Combustor with secondary fuel injector

Abstract

A combustor (202) includes: a transition duct (212) having a transition duct liner (224) defining an opening (226) extending through the transition duct liner; and a secondary fuel injector (300) disposed in the opening. The secondary fuel injector (300) has: an inner housing (306) arranged to define an interior space; an outer shell (304) cooperating with the inner shell (306) to define an annular outer space; a plurality of internal deflectors (312) positioned within the internal space and arranged around the inner shell, each internal deflector arranged to divert a first mixture of fuel and air around the inner shell in one of a clockwise direction and a counterclockwise direction; a plurality of outer deflectors (310) positioned within the outer space and arranged around the inner shell, each outer deflector being arranged to divert a second mixture of fuel and air around the inner shell in the other of the clockwise direction and the counterclockwise direction.

Description

Background Art

[0001] A gas turbine engine generally includes a compressor section, a turbine section, and a combustion section disposed therebetween. The compressor section includes multiple stages of rotating compressor blades and fixed compressor guide vanes. The combustion section generally includes multiple burners. The turbine section includes multiple stages of rotating turbine blades and fixed turbine guide vanes.

[0002] The combustor may include a fuel injector for providing fuel to mix with the compressed air from the compressor section and an ignition source for igniting the mixture to form a hot exhaust gas for the turbine section. Gas turbine combustion produces undesirable emissions, including unburned hydrocarbons. In addition, operating at higher temperatures produces higher efficiency. Therefore, it is desirable to operate at the highest possible temperature and ensure thorough combustion within the combustor. Summary of the invention

[0003] In one aspect, a combustor includes: a transition duct having a transition duct liner defining an opening extending through the transition duct liner; and a secondary fuel injector disposed in the opening. The secondary fuel injector includes: an inner shell arranged to define an inner space; an outer shell cooperating with the inner shell to define an annular outer space; a plurality of inner guides positioned within the inner space and arranged around the inner shell, each of the plurality of inner guides being arranged to divert a first mixture of fuel and air around the inner shell in one of a clockwise direction and a counterclockwise direction; and a plurality of outer guides positioned within the outer space and arranged around the inner shell, each of the plurality of outer guides being arranged to divert a second mixture of fuel and air around the inner shell in the other of a clockwise direction and a counterclockwise direction.

[0004] In one aspect, a combustor includes: a transition duct having a transition duct liner, the transition duct liner defining an opening extending through the transition duct liner; and a secondary fuel injector disposed in the opening. The secondary fuel injector includes: an inner shell arranged to define an inner space; an outer shell cooperating with the inner shell to define an annular outer space; a plurality of inner guides positioned within the inner space and arranged around the inner shell, the plurality of inner guides being arranged to divert a first mixture of fuel and air around the inner shell in one of a clockwise direction and a counterclockwise direction, each of the plurality of inner guides comprising an airfoil shape having an inner guide pressure side wall and an inner guide suction side wall; and a plurality of outer guides positioned within the outer space and arranged around the inner shell, the plurality of outer guides being arranged to divert a second mixture of fuel and air around the inner shell in the other of a clockwise direction and a counterclockwise direction, each of the plurality of outer guides having an airfoil shape having an outer guide pressure side wall and an outer guide suction side wall. BRIEF DESCRIPTION OF THE DRAWINGS

[0005] To easily identify the discussion of any particular element or act, the first one or more digits in a reference number refers to the figure number that first introduces the element.

[0006] Figure 1 is a longitudinal cross-sectional view of the gas turbine engine taken along a plane containing the longitudinal axis.

[0007] Figure 2 yes Figure 1 A longitudinal cross-sectional view of a combustion section of a gas turbine engine is shown in FIG.

[0008] Figure 3 yes Figure 2 A perspective view of a secondary fuel injector is shown in FIG.

[0009] Figure 4 yes Figure 3 A perspective cutaway view of a secondary fuel injector is shown in FIG.

