Combustor with fuel sweep structure

Abstract

To provide a combustor for a turbomachine.SOLUTION: A combustor (17) includes: a combustion liner (46) surrounded by an outer sleeve (48); and a fuel injection assembly (80). The fuel injection assembly (80) includes a fuel injector (100) that extends through the outer sleeve (48) and the combustion liner (46) to a secondary combustion zone (72). A fuel supply conduit (254) is positioned outside of the outer sleeve (48), and extends to the fuel injector (100). The fuel injection assembly (80) further includes a shielding assembly (102) coupled to the outer sleeve (48) and at least partially surrounding the fuel supply conduit (254). The shielding assembly (102) includes a venturi nozzle (296) having a circumferentially converging portion (297) and a circumferentially diverging portion (298). At least one fuel sweep opening (260) is defined in the outer sleeve (48) and disposed within the shielding assembly (102).SELECTED DRAWING: Figure 2

Description

Technical Field

[0001] The present disclosure generally relates to combustors of turbomachines. In particular, the present disclosure relates to combustors having a structure for inducing a swept flow of air and fuel.

Background Art

[0002] Turbomachines are utilized in various industries and applications for energy transfer purposes. For example, a gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed within the combustion section and burned within the combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section to the turbine section, where they expand to generate work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to a generator to generate electricity. Then, the combustion gases exit the gas turbine via the exhaust section.

[0003] In some combustors, the generation of combustion gases occurs in two axially spaced stages. Such combustors are herein referred to as those including an "axial fuel staging" (AFS) system, which delivers fuel and an oxidizer to one or more fuel injectors downstream of the head end of the combustor. In a combustor having an AFS system, a primary fuel nozzle at the upstream end of the combustor injects fuel and air (or a fuel / air mixture) axially into a primary combustion zone, and an AFS fuel injector located at a location downstream of the primary fuel nozzle injects fuel and air (or a second fuel / air mixture) as a crossflow into a secondary combustion zone downstream of the primary combustion zone. The crossflow generally crosses the flow of combustion products from the primary combustion zone.

[0004] AFS fuel injectors are typically supplied with fuel through one or more fluid conduits that extend generally axially along the outer sleeve of the combustor. In some cases, one or more components of the AFS system (such as fuel conduits) may wear out over time, causing fuel to leak around the combustor. It is important to keep the leaked fuel away from the hot components of the combustor to prevent autoignition of the leaked fuel, which could damage or destroy the combustor components.

[0005] Therefore, an improved combustor having an AFS system that advantageously reduces the risk of damage from leaking fuel would be desirable in the art. [Overview of the project]

[0006] The embodiments and advantages of the combustors and turbomachinery described herein are partially described in the following description, or become apparent from the description, or can be learned through the practice of the art.

[0007] According to one embodiment, a combustor is provided. The combustor includes an end cover and a front casing. The combustor further includes at least one fuel nozzle extending from the end cover and at least partially enclosed by the front casing. A combustion liner extends between the at least one fuel nozzle and a rear frame. An outer sleeve surrounds the combustion liner, spaced apart from it such that an annular portion is defined between them. The combustion liner defines a combustion chamber having a primary combustion zone downstream of the at least one fuel nozzle and a secondary combustion zone downstream of the primary combustion zone. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector extending through the outer sleeve, the annular portion, and the combustion liner to the secondary combustion zone. A fuel supply conduit is positioned outside the outer sleeve. The fuel supply conduit extends to the fuel injector. The fuel injection assembly further includes a shielding assembly coupled to the outer sleeve and at least partially enclosing the fuel supply conduit. The shielding assembly includes a venturi nozzle having a circumferentially converging portion and a circumferentially expanding portion. At least one fuel sweep opening is defined in the outer sleeve and located within the shielding assembly.

