemplary embodiment of the premixed dual fuel burner including the injection component,
- FIG 4
- schematically illustrates a cross-sectional view of the injection component of the embodiment depicted in
FIG 3 , - FIG 5
- schematically illustrates a cross-sectional view of an exemplary embodiment of the premixed dual fuel burner depicting the injection component at a first position,
- FIG 6
- schematically illustrates a cross-sectional view of an exemplary embodiment of the premixed dual fuel burner depicting the injection component at a second position as compared to the first position depicted in
FIG 5 , and - FIG 7
- schematically illustrates a cross-sectional view of an exemplary embodiment of the premixed dual fuel burner depicting the injection component at another second position as compared to the first position depicted in
FIG 5 and the second position depicted inFIG 6 , in accordance with the present technique. - Hereinafter, above-mentioned and other features of the present technique are described in details. Various embodiments are described with reference to the drawing, wherein like reference numerals are used to refer to like elements throughout. In the following description, for purpose of explanation, numerous specific details are set forth in order to provide a thorough understanding of one or more embodiments. It may be noted that the illustrated embodiments are intended to explain, and not to limit the invention. It may be evident that such embodiments may be practiced without these specific details.
- It may be noted that in the present disclosure, the terms "first", "second", "another second" etc. are used herein only to facilitate discussion, and carry no particular temporal or chronological significance unless otherwise indicated.
- Referring to
FIG 1 , a cross-sectional view of an exemplary embodiment of a premixeddual fuel burner 1, hereinafter referred to as theburner 1 has been schematically represented. Theburner 1 essentially uses at least two main fuels - a main gas fuel and a main liquid fuel - in addition to and besides a pilot fuel and associated pilot fuel supply lines and techniques. - The
burner 1 includes aburner head 10, aburner interior 20, aswirler 30, apremixing section 40 and aninjection component 50. Theburner 1 is assembled in association with acombustion chamber 99 in a turbomachine (not shown) which work with dual fuel combustion reaction. The main fuel is combusted in thecombustion chamber 99 in form of a combustion mixture after being mixed with an air from a compressor section (now shown) of the turbomachine. The main gas fuel mixed with air and the main liquid fuel may be combusted in thecombustion chamber 99 separately or simultaneously. - The
burner head 10 includes aburner head end 12. Theswirler 30 is arranged in series between theburner head 10 and thepremixing section 40. Theburner 1 has amain axis 9. Theburner head 10, theswirler 30 and thepremixing section 40 are arranged along themain axis 9. Theswirler 30 is an elongated 3-dimensional body. When visualized as not integrated as a part of theburner 1, theswirler 30 is open at both ends and has a side wall enclosing a volume or limiting a volume within the side wall and the open ends. Similarly, thepremixing section 40 is an elongated 3-dimensional body. When visualized as not integrated as a part of theburner 1, thepremixing section 40 is open at both ends and has a side wall enclosing a volume or limiting a volume within the side wall and the open ends. - However, when integrated as parts of the
burner 1, and when arranged in series such that theswirler 30 is positioned between theburner head 10 and thepremixing section 40, as depicted inFIG 1 , the volume enclosed byswirler 30 and the volume enclosed by thepremixing section 40 together form a volume referred to as theburner interior 20. Theswirler 30 may be connected to theburner head 10 by direct physical contact, as depicted inFIG 1 , or may be connected to theburner head 10 through an intermediate piece (not shown) or a connecting region (not shown). Similarly, in theburner 1, theswirler 30 may be connected to thepremixing section 40 by direct physical contact with thepremixing section 40 or may be connected to thepremixing section 40 through an intermediate connecting piece (not shown). Theburner interior 20 represents a total volume enclosed by the swirler 30 and thepremixing section 40 withburner head 10 at one end of the total volume and thecombustion chamber 99 at the other end of the total volume, either with or without one or more such intermediate connecting pieces. - The