[0010] Figure 5 yes Figure 3 A portion of a perspective view of a secondary fuel injector is shown in , better illustrating the plurality of external flow guides.

[0011] Figure 6 yes Figure 3 A portion of a perspective view of a secondary fuel injector is shown in , better illustrating the multiple internal flow directors. DETAILED DESCRIPTION

[0012] Before explaining any embodiment of the present invention in detail, it should be understood that the application of the present invention is not limited to the details of the construction and arrangement of the components set forth in this specification or shown in the following drawings. The present invention can have other embodiments and can be practiced or implemented in various ways. Moreover, it should be understood that the words and terms used herein are for descriptive purposes and should not be considered as limiting.

[0013] Various techniques related to systems and methods will now be described with reference to the accompanying drawings, wherein the same reference numerals represent the same elements throughout the text. The accompanying drawings discussed below and the various embodiments for describing the principles of the present invention in this patent document are intended to be illustrative only and should not be interpreted as limiting the scope of the present invention in any way. It will be appreciated by those skilled in the art that the principles of the present invention can be implemented in any suitably arranged device. It should be understood that the functions described as being performed by certain system elements can be performed by multiple elements. Similarly, for example, an element can be configured to perform the functions described as being performed by multiple elements. Multiple innovative teachings of the present application will be described with reference to exemplary non-limiting embodiments.

[0014] Moreover, it should be understood that the words or phrases used in the present invention should be interpreted broadly, unless explicitly limited in some examples. For example, the terms "include", "have" and "include" and their derivatives are meant to include without limitation. The singular forms "one" and "said" are also intended to include plural forms, unless the context clearly indicates otherwise. In addition, the term "and / or" used in the present invention refers to and covers any and all possible combinations of one or more items in the relevant listed items. The term "or" is inclusive, meaning "and / or", unless the context clearly indicates otherwise. The phrases "associated with..." and "associated with it" and their derivatives may mean including, included, interconnected with..., including, included, connected to... or connected with..., connected to... or connected with..., communicated with..., coordinated with..., interlaced, juxtaposed, close to, bound to or bound with..., have, have... characteristics, etc. In addition, although the present invention may describe multiple embodiments or configurations, any features, methods, steps, components, etc. described with reference to one embodiment are equally applicable to other embodiments without specific statements to the contrary.

[0015] In addition, although the present invention may use the terms "first", "second", "third" etc. to refer to various elements, information, functions or actions, these elements, information, functions or actions should not be limited by these terms. On the contrary, these digital adjectives are used to distinguish between different elements, information, functions or actions. For example, the first element, information, function or action can be referred to as the second element, information, function or action, and similarly, the second element, information, function or action can be referred to as the first element, information, function or action, without departing from the scope of the present invention.

[0016] In addition, in the specification, the term "axial" or "axially" refers to a direction along the longitudinal axis of the gas turbine engine. The term "radial" or "radially" refers to a direction perpendicular to the longitudinal axis of the gas turbine engine. The term "downstream" or "rearward" refers to a direction along the flow direction. The term "upstream" or "forward" refers to a direction opposite to the flow direction.

[0017] In addition, the term "adjacent" may refer to an element being relatively close to another element but not in contact with the other element, or the element being in contact with another part, unless the context clearly indicates otherwise. In addition, the phrase "based on" is intended to mean "based at least in part on," unless otherwise clearly indicated. The term "about" or "substantially" or similar terms are intended to encompass variations in values ​​within normal industrial manufacturing tolerances for the dimensions described. If no industry standard is available, a variation of 20% will fall within the meaning of these terms unless otherwise indicated.

[0018] Figure 1An example of a gas turbine engine 100 is shown, which includes a compressor section 102, a combustion section 104, and a turbine section 106 arranged along a longitudinal axis 108. The compressor section 102 includes a plurality of compressor stages 110, each compressor stage 110 including a set of fixed guide vanes 112 or adjustable guide vanes and a set of rotating blades 114. A rotor 116 supports the rotating blades 114 for rotation about the longitudinal axis 108 during operation. In some configurations, a single one-piece rotor 116 extends the length of the gas turbine engine 100 and is supported for rotation at either end by bearings. In other configurations, the rotor 116 is assembled from several separate tube shafts that are attached to each other, or may include multiple disk segments attached by one or more bolts.

