US20060156734A1 - Gas turbine combustor - Google Patents
Gas turbine combustor Download PDFInfo
- Publication number
- US20060156734A1 US20060156734A1 US11/035,560 US3556005A US2006156734A1 US 20060156734 A1 US20060156734 A1 US 20060156734A1 US 3556005 A US3556005 A US 3556005A US 2006156734 A1 US2006156734 A1 US 2006156734A1
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- Prior art keywords
- combustor
- fuel
- burner
- flow
- vortex generator
- 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.)
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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
- F23R3/34—Feeding into different combustion zones
- F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
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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
- F23R3/02—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
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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
Definitions
- This invention relates generally to gas turbines, and, more particularly, to a gas turbine combustor including a vortex generator.
- Gas turbines having annular combustors are known to include a plurality of individual burners disposed in a ring about an axial centerline for providing a mixture of fuel and air to an annular combustion chamber disposed upstream of a turbine inlet.
- Each burner may include an annular main burner comprising a swirler disposed annularly around a central pilot burner.
- the combustion process of the plurality of burners interacts in the combustion chamber because all burners discharge their respective combustible mixtures into the single annular combustion chamber. Consequently, combustion processes for one burner may affect the combustion processes in the other burners. Burners for such annular combustors are generally simple to fabricate and are mechanically robust.
- Gas turbines having can-annular combustors are known wherein individual cans, including a combustion zone within the can, feed hot combustion gas into respective individual portions of an arc of a turbine inlet.
- Each can includes a plurality of main burners disposed in a ring around a central pilot burner.
- Each of the main burners may comprise an annular swirler.
- Cross flame tubes may be provided to connect the cans.
- Can annular combustors are generally more expensive to fabricate as a result of the use of multiple burners within each of the combustor burners.
- Annular combustion chamber dynamics are generally dominated by circumferential pressure pulsation modes between the plurality of burners.
- each burner of a can annular combustor is relatively isolated from interaction with the combustion process of adjacent cans.
- can annular combustion chamber dynamics are generally dominated by axial pressure pulsation modes within the individual burners.
- Fuel staging may be used to stabilize the combustion process. This approach, however, may produce an undesirable level of exhaust emissions, such as oxides of nitrogen (NO x ).
- FIG. 1 is a functional diagram of a gas turbine engine having an improved combustor design.
- FIG. 2 is a sectional view of an improved burner for use with an annular embodiment of the combustor of FIG. 1 .
- FIG. 3 shows an end view of the burner of FIG. 2 as seen along line 3 - 3 .
- FIG. 4 is a sectional view of an exemplary annular embodiment of the combustor of FIG. 1 including a plurality of improved burners.
- FIG. 5 is a sectional view of an improved combustor burner for use with a can-annular embodiment of the combustor of FIG. 1 .
- FIG. 6 is a sectional view of an improved burner for use with the combustor of FIG. 1 .
- FIG. 1 illustrates a gas turbine engine 10 having a compressor 12 for receiving a flow of filtered ambient air 14 and for producing a flow of compressed air 16 .
- the compressed air 16 is received by a combustor 18 where it is used to burn a flow of a combustible fuel 20 , such as natural gas or fuel oil provided by fuel supply 24 , to produce a flow of hot combustion gas 22 .
- the combustor 18 may be a burner annular type combustor including a plurality of combustor burners feeding hot combustion gas into respective individual portions of an arc of a turbine inlet 33 .
- the combustor 18 may be an annular type combustor including a plurality of individual burners disposed in a ring about an axial centerline of the combustor 18 for providing a mixture of fuel and air to an annular combustion chamber disposed upstream of the turbine inlet 33 .
- the hot combustion gas 22 from the combustor 18 is received by a turbine 26 , where it is expanded to extract mechanical shaft power.
- a common shaft 28 may interconnect the turbine 26 with the compressor 12 , as well as an electrical generator 30 , to provide mechanical power for compressing the ambient air 14 and for producing electrical power, respectively.
- the expanded combustion gas 32 may be exhausted directly to the atmosphere or it may be routed through additional heat recovery systems (not shown).
- FIG. 2 is a cross sectional view of a combustor burner 34 used, for example, in an annular type embodiment of the combustor 18 .
- FIG. 2 illustrates a cross section taken perpendicular to a direction of flow through the combustor 18 and shows a portion 74 of an annular combustion chamber 75 in fluid communication with the burner 34 .
- the combustor burner 34 generally includes a outer annulus 39 , a fuel outlet 46 , and an annular vortex generator 38 .
