US20170268783A1 - Axially staged fuel injector assembly mounting - Google Patents
Axially staged fuel injector assembly mounting Download PDFInfo
- Publication number
- US20170268783A1 US20170268783A1 US15/070,093 US201615070093A US2017268783A1 US 20170268783 A1 US20170268783 A1 US 20170268783A1 US 201615070093 A US201615070093 A US 201615070093A US 2017268783 A1 US2017268783 A1 US 2017268783A1
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- United States
- Prior art keywords
- support plate
- injector
- liner
- fuel injector
- flow sleeve
- 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.)
- Abandoned
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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
-
- 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
- F23R3/346—Feeding into different combustion zones for staged combustion
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
-
- 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
- F23R3/002—Wall structures
-
- 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
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
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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
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
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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
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/35—Combustors or associated equipment
Definitions
- the subject matter disclosed herein relates to a combustor for a gas turbine. More specifically, the disclosure is directed to a system and method for mounting an axially staged fuel injector assembly of a gas turbine combustor.
- Gas turbines usually burn hydrocarbon fuels and produce air polluting emissions such as oxides of nitrogen (NOx) and carbon monoxide (CO). Oxidization of molecular nitrogen in the gas turbine depends upon the temperature of gas located in a combustor, as well as the residence time for reactants located in the highest temperature regions within the combustor. Thus, the amount of NOx produced by the gas turbine may be reduced by either maintaining the combustor temperature below a temperature at which NOx is produced, or by limiting the residence time of the reactant in the combustor.
- NOx oxides of nitrogen
- CO carbon monoxide
- One approach for controlling the temperature of the combustor involves pre-mixing fuel and air to create a lean fuel-air mixture prior to combustion.
- This approach may include the axial staging of fuel injection where a first fuel-air mixture is injected and ignited at a first or primary combustion zone of the combustor to produce a main flow of high energy combustion gases, and where a second fuel-air mixture is injected into and mixed with the main flow of high energy combustion gases via a plurality of radially oriented and circumferentially spaced fuel injectors or axially staged fuel injector assemblies positioned downstream from the primary combustion zone.
- Axially staged injection increases the likelihood of complete combustion of available fuel, which in turn reduces the air polluting emissions.
- Liner cooling is typically achieved by routing a cooling medium such as the compressed air through a cooling flow annulus or flow passage defined between the liner and a flow sleeve and/or an impingement sleeve that surrounds the liner.
- a cooling medium such as the compressed air
- hardware for mounting the axially staged fuel injector assemblies creates a flow blockage or obstruction within the cooling flow annulus, thereby disrupting the cooling flow through the cooling flow annulus. This disruption in the cooling flow annulus may result in reduced pressure of the cooling medium at a head end portion of the combustor and/or reduced cooling effectiveness of the cooling medium within the cooling flow annulus, particularly downstream from the mounting hardware.
- One embodiment of the present disclosure is directed to a system for mounting an axially staged fuel injector.
- the system includes an annularly shaped liner that at least partially defines a hot gas path of a combustor.
- the liner defines an injector opening that extends radially through the liner.
- a flow sleeve circumferentially surrounds at least a portion of the liner and is radially spaced from the liner to form a cooling flow annulus therebetween.
- An annular injector boss extends radially from the liner through the flow sleeve.
- the injector boss includes a first end portion that extends circumferentially about the injector opening and a second end portion that is disposed radially outwardly from an outer surface of the flow sleeve.
- the injector boss is formed to receive a fuel injector.
- the present disclosure is directed to a system for mounting an axially staged fuel injector.
- the system includes an annularly shaped liner that at least partially defines a hot gas path of a combustor.
- the liner defines a injector boss opening that extends radially through the liner.
- a flow sleeve circumferentially surrounds at least a portion of the liner.
- the flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween.
- An annular injector boss is coaxially aligned with the injector opening and extends radially from the liner through the flow sleeve.
- the injector boss has a first end portion that is fixedly connected to the liner and a second end portion disposed radially outwardly from an outer surface of the flow sleeve.
- the injector boss is formed to receive a fuel injector.
- Another embodiment includes a method for mounting an axially staged fuel injector.
- the method includes inserting a support plate into a slot defined along a side wall of a second end portion of an injector boss where the second end portion is disposed radially outwardly from an outer surface of the flow sleeve, placing a support plate cap over the support plate, threading a first end of a double ended stud into a fastener opening defined by the support plate where the double ended stud extends through the support plate cap and inserting a fuel injector into the injector boss where a second end of the double ended stud extends through a mounting hole defined by the fuel injector.
- the method further includes securing the fuel injector to the support plate cap via a nut that is threadingly engaged with the second end of the double ended stud.
- FIG. 1 is a functional block diagram of an exemplary gas turbine that may incorporate various embodiments of the present disclosure
- FIG. 2 is a simplified cross-section side view of an exemplary combustor as may incorporate various embodiments of the present disclosure
- FIG. 3 provides an exploded perspective view of a portion of the combustor including a system for mounting an axially staged fuel injector according to at least one embodiment of the present disclosure
- FIG. 4 provides an assembled cross sectional upstream view of the system as shown in FIG. 3 , according to at least one embodiment of the present disclosure
- FIG. 5 provides a top view of a portion of the system as shown in FIGS. 3 and 4 , according to at least one embodiment of the present disclosure.