[0019] The compressor section 102 is in fluid communication with the inlet section 118 to allow the gas turbine engine 100 to draw atmospheric air into the compressor section 102. During operation of the gas turbine engine 100, the compressor section 102 draws in atmospheric air and compresses the air for delivery to the combustion section 104. The compressor section 102 shown is an example of one compressor section 102, and other arrangements and designs are possible.

[0020] In the illustrated configuration, the combustion section 104 includes a plurality of individual combustors 120, each of which operates to mix a fuel flow with compressed air from the compressor section 102 and combust the air-fuel mixture to produce a high temperature, high pressure combustion gas or exhaust flow 122. Of course, the combustion section 104 may be of many other arrangements.

[0021] The turbine section 106 includes a plurality of turbine stages 124, each turbine stage 124 including a plurality of fixed turbine guide vanes 126 and a plurality of rotating turbine blades 128. The turbine stage 124 is arranged to receive the exhaust gas 122 from the combustion section 104 at a turbine inlet 130 and expand the gas to convert the heat energy and pressure energy into rotational or mechanical work. The turbine section 106 is connected to the compressor section 102 to drive the compressor section 102. For a gas turbine engine 100 used for power generation or as a prime mover, the turbine section 106 is also connected to a generator, a pump, or other device to be driven. Like the compressor section 102, the turbine section 106 can also be of other designs and arrangements.

[0022] The exhaust section 132 is positioned downstream of the turbine section 106 and is arranged to receive the expanded exhaust gas flow 122 from the last turbine stage 124 in the turbine section 106. The exhaust section 132 is arranged to effectively direct the exhaust gas 122 away from the turbine section 106 to ensure efficient operation of the turbine section 106. There can be many variations and design differences in the exhaust section 132. As such, the exhaust section 132 shown is only one example of these variations.

[0023] The control system 134 is coupled to the gas turbine engine 100 and operates to monitor various operating parameters and control various operations of the gas turbine engine 100. In a preferred configuration, the control system 134 is typically microprocessor-based and includes memory devices and data storage devices for collecting, analyzing, and storing data. In addition, the control system 134 provides output data to various devices, including monitors, printers, indicators, etc., which allow users to interact with the control system 134 to provide input or adjustments. In the example of a power generation system, a user can input a power output setpoint, and the control system 134 can adjust various control inputs to achieve the power output in an efficient manner.

[0024] The control system 134 can control various operating parameters, including but not limited to variable inlet guide vane position, fuel flow rate and pressure, engine speed, valve position, generator load, and generator excitation. Of course, other applications may have fewer or more controllable devices. The control system 134 also monitors various parameters to ensure that the gas turbine engine 100 operates properly. Some of the parameters monitored may include inlet air temperature, compressor outlet temperature and pressure, combustor outlet temperature, fuel flow rate, generator power output, bearing temperature, etc. Many of these measurements are displayed to the user and recorded for later inspection if such inspection is necessary.

[0025] Figure 2 Shows the application Figure 1 A longitudinal cross-sectional view of a combustion section 200 of a gas turbine engine 100. The combustion section 200 may be replaced by Figure 1 The combustion section 104.

[0026] The combustion section 200 includes a casing 204 and a combustor 202 surrounded by the casing 204. A plurality of combustors 202 are arranged circumferentially around the longitudinal axis 108 of the gas turbine engine 100 and are spaced apart from each other to define a can combustor, although other arrangements are possible. The plurality of combustors 202 are surrounded by the casing 204. A compressor outlet diffuser 206 is connected to the outlet of the compressor section 102 for providing compressed air 208 to the combustor 202.