- the combustor burner 34 receives an oxidizer flow, such as a respective burner portion 36 of the compressed air 16 and a respective burner portion 37 of the flow of combustible fuel 20 , and discharges a respective burner portion 23 of the hot combustion gas 22 .
- the annular vortex generator 38 may be disposed around a central region 40 of the burner 34 for generating a vortex in a fluid flow flowing past the vortex generator 38 , thereby promoting mixing of fluid flows downstream of the vortex generator 38 .
- vortex generator 38 may be configured to limit generation of flow zones having flow speeds of less than 10 meters per second.
- the vortex generator 38 separates a first portion 42 of the respective burner portion 36 from a second portion 44 of the respective burner portion 36 and imparts a flow direction change to at least one of the portions 42 , 44 so that the portions 42 , 44 exit the vortex generator 38 at different angles with respect to each other.
- a fuel outlet 46 may be disposed proximate the vortex generator 38 , such as upstream of an upstream end 48 of the vortex generator 38 , for discharging a fuel outlet portion 47 of the respective burner portion 37 into one, or both, of the portions 42 , 44 .
- the portions 42 , 44 exiting the vortex generator 38 at different angles with respect to each other are combined to create a vortex 52 to promote mixing of the portions 42 , 44 to create a combustible mixture 54 .
- the downstream end 50 of the vortex generator 38 may open directly into the portion 74 of an annular combustion chamber 35 to provide the combustible mixture 54 therein.
- the combustible mixture 54 may then be combusted in the portion 74 of the combustion chamber 75 to generate a respective burner portion 23 of the hot combustion gas 22 provided to the downstream turbine 26 .
- a pilot burner 56 supplied by a pilot portion 49 of the burner portion 37 may be located in the central region 40 for igniting the combustible mixture 54 .
- the annular vortex generator 38 may include a lobe mixer.
- FIG. 3 shows an end view of the combustor burner 34 of FIG. 2 as seen along line 3 - 3 , wherein the annular vortex generator 38 is a lobe mixer.
- the lobe mixer includes a plurality of circumferentially spaced apart radially extending lobes 58 defining a plurality of external flow directing channels 60 between the spaced apart lobes 58 conducting, for example, the second portion 44 along external surfaces 62 of each lobe 58 .
- the lobes 58 also define a plurality of internal flow directing channels 64 conducting the first portion 42 along internal surfaces 66 of each lobe 58 .
- the lobes 58 may be arranged so that the first portion 42 entering at the upstream end 48 of the vortex generator 38 and flowing along the internal surface 66 is given a radially outward directed flow component, while the second portion 44 flowing along the exterior surface 62 is given a radially inward directed component so that when the portions 42 , 44 exit the vortex generator 38 , the portions 42 , 44 are directed to flow at different angles with respect to each other, thereby producing a vortex 52 downstream of the downstream end 50 of the vortex generator 38 .
- the vortex 52 promotes mixing of the portions 42 , 44 to produce the combustible mixture 54 as well as promoting suction of a pilot flame 43 burning in a pilot zone 41 into the vortex 52 .
- a swirling flow of the vortex 52 is “coated” by the pilot flame 43 and then burns from an exterior portion of the vortex radially inward.
- the lobes 58 may comprise different geometries to generate different respective vortex flow patterns to achieve different burn patterns.
- the fuel outlet 46 may comprise a plurality of radially extending fuel pegs 66 disposed to discharge the fuel outlet portion 47 of the burner portion 37 into one or both of the portions 42 , 44 flowing through the respective flow directing channels 60 , 64 .
- the fuel pegs 66 may be radially aligned with the lobes 58 to inject the fuel outlet portion 47 of the combustible fuel 20 into the respective directing channels 60 , 64 .
- each fuel peg 46 may include opposed fuel orifices 68 spaced apart along a radial length of the peg 46 for directing respective jets 69 of the fuel outlet portion 47 of the combustible fuel 20 at an oblique angle to an axial flow direction of the burner portion 36 of the compressed air 16 to provide improved mixing of the fuel outlet portion 47 of the fuel 20 into the portions 42 , 44 than if the fuel 20 was injected coaxially to the flow direction.
- the number, size and orientation of the fuel orifices 68 may be configured to achieve a desired fuel/oxidizer ratio in the resulting combustible mixture 54 .
- the fuel outlet 46 may be disposed upstream of the vortex generator 38 as shown in FIG. 2 , or the outlet 46 may be disposed between the upstream end 48 and the downstream end 50 of the vortex generator 38 .
- the fuel outlet 46 may be configured to inject the fuel outlet portion 47 of the combustible fuel 20 into one or both of the portions 42 , 44 flowing through the through the respective flow directing channels 60 , 64 .