- FIG. 6 provides a block diagram of a method for mounting an axially staged fuel injector according to at least one embodiment of the present disclosure.
- upstream refers to the relative direction with respect to fluid flow in a fluid pathway.
- upstream refers to the direction from which the fluid flows
- downstream refers to the direction to which the fluid flows.
- radially refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component
- axially refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component
- circumferentially refers to the relative direction that extends around the axial centerline of a particular component.
- FIG. 1 illustrates a schematic diagram of an exemplary gas turbine 10 .
- the gas turbine 10 generally includes an inlet section 12 , a compressor 14 disposed downstream of the inlet section 12 , at least one combustor 16 disposed downstream of the compressor 14 , a turbine 18 disposed downstream of the combustor 16 and an exhaust section 20 disposed downstream of the turbine 18 . Additionally, the gas turbine 10 may include one or more shafts 22 that couple the compressor 14 to the turbine 18 .
- air 24 flows through the inlet section 12 and into the compressor 14 where the air 24 is progressively compressed, thus providing compressed air 26 to the combustor 16 .
- At least a portion of the compressed air 26 is mixed with a fuel 28 within the combustor 16 and burned to produce combustion gases 30 .
- the combustion gases 30 flow from the combustor 16 into the turbine 18 , wherein energy (kinetic and/or thermal) is transferred from the combustion gases 30 to rotor blades (not shown), thus causing shaft 22 to rotate.
- the mechanical rotational energy may then be used for various purposes such as to power the compressor 14 and/or to generate electricity.
- the combustion gases 30 exiting the turbine 18 may then be exhausted from the gas turbine 10 via the exhaust section 20 .
- the combustor 16 may be at least partially surrounded an outer casing 32 such as a compressor discharge casing.
- the outer casing 32 may at least partially define a high pressure plenum 34 that at least partially surrounds various components of the combustor 16 .
- the high pressure plenum 34 may be in fluid communication with the compressor 14 ( FIG. 1 ) so as to receive the compressed air 26 therefrom.
- An end cover 36 may be coupled to the outer casing 32 .
- the outer casing 32 and the end cover 36 may at least partially define a head end volume or portion 38 of the combustor 16 .
- the head end portion 38 is in fluid communication with the high pressure plenum 34 and/or the compressor 14 .
- Fuel nozzles 40 extend axially downstream from the end cover 36 .
- One or more annularly shaped liners or ducts 42 may at least partially define a primary or first combustion or reaction zone 44 for combusting the first fuel-air mixture and/or may at least partially define a secondary combustion or reaction zone 46 formed axially downstream from the first combustion zone 44 with respect to an axial centerline 48 of the combustor 16 .
- the liner 42 at least partially defines a hot gas path 50 from the primary fuel nozzle(s) 40 to an inlet 52 of the turbine 18 ( FIG. 1 ).
- the liner 42 may be formed so as to include a tapering or transition portion.
- the liner 42 may be formed from a singular or continuous body.
- a flow sleeve 54 circumferentially surrounds at least a portion of the liner 42 . The flow sleeve 54 is radially spaced from the liner 42 to form a cooling flow annulus 56 therebetween.
- the combustor 16 includes an axially staged fuel injection system 58 .
- the axially staged fuel injection system 58 includes at least one fuel injector or fuel injector assembly 60 axially staged or spaced from the primary fuel nozzle(s) 40 with respect to axial centerline 48 .
- the fuel injector 60 is disposed downstream of the primary fuel nozzle(s) 40 and upstream of the inlet 52 to the turbine 18 . It is contemplated that a number of fuel injectors 60 (including two, three, four, five, or more fuel injector assemblies 60 ) may be used in a single combustor 16 .
- FIG. 3 provides an exploded perspective view of a portion of the combustor 16 including the system 100 according to at least one embodiment of the present disclosure.
- FIG. 4 provides an assembled cross sectional upstream view of the system 100 as shown in FIG. 3 , according to at least one embodiment of the present disclosure.
- FIG. 5 provides a top view of a portion of the system 100 as shown in FIGS. 3 and 4 according to at least one embodiment of the present disclosure.
- the system 100 includes the annularly shaped liner 42 .
- the liner 42 defines an injector opening 102 that extends radially through the liner 42 .
- the flow sleeve 54 circumferentially surrounds at least a portion of the liner 42 and the cooling flow annulus 56 is formed radially therebetween.
- an annular injector boss 104 extends radially from the liner 42 through the flow sleeve 54 .
- the injector boss 104 is formed to receive a portion of the fuel injector 60 .
- the injector boss 104 has a first end portion 106 ( FIG.
- the injector boss 104 includes a second end portion 108 that is disposed radially outwardly from an outer surface 62 of the flow sleeve 54 .
- the injector boss 104 at least partially defines a slot or groove 110 .
- the slot 110 may be defined along a side wall 112 of the injector boss 104 proximate to the second end portion 108 .