[0027] Each of the plurality of combustors 202 includes a head end section 210 connected to a transition duct 212. The head end section 210 includes a primary fuel injector 214, which includes a primary fuel supply pipe 216 and a pilot burner 218. The primary fuel supply pipe 216 injects fuel to the combustor 202. The fuel is mixed with the compressed air 208 and ignited by the pilot burner 218 to produce exhaust gas 220.

[0028] The transition duct 212 has a transition duct liner 224 that surrounds an interior that defines a combustion chamber 222 through which exhaust gas 220 passes. The outlet of the transition duct 212 is connected to the inlet of the turbine section 106 so that the exhaust gas 220 enters the turbine section 106. The transition duct liner 224 defines a plurality of openings 226 that are circumferentially arranged around the transition duct 212 and spaced apart from each other. Each opening 226 of the plurality of openings 226 extends through the transition duct liner 224.

[0029] The combustor 202 includes a plurality of secondary fuel injectors 300 disposed downstream of the primary fuel injectors 214 and on an upstream side of the transition duct 212. Each of the plurality of secondary fuel injectors 300 is disposed in one of the plurality of openings 226.

[0030] Figure 3 Shows Figure 2 3. A perspective view of one of the plurality of secondary fuel injectors 300 shown in FIG. The secondary fuel injector 300 includes a fuel supply tube 302, an outer shell 304, an inner shell 306, and a center hub 308. The fuel supply tube 302 connects the secondary fuel injector 300 to a fuel chamber ring (not shown) to provide a secondary fuel flow 314 to the secondary fuel injector 300. The fuel supply tube 302 is attached to the outer shell 304.

[0031] The inner shell 306 has a generally cylindrical shape and defines an inner space 316 therein. The central hub 308 is disposed at the center of the inner space 316. The outer shell 304 has a generally cylindrical shape and is disposed around the inner shell 306. The outer space 318 has an annular shape defined between the outer shell 304 and the inner shell 306. The outer shell 304, the inner shell 306, and the central hub 308 are concentric along a central axis 320. The radius of the central hub 308 is between 10% and 90% of the radius of the inner shell 306. In other configurations, the radius of the central hub 308 may not be between 10% and 90% of the radius of the inner shell 306.

[0032] The secondary fuel injector 300 includes a plurality of internal flow directors 312 located within the internal space 316. The plurality of internal flow directors 312 are arranged around the inner shell 306 and are spaced apart from each other. The plurality of internal flow directors 312 are located between the central hub 308 and the inner shell 306. The inner span length of each internal flow director 312 is the distance between the inner shell 306 and the central hub 308. In a configuration without the central hub 308, the inner span length of each internal flow director 312 is the distance between the inner shell 306 and the center of the internal space 316.

[0033] The secondary fuel injector 300 includes a plurality of outer flow guides 310 located within the outer space 318. The plurality of outer flow guides 310 are arranged around the inner shell 306 and are spaced apart from each other. The outer span length of each outer flow guide 310 is the distance between the outer shell 304 and the inner shell 306. The inner span length is less than the outer span length. In other configurations, the inner span length may be greater than or equal to the outer span length.

[0034] The number of the outer flow directors 310 is greater than the number of the inner flow directors 312. Figure 3 In the illustrated configuration, the number of outer flow directors 310 is twice the number of inner flow directors 312. In other configurations, the ratio of the number of outer flow directors 310 to the number of inner flow directors 312 may be greater or less than two.

[0035] Figure 4 Shows Figure 3 2. The secondary fuel injector 300 is a perspective cutaway view of the secondary fuel injector 300 shown in FIG. The housing 304 has an outer wall 402, an inner wall 404, a first side wall 406, and a second side wall 408. The first side wall 406 and the second side wall 408 are disposed between the outer wall 402 and the inner wall 404. The first side wall 406 tapers from the outer wall 402 to the inner wall 404 toward the transition duct 212. The outer wall 402, the inner wall 404, the first side wall 406, and the second side wall 408 define a hollow housing interior 410.