- the fuel outlet portion 47 of the combustible fuel 20 may be delivered to the vortex generator 38 and directed to exit from an orifice 70 in a surface of the vortex generator 38 into an oxidizer flow flowing along the surface of the vortex generator 38 .
- the fuel orifice 70 in fluid communication with the fuel source 24 , may be provided in the internal 66 and/or the external surface 62 of the vortex generator 38 to inject fuel into the respective portions 42 , 44 of the compressed air 16 flowing over the surfaces 66 , 62 .
- FIG. 4 illustrates a section taken perpendicular to the direction of flow through an exemplary annular embodiment of the combustor 18 of FIG. 1 .
- the annular embodiment may include a plurality of combustor burners 34 , such as the burner depicted in FIG. 2 , spaced apart in a ring around a central region 72 of the combustor 18 .
- a cylindrical liner 76 surrounds the plurality of combustor burners 34 .
- Each burner 34 may include an annular vortex generator 38 , such as a lobe mixer, disposed around a central region 40 of the burner 34 , and a fuel outlet 46 (such as shown in FIG. 2 ) disposed proximate the vortex generator 38 .
- Each burner 34 may provide a fuel/air mixture to a respective portion of the annular combustion chamber 74 as shown in FIG. 2 .
- the burner 34 may be configured for use in a can annular embodiment of the combustor 18 , wherein the burner 34 is in fluid communication with a combustion zone 41 defined by a can liner 78 .
- a plurality of burners 34 maybe spaced apart around the central region 72 such as shown in FIG. 2 .
- Each burner 34 may feed hot combustion gas 23 , such as via a known transition piece, into respective individual portions of an arc of a turbine inlet.
- the burner 34 may be configured to be interchangeably used in can annular type combustors and annular type combustors with limited or no modifications necessary to adapt the burner 34 to either type.
- a mounting arrangement at the downstream end 50 of the burner 34 may need to be modified for accommodating respective attachment configurations in a can annular or annular embodiment of the combustor 18 .
- the vortex generator 38 may include a plurality of annularly arranged flow directing elements 80 , 81 projecting into the burner portion of compressed air 36 to cause different portions 42 , 44 to be directed to flow at different angles with respect to each other, thereby producing a vortex 52 downstream of the downstream end 50 of the vortex generator 38 .
- the flow directing elements 80 , 81 may be pyramid-shaped bluff bodies annularly spaced apart around an inside circumference 82 of the outer annulus 39 .
- the elements 80 , 81 may be configured to have different geometries to generate different respective vortexes 52 , 53 to achieve desired flow field patterns downstream of the downstream end 50 of the vortex generator 38 .
- the elements 80 , 81 may extend radially inwards from the inside circumference 82 different distances, or the elements may be shaped differently to generate different respective vortexes 52 , 53 .
Abstract
Description
- This invention relates generally to gas turbines, and, more particularly, to a gas turbine combustor including a vortex generator.
- Gas turbines having annular combustors are known to include a plurality of individual burners disposed in a ring about an axial centerline for providing a mixture of fuel and air to an annular combustion chamber disposed upstream of a turbine inlet. Each burner may include an annular main burner comprising a swirler disposed annularly around a central pilot burner. The combustion process of the plurality of burners interacts in the combustion chamber because all burners discharge their respective combustible mixtures into the single annular combustion chamber. Consequently, combustion processes for one burner may affect the combustion processes in the other burners. Burners for such annular combustors are generally simple to fabricate and are mechanically robust.
- Gas turbines having can-annular combustors are known wherein individual cans, including a combustion zone within the can, feed hot combustion gas into respective individual portions of an arc of a turbine inlet. Each can includes a plurality of main burners disposed in a ring around a central pilot burner. Each of the main burners may comprise an annular swirler. Cross flame tubes may be provided to connect the cans. Can annular combustors are generally more expensive to fabricate as a result of the use of multiple burners within each of the combustor burners.
- Combustion dynamics concerns vary among the different types of combustor designs. Annular combustion chamber dynamics are generally dominated by circumferential pressure pulsation modes between the plurality of burners. In contrast, each burner of a can annular combustor is relatively isolated from interaction with the combustion process of adjacent cans. Accordingly, can annular combustion chamber dynamics are generally dominated by axial pressure pulsation modes within the individual burners. Fuel staging may be used to stabilize the combustion process. This approach, however, may produce an undesirable level of exhaust emissions, such as oxides of nitrogen (NOx).
- The demand to decrease exhaust emissions while simplifying combustor construction continues, thus improved techniques for economically controlling the combustion conditions of a gas turbine engine are needed.