- the slot 110 may extend circumferentially about the injector boss 104 within and/or along the side wall 112 .
- the slot 110 is positioned radially outward from the outer surface 62 of the flow sleeve 54 .
- the system 100 includes a support plate 114 disposed radially outwardly from the outer surface 62 of the flow sleeve 54 .
- the support plate 114 extends circumferentially at least partially around the injector boss 104 .
- the support plate 114 includes an inner portion or surface 116 that extends into the slot 110 defined by the injector boss 104 .
- the support plate 114 is made up of multiple plates formed to wrap around the injector boss and/or extend into the slot 110 .
- the support plate 114 may comprise a first plate 114 ( a ) and a second plate 114 ( b ).
- Each of the first plate 114 ( a ) and the second plate 114 ( b ) may include a respective inner surface or portion 116 ( a ), 116 ( b ) which extends within the slot 110 .
- the inner surface 116 ( a ), 116 ( b ) may be generally arcuate.
- one or more of the support plate 114 or support plates 114 ( a ), 114 ( b ) define one or more fastener openings 118 along a top side 120 of the respective support plate 114 , 114 ( a ), 114 ( b ).
- one or more fastener openings 118 may be threaded or may include a threaded insert 122 ( FIG. 4 ) for receiving a threaded fastener.
- the system 100 may include a support plate cap 124 .
- the support plate cap 124 includes an inner side 126 , an outer side 128 and a pocket or void 130 defined along the inner side 126 . At least a portion of the support plate 104 may be seated or disposed within the pocket 130 .
- the support plate cap 124 is fixedly connected to the flow sleeve 54 .
- the support plate cap 124 may be bolted or otherwise fastened or attached to the flow sleeve 54 via one or more fasteners 132 .
- the support plate cap 124 is sealed against the outer surface 62 of the flow sleeve 54 .
- the support plate cap 124 defines a plurality of fastener holes 134 coaxially aligned with a respective fastener opening 118 defined by the support plate 114 and a respective mounting hole 136 defined by the axially staged fuel injector 60 .
- at least one doubled ended stud 138 may be used to secure or attach the support plate cap 124 to the support plate 114 . As shown in FIG.
- a first end portion 140 of the double ended stud 138 is threadingly engaged with the support plate 114 for example via the threaded insert 122 and a second end portion 142 of the doubled ended stud 138 extends radially through a respective mounting hole 136 defined by the fuel injector 60 .
- At least one doubled ended stud 138 extends from the support plate 114 through a respective fastener hole 134 of the support plate cap 124 and through a respective mounting hole 136 defined by the fuel injector 60 .
- the first end 140 of the double ended stud 138 is threadingly engaged with the support plate 114 and the second end 142 of the doubled ended stud 138 is threadingly engaged with a nut 144 .
- FIG. 6 provides a block diagram of method 200 according to one embodiment of the present disclosure.
- method 200 includes inserting the support plate 114 and/or supports plates 114 ( a ), 114 ( b ) into the slot 110 defined along the side wall 112 of the second end portion 108 of the injector boss 104 where the second end portion 108 is disposed radially outwardly from the outer surface 62 of the flow sleeve 54 .
- method 200 includes placing the support plate cap 124 over the support plate 114 .
- method 200 includes threading the first end 140 of a respective double ended stud 138 into a respective fastener opening 118 defined by the support plate 114 where the double ended stud 138 extends through the support plate cap 124 .
- method 200 includes inserting the fuel injector 60 into the injector boss 104 where the second end 142 of the double ended stud 138 extends through a respective mounting hole 136 defined by the fuel injector 62 .
- method 200 includes securing or attaching the fuel injector 60 to the support plate cap 124 via a nut 144 threadingly engaged with the second end 142 of the double ended stud 138 .
- the various embodiment of the system for mounting axially staged fuel injectors 100 described and illustrated herein provide various technical benefits over existing mounting configurations. For example, by positioning the various mounting components such as the support plate 114 , the support plate cap 124 , the double ended studs 138 and the portion of the injector boss 104 that engages with these components flow obstructions within the cooling flow annulus are reduced, thereby enhancing cooling of the liner during operation of the combustor 16 .
- the system 100 may reduce assembly and disassembly time for installing and removing the fuel injectors 60 .
Abstract
The present disclosure is directed to a system for mounting an axially staged fuel injector assembly. The system includes an annularly shaped liner that at least partially defines a hot gas path of a combustor. The liner defines an injector opening that extends radially through the liner. A flow sleeve circumferentially surrounds at least a portion of the liner and is radially spaced from the liner to form a cooling flow annulus therebetween. An annular injector boss extends radially from the liner through the flow sleeve. The injector boss includes a first end portion that extends circumferentially about the injector opening and a second end portion that is disposed radially outwardly from an outer surface of the flow sleeve. The injector boss is formed to receive a fuel injector. The present disclosure is also directed to a method for mounting an axially staged fuel injector.
Description
- The subject matter disclosed herein relates to a combustor for a gas turbine. More specifically, the disclosure is directed to a system and method for mounting an axially staged fuel injector assembly of a gas turbine combustor.