[0036] Each of the plurality of outer flow directors 310 has a hollow outer flow director interior 412 that is fluidly connected to the hollow outer shell interior 410. Each of the plurality of inner flow directors 312 has a hollow inner flow director interior 414 that is fluidly connected to a hollow outer flow director interior 412 of one of the plurality of outer flow directors 310.

[0037] The secondary fuel injector 300 includes a mixing tube 416 extending from the inner wall 404 toward the transition duct 212. The secondary fuel 314 and the compressed air 208 are mixed in the mixing tube 416 to produce a mixture of fuel and air. The center hub 308 includes a purge air passage 418 to prevent a flame from being retained at the end of the center hub 308. The mixture of fuel and air exits the secondary fuel injector 300 and enters the combustion chamber 222 where it is ignited when mixed with the exhaust gas 220 from the head end section 210 of the combustor 202.

[0038] Figure 5 Shows Figure 3, better illustrating the plurality of outer deflectors 310. Each outer deflector 310 has an airfoil shape having an outer deflector pressure side wall 502 and an outer deflector suction side wall 504. A hollow outer deflector interior 412 is defined between the outer deflector pressure side wall 502 and the outer deflector suction side wall 504. Figure 5 In the illustrated configuration, each outer deflector pressure side wall 502 and each outer deflector suction side wall 504 are curved with a curvature arranged to turn flow passing between adjacent outer deflectors 310 in a counterclockwise direction about the inner shell 306 relative to the central axis 320 of the secondary fuel injector 300. In other configurations, each outer deflector pressure side wall 502 and each outer deflector suction side wall 504 may be curved with a curvature arranged to turn flow passing between adjacent outer deflectors 310 in a clockwise direction about the inner shell 306 relative to the central axis 320 of the secondary fuel injector 300.

[0039] Each outer deflector 310 has at least one outer deflector fuel outlet 508 defined on one side wall of the outer deflector fuel outlet 508. Figure 5 In the configuration shown in , each outer inducer 310 has four outer inducer fuel outlets 508 defined at the outer inducer pressure side wall 502. In other configurations, each outer inducer 310 may have more or less than four outer inducer fuel outlets 508 defined at the outer inducer pressure side wall 502, and / or at least one outer inducer fuel outlet 508 may be defined at the outer inducer suction side wall 504.

[0040] The secondary fuel injector 300 has a plurality of external vortex generators 506. At least one of the plurality of external vortex generators 506 is attached to a side wall of an external flow guide 310 and protrudes outward from the side wall. Figure 5 In the illustrated configuration, three external vortex generators 506 are attached to the external inducer suction sidewall 504 of each external inducer 310. The external vortex generators 506 have a generally prismatic shape. In other configurations, the number of external vortex generators 506 attached to the external inducer suction sidewall 504 may be greater than or less than three, and / or the external vortex generators 506 may be attached to the external inducer pressure sidewall 502, and / or the external vortex generators 506 may have different geometries. It is also possible that at least one external inducer 310 has no external vortex generators 506 attached.

[0041] Figure 6 Shows Figure 3, better illustrating the plurality of inner inducers 312. Each inner inducer 312 has an airfoil shape having an inner inducer pressure side wall 602 and an inner inducer suction side wall 604. A hollow inner inducer interior 414 is defined between the inner inducer pressure side wall 602 and the inner inducer suction side wall 604. Figure 6 In the illustrated configuration, each inner inducer pressure side wall 602 and each inner inducer suction side wall 604 are curved, with the curvature thereof turning such that the flow passing between adjacent inner inducers 312 turns in a clockwise direction about the inner shell 306 relative to the central axis 320 of the secondary fuel injector 300. In other configurations, each inner inducer pressure side wall 602 and each inner inducer suction side wall 604 may be curved, with the curvature thereof turning such that the flow passing between adjacent inner inducers 312 turns in a counterclockwise direction about the inner shell 306 relative to the central axis 320 of the secondary fuel injector 300.