- The invention will be more apparent from the following description in view of the drawings that show:
-
FIG. 1 is a functional diagram of a gas turbine engine having an improved combustor design. -
FIG. 2 is a sectional view of an improved burner for use with an annular embodiment of the combustor ofFIG. 1 . -
FIG. 3 shows an end view of the burner ofFIG. 2 as seen along line 3-3. -
FIG. 4 is a sectional view of an exemplary annular embodiment of the combustor ofFIG. 1 including a plurality of improved burners. -
FIG. 5 is a sectional view of an improved combustor burner for use with a can-annular embodiment of the combustor ofFIG. 1 . -
FIG. 6 is a sectional view of an improved burner for use with the combustor ofFIG. 1 . -
FIG. 1 illustrates agas turbine engine 10 having acompressor 12 for receiving a flow of filteredambient air 14 and for producing a flow of compressedair 16. The compressedair 16 is received by acombustor 18 where it is used to burn a flow of acombustible fuel 20, such as natural gas or fuel oil provided byfuel supply 24, to produce a flow ofhot combustion gas 22. In one embodiment, thecombustor 18 may be a burner annular type combustor including a plurality of combustor burners feeding hot combustion gas into respective individual portions of an arc of aturbine inlet 33. In another embodiment, thecombustor 18 may be an annular type combustor including a plurality of individual burners disposed in a ring about an axial centerline of thecombustor 18 for providing a mixture of fuel and air to an annular combustion chamber disposed upstream of theturbine inlet 33. - The
hot combustion gas 22 from thecombustor 18 is received by aturbine 26, where it is expanded to extract mechanical shaft power. Acommon shaft 28 may interconnect theturbine 26 with thecompressor 12, as well as anelectrical generator 30, to provide mechanical power for compressing theambient air 14 and for producing electrical power, respectively. The expandedcombustion gas 32 may be exhausted directly to the atmosphere or it may be routed through additional heat recovery systems (not shown). - The
gas turbine engine 10 provides improved structural robustness and operability as a result of features of thecombustor 18 that are shown more clearly inFIG. 2 .FIG. 2 is a cross sectional view of acombustor burner 34 used, for example, in an annular type embodiment of thecombustor 18.FIG. 2 illustrates a cross section taken perpendicular to a direction of flow through thecombustor 18 and shows aportion 74 of anannular combustion chamber 75 in fluid communication with theburner 34. Thecombustor burner 34 generally includes aouter annulus 39, afuel outlet 46, and anannular vortex generator 38. Thecombustor burner 34 receives an oxidizer flow, such as arespective burner portion 36 of thecompressed air 16 and arespective burner portion 37 of the flow ofcombustible fuel 20, and discharges arespective burner portion 23 of thehot combustion gas 22. Theannular vortex generator 38 may be disposed around acentral region 40 of theburner 34 for generating a vortex in a fluid flow flowing past thevortex generator 38, thereby promoting mixing of fluid flows downstream of thevortex generator 38. To avoid creation of flame holding zones proximate adownstream end 50 of thevortex generator 38,vortex generator 38 may be configured to limit generation of flow zones having flow speeds of less than 10 meters per second. In an embodiment, thevortex generator 38 separates afirst portion 42 of therespective burner portion 36 from asecond portion 44 of therespective burner portion 36 and imparts a flow direction change to at least one of theportions portions vortex generator 38 at different angles with respect to each other. - A
fuel outlet 46 may be disposed proximate thevortex generator 38, such as upstream of anupstream end 48 of thevortex generator 38, for discharging afuel outlet portion 47 of therespective burner portion 37 into one, or both, of theportions downstream end 50 of thevortex generator 38, theportions vortex generator 38 at different angles with respect to each other are combined to create avortex 52 to promote mixing of theportions combustible mixture 54. Thedownstream end 50 of thevortex generator 38 may open directly into theportion 74 of an annular combustion chamber 35 to provide thecombustible mixture 54 therein. Thecombustible mixture 54 may then be combusted in theportion 74 of thecombustion chamber 75 to generate arespective burner portion 23 of thehot combustion gas 22 provided to thedownstream turbine 26. Apilot burner 56, supplied by apilot portion 49 of theburner portion 37 may be located in thecentral region 40 for igniting thecombustible mixture 54. - In an aspect of the invention that may be more readily viewed in