- Gas turbines usually burn hydrocarbon fuels and produce air polluting emissions such as oxides of nitrogen (NOx) and carbon monoxide (CO). Oxidization of molecular nitrogen in the gas turbine depends upon the temperature of gas located in a combustor, as well as the residence time for reactants located in the highest temperature regions within the combustor. Thus, the amount of NOx produced by the gas turbine may be reduced by either maintaining the combustor temperature below a temperature at which NOx is produced, or by limiting the residence time of the reactant in the combustor.
- One approach for controlling the temperature of the combustor involves pre-mixing fuel and air to create a lean fuel-air mixture prior to combustion. This approach may include the axial staging of fuel injection where a first fuel-air mixture is injected and ignited at a first or primary combustion zone of the combustor to produce a main flow of high energy combustion gases, and where a second fuel-air mixture is injected into and mixed with the main flow of high energy combustion gases via a plurality of radially oriented and circumferentially spaced fuel injectors or axially staged fuel injector assemblies positioned downstream from the primary combustion zone. Axially staged injection increases the likelihood of complete combustion of available fuel, which in turn reduces the air polluting emissions.
- During operation of the combustor, it is necessary to cool one or more liners or ducts that form a combustion chamber and/or a hot gas path through the combustor. Liner cooling is typically achieved by routing a cooling medium such as the compressed air through a cooling flow annulus or flow passage defined between the liner and a flow sleeve and/or an impingement sleeve that surrounds the liner. However, in particular configurations, hardware for mounting the axially staged fuel injector assemblies creates a flow blockage or obstruction within the cooling flow annulus, thereby disrupting the cooling flow through the cooling flow annulus. This disruption in the cooling flow annulus may result in reduced pressure of the cooling medium at a head end portion of the combustor and/or reduced cooling effectiveness of the cooling medium within the cooling flow annulus, particularly downstream from the mounting hardware.
- Aspects and advantages are set forth below in the following description, or may be obvious from the description, or may be learned through practice.
- One embodiment of the present disclosure is directed to a system for mounting an axially staged fuel injector. The system includes an annularly shaped liner that at least partially defines a hot gas path of a combustor. The liner defines an injector opening that extends radially through the liner. A flow sleeve circumferentially surrounds at least a portion of the liner and is radially spaced from the liner to form a cooling flow annulus therebetween. An annular injector boss extends radially from the liner through the flow sleeve. The injector boss includes a first end portion that extends circumferentially about the injector opening and a second end portion that is disposed radially outwardly from an outer surface of the flow sleeve. The injector boss is formed to receive a fuel injector.
- Another embodiment of the present disclosure is directed to a system for mounting an axially staged fuel injector. The system includes an annularly shaped liner that at least partially defines a hot gas path of a combustor. The liner defines a injector boss opening that extends radially through the liner. A flow sleeve circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. An annular injector boss is coaxially aligned with the injector opening and extends radially from the liner through the flow sleeve. The injector boss has a first end portion that is fixedly connected to the liner and a second end portion disposed radially outwardly from an outer surface of the flow sleeve. The injector boss is formed to receive a fuel injector.
- Another embodiment includes a method for mounting an axially staged fuel injector. The method includes inserting a support plate into a slot defined along a side wall of a second end portion of an injector boss where the second end portion is disposed radially outwardly from an outer surface of the flow sleeve, placing a support plate cap over the support plate, threading a first end of a double ended stud into a fastener opening defined by the support plate where the double ended stud extends through the support plate cap and inserting a fuel injector into the injector boss where a second end of the double ended stud extends through a mounting hole defined by the fuel injector. The method further includes securing the fuel injector to the support plate cap via a nut that is threadingly engaged with the second end of the double ended stud.
- Those of ordinary skill in the art will better appreciate the features and aspects of such embodiments, and others, upon review of the specification.
- A full and enabling disclosure of the of various embodiments, including the best mode thereof to one skilled in the art, is set forth more particularly in the remainder of the specification, including reference to the accompanying figures, in which:
-
FIG. 1 is a functional block diagram of an exemplary gas turbine that may incorporate various embodiments of the present disclosure; -
FIG. 2 is a simplified cross-section side view of an exemplary combustor as may incorporate various embodiments of the present disclosure; -
FIG. 3 provides an exploded perspective view of a portion of the combustor including a system for mounting an axially staged fuel injector according to at least one embodiment of the present disclosure; -
FIG. 4 provides an assembled cross sectional upstream view of the system as shown inFIG. 3 , according to at least one embodiment of the present disclosure; -
FIG. 5 provides a top view of a portion of the system as shown inFIGS. 3 and 4 , according to at least one embodiment of the present disclosure; and -
FIG. 6 provides a block diagram of a method for mounting an axially staged fuel injector according to at least one embodiment of the present disclosure. - Reference will now be made in detail to present embodiments of the disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to features in the drawings. Like or similar designations in the drawings and description have been used to refer to like or similar parts of the disclosure.