[0008] According to another embodiment, a turbomachinery is provided. The turbomachinery includes a compressor section, a turbine section, and a combustor. The combustor is located downstream of the compressor section and upstream of the turbine section. The combustor includes an end cover and a forward casing. The combustor further includes at least one fuel nozzle extending from the end cover and at least partially enclosed by the forward casing. A combustion liner extends between the at least one fuel nozzle and a rear frame. An outer sleeve is spaced apart from the combustion liner and surrounds the combustion liner such that an annular portion is defined between them. The combustion liner defines a combustion chamber having a primary combustion zone downstream of the at least one fuel nozzle and a secondary combustion zone downstream of the primary combustion zone. The combustor further includes a fuel injection assembly. The fuel injection assembly includes a fuel injector extending through the outer sleeve, the annular portion, and the combustion liner to the secondary combustion zone. A fuel supply conduit is positioned outside the outer sleeve. The fuel supply conduit extends to the fuel injector. The fuel injection assembly further includes a shielding assembly coupled to an outer sleeve and at least partially enclosing the fuel supply conduit. The shielding assembly includes a venturi nozzle having a circumferential converging portion and a circumferential expanding portion. At least one fuel sweep opening is defined in the outer sleeve and located within the shielding assembly.

[0009] These and other features, aspects, and advantages of the combustor and turbomachinery will be better understood by referring to the following description and the appended claims. The appended drawings, which are incorporated herein and constitute part of this specification, illustrate embodiments of the art and, together with the description in the specification, help to illustrate the principles of the art.

[0010] A complete and implementable disclosure of the combustor and turbomachinery, including the best modes of manufacture and use of the system and method, intended for those skilled in the art, is described herein with reference to the accompanying drawings. [Brief explanation of the drawing]

[0011] [Figure 1] This is a schematic diagram of a turbomachinery according to an embodiment of the present disclosure. [Figure 2] This is a cross-sectional view of a combustor according to an embodiment of the present disclosure. [Figure 3] This is an enlarged view of a combustor having a fuel injection assembly according to an embodiment of the present disclosure. [Figure 4] This is an enlarged cross-sectional view of a combustor having a fuel injection assembly according to an embodiment of the present disclosure. [Figure 5] This is an enlarged perspective view of a forward tube shield installed in a combustor according to an embodiment of the present disclosure. [Figure 6] This is an enlarged cross-sectional view of a forward tube shield installed in a combustor according to an embodiment of the present disclosure. [Figure 7] This is an exploded view of a shielding assembly and fuel supply conduit separated from the combustor according to an embodiment of the present disclosure. [Modes for carrying out the invention]

[0012] Embodiments of the combustor and turbomachinery described herein are referenced in detail, with one or more examples shown in the drawings. Each example is provided for illustrative purposes of the present art and is not intended to limit the present art. Indeed, it will be apparent to those skilled in the art that modifications and alterations are possible in the present art without departing from the scope or spirit of the claimed art. For example, features illustrated or described as part of one embodiment can also be used in another embodiment to bring about further embodiments. Thus, this disclosure is intended to encompass such modifications and alterations within the scope of the appended claims and their equivalents.

[0013] Detailed descriptions use numerals and letters to refer to features in the drawings. Similar or identical reference numerals in the drawings and descriptions are used to refer to similar or identical parts of the invention. As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of any individual component.

[0014] As used herein, the terms “upstream” and “downstream” refer to the relative direction of fluid flow in a fluid path. For example, “upstream” refers to the direction in which the fluid is flowing, and “downstream” refers to the direction in which the fluid is flowing. Unless otherwise specified, the terms “forward” and “rear” refer to directions, “forward” refers to the front or compressor end of a gas turbine, and “rear” refers to the rear section of a gas turbine.

[0015] The term “radially” refers to a relative direction substantially perpendicular to the axial centerline of a particular component; the term “axially” refers to a relative direction substantially parallel to and / or coaxially aligned with the axial centerline of a particular component; and the term “circumferentially” refers to a relative direction extending around the axial centerline of a particular component. Approximate terms such as “generally” or “about” include values ​​within a range of plus or minus 10 percent of the stated value. When used in the context of angles or directions, such terms include a range of plus or minus 10 degrees of the stated angle or direction. For example, “generally perpendicular” includes any direction, e.g., within 10 degrees from perpendicular in a clockwise or counterclockwise direction.

[0016] Referring here to the drawings, Figure 1 shows a schematic diagram of one embodiment of a turbomachinery, which in the illustrated embodiment is a gas turbine 10. Although industrial and onshore gas turbines are shown and described herein, this disclosure is not limited to onshore and / or industrial gas turbines unless specifically stated in the claims. For example, the present invention as described herein can be used in any type of turbomachinery, including, but is not limited to, steam turbines, aircraft gas turbines, or marine gas turbines.