FIG. 3 , theannular vortex generator 38 may include a lobe mixer.FIG. 3 shows an end view of thecombustor burner 34 ofFIG. 2 as seen along line 3-3, wherein theannular vortex generator 38 is a lobe mixer. The lobe mixer includes a plurality of circumferentially spaced apart radially extendinglobes 58 defining a plurality of externalflow directing channels 60 between the spaced apartlobes 58 conducting, for example, thesecond portion 44 alongexternal surfaces 62 of eachlobe 58. Thelobes 58 also define a plurality of internalflow directing channels 64 conducting thefirst portion 42 alonginternal surfaces 66 of eachlobe 58. Thelobes 58 may be arranged so that thefirst portion 42 entering at theupstream end 48 of thevortex generator 38 and flowing along theinternal surface 66 is given a radially outward directed flow component, while thesecond portion 44 flowing along theexterior surface 62 is given a radially inward directed component so that when theportions vortex generator 38, theportions vortex 52 downstream of thedownstream end 50 of thevortex generator 38. Advantageously, thevortex 52 promotes mixing of theportions combustible mixture 54 as well as promoting suction of apilot flame 43 burning in apilot zone 41 into thevortex 52. A swirling flow of thevortex 52 is “coated” by thepilot flame 43 and then burns from an exterior portion of the vortex radially inward. In an aspect of the invention, thelobes 58 may comprise different geometries to generate different respective vortex flow patterns to achieve different burn patterns. For example, lobe 59 may have a wider, shorter cross sectional profile at thedownstream end 50 than anotherlobe 58, thereby creating a different vortex flow patterns among the differentlyshaped lobes 58, 59 as theportions vortex generator 38. - In another aspect of the invention shown in
FIGS. 2 and 3 , thefuel outlet 46 may comprise a plurality of radially extendingfuel pegs 66 disposed to discharge thefuel outlet portion 47 of theburner portion 37 into one or both of theportions flow directing channels fuel pegs 66 may be radially aligned with thelobes 58 to inject thefuel outlet portion 47 of thecombustible fuel 20 into therespective directing channels fuel peg 46 may includeopposed fuel orifices 68 spaced apart along a radial length of thepeg 46 for directingrespective jets 69 of thefuel outlet portion 47 of thecombustible fuel 20 at an oblique angle to an axial flow direction of theburner portion 36 of thecompressed air 16 to provide improved mixing of thefuel outlet portion 47 of thefuel 20 into theportions fuel 20 was injected coaxially to the flow direction. The number, size and orientation of thefuel orifices 68 may be configured to achieve a desired fuel/oxidizer ratio in the resultingcombustible mixture 54. - The
fuel outlet 46 may be disposed upstream of thevortex generator 38 as shown inFIG. 2 , or theoutlet 46 may be disposed between theupstream end 48 and thedownstream end 50 of thevortex generator 38. Thefuel outlet 46 may be configured to inject thefuel outlet portion 47 of thecombustible fuel 20 into one or both of theportions flow directing channels FIG. 2 , thefuel outlet portion 47 of thecombustible fuel 20 may be delivered to thevortex generator 38 and directed to exit from anorifice 70 in a surface of thevortex generator 38 into an oxidizer flow flowing along the surface of thevortex generator 38. For example, thefuel orifice 70, in fluid communication with thefuel source 24, may be provided in the internal 66 and/or theexternal surface 62 of thevortex generator 38 to inject fuel into therespective portions compressed air 16 flowing over thesurfaces -
FIG. 4 illustrates a section taken perpendicular to the direction of flow through an exemplary annular embodiment of thecombustor 18 ofFIG. 1 . The annular embodiment may include a plurality ofcombustor burners 34, such as the burner depicted inFIG. 2 , spaced apart in a ring around acentral region 72 of thecombustor 18. Acylindrical liner 76 surrounds the plurality ofcombustor burners 34. Eachburner 34 may include anannular vortex generator 38, such as a lobe mixer, disposed around acentral region 40 of theburner 34, and a fuel outlet 46 (such as shown inFIG. 2 ) disposed proximate thevortex generator 38. Eachburner 34 may provide a fuel/air mixture to a respective portion of theannular combustion chamber 74 as shown inFIG. 2 . - In another aspect of the invention shown in
FIG. 5 , theburner 34, incorporating the innovative features of thevortex generator 38 and thecorresponding fuel outlet 46 such as depicted inFIG. 2 , may be configured for use in a can annular embodiment of thecombustor 18, wherein theburner 34 is in fluid communication with acombustion zone 41 defined by acan liner 78. A plurality ofburners 34 maybe spaced apart around thecentral region 72 such as shown inFIG. 2 . Eachburner 34 may feedhot combustion gas 23, such as via a known transition piece, into respective individual portions of an arc of a turbine inlet. Advantageously, theburner 34 may be configured to be interchangeably used in can annular type combustors and annular type combustors with limited or no modifications necessary to adapt theburner 34 to either type. For example, only a mounting arrangement at thedownstream end 50 of theburner 34 may need to be modified for accommodating respective attachment configurations in a can annular or annular embodiment of thecombustor 18. - In yet another aspect of the invention depicted in
FIG. 6 , thevortex generator 38 may include a plurality of annularly arrangedflow directing elements compressed air 36 to causedifferent portions vortex 52 downstream of thedownstream end 50 of thevortex generator 38. For example, theflow directing elements inside circumference 82 of theouter annulus 39. In an embodiment, theelements respective vortexes downstream end 50 of thevortex generator 38. For example, theelements inside circumference 82 different distances, or the elements may be shaped differently to generate differentrespective vortexes - While various embodiments of the present invention have been shown and described herein, it will be obvious that such embodiments are provided by way of example only. Numerous variations, changes and substitutions may be made without departing from the invention herein. Accordingly, it is intended that the invention be limited only by the spirit and scope of the appended claims.