- As used herein, the terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components. The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid pathway. For example, “upstream” refers to the direction from which the fluid flows, and “downstream” refers to the direction to which the fluid flows. The term “radially” refers to the relative direction that is substantially perpendicular to an axial centerline of a particular component, the term “axially” refers to the relative direction that is substantially parallel and/or coaxially aligned to an axial centerline of a particular component and the term “circumferentially” refers to the relative direction that extends around the axial centerline of a particular component.
- The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting. As used herein, the singular forms “a”, “an” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and/or groups thereof.
- Each example is provided by way of explanation, not limitation. In fact, it will be apparent to those skilled in the art that modifications and variations can be made without departing from the scope or spirit thereof. For instance, features illustrated or described as part of one embodiment may be used on another embodiment to yield a still further embodiment. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents. Although exemplary embodiments of the present disclosure will be described generally in the context of a combustor for a land based power generating gas turbine combustor for purposes of illustration, one of ordinary skill in the art will readily appreciate that embodiments of the present disclosure may be applied to any style or type of combustor for a turbomachine and are not limited to combustors or combustion systems for land based power generating gas turbines unless specifically recited in the claims.
- Referring now to the drawings,
FIG. 1 illustrates a schematic diagram of anexemplary gas turbine 10. Thegas turbine 10 generally includes aninlet section 12, acompressor 14 disposed downstream of theinlet section 12, at least onecombustor 16 disposed downstream of thecompressor 14, aturbine 18 disposed downstream of thecombustor 16 and anexhaust section 20 disposed downstream of theturbine 18. Additionally, thegas turbine 10 may include one ormore shafts 22 that couple thecompressor 14 to theturbine 18. - During operation,
air 24 flows through theinlet section 12 and into thecompressor 14 where theair 24 is progressively compressed, thus providingcompressed air 26 to thecombustor 16. At least a portion of the compressedair 26 is mixed with afuel 28 within thecombustor 16 and burned to producecombustion gases 30. Thecombustion gases 30 flow from thecombustor 16 into theturbine 18, wherein energy (kinetic and/or thermal) is transferred from thecombustion gases 30 to rotor blades (not shown), thus causingshaft 22 to rotate. The mechanical rotational energy may then be used for various purposes such as to power thecompressor 14 and/or to generate electricity. Thecombustion gases 30 exiting theturbine 18 may then be exhausted from thegas turbine 10 via theexhaust section 20. - As shown in
FIG. 2 , thecombustor 16 may be at least partially surrounded anouter casing 32 such as a compressor discharge casing. Theouter casing 32 may at least partially define ahigh pressure plenum 34 that at least partially surrounds various components of thecombustor 16. Thehigh pressure plenum 34 may be in fluid communication with the compressor 14 (FIG. 1 ) so as to receive thecompressed air 26 therefrom. Anend cover 36 may be coupled to theouter casing 32. In particular embodiments, theouter casing 32 and theend cover 36 may at least partially define a head end volume orportion 38 of thecombustor 16. In particular embodiments, thehead end portion 38 is in fluid communication with thehigh pressure plenum 34 and/or thecompressor 14. -
Fuel nozzles 40 extend axially downstream from theend cover 36. One or more annularly shaped liners orducts 42 may at least partially define a primary or first combustion orreaction zone 44 for combusting the first fuel-air mixture and/or may at least partially define a secondary combustion orreaction zone 46 formed axially downstream from thefirst combustion zone 44 with respect to anaxial centerline 48 of thecombustor 16. Theliner 42 at least partially defines ahot gas path 50 from the primary fuel nozzle(s) 40 to aninlet 52 of the turbine 18 (FIG. 1 ). In at least one embodiment, theliner 42 may be formed so as to include a tapering or transition portion. In particular embodiments, theliner 42 may be formed from a singular or continuous body. Aflow sleeve 54 circumferentially surrounds at least a portion of theliner 42. Theflow sleeve 54 is radially spaced from theliner 42 to form acooling flow annulus 56 therebetween. - In at least one embodiment, the
combustor 16 includes an axially stagedfuel injection system 58. The axially stagedfuel injection system 58 includes at least one fuel injector orfuel injector assembly 60 axially staged or spaced from the primary fuel nozzle(s) 40 with respect toaxial centerline 48. Thefuel injector 60 is disposed downstream of the primary fuel nozzle(s) 40 and upstream of theinlet 52 to theturbine 18. It is contemplated that a number of fuel injectors 60 (including two, three, four, five, or more fuel injector assemblies 60) may be used in asingle combustor 16. - In various embodiments, a system for mounting the axially staged fuel injector(s) 60, herein referred to as “system” is provided.