burner interior 20 is a volume or a hollow that is elongated along themain axis 9. Theburner interior 20 is formed of anupstream side 22 and adownstream side 24. Theupstream side 22 is disposed between theburner head 10 and thedownstream side 24. As depicted inFIG 1 , theupstream side 22 and thedownstream side 24 may be understood as a continuous volume, or in other words, theupstream side 22 is fluidly connected to thedownstream side 24, i.e. theupstream side 22 and thedownstream side 24 are continuous and together form theburner interior 20 inFIG 1 . A part of theburner interior 20 enclosed by theswirler 30 is theupstream side 22 of theburner interior 20 and the other part of theburner interior 20 enclosed by thepremixing section 40 is thedownstream side 24 of theburner interior 20. - As depicted in
FIG 1 , in an exemplary embodiment of theburner 1, theswirler 30 is directly connected to or affixed to or assembled with the burner head end 12 of theburner head 10, and theswirler 30 is also directly connected to or affixed to or assembled with thepremixing section 40. As shown inFIG 1 , theswirler 30 may be conically designed for example having a conical frustum shape. The conical frustum shape of theswirler 30 has atop side 36 and abottom side 38. A cross-sectional area of thebottom side 38 is greater than a cross-sectional area of thetop side 36, or in other words, a cross-section of the conical frustum increases from thetop side 36 towards thebottom side 38 along themain axis 9. Thetop side 36 is connected to the burner head end 12 of theburner head 10 and thebottom side 38 is connected to thepre-mixing section 40. - The
swirler 30 includes aninlet section 32. Theinlet section 32 is fluidly connected to the compressor (not shown) of the turbomachine (not shown). Theinlet section 32 receives compressed air from the compressor and introduces the compressed air into theburner interior 20, more precisely into theupstream side 22 of theburner interior 20. Similarly, theinlet section 32 is fluidly connected to a fuel supply (not shown) of the turbomachine. Theinlet section 32 receives main gas fuel from the fuel supply and introduces the main gas fuel into theburner interior 20, more precisely into theupstream side 22 of theburner interior 20. - In an exemplary embodiment of the
burner 1 as depicted inFIG 1 , theinlet section 32 of theswirler 30 includes at least one air inlet 33 and at least one main fuel gas inlet 34. The compressed air is introduced into theburner interior 20 via the air inlet 33 and the main gas fuel is introduced into theburner interior 20 via the main fuel gas inlet 34. The air inlet 33 may be tangentially arranged along theswirler 30 with respect to themain axis 9. Similarly, the main fuel gas inlet 34 may be tangentially arranged along theswirler 30 with respect to themain axis 9. For example, when theswirler 30 is conical frustum shaped, the air inlet 33 and/or the main fuel gas inlet 34 may be formed as longitudinally extending slots through a body wall (now shown) of the conical frustum. In an exemplary embodiment of theburner 1, theinlet section 32 includes a plurality of the air inlets 33 and a plurality of the main fuel gas inlets 34 arranged around theswirler 30 in a distributed way such that when the main gas fuel and the compressed air enter theburner interior 20 though the air inlets 33 and the main fuel gas inlets 34, a swirl is generated in the compressed air and the main gas fuel. Principle of swirl generation through longitudinal slots i.e. the air inlets 33 and the main fuel gas inlets 34, on such a conical shapedswirler 30 is known in the art of turbomachines and thus not explained in details herein for sake of brevity. - The
premixing section 40 is an elongated tubular body. Thepremixing section 40 has aburner outlet 42 through which thepremixing section 40 is arranged or fixed or assembled with thecombustion chamber 99. As seen inFIG 1 , in theburner 1 theburner outlet 42 of thepremixing section 40 is an opening through which theburner interior 20, more precisely thedownstream side 24 of theburner interior 20 fluidly connects to thecombustion chamber 99. Thus theburner interior 20 is continuous with thecombustion chamber 99 through theburner outlet 42. The combustion mixture and/or its constituents flow from theswirler 30 into thepremixing section 40 and then into thecombustion chamber 99 though theburner outlet 42. Thepremixing section 40, also referred to asmixer 40, performs or allows the mixing of the compressed air and the main gas fuel. - The