[0017] As shown in the figure, the gas turbine 10 generally includes an inlet section 12, a compressor section 14 located downstream of the inlet section 12, a number of combustors (not shown) in a combustor section 16 located downstream of the compressor section 14, a turbine section 18 located downstream of the combustor section 16, and an exhaust section 20 located downstream of the turbine section 18. In addition, the gas turbine 10 may include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.

[0018] The compressor section 14 may generally include a plurality of rotor disks 24 (one of which is shown) and a plurality of rotor blades 26 extending radially outward from each rotor disk 24 and connected to each rotor disk 24. Each rotor disk 24 may then be coupled to or form part of a shaft 22 extending through the compressor section 14.

[0019] The turbine section 18 may generally include a plurality of rotor disks 28 (one of which is shown) and a plurality of rotor blades 30 extending radially outward from each rotor disk 28 and connected to each rotor disk 28. Each rotor disk 28 may then be coupled to or form part of a shaft 22 extending through the turbine section 18. The turbine section 18 further includes an outer casing 31 that circumferentially surrounds part of the shaft 22 and the rotor blades 30, thereby at least partially defining a hot gas path 32 through the turbine section 18.

[0020] During operation, a working fluid such as air flows through the inlet section 12 to the compressor section 14, where the air is gradually compressed, thereby supplying pressurized or compressed air 15 to the combustors 17 of the combustor section 16. The compressed air 15 is mixed with fuel and burned in each combustor to produce combustion gases 34. The combustion gases 34 flow from the combustor section 16 to the turbine section 18 through the high-temperature gas path 32, where energy (kinetic and / or thermal energy) is transferred from the combustion gases 34 to the rotor blades 30, causing the shaft 22 to rotate. The mechanical rotational energy can then be used to supply power to the compressor section 14 and / or generate electricity. The combustion gases 34 exiting the turbine section 18 can then be exhausted from the gas turbine 10 through the exhaust section 20.

[0021] Figure 2 is a schematic diagram of a combustor 17 that may be included in a can-ring combustion system for a heavy-duty gas turbine 10. In a can-ring combustion system, multiple combustors 17 (e.g., 8, 10, 12, 14, 16, or more) are positioned in an annular array around a shaft 22 that connects the compressor section 14 to the turbine section 18.

[0022] As shown in FIG. 2, the combustor 17 can define an axial direction A extending along an axial centerline 170. The combustor can also define a circumferential direction C extending around the axial direction A and the axial centerline 170. The combustor 17 can further define a radial direction R perpendicular to the axial direction A and the axial centerline 170.

[0023] FIG. 2 shows a combustor 17 having one or more exemplary fuel injection assemblies 80 (also referred to as an axial fuel staging (AFS) system) further described herein. The combustor 17 includes a combustion liner 46 that defines a combustion chamber 70. The combustion liner 46 can be positioned within an outer sleeve 48 such that an annular portion 47 is formed therebetween (i.e., may be circumferentially surrounded by the outer sleeve 48). At least one fuel nozzle 40 can be positioned at a front end of the combustor 17. Fuel 37 may be directed to the fuel nozzle 40 through a fuel supply line 38 extending through an end cover 42. The fuel nozzle 40 conveys fuel 37 and compressed air 15 to a primary combustion zone 72 where combustion occurs. In some embodiments, fuel 37 and compressed air 15 are combined as a mixture before reaching the primary combustion zone 72.

[0024] The combustion liner 46 can contain the combustion gas 27 and convey it to the turbine section 18. The combustion liner 46 defines a combustion chamber 70 where combustion occurs. As shown in FIG. 2, the combustion liner can extend between the fuel nozzle 40 and the rear frame 118. Similar to many conventional combustion systems, the combustion liner 46 can have a cylindrical liner portion and a tapered transition portion separate from the cylindrical liner portion. Alternatively, the combustion liner 46 may have a unitary body (or "unibody") configuration in which the cylindrical portion and the tapered portion are integrated with each other. Thus, the description of the combustion liner 46 in this specification is intended to encompass both conventional combustion systems with separate liners and transition pieces and combustion systems with a unibody liner. Further, the present disclosure is equally applicable to combustion systems in which the transition piece and the first-stage nozzle of the turbine are integrated into a single unit, sometimes referred to as a "transition nozzle" or "integrated outlet piece".