FIG. 3 provides an exploded perspective view of a portion of thecombustor 16 including thesystem 100 according to at least one embodiment of the present disclosure.FIG. 4 provides an assembled cross sectional upstream view of thesystem 100 as shown inFIG. 3 , according to at least one embodiment of the present disclosure.FIG. 5 provides a top view of a portion of thesystem 100 as shown inFIGS. 3 and 4 according to at least one embodiment of the present disclosure. - In at least one embodiment, as shown in
FIGS. 3 and 4 collectively, thesystem 100 includes the annularly shapedliner 42. As shown inFIG. 4 , theliner 42 defines aninjector opening 102 that extends radially through theliner 42. Theflow sleeve 54 circumferentially surrounds at least a portion of theliner 42 and thecooling flow annulus 56 is formed radially therebetween. As shown inFIGS. 3 and 4 , anannular injector boss 104 extends radially from theliner 42 through theflow sleeve 54. Theinjector boss 104 is formed to receive a portion of thefuel injector 60. Theinjector boss 104 has a first end portion 106 (FIG. 4 ) that extends circumferentially about theinjector opening 102. Thefirst end portion 106 may partially define the hot gas path 50 (FIG. 2 ). As shown inFIGS. 3 and 4 , theinjector boss 104 includes asecond end portion 108 that is disposed radially outwardly from anouter surface 62 of theflow sleeve 54. - In particular embodiments, as shown in
FIGS. 3 and 4 theinjector boss 104 at least partially defines a slot orgroove 110. In at least one embodiment, theslot 110 may be defined along aside wall 112 of theinjector boss 104 proximate to thesecond end portion 108. Theslot 110 may extend circumferentially about theinjector boss 104 within and/or along theside wall 112. In various embodiments, theslot 110 is positioned radially outward from theouter surface 62 of theflow sleeve 54. - In at least one embodiment, as shown in
FIGS. 3 and 4 collectively, thesystem 100 includes asupport plate 114 disposed radially outwardly from theouter surface 62 of theflow sleeve 54. Thesupport plate 114 extends circumferentially at least partially around theinjector boss 104. As shown inFIG. 4 , thesupport plate 114 includes an inner portion orsurface 116 that extends into theslot 110 defined by theinjector boss 104. - In at least one embodiment, as shown in
FIG. 3 , thesupport plate 114 is made up of multiple plates formed to wrap around the injector boss and/or extend into theslot 110. For example, as shown inFIG. 3 , thesupport plate 114 may comprise a first plate 114(a) and a second plate 114(b). Each of the first plate 114(a) and the second plate 114(b) may include a respective inner surface or portion 116(a), 116(b) which extends within theslot 110. The inner surface 116(a), 116(b) may be generally arcuate. - In at least one embodiment, as shown in
FIGS. 3 and 4 , one or more of thesupport plate 114 or support plates 114(a), 114(b) define one ormore fastener openings 118 along atop side 120 of therespective support plate 114, 114(a), 114(b). In particular embodiments, one ormore fastener openings 118 may be threaded or may include a threaded insert 122 (FIG. 4 ) for receiving a threaded fastener. - In at least one embodiment, as shown in
FIGS. 3 and 4 collectively, thesystem 100 may include asupport plate cap 124. As shown inFIG. 4 , thesupport plate cap 124 includes aninner side 126, anouter side 128 and a pocket or void 130 defined along theinner side 126. At least a portion of thesupport plate 104 may be seated or disposed within thepocket 130. - In particular embodiments, the
support plate cap 124 is fixedly connected to theflow sleeve 54. For example, as shown inFIG. 5 , thesupport plate cap 124 may be bolted or otherwise fastened or attached to theflow sleeve 54 via one ormore fasteners 132. In particular embodiments, thesupport plate cap 124 is sealed against theouter surface 62 of theflow sleeve 54. - In particular embodiments, as shown in
FIGS. 3 and 4 , thesupport plate cap 124 defines a plurality offastener holes 134 coaxially aligned with arespective fastener opening 118 defined by thesupport plate 114 and arespective mounting hole 136 defined by the axially stagedfuel injector 60. In at least one embodiment, as shown inFIGS. 3, 4 and 5 collectively, at least one doubled endedstud 138 may be used to secure or attach thesupport plate cap 124 to thesupport plate 114. As shown inFIG. 4 , afirst end portion 140 of the double endedstud 138 is threadingly engaged with thesupport plate 114 for example via the threadedinsert 122 and asecond end portion 142 of the doubled endedstud 138 extends radially through arespective mounting hole 136 defined by thefuel injector 60. - In particular embodiments, as shown in
FIGS. 3, 4 and 5 collectively, at least one doubled endedstud 138 extends from thesupport plate 114 through arespective fastener hole 134 of thesupport plate cap 124 and through arespective mounting hole 136 defined by thefuel injector 60. Thefirst end 140 of the double endedstud 138 is threadingly engaged with thesupport plate 114 and thesecond end 142 of the doubled endedstud 138 is threadingly engaged with anut 144. - The various embodiments described and illustrated herein provide a
method 200 for mounting an axially stagedfuel injector 60.FIG. 6 provides a block diagram ofmethod 200 according to one embodiment of the present disclosure. As shown inFIG. 6 atstep 202,method 200 includes inserting thesupport plate 114 and/or supports plates 114(a), 114(b) into theslot 110 defined along theside wall 112 of thesecond end portion 108 of theinjector boss 104 where thesecond end portion 108 is disposed radially outwardly from theouter surface 62 of theflow sleeve 54. Atstep 204,method 200 includes placing thesupport plate cap 124 over thesupport plate 114. Atstep 206,method 200 includes threading thefirst end 140 of a respective double endedstud 138 into arespective fastener opening 118 defined by thesupport plate 114 where the double endedstud 138 extends through thesupport plate cap 124. Atstep 208,method 200 includes inserting thefuel injector 60 into theinjector boss 104 where thesecond end 142 of the double endedstud 138 extends through arespective mounting hole 136 defined by thefuel injector 62. Atstep 210,method 200 includes securing or attaching thefuel injector 60 to thesupport plate cap 124 via anut 144 threadingly engaged with thesecond end 142 of the double endedstud 138. - The various embodiment of the system for mounting axially staged
fuel injectors 100 described and illustrated herein provide various technical benefits over existing mounting configurations. For example, by positioning the various mounting components such as thesupport plate 114, thesupport plate cap 124, the double endedstuds 138 and the portion of theinjector boss 104 that engages with these components flow obstructions within the cooling flow annulus are reduced, thereby enhancing cooling of the liner during operation of thecombustor 16. In addition, thesystem 100 may reduce assembly and disassembly time for installing and removing thefuel injectors 60. - This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.