injection component 50 has a tapering structure positioned along themain axis 9. The tapering structure of theinjection component 50 extends from theburner head 12 into theburner interior 20. The injection component has aburner head side 52 and aninjection side 54. Theinjection component 50 tapers from theburner head side 52 to theinjection side 54 along themain axis 9. The tapering means a cross-sectional area perpendicular to themain axis 9 of theinjection component 50 decreases when moving from thehead side 52 to theinjection side 54 along themain axis 9. In one embodiment the decrease in the cross-sectional area is gradual for example when theinjection body 50 is designed like in form of a regular conical structure, as also depicted inFIG 2 . - The
injection component 50 may be hollow for guiding fuel. Particularly, as theinjection component 50 is tapered, the inner hollow space may also be tapered accordingly. So the fuel passage within theinjection component 50 reduces in width along an axial direction of the tapered section of theinjection component 50. - As seen in
FIG 1 in combination withFIG 2 , theinjection component 50 includes at least oneliquid fuel outlet 55 at theinjection side 54. A main liquid fuel is introduced into theburner interior 20 through the at least oneliquid fuel outlet 55. The main liquid fuel may be fed to theliquid fuel outlet 55 via fuel lines (not shown) formed inside theinjection body 50. The fuel lines within theinjection component 50 may in turn be connected to a liquid fuel supply (now shown) of the turbomachine. As depicted inFIG 1 , theinjection side 54 of theinjection component 50 is disposed in theburner interior 20 as a free standing manner i.e. without any physical supports at theinjection side 54. As seen inFIG 1 , theinjection body 50, in an exemplary embodiment of theburner 1, is coaxially positioned with themain axis 9. - As shown in
FIGs 1 and 2 , the at least oneliquid fuel outlet 55 is at aside 58 of theinjection side 54 of theinjection component 50. In an exemplary embodiment of theburner 1, there are more than oneliquid fuel outlets 55 located on theinjection side 54 of theinjection component 50, for exampleFIG 1 shows twoliquid fuel outlets 55, from each of theliquid fuel outlets 55 the main liquid fuel is discharged in form of a fluid stream or in atomized form with a direction towards thecombustion chamber 99, for example as depicted byarrows 71. Furthermore, as depicted inFIG 2 , theinjection component 50 may include a secondadditional outlet 62 which may have different shape or size as compared to theliquid fuel outlet 55. The secondadditional outlet 62 is also used to introduce the main liquid fuel into theburner interior 20, albeit the secondadditional outlet 62 is at a different position on theinjection side 54 for example anend 56 of theinjection side 54 of theinjection component 50. - Referring now to
FIGs 3 and 4 that schematically illustrate a cross-sectional view of another exemplary embodiment of theburner 1. As shown inFIGs 3 and 4 , the at least oneliquid fuel outlet 55 is at anend 56 of theinjection side 54 of theinjection component 50. In an exemplary embodiment of theburner 1, there may be more than oneliquid fuel outlets 55 located on theend 56 of theinjection side 54 of theinjection component 50.FIG 3 shows oneliquid fuel outlet 55 from which the main liquid fuel is discharged in form of a fluid stream or in atomized form with a direction towards thecombustion chamber 99, for example as depicted byarrow 71. Furthermore, as depicted inFIG 4 , theinjection component 50 may include a firstadditional outlet 61 which may have different shape or size as compared to theliquid fuel outlet 55.Fig 4 depicts two such firstadditional outlets 61. Theadditional outlet 61 is also used to introduce the main liquid fuel into theburner interior 20, albeit the firstadditional outlet 61 is at a different position on theinjection side 54 for example aside 58 of theinjection side 54 of theinjection component 50. - As can be seen in
FIGs 1 and3 , in both embodiments of theburner 1, due to the tapering structure of theinjection component 50 which aids in the axial flow of the air from the compressor and/or combustion mixture along themain axis 9 and due to injection of the main liquid fuel via theliquid fuel outlet 55 in a suitable position within thedownstream side 24 of theburner interior 20, formation of acentral recirculation zone 4 in thecombustion chamber 99 is achieved, and undesired formation of any recirculation zone extending into theburner interior 20 is obviated. - Furthermore, as seen in