Claims (18)
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US11/035,560 US20060156734A1 (en) | 2005-01-15 | 2005-01-15 | Gas turbine combustor |
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US11/035,560 US20060156734A1 (en) | 2005-01-15 | 2005-01-15 | Gas turbine combustor |
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US20060156734A1 true US20060156734A1 (en) | 2006-07-20 |
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Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20070227156A1 (en) * | 2006-03-30 | 2007-10-04 | Mitsubishi Heavy Industries, Ltd. | Combustor of gas turbine and combustion control method for gas turbine |
US20090277177A1 (en) * | 2008-05-09 | 2009-11-12 | William Kirk Hessler | Fuel nozzle for a gas turbine engine and method for fabricating the same |
US20100051756A1 (en) * | 2006-12-12 | 2010-03-04 | Lockheed Martin Corporation | System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines |
US20110232289A1 (en) * | 2008-09-29 | 2011-09-29 | Giacomo Colmegna | Fuel Nozzle |
FR2968064A1 (en) * | 2010-11-30 | 2012-06-01 | Gen Electric | PREMIXER FOR COMBUSTION SYSTEM |
US20120279224A1 (en) * | 2011-05-03 | 2012-11-08 | General Electric Company | Gas turbine engine combustor |
EP2522912A1 (en) * | 2011-05-11 | 2012-11-14 | Alstom Technology Ltd | Flow straightener and mixer |
US20130067920A1 (en) * | 2010-02-23 | 2013-03-21 | Timothy A. Fox | Fuel injector and swirler assembly with lobed mixer |
US8429915B1 (en) * | 2011-10-17 | 2013-04-30 | General Electric Company | Injector having multiple fuel pegs |
US20130283801A1 (en) * | 2012-04-27 | 2013-10-31 | General Electric Company | System for supplying fuel to a combustor |
US20160290648A1 (en) * | 2015-03-30 | 2016-10-06 | Ansaldo Energia Switzerland AG | Fuel injector device |
US20170003031A1 (en) * | 2015-06-30 | 2017-01-05 | General Electric Company | Fuel nozzle assembly |
WO2018082538A1 (en) | 2016-11-01 | 2018-05-11 | Beijing Huatsing Gas Turbine & Igcc Technology Co., Ltd | Method of optimizing premix fuel nozzles for a gas turbine |
US20200025383A1 (en) * | 2018-07-18 | 2020-01-23 | General Electric Company | Combustor Assembly for a Heat Engine |
Citations (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3861140A (en) * | 1972-07-05 | 1975-01-21 | Gen Electric | Turbofan engine mixer |
US4696159A (en) * | 1986-08-04 | 1987-09-29 | United Technologies Corporation | Gas turbine outlet arrangement |
US5235813A (en) * | 1990-12-24 | 1993-08-17 | United Technologies Corporation | Mechanism for controlling the rate of mixing in combusting flows |
US5400587A (en) * | 1991-11-13 | 1995-03-28 | Asea Brown Boveri Ltd. | Gas turbine annular combustion chamber having radially displaced groups of oppositely swirling burners. |
US5491970A (en) * | 1994-06-10 | 1996-02-20 | General Electric Co. | Method for staging fuel in a turbine between diffusion and premixed operations |
US5577378A (en) * | 1993-04-08 | 1996-11-26 | Abb Management Ag | Gas turbine group with reheat combustor |
US5622054A (en) * | 1995-12-22 | 1997-04-22 | General Electric Company | Low NOx lobed mixer fuel injector |
US5638675A (en) * | 1995-09-08 | 1997-06-17 | United Technologies Corporation | Double lobed mixer with major and minor lobes |
US5685139A (en) * | 1996-03-29 | 1997-11-11 | General Electric Company | Diffusion-premix nozzle for a gas turbine combustor and related method |
US5722230A (en) * | 1995-08-08 | 1998-03-03 | General Electric Co. | Center burner in a multi-burner combustor |
US5839283A (en) * | 1995-12-29 | 1998-11-24 | Abb Research Ltd. | Mixing ducts for a gas-turbine annular combustion chamber |
US6038861A (en) * | 1998-06-10 | 2000-03-21 | Siemens Westinghouse Power Corporation | Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors |
US6070411A (en) * | 1996-11-29 | 2000-06-06 | Kabushiki Kaisha Toshiba | Gas turbine combustor with premixing and diffusing fuel nozzles |
US6189320B1 (en) * | 1996-12-20 | 2001-02-20 | Siemens Aktiengesellschaft | Burner for fluidic fuels having multiple groups of vortex generating elements |
US20010052229A1 (en) * | 1998-02-10 | 2001-12-20 | General Electric Company | Burner with uniform fuel/air premixing for low emissions combustion |
US20020174657A1 (en) * | 2001-05-24 | 2002-11-28 | Rice Edward C. | Apparatus for forming a combustion mixture in a gas turbine engine |
US20030010032A1 (en) * | 2001-07-13 | 2003-01-16 | Stuttaford Peter John | Swirled diffusion dump combustor |
US20040020211A1 (en) * | 2001-07-23 | 2004-02-05 | Ramgen Power Systems, Inc. | Trapped vortex combustor |
US20040050057A1 (en) * | 2002-09-17 | 2004-03-18 | Siemens Westinghouse Power Corporation | Flashback resistant pre-mix burner for a gas turbine combustor |
US20040055306A1 (en) * | 2002-09-23 | 2004-03-25 | Siemens Westinghouse Power Corporation | Premixed pilot burner for a combustion turbine engine |
US20040060297A1 (en) * | 2002-09-26 | 2004-04-01 | Siemens Westinghouse Power Corporation | Turbine engine fuel nozzle |
US20040103663A1 (en) * | 2002-06-11 | 2004-06-03 | Haynes Joel Meier | Gas turbine engine combustor can with trapped vortex cavity |
US20050223710A1 (en) * | 2004-04-07 | 2005-10-13 | Creighton Sherman C | Swirler |
-
2005
- 2005-01-15 US US11/035,560 patent/US20060156734A1/en not_active Abandoned
Patent Citations (24)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3861140A (en) * | 1972-07-05 | 1975-01-21 | Gen Electric | Turbofan engine mixer |
US4696159A (en) * | 1986-08-04 | 1987-09-29 | United Technologies Corporation | Gas turbine outlet arrangement |
US5235813A (en) * | 1990-12-24 | 1993-08-17 | United Technologies Corporation | Mechanism for controlling the rate of mixing in combusting flows |
US5400587A (en) * | 1991-11-13 | 1995-03-28 | Asea Brown Boveri Ltd. | Gas turbine annular combustion chamber having radially displaced groups of oppositely swirling burners. |
US5577378A (en) * | 1993-04-08 | 1996-11-26 | Abb Management Ag | Gas turbine group with reheat combustor |
US5491970A (en) * | 1994-06-10 | 1996-02-20 | General Electric Co. | Method for staging fuel in a turbine between diffusion and premixed operations |
US5722230A (en) * | 1995-08-08 | 1998-03-03 | General Electric Co. | Center burner in a multi-burner combustor |
US5638675A (en) * | 1995-09-08 | 1997-06-17 | United Technologies Corporation | Double lobed mixer with major and minor lobes |
US5622054A (en) * | 1995-12-22 | 1997-04-22 | General Electric Company | Low NOx lobed mixer fuel injector |
US5839283A (en) * | 1995-12-29 | 1998-11-24 | Abb Research Ltd. | Mixing ducts for a gas-turbine annular combustion chamber |
US5685139A (en) * | 1996-03-29 | 1997-11-11 | General Electric Company | Diffusion-premix nozzle for a gas turbine combustor and related method |
US6070411A (en) * | 1996-11-29 | 2000-06-06 | Kabushiki Kaisha Toshiba | Gas turbine combustor with premixing and diffusing fuel nozzles |
US6189320B1 (en) * | 1996-12-20 | 2001-02-20 | Siemens Aktiengesellschaft | Burner for fluidic fuels having multiple groups of vortex generating elements |
US20010052229A1 (en) * | 1998-02-10 | 2001-12-20 | General Electric Company | Burner with uniform fuel/air premixing for low emissions combustion |
US6038861A (en) * | 1998-06-10 | 2000-03-21 | Siemens Westinghouse Power Corporation | Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors |
US20020174657A1 (en) * | 2001-05-24 | 2002-11-28 | Rice Edward C. | Apparatus for forming a combustion mixture in a gas turbine engine |