Claims (19)
1. A system for mounting an axially staged fuel injector, comprising:
an annularly shaped liner at least partially defining a hot gas path of a combustor, wherein the liner defines an injector opening that extends radially through the liner;
a flow sleeve circumferentially surrounding at least a portion of the liner, wherein the flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween; and
an annular injector boss extending radially from the liner through the flow sleeve, the injector boss having a first end portion that extends circumferentially about the injector opening and a second end portion disposed radially outwardly from an outer surface of the flow sleeve, wherein the injector boss is formed to receive a fuel injector.
2. The system as in claim 1 , further comprising a support plate disposed radially outwardly from the outer surface of the flow sleeve, wherein the support plate extends circumferentially around the injector boss, wherein the support plate includes an inner portion that extends into a slot defined by the injector boss.
3. The system as in claim 2 , wherein the support plate comprises a first plate and a second plate, wherein an inner portion of the first plate and an inner portion of the second plate extend within the slot defined by the injector boss.
4. The system as in claim 2 , further comprising a doubled ended stud, wherein a first end of the double ended stud is threadingly engaged with the support plate and a second end of the doubled ended stud extends radially through a mounting hole defined by the fuel injector.
5. The system as in claim 2 , further comprising a support plate cap having an inner side, an outer side and a pocket defined along the inner side, wherein at least a portion of the support plate is seated within the pocket.
6. The system as in claim 5 , wherein the support plate cap is fixedly connected to the flow sleeve.
7. The system as in claim 5 , wherein the support plate cap is sealed against the outer surface of the flow sleeve.
8. The system as claim 5 , wherein the support plate cap defines a plurality of fastener holes, wherein each fastener hole is coaxially aligned with a respective fastener opening defined by the support plate and a mounting hole defined by the axially staged fuel injector.
9. The system as in claim 5 , further comprising a doubled ended stud that extends from the support plate through the support cover and through a mounting hole defined by the fuel injector, wherein a first end of the double ended stud is threadingly engaged with the support plate and a second end of the doubled ended stud is threadingly engaged with a nut.
10. A system for mounting an axially staged fuel injector, comprising:
an annularly shaped liner at least partially defining a hot gas path of a combustor, wherein the liner defines a injector boss opening that extends radially through the liner;
a flow sleeve circumferentially surrounding at least a portion of the liner, wherein the flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween; and
an annular injector boss coaxially aligned with the injector opening and extending radially from the liner through the flow sleeve, the injector boss having a first end portion fixedly connected to the liner and a second end portion disposed radially outwardly from an outer surface of the flow sleeve, wherein the injector boss is formed to receive a fuel injector.
11. The system as in claim 10 , further comprising a support plate disposed radially outwardly from the outer surface of the flow sleeve, wherein the support plate extends circumferentially around the injector boss, wherein the support plate includes an inner portion that extends into a slot defined by the injector boss.
12. The system as in claim 11 , wherein the support plate comprises a first plate and a second plate, wherein an inner portion of the first plate and an inner portion of the second plate extend within the slot defined by the injector boss.
13. The system as in claim 11 , further comprising a doubled ended stud, wherein a first end of the double ended stud is threadingly engaged with the support plate and a second end of the doubled ended stud extends radially through a mounting hole defined by the fuel injector.
14. The system as in claim 11 , further comprising a support plate cap having an inner side, an outer side and a pocket defined along the inner side, wherein at least a portion of the support plate is seated within the pocket.
15. The system as in claim 14 , wherein the support plate cap is fixedly connected to the flow sleeve.
16. The system as in claim 15 , wherein the support plate cap is sealed against the outer surface of the flow sleeve.
17. The system as claim 15 , wherein the support plate cap defines a plurality of fastener holes, wherein each fastener hole is coaxially aligned with a respective fastener opening defined by the support plate and a mounting hole defined by the axially staged fuel injector.
18. The system as in claim 15 , further comprising a doubled ended stud that extends from the support plate through the support cover and through a mounting hole defined by the fuel injector, wherein a first end of the double ended stud is threadingly engaged with the support plate and a second end of the doubled ended stud is threadingly engaged with a nut.