FIGs 1 and3 , in theburner 1, thepremixing section 40 has apart 44 of thepremixing section 40 that surrounds theburner outlet 42 of thepremixing section 40. Thepart 44 includes anexternal pilot 45, as depicted inFIG 1 . From theexternal pilot 45, a pilot fuel is introduced into thecombustion chamber 99.FIGs 1 and3 show introduction of the pilot fuel through thepart 44 into thecombustion chamber 99. A direction of injection of the pilot fuel is depicted byarrow 72 inFIGs 1 and3 . It may be noted that thoughFIG 1 shows just oneexternal pilot 45, it is well within the scope of the present technique that a plurality of theexternal pilots 45 are present distributed circumferentially around a body (not shown) of thepremixing section 40 around theburner outlet 42. - As depicted in
FIGs 1 and3 , in both embodiments of theburner 1, due to theexternal pilot 45 and the ejection of the pilot fuel from theexternal pilot 45 in thedirection 72, formation of anexternal recirculation zone 5 in thecombustion chamber 99 is achieved. In exemplary embodiment of theburner 1, theexternal recirculation zone 5 surrounds thecentral recirculation zone 4 annularly and helps to further stabilize thecentral recirculation zone 4. - Now referring to
FIGs 5, 6 and 7 , different positions of theinjection component 50 along themain axis 9 are depicted. As seen inFIG 5 , in an embodiment of theburner 1, theliquid fuel outlet 55 is positioned in thedownstream side 24 of theburner interior 20. Similarly, as seen inFIG 6 , in another embodiment of theburner 1, theliquid fuel outlet 55 is positioned in thedownstream side 24 of theburner interior 20 albeit in a different position with respect to the position of theliquid fuel outlet 55 ofFIG 5 . Alternatively, as seen inFIG 7 , in an alternate embodiment of theburner 1, theliquid fuel outlet 55 is positioned in theupstream side 22 of theburner interior 20. - As depicted in
FIGs 1 ,3 and5 , afirst distance 91 is a distance along themain axis 9 between the at least oneliquid fuel outlet 55 and theburner head end 12, and asecond distance 92 is a distance along themain axis 9 between theburner outlet 42 of thepremixing section 40 and theburner head end 12. In embodiments of theburner 1, where there are more than oneliquid fuel outlets 55, thefirst length 91 is calculated as a mathematical average of all the distances of each individualliquid fuel outlets 55 from theburner head end 12. In other embodiments of theburner 1, as depicted in way of exemplary embodiments ofFIGs 5, 6 and 7 mainly, a ratio of thefirst distance 91 and thesecond distance 92 may vary, for example thefirst distance 91 may be between 20% and 80% of thesecond distance 92 along themain axis 9. - Furthermore, in one embodiment of the
burner 1, theinjection component 50 is longitudinally adjustable or moveable along thecentral axis 9, such that a position of the at least oneliquid fuel outlet 55 of theinjection component 50 gets changed from afirst location 93, as depicted inFIG 5 along themain axis 9 to asecond location 94 along themain axis 9, as depicted inFIG 6 . Thus theinjection component 50 is retractable into the burner interior 20 from thecombustor chamber outlet 42 towards theburner head 10 and/or is extendable into the burner interior 20 fromburner head 10 towards thecombustor chamber outlet 42. - Furthermore, as depicted from a combination of
FIGs 5, 6 and 7 , it can been seen that theinjection component 50 has progressively retracted into the burner interior 20 from thecombustor chamber outlet 42 towards theburner head 10 gradually fromFIGs 5 to 7. FIG 7 shows anothersecond location 94 depicted inFIG 7 as compared to thesecond location 94 ofFIG 6 and as compared to thefirst location 93 ofFIG 5 . - According to the invention, the shape of a fuel lance - i.e. the injection component 50 - is tapered in a way, that the fuel lance is an elongated component. It reduces its width taken in radial direction along an axial distance D only by or less than D/10, preferably less than D/20.
- While the present technique has been described in detail with reference to certain embodiments, it should be appreciated that the present technique is not limited to those precise embodiments. Rather, in view of the present disclosure which describes exemplary modes for practicing the invention, many modifications and variations would present themselves, to those skilled in the art without departing from the scope of this invention. The scope of the invention is, therefore, indicated by the following claims rather than by the foregoing description. All changes, modifications, and variations coming within the meaning and range of equivalency of the claims are to be considered within their scope.