[0025] The combustion liner 46 may be surrounded by an outer sleeve 48, which is radially spaced outward from the combustion liner 46 so as to define an annular portion 47 between the combustion liner 46 and the outer sleeve 48. In exemplary embodiments, the outer sleeve 48 may include a flow sleeve 110 at its front end and an impingement sleeve 112 at its rear end. The flow sleeve 110 and the impingement sleeve 112 may be coupled to each other. For example, the flow sleeve 110 may include a first end or front end coupled to the front casing 50 and a second end or rear end extending into the front end of the impingement sleeve 112 so as to form an interference fit between the impingement sleeve 112 and the flow sleeve 110, and overlapping the front end axially. In many embodiments, the flow sleeve 110 extends between the front casing 50 and the impingement sleeve 112. As shown in the figures, the impingement sleeve may extend between the flow sleeve 110 and the rear frame 118 of the combustor 17. Alternatively, the outer sleeve 48 may have a single integrated body (or "unisleeve") configuration in which the flow sleeve 110 and the impingement sleeve 112 are integrated with each other in the axial direction. As stated above, the description of the outer sleeve 48 in this specification is intended to encompass both conventional combustion systems having separate flow sleeves 110 and impingement sleeves 112 and combustion systems having a unisleeve outer sleeve. However, in exemplary embodiments of this disclosure, the combustor 17 includes the flow sleeve 110 and the impingement sleeve 112 as separate components coupled together.

[0026] In an exemplary embodiment, the combustion liner 46 is surrounded by an outer sleeve 48, which forms an annular section 47 between them through which compressed air 15 flows to the head end of the combustor 17. Heat is convectivally transferred from the combustion liner 46 to the compressed air 15, thus cooling the combustion liner 46 and heating the compressed air 15. The combustion liner 46 can be formed of an upstream liner component and a downstream transition component. The liner component may be generally cylindrical, and the transition component may be tapered from a cylindrical front end to a generally rectangular rear end.

[0027] The forward casing 50 and end cover 42 of the combustor 17 can define a head-end air plenum 122, which includes one or more fuel nozzles 40. The fuel nozzles 40 may be any type of fuel nozzle, such as a bundle fuel nozzle or a swaddle nozzle. For example, the fuel nozzles 40 are positioned within the head-end air plenum 122 defined by the forward casing 50. In many embodiments, the fuel nozzles 40 may extend from the end cover 42. For example, each fuel nozzle 40 may be coupled to the rear surface of the end cover 42 via a flange (not shown). As shown in Figure 2, at least one fuel nozzle 40 may be partially enclosed by a combustion liner 46. The rear end or downstream end of the fuel nozzle 40 extends through a cap 44 that defines the upstream end of the combustion chamber 70.

[0028] The forward casing 50 connects to a compressor discharge casing 60 which defines a high-pressure plenum 66 around the combustion liner 46 and outer sleeve 48. Compressed air 15 from the compressor section 14 travels through the high-pressure plenum 66 and enters the combustor 17 through an opening (not shown) at the downstream end of the outer sleeve 48 (indicated by an arrow near the rear frame 118). The compressed air travels upstream through the annular section 47, is rotated by the end cover 42, and enters the fuel nozzle 40 to cool the head end. Specifically, the compressed air 15 flows from the high-pressure plenum 66 into the annular section 47 at the rear end of the combustor 17 through an opening defined in the outer sleeve 48. The compressed air 15 travels upstream from the rear end of the combustor 17 to the head end air plenum 122, where it reverses direction and enters the fuel nozzle 40.

[0029] In exemplary embodiments, fuel injection assemblies 80 are provided to deliver a second fuel / air mixture to a secondary combustion zone 74. For example, a second flow of fuel and air can be introduced into the secondary combustion zone 74 by one or more fuel injection assemblies 80. The secondary combustion zone 74 can be defined by a combustion liner 46 and positioned downstream of the primary combustion zone 72. Such a combustion system having axially separated combustion zones is described as an "axial fuel staging" (AFS) system. The fuel injection assemblies 80 may be spaced circumferentially apart from each other on the outer sleeve 48 (e.g., equally spaced in some embodiments). In many embodiments, the combustor 17 may include four fuel injection assemblies 80 spaced apart from each other and configured to inject a second mixture of fuel and air into the secondary combustion zone 74 in order to raise the combustion gas 34 and its temperature. In other embodiments, the combustor 17 may include any number of fuel injection assemblies 80 (e.g., 1, 2, 3, or up to 10).