[0042] Each inner deflector 312 has at least one inner deflector fuel outlet 608 defined on a side wall of the inner deflector 312. Figure 6 In the illustrated configuration, each inner inducer 312 has one inner inducer fuel outlet 608 defined at the inner inducer pressure side wall 602. In other configurations, each inner inducer 312 may have more than one inner inducer fuel outlet 608 defined at the inner inducer pressure side wall 602, and / or at least one inner inducer fuel outlet 608 may be defined at the inner inducer suction side wall 604.

[0043] The secondary fuel injector 300 has a plurality of internal vortex generators 606. At least one of the plurality of internal vortex generators 606 is attached to one side wall of the inner flow guide 312 and protrudes outward from the one side wall. Figure 6 In the illustrated configuration, one internal vortex generator 606 is attached to the internal inducer suction sidewall 604 of each internal inducer 312. The internal vortex generator 606 has a generally prismatic shape. In other configurations, the number of internal vortex generators 606 attached to the internal inducer suction sidewall 604 may be more than one, and / or the internal vortex generator 606 may be attached to the internal inducer pressure sidewall 602, and / or the internal vortex generator 606 may have a different geometry. It is also possible that at least one internal inducer 312 does not have an internal vortex generator 606 attached.

[0044] refer to Figure 5 and Figure 6The plurality of outer guides 310 and the plurality of inner guides 312 are arranged such that the outer guide pressure side wall 502 and the inner guide pressure side wall 602 turn the flow passing therethrough in opposite circumferential directions. Figure 5 and Figure 6 In the illustrated configuration, the outer inducer pressure side wall 502 turns the flow therethrough in a counterclockwise direction around the inner shell 306, and the inner inducer pressure side wall 602 turns the flow therethrough in a clockwise direction around the inner shell 306. In other configurations, the outer inducer pressure side wall 502 can turn the flow therethrough in a clockwise direction, and the inner inducer pressure side wall 602 can turn the flow therethrough in a counterclockwise direction.

[0045] During operation, refer to Figures 1 to 6 , secondary fuel 314 is provided from a fuel chamber ring (not shown) to the fuel supply tube 302 and enters the hollow housing interior 410. The secondary fuel 314 is then provided to the plurality of outer deflectors 310 through the hollow outer deflector interior 412, where a portion of the fuel exits the outer deflector 310 through the outer deflector fuel outlet 508 and enters the exterior space 318. The remainder of the secondary fuel 314 flows through the hollow inner deflector interior 414 to the plurality of inner deflectors 312, and exits the inner deflector 312 through the inner deflector fuel outlet 608 and enters the interior space 316.

[0046] The compressed air 208 enters the interior space 316 and mixes with the secondary fuel 314 in the interior space 316 to form a first mixture of fuel and air. The compressed air 208 enters the exterior space 318 and mixes with the secondary fuel 314 in the exterior space 318 to form a second mixture of fuel and air. The first mixture of fuel and air is rotated by the arrangement of the plurality of internal flow guides 312 and turned around the inner shell 306 in one direction of a clockwise direction and a counterclockwise direction to improve mixing in the interior space 316. The second mixture of fuel and air is rotated by the arrangement of the plurality of external flow guides 310 and turned around the inner shell 306 in the other direction of a clockwise direction and a counterclockwise direction to improve mixing in the exterior space 318. The first mixture of fuel and air and the second mixture of fuel and air are mixed together in the mixing tube 416 before leaving the secondary fuel injector 300. The mixing of the secondary fuel 314 and the compressed air 208 is further improved in the mixing tube 416 by turning the first mixture of fuel and air in the interior space 316 and the second mixture of fuel and air in the exterior space 318 in opposite clockwise and counterclockwise directions. The plurality of outer vortex generators 506 and the plurality of inner vortex generators 606 also enhance the mixing of the secondary fuel 314 and the compressed air 208.