Claims (13)
- A premixed dual fuel burner (1) for a combustion chamber (99) of a turbomachine, the premixed dual fuel burner (1) comprising:- a burner head (10) having a burner head end (12),- a burner interior (20) elongated along a main axis (9) and having an upstream side (22) and a downstream side (24), wherein the upstream side (22) is disposed between the burner head (10) and the downstream side (24) and wherein the upstream side (22) is fluidly connected to the downstream side (24),- a swirler (30) enclosing the upstream side (22) of the burner interior (20) and comprising an inlet section (32) configured to introduce air and a main gas fuel into the burner interior (20),- a premixing section (40) enclosing the downstream side (24) of the burner interior (20), wherein the swirler (30) is arranged between the burner head (10) and the premixing section (40), and wherein the premixing section (40) comprises a burner outlet (42) configured to be arranged with the combustion chamber (99) such that the downstream side (24) is fluidly connected to the combustion chamber (99), and- an injection component (50) positioned along the main axis (9) and extending from the burner head (10) into the burner interior (20), the injection component (50) having a burner head side (52) and an injection side (54) and wherein the injection component (50) tapers from the burner head side (52) to the injection side (54) along the main axis (9), wherein the injection component (50) comprises at least one liquid fuel outlet (55) at the injection side (54) and the injection component (50) is configured to introduce a main liquid fuel into the burner interior (20) through the at least one liquid fuel outlet (55) and wherein the injection side (54) of the injection component (50) is disposed in the burner interior (20), and
wherein at least one of the at least one liquid fuel outlet (55) is at a side (58) of the injection side (54) of the injection component (50),
characterized in that
the injection component (50) has a tapering structure and its radial width reduces over an axial distance D by only or less than D/10. - The premixed dual fuel burner (1) according to claim 1, wherein the tapering structure of the injection component (50) is a conical structure.
- The premixed dual fuel burner (1) according to claim 1 or 2, wherein the tapering structure of the injection component (50) is arranged coaxially to the main axis (9).
- The premixed dual fuel burner (1) according to any of claims 1 to 3, wherein a first distance (91) along the main axis (9) between the at least one liquid fuel outlet (55) and the burner head end (12) is between 20% and 80% of a second distance (92) along the main axis (9) between the burner outlet (42) of the premixing section (40) and the burner head end (12).
- The premixed dual fuel burner (1) according to any of claims 1 to 4, wherein the injection component (50) is configured to be longitudinally adjustable such that a position of the at least one liquid fuel outlet (55) of the injection component (50) is changeable from a first location (93) along the main axis (9) to a second location (94) along the main axis (9).
- The premixed dual fuel burner (1) according to any of claims 1 to 5, wherein the at least one liquid fuel outlet (55) is positioned in the upstream side (22) of the burner interior (20).
- The premixed dual fuel burner (1) according to any of claims 1 to 5, wherein the at least one liquid fuel outlet (55) is positioned in the downstream side (24) of the burner interior (20).
- The premixed dual fuel burner (1) according to any of claims 1 to 7, wherein the injection component (50) comprises a second additional outlet (62) configured to introduce the main liquid fuel into the burner interior (20) and wherein the second additional outlet (62) is at an end (56) of the injection side (54), particularly at a tip, of the injection component (50).
- The premixed dual fuel burner (1) according to any of claims 1 to 8, wherein the inlet section (32) of the swirler (30) comprises at least one air inlet (33) and at least one main fuel gas inlet (34).
- The premixed dual fuel burner (1) according to claim 9, wherein at least one of the at least one air inlet (33) and the at least one main fuel gas inlet (34) is arranged tangentially along the swirler (30) with respect to the main axis (9).
- The premixed dual fuel burner (1) according to any of claims 1 to 10, wherein the swirler (30) has a conical frustum shape having a top side (36) and a bottom side (38) and wherein a cross-section of the conical frustum increases from the top side (36) towards the bottom side (38) and wherein the top side (36) is connected to the burner head (10) and the bottom side (38) is connected to the pre-mixing section (40).
- The premixed dual fuel burner (1) according to any of claims 1 to 11, wherein a part (44) of the premixing section (40) surrounding the burner outlet (42) of the premixing section (40) comprises an external pilot (45) configured to introduce a pilot fuel into the combustion chamber (99).