US6564555B2 (en) * | 2001-05-24 | 2003-05-20 | Allison Advanced Development Company | Apparatus for forming a combustion mixture in a gas turbine engine |
US20030010032A1 (en) * | 2001-07-13 | 2003-01-16 | Stuttaford Peter John | Swirled diffusion dump combustor |
US20040020211A1 (en) * | 2001-07-23 | 2004-02-05 | Ramgen Power Systems, Inc. | Trapped vortex combustor |
US20040103663A1 (en) * | 2002-06-11 | 2004-06-03 | Haynes Joel Meier | Gas turbine engine combustor can with trapped vortex cavity |
US20040050057A1 (en) * | 2002-09-17 | 2004-03-18 | Siemens Westinghouse Power Corporation | Flashback resistant pre-mix burner for a gas turbine combustor |
US20040055306A1 (en) * | 2002-09-23 | 2004-03-25 | Siemens Westinghouse Power Corporation | Premixed pilot burner for a combustion turbine engine |
US20040060297A1 (en) * | 2002-09-26 | 2004-04-01 | Siemens Westinghouse Power Corporation | Turbine engine fuel nozzle |
US20050223710A1 (en) * | 2004-04-07 | 2005-10-13 | Creighton Sherman C | Swirler |
Cited By (32)
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---|---|---|---|---|
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US20100051756A1 (en) * | 2006-12-12 | 2010-03-04 | Lockheed Martin Corporation | System, method, and apparatus for throat corner scoop offtake for mixed compression inlets on aircraft engines |
US20090277177A1 (en) * | 2008-05-09 | 2009-11-12 | William Kirk Hessler | Fuel nozzle for a gas turbine engine and method for fabricating the same |
US7757491B2 (en) * | 2008-05-09 | 2010-07-20 | General Electric Company | Fuel nozzle for a gas turbine engine and method for fabricating the same |
US20110232289A1 (en) * | 2008-09-29 | 2011-09-29 | Giacomo Colmegna | Fuel Nozzle |
US8959922B2 (en) * | 2008-09-29 | 2015-02-24 | Siemens Aktiengesellschaft | Fuel nozzle with flower shaped nozzle tube |
US20130067920A1 (en) * | 2010-02-23 | 2013-03-21 | Timothy A. Fox | Fuel injector and swirler assembly with lobed mixer |
JP2013520635A (en) * | 2010-02-23 | 2013-06-06 | シーメンス アクチエンゲゼルシヤフト | Fuel injector and swirler assembly with lobe mixer |
US8511087B2 (en) * | 2010-02-23 | 2013-08-20 | Siemens Atkiengesellschaft | Fuel injector and swirler assembly with lobed mixer |
FR2968064A1 (en) * | 2010-11-30 | 2012-06-01 | Gen Electric | PREMIXER FOR COMBUSTION SYSTEM |
US9435537B2 (en) | 2010-11-30 | 2016-09-06 | General Electric Company | System and method for premixer wake and vortex filling for enhanced flame-holding resistance |
US20120279224A1 (en) * | 2011-05-03 | 2012-11-08 | General Electric Company | Gas turbine engine combustor |
US8938978B2 (en) * | 2011-05-03 | 2015-01-27 | General Electric Company | Gas turbine engine combustor with lobed, three dimensional contouring |
US8938971B2 (en) | 2011-05-11 | 2015-01-27 | Alstom Technology Ltd | Flow straightener and mixer |
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US20130283801A1 (en) * | 2012-04-27 | 2013-10-31 | General Electric Company | System for supplying fuel to a combustor |
JP2013231580A (en) * | 2012-04-27 | 2013-11-14 | General Electric Co <Ge> | System for supplying fuel to combustor |
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US9200808B2 (en) * | 2012-04-27 | 2015-12-01 | General Electric Company | System for supplying fuel to a late-lean fuel injector of a combustor |
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US20160290648A1 (en) * | 2015-03-30 | 2016-10-06 | Ansaldo Energia Switzerland AG | Fuel injector device |
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US20170003031A1 (en) * | 2015-06-30 | 2017-01-05 | General Electric Company | Fuel nozzle assembly |
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