[0030] As shown in Figure 2, each fuel injection assembly 80 may include a fuel injector 100 and a fuel supply conduit 254 that supplies fuel (e.g., gaseous fuel) to the fuel injector 100. Each fuel injector 100 may extend through an outer sleeve 48, annular section 47, and combustion liner 46 to the secondary combustion zone 74. For example, each fuel injector 100 may extend radially from a high-pressure plenum 66 through an outer sleeve 48, annular section 47, and combustion liner 46 so that the fuel injector 100 can deliver a second flow of fuel and air to the secondary combustion zone 74. The fuel injectors 100 may be coupled to the combustion liner 46 and / or outer sleeve 48 so that each fuel injector 100 introduces a second fuel / air mixture as a jet that enters the crossflow of combustion products generated in the primary combustion zone 72. The second fuel / air mixture is ignited by the combustion products from the primary combustion zone 72 and burns in the secondary combustion zone 74.

[0031] The fuel injector 100 can be coupled to an outer sleeve 48 and can extend through the outer sleeve 48 and the combustion liner 46. In one embodiment, a boss (not shown) supporting the fuel injector 100 serves as a fastener for securing the outer sleeve 48 to the combustion liner 46. In other embodiments, the fuel injector 100 can be coupled to the outer sleeve 48 in any suitable manner, and the outer sleeve 48 can have any suitable number of components coupled between the flange of the forward casing 50 and the turbine nozzle in any suitable manner, enabling the fuel injection assembly 80 to function as described herein. In addition to the fuel injector 100, the fuel injection assembly 80 further includes a shielding assembly 102 and a number of fuel supply conduits 254 corresponding to the number of fuel injectors 100.

[0032] In exemplary embodiments, the fuel supply conduit 254 may be positioned outside the outer sleeve 48. For example, the fuel supply conduit 254 may be positioned at least partially within the high-pressure plenum 66, radially outward from the outer sleeve 48. In many embodiments, as shown in Figure 2, the fuel supply conduit 254 may be radially separated from the outer sleeve 48. In various embodiments, the fuel supply conduit 254 may extend generally axially along the outer sleeve 48 (e.g., generally parallel to the outer sleeve but radially spaced away from it). As shown in Figure 2, the fuel supply conduit 254 may extend between the forward casing 50 and the fuel injector 100. For example, the fuel supply conduit 254 may extend from an inlet 256 positioned outside the high-pressure plenum 66, through the forward casing 50, into the high-pressure plenum 66, to the fuel injector 100. In this way, the fuel injection assembly 80 can receive fuel through the inlet 256 and deliver the fuel to the fuel injector 100 via the fuel supply conduit 254 located outside the combustor 17, which injects the fuel along with air into the secondary combustion zone 74.

[0033] In certain embodiments, the fuel supply conduit may include a front portion 272 and a rear portion 274 (Figure 4). The front portion 272 of the fuel supply conduit 254 may extend along the flow sleeve 110. For example, the front portion 272 of the fuel supply conduit 254 may extend generally axially together with the flow sleeve 110. Similarly, the rear portion 274 of the fuel supply conduit 254 may extend generally along the impingement sleeve 112. For example, the rear portion 274 of the fuel supply conduit 254 may extend generally axially together with the flow sleeve 110.

[0034] The shielding assembly 102 is located radially outside the fuel injector 100 and fuel supply conduit 254, at least partially enclosing them to create a protective environment around the fuel injector 100 and fuel supply conduit 254. The shielding assembly 102 protects the fuel supply conduit 254 from damage or displacement that may occur during handling, installation, or maintenance of the combustor 17. The shielding assembly 102 can be fixed to the outer surface of the outer sleeve 48 by mechanical fasteners or by welding or other joining techniques. Alternatively or additionally, the shielding assembly 102 may be fixed to the fuel injector 100.

[0035] The fuel 37 enters through the inlet 256 of a fuel supply conduit 252, which may extend through and / or be coupled to the forward casing 50 (specifically, the casing flange), or through some other convenient location. The fuel injector 100 mixes the fuel 37 with compressed air 15 and injects the second fuel / air mixture into the combustion chamber 70 of the secondary (downstream) combustion zone 74. The first and second fuel / air mixtures ignite within the combustion chamber 70 and generate a flow of combustion gases 27 that are sent to the turbine section 18.