- The premixed dual fuel burner (1) according to any of claims 1 to 12, wherein a radial width of the injection component (50) reduces over an axial distance D by only or less than D/15.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP15181707.9A EP3133342A1 (en) | 2015-08-20 | 2015-08-20 | A premixed dual fuel burner with a tapering injection component for main liquid fuel |
PCT/EP2016/068139 WO2017029101A1 (en) | 2015-08-20 | 2016-07-29 | A premixed dual fuel burner with a tapering injection component for main liquid fuel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3314165A1 EP3314165A1 (en) | 2018-05-02 |
EP3314165B1 true EP3314165B1 (en) | 2021-01-13 |
Family
ID=53938197
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15181707.9A Withdrawn EP3133342A1 (en) | 2015-08-20 | 2015-08-20 | A premixed dual fuel burner with a tapering injection component for main liquid fuel |
EP16745457.8A Active EP3314165B1 (en) | 2015-08-20 | 2016-07-29 | A premixed dual fuel burner with a tapering injection component for main liquid fuel |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15181707.9A Withdrawn EP3133342A1 (en) | 2015-08-20 | 2015-08-20 | A premixed dual fuel burner with a tapering injection component for main liquid fuel |
Country Status (4)
Country | Link |
---|---|
US (1) | US20180216828A1 (en) |
EP (2) | EP3133342A1 (en) |
CN (1) | CN107923612B (en) |
WO (1) | WO2017029101A1 (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
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US10955141B2 (en) * | 2017-06-19 | 2021-03-23 | General Electric Company | Dual-fuel fuel nozzle with gas and liquid fuel capability |
JP2019174051A (en) * | 2018-03-28 | 2019-10-10 | 株式会社Ihi | Combustion device and gas turbine |
US11774093B2 (en) | 2020-04-08 | 2023-10-03 | General Electric Company | Burner cooling structures |
KR20230125273A (en) | 2021-02-19 | 2023-08-29 | 가부시키가이샤 아이에이치아이 | Combustion equipment and boilers |
US11454396B1 (en) | 2021-06-07 | 2022-09-27 | General Electric Company | Fuel injector and pre-mixer system for a burner array |
EP4202308A1 (en) * | 2021-12-21 | 2023-06-28 | Ansaldo Energia Switzerland AG | Premix burner for a gas turbine assembly for power plant suitable to be fed with common and highly reactive fuels, method for operating this burner and gas turbine assembly for power plant comprising this burner |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5307634A (en) * | 1992-02-26 | 1994-05-03 | United Technologies Corporation | Premix gas nozzle |
DE4426351B4 (en) * | 1994-07-25 | 2006-04-06 | Alstom | Combustion chamber for a gas turbine |
DE19545026A1 (en) * | 1995-12-02 | 1997-06-05 | Abb Research Ltd | Premix burner |
JP2009531642A (en) * | 2006-03-27 | 2009-09-03 | アルストム テクノロジー リミテッド | Burner for heat generator operation |
WO2009019113A2 (en) * | 2007-08-07 | 2009-02-12 | Alstom Technology Ltd | Burner for a combustion chamber of a turbo group |
EP2225488B1 (en) * | 2007-11-27 | 2013-07-17 | Alstom Technology Ltd | Premix burner for a gas turbine |
ES2576651T3 (en) * | 2009-01-15 | 2016-07-08 | Alstom Technology Ltd | Burner of a gas turbine |
EP2722591A1 (en) * | 2012-10-22 | 2014-04-23 | Alstom Technology Ltd | Multiple cone gas turbine burner |
US20140338340A1 (en) * | 2013-03-12 | 2014-11-20 | General Electric Company | System and method for tube level air flow conditioning |
-
2015
- 2015-08-20 EP EP15181707.9A patent/EP3133342A1/en not_active Withdrawn
-
2016
- 2016-07-29 US US15/747,502 patent/US20180216828A1/en not_active Abandoned
- 2016-07-29 WO PCT/EP2016/068139 patent/WO2017029101A1/en active Application Filing
- 2016-07-29 CN CN201680046564.6A patent/CN107923612B/en active Active
- 2016-07-29 EP EP16745457.8A patent/EP3314165B1/en active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
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CN107923612B (en) | 2020-06-26 |
CN107923612A (en) | 2018-04-17 |
WO2017029101A1 (en) | 2017-02-23 |
EP3133342A1 (en) | 2017-02-22 |
EP3314165A1 (en) | 2018-05-02 |
US20180216828A1 (en) | 2018-08-02 |
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