[0047] The outer span length of each outer flow director 310 is greater than the inner span length of each inner flow director 312, so that the flow area in the outer space 318 is greater than the flow area in the inner space 316. The number of outer flow directors 310 is greater than the number of inner flow directors 312. The span length, shell diameter, number of flow directors, and other parameters are selected so that a residual vortex remains at the outlet of the secondary fuel injector 300 in the direction generated by the flow through the outer space 318. Other configurations may be reversed so that a residual vortex remains at the outlet of the secondary fuel injector 300 in the direction generated by the flow through the inner space 316.

[0048] Although the exemplary embodiments of the present invention have been described in detail, those skilled in the art will understand that they may make various changes, substitutions, alterations, and modifications herein without departing from the spirit and scope of the invention in its broadest form.

[0049] Nothing in the description of this application should be read as implying that any particular element, step, action, or function is an essential element that must be included within the scope of the claims. The scope of the subject matter of this patent is limited only by the issued claims. Furthermore, unless the exact words "means for..." are followed by a participle, none of the claims are intended to invoke a means-plus-function claim construction.

[0050] Reference numerals

[0051] 100: Gas turbine engine

[0052] 102: Compressor section

[0053] 104: Combustion section

[0054] 106: Turbine section

[0055] 108: Longitudinal axis

[0056] 110: Compressor stage

[0057] 112: Fixed guide vane

[0058] 114: Rotating blades

[0059] 116: Rotor

[0060] 118: Entrance section

[0061] 120: Burner

[0062] 122: Exhaust

[0063] 124: Turbine stage

[0064] 126: Fixed turbine guide vane

[0065] 128: Rotating turbine blades

[0066] 130: Turbine inlet

[0067] 132: Exhaust

[0068] 134: Control System

[0069] 200: Combustion section

[0070] 202: Burner

[0071] 204: Shell

[0072] 206: Compressor outlet diffuser

[0073] 208: Compressed air

[0074] 210: Headend

[0075] 212: Transition Pipeline

[0076] 214: Primary fuel injector

[0077] 216: Primary fuel supply pipe

[0078] 218: Ignition

[0079] 220: Exhaust

[0080] 222: Combustion Chamber

[0081] 224: Transition pipe bushing

[0082] 226: Opening

[0083] 300: Secondary fuel injector

[0084] 302: Fuel supply pipe

[0085] 304: Shell

[0086] 306: Inner shell

[0087] 308: Center Hub

[0088] 310: External deflector

[0089] 312: Internal deflector

[0090] 314: Secondary Fuel

[0091] 316: Inner Space

[0092] 318: External Space

[0093] 320: Central axis

[0094] 402: Outer wall

[0095] 404: Inner wall

[0096] 406: First side wall

[0097] 408: Second side wall

[0098] 410: Inside the hollow shell

[0099] 412: Hollow external deflector interior

[0100] 414: Hollow internal deflector interior

[0101] 416: Mixing tube

[0102] 418: Purge air channel

[0103] 502: External guide pressure side wall

[0104] 504: External deflector suction side wall

[0105] 506: External vortex generator

[0106] 508: External deflector fuel outlet

[0107] 602: Internal guide pressure side wall

[0108] 604: Internal deflector suction side wall

[0109] 606: Internal vortex generator

[0110] 608: Internal deflector fuel outlet

Claims

1. A burner, comprising: a transition duct including a transition duct liner defining an opening extending through the transition duct liner; as well as A secondary fuel injector is disposed in the opening, the secondary fuel injector comprising: an inner shell arranged to define an interior space; An outer shell, cooperating with the inner shell to define an annular outer space; a plurality of internal flow directors positioned within the interior space and arranged around the inner shell, each of the plurality of internal flow directors arranged to divert a first mixture of fuel and air around the inner shell in one of a clockwise direction and a counterclockwise direction; and A plurality of outer flow guides are positioned within the outer space and arranged around the inner shell, each of the plurality of outer flow guides being arranged to divert the second mixture of fuel and air around the inner shell in the other of a clockwise direction and a counterclockwise direction.