[0036] In some cases, fuel leaks may occur in various components of the fuel injection assembly 80, particularly in the fuel injector 100, and especially in the fuel supply conduit 254 (particularly one or more welded joints 255). Therefore, the fuel injection assembly 80 and the combustor 17 provide means to prevent the fuel leak from coming into contact with the hot surface of the combustor 17 (without such means, the leaked fuel could automatically ignite outside the combustion chamber 70 and damage the combustor 17).

[0037] Figure 3 shows an enlarged view of the combustor 17 having the fuel injection assembly 80 at its circumferential position, viewed from the radially outside of the outer sleeve 48. Figure 4 shows a cross-sectional view of the combustor 17 of Figure 4 according to an embodiment of the present disclosure. Figure 5 shows an enlarged perspective view of the forward tube shield 268 installed in the combustor 17. Figure 6 shows an enlarged cross-sectional view of the forward tube shield 268 installed in the combustor 17. In addition, Figure 7 shows an exploded view of the shielding assembly 102 and fuel supply conduit 254 separated from the combustor 17 according to an embodiment of the present disclosure.

[0038] In many embodiments, as described above and shown in Figures 3 and 4, the outer sleeve 48 may include a flow sleeve 110 and an impingement sleeve 112 coupled together. The flow sleeve 110 may extend between the front casing 50 and the impingement sleeve 112, and the impingement sleeve 112 may extend between the flow sleeve 110 and the rear frame 118 of the combustor 17. The flow sleeve 110 may be inserted axially into the impingement sleeve 112 (overlapping each other axially). For example, the outer surface of the flow sleeve 110 may form an interference fit (or friction fit) with the inner surface of the impingement sleeve 112.

[0039] As best shown in Figures 3 and 4 (shown by dashed lines in Figure 3), the outer sleeve 48 of the combustor 17 can define at least one fuel sweep opening 260 (or more fuel sweep openings in some embodiments) inside the fuel supply conduit 254. For example, at least one fuel sweep opening 260 can be located radially inward of the fuel supply conduit 254 and aligned circumferentially with the fuel supply conduit 254. For example, the axial centerline of the fuel supply conduit 254 may be aligned with and generally parallel to the axial centerline of the fuel sweep opening 260. In exemplary embodiments, the fuel sweep opening 260 may be defined in the flow sleeve 110 of the outer sleeve 48.

[0040] For example, each fuel sweep opening 260 may be a slot or a geometric stadium-shaped opening (rectangle with circular ends) defined in the flow sleeve 110 located directly radially inward of the fuel supply conduit 254. In exemplary embodiments, the fuel sweep openings 260 may be partially (or fully in some embodiments) housed within the forward tube shield 268 so that the fuel sweep openings 260 are not directly exposed to the high-pressure plenum 66. The fuel sweep openings 260 may have defined major and minor axes that are perpendicular to each other, with the major axis being longer than the minor axis. The major and minor axes may each extend across the fuel sweep opening 260 and through its center point. The longest length of the fuel sweep opening 260 may be defined along the major axis (for example, the major axis may extend from one circular end of the fuel sweep opening to the other circular end). The minor axis of the fuel sweep opening is generally parallel to axial direction A and may also be generally parallel to the axial centerline (not shown) of the fuel supply conduit 254. In this way, the minor axis of each fuel sweep opening 260 is directly positioned radially inward of the fuel supply conduit 254 and may be generally parallel to the axial centerline of the fuel supply conduit 254.

[0041] As shown in Figures 3 and 4, both the flow sleeve 110 and the impingement sleeve 112 can define impingement openings 158, 162 that provide fluid communication between the high-pressure plenum 66 and the annular section 47 of the combustor 17. For example, the impingement sleeve 112 can define multiple impingement openings 158 in an irregularly arranged array (or scattered arrangement) on the impingement sleeve 112, so that compressed air 15 can enter the annular section 47 through each of the impingement openings 158. Although only a portion of the impingement sleeve 112 is shown in Figures 3 and 4, the impingement openings 158 may be defined circumferentially spaced apart around the axial centerline 170 of the combustor (e.g., defined on the impingement sleeve 112 at each circumferential position). In this way, a uniform circumferential flow of compressed air 15 can be supplied to the annular section 47, thereby advantageously increasing the operating efficiency of the combustor 17.