19. A method for mounting an axially staged fuel injector, comprising:
inserting a support plate into a slot defined along a side wall of a second end portion of an injector boss, wherein the second end portion is disposed radially outwardly from an outer surface of the flow sleeve;
placing a support plate cap over the support plate;
threading a first end of a double ended stud into a fastener opening defined by the support plate, wherein the double ended stud extends through the support plate cap;
inserting a fuel injector into the injector boss, wherein a second end of the double ended stud extends through a mounting hole defined by the fuel injector; and
securing the fuel injector to the support plate cap via a nut threadingly engaged with the second end of the double ended stud.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/070,093 US20170268783A1 (en) | 2016-03-15 | 2016-03-15 | Axially staged fuel injector assembly mounting |
JP2017039941A JP2017166811A (en) | 2016-03-15 | 2017-03-03 | Axially staged fuel injector assembly mounting |
EP17160047.1A EP3220053A1 (en) | 2016-03-15 | 2017-03-09 | Axially staged fuel injector assembly and method of mounting |
KR1020170031187A KR20170107391A (en) | 2016-03-15 | 2017-03-13 | Axially staged fuel injector assembly mounting |
CN201710153136.XA CN107191969A (en) | 2016-03-15 | 2017-03-15 | Axially staged fuel injector assembly is installed |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/070,093 US20170268783A1 (en) | 2016-03-15 | 2016-03-15 | Axially staged fuel injector assembly mounting |
Publications (1)
Publication Number | Publication Date |
---|---|
US20170268783A1 true US20170268783A1 (en) | 2017-09-21 |
Family
ID=58265869
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US15/070,093 Abandoned US20170268783A1 (en) | 2016-03-15 | 2016-03-15 | Axially staged fuel injector assembly mounting |
Country Status (5)
Country | Link |
---|---|
US (1) | US20170268783A1 (en) |
EP (1) | EP3220053A1 (en) |
JP (1) | JP2017166811A (en) |
KR (1) | KR20170107391A (en) |
CN (1) | CN107191969A (en) |
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US20170260866A1 (en) * | 2016-03-10 | 2017-09-14 | Siemens Energy, Inc. | Ducting arrangement in a combustion system of a gas turbine engine |
US10203114B2 (en) | 2016-03-04 | 2019-02-12 | General Electric Company | Sleeve assemblies and methods of fabricating same |
US10228141B2 (en) | 2016-03-04 | 2019-03-12 | General Electric Company | Fuel supply conduit assemblies |
US10422237B2 (en) * | 2017-04-11 | 2019-09-24 | United Technologies Corporation | Flow diverter case attachment for gas turbine engine |
US11047576B2 (en) * | 2017-03-29 | 2021-06-29 | Delavan, Inc. | Combustion liners and attachments for attaching to nozzles |
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US11067281B1 (en) * | 2020-09-25 | 2021-07-20 | General Electric Company | Fuel injection assembly for a turbomachine combustor |
CN114033580A (en) * | 2021-11-02 | 2022-02-11 | 上海中船三井造船柴油机有限公司 | Liner assembly for mounting gas valve and mounting method thereof |
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2016
- 2016-03-15 US US15/070,093 patent/US20170268783A1/en not_active Abandoned
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- 2017-03-03 JP JP2017039941A patent/JP2017166811A/en active Pending
- 2017-03-09 EP EP17160047.1A patent/EP3220053A1/en not_active Withdrawn
- 2017-03-13 KR KR1020170031187A patent/KR20170107391A/en unknown
- 2017-03-15 CN CN201710153136.XA patent/CN107191969A/en active Pending
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US3879940A (en) * | 1973-07-30 | 1975-04-29 | Gen Electric | Gas turbine engine fuel delivery tube assembly |
US4441323A (en) * | 1981-04-16 | 1984-04-10 | Rolls-Royce Limited | Combustion equipment for a gas turbine engine including a fuel burner capable of accurate positioning and installation as a unit in a flame tube |
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US10203114B2 (en) | 2016-03-04 | 2019-02-12 | General Electric Company | Sleeve assemblies and methods of fabricating same |
US10228141B2 (en) | 2016-03-04 | 2019-03-12 | General Electric Company | Fuel supply conduit assemblies |
US20170260866A1 (en) * | 2016-03-10 | 2017-09-14 | Siemens Energy, Inc. | Ducting arrangement in a combustion system of a gas turbine engine |
US11047576B2 (en) * | 2017-03-29 | 2021-06-29 | Delavan, Inc. | Combustion liners and attachments for attaching to nozzles |
US11774102B2 (en) | 2017-03-29 | 2023-10-03 | Collins Engine Nozzles, Inc. | Combustion liners and attachments for attaching to nozzles |
US10422237B2 (en) * | 2017-04-11 | 2019-09-24 | United Technologies Corporation | Flow diverter case attachment for gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
CN107191969A (en) | 2017-09-22 |
JP2017166811A (en) | 2017-09-21 |
EP3220053A1 (en) | 2017-09-20 |
KR20170107391A (en) | 2017-09-25 |
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