2. The burner according to claim 1, wherein: Each inner flow inducer of the plurality of inner flow inducers includes an airfoil shape having an inner flow inducer pressure sidewall and an inner flow inducer suction sidewall.

3. The burner according to claim 2, wherein: The inner inducer pressure side wall defines an inner inducer fuel outlet.

4. The burner according to claim 2, wherein: The secondary fuel injector includes a plurality of internal vortex generators, and wherein one of the plurality of internal vortex generators is attached to the inner inducer suction sidewall.

5. The burner according to claim 1, wherein: Each outer flow inducer of the plurality of outer flow inducers includes an airfoil shape having an outer flow inducer pressure sidewall and an outer flow inducer suction sidewall.

6. The burner according to claim 5, wherein: The outer inducer pressure side wall defines an outer inducer fuel outlet.

7. The burner according to claim 5, wherein: The secondary fuel injector includes a plurality of external vortex generators, and wherein one of the plurality of external vortex generators is attached to the outer inducer suction sidewall.

8. The burner according to claim 1, wherein: Each inner flow director of the plurality of inner flow directors has an inner span length, wherein each outer flow director of the plurality of outer flow directors has an outer span length, and wherein the inner span length is less than the outer span length.

9. The burner according to claim 1, wherein: The housing defines a hollow housing interior to provide fuel to the plurality of outer deflectors.

10. The burner according to claim 1, wherein Each of the plurality of inner flow directors is in fluid communication with one of the plurality of outer flow directors.

11. The burner according to claim 1, wherein: The number of the outer flow directors is greater than the number of the inner flow directors.

12. The burner according to claim 1, wherein: The secondary fuel injector includes a central hub disposed at a center of the interior space, wherein the central hub includes a radius between 10% and 90% of a radius of the inner shell, and wherein the plurality of internal guides are positioned between the central hub and the inner shell.

13. A burner comprising: a transition duct including a transition duct liner defining an opening extending through the transition duct liner; as well as A secondary fuel injector is disposed in the opening, the secondary fuel injector comprising: an inner shell arranged to define an interior space; An outer shell, cooperating with the inner shell to define an annular outer space; a plurality of internal guides positioned within the interior space and arranged around the inner shell, the plurality of internal guides arranged to divert a first mixture of fuel and air around the inner shell in one of a clockwise direction and a counterclockwise direction, each of the plurality of internal guides comprising an airfoil shape having an internal guide pressure side wall and an internal guide suction side wall; and A plurality of external guides are positioned within the outer space and arranged around the inner shell, the plurality of external guides being arranged to divert the second mixture of fuel and air around the inner shell in the other of a clockwise direction and a counterclockwise direction, each of the plurality of external guides comprising an airfoil shape having an external guide pressure side wall and an external guide suction side wall.

14. The burner according to claim 13, wherein: The inner inducer pressure side wall defines an inner inducer fuel outlet.

15. The burner according to claim 13, wherein: The secondary fuel injector includes a plurality of internal vortex generators, and wherein one of the plurality of internal vortex generators is attached to the inner inducer suction sidewall.

16. The burner according to claim 13, wherein: The outer inducer pressure side wall defines an outer inducer fuel outlet.

17. The burner according to claim 13, wherein: The secondary fuel injector includes a plurality of external vortex generators, and wherein one of the plurality of external vortex generators is attached to the outer inducer suction sidewall.

18. The burner according to claim 13, wherein: Each inner flow director of the plurality of inner flow directors has an inner span length, wherein each outer flow director of the plurality of outer flow directors has an outer span length, and wherein the inner span length is less than the outer span length.

19. The burner according to claim 13, wherein: The housing defines a hollow housing interior to provide fuel to the plurality of outer deflectors.

20. The burner according to claim 13, wherein: Each of the plurality of inner flow directors is in fluid communication with one of the plurality of outer flow directors.

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