[0042] In various embodiments, the flow sleeve 110 can define multiple rows 160 of impingement openings 162 in the circumferential direction of the combustor 17. As shown in Figure 3, the multiple rows 160 of impingement openings 162 may be spaced apart from each other in the axial direction. In an exemplary embodiment, the multiple rows 160 of impingement openings 162 can fluidly couple the high-pressure plenum 66 to the annular section 47. As shown in Figure 3, each impingement opening 162 in a row 160 may be spaced apart in the circumferential direction and in similar axial positions, so that each impingement opening 162 in a row 160 is positioned on a common circumferential line. The rows 160 of impingement openings 162 defined within the flow sleeve 110 can improve the uniformity of the compressed air flow in the annular section 47 by introducing a uniform circumferential flow of compressed air at various axial positions, thereby improving the efficiency of the combustor 17.

[0043] In exemplary embodiments, the fuel sweep opening 260 may be positioned upstream of the rows 160 of the impingement opening 162 with respect to the flow of combustion gas 34 through the combustor 17. In many embodiments, the fuel sweep opening 260 may be larger than the impingement openings 158 and 162 (for example, it may have a larger area) to guide a strong flow of compressed air 15 through the forward tube shield 268. In many embodiments, the rows 160 of the impingement opening 162 may be spaced axially apart from each other. In addition, the fuel sweep opening 260 may be positioned closer to the end cover 42 than the rows 160 of the impingement opening 162.

[0044] In some embodiments, the flow sleeve 110 can define a plurality of openings 286 upstream of both the plurality of rows 160 of impingement openings 162 and the fuel sweep opening 260 with respect to the flow of combustion gases 34 in the combustor 17. For example, the plurality of openings 286 may be circumferentially spaced apart from each other around the entire flow sleeve 110 (e.g., equally spaced), except for circumferential locations of the fuel injection assembly 80 where no openings 286 are defined. In many embodiments, the plurality of openings 286 may be axially arranged between the forward casing 50 and the fuel sweep opening 260.

[0045] In various embodiments, as shown in Figures 3 to 7, the shielding assembly 102 may further include a forward tube shield 268 and a rear tube shield 270, each enclosing a portion of the fuel supply conduit 254 and defining their respective flow paths 276 and 277. In many embodiments, the forward tube shield 268 may be coupled (e.g., directly coupled) to the flow sleeve 110, and the rear tube shield 270 may be coupled (e.g., directly coupled) to the impingement sleeve 112.

[0046] In many embodiments, the forward tube shield 268 and the flow sleeve 110 can collectively enclose the forward portion 272 of the fuel supply conduit 254. At least one fuel sweep opening 260 may be defined in the flow sleeve 110 and positioned within the forward tube shield 268 such that a first flow path 276 is defined within the forward tube shield 268. The first flow path 276 is in fluid communication with both the at least one fuel sweep opening 260 and the high-pressure plenum 66. For example, the first flow path 276 can receive compressed air 15 from the high-pressure plenum 66 and discharge the compressed air 15 to the annular portion 47 through the fuel sweep opening 260. The forward tube shield 268 can extend axially from the proximal part of the mounting flange 269 to the rear tube shield 270. The mounting flange 269 can connect the fuel injection assembly 80 to the forward casing 50.

[0047] The rear tube shield 270 can enclose the rear portion 274 of the fuel supply conduit 254 such that a second passage 277 is defined within the rear tube shield 270. The second passage 277 is in fluid communication with both the injector 100 and the high-pressure plenum 66. For example, the second passage 277 can receive compressed air 15 from the high-pressure plenum 66 and discharge the compressed air 15 into the combustion chamber 70. The rear tube shield 270 can extend axially between the front tube shield 268 and the inlet flow regulator 288.

[0048] In certain embodiments, the forward tube shield 268 and the flow sleeve 110 may collectively define the boundary of the first flow path 276. For example, the forward tube shield 268 may be coplanar with and in contact with the flow sleeves 110 on both sides of the fuel supply conduit 254 when the forward tube shield 268 extends together with the flow sleeve 110 generally in the axial direction. In this way, the flow sleeve 110 and the forward tube shield 268 can collectively define the first flow path 276. The forward tube shield 268 can define a number of inlets 318, 320, 322 into the first flow path 276, each of which can be in direct fluid communication with the high-pressure plenum 66.

[0049] In particular, the forward tube shield 268 may include a first radial wall 290, a second radial wall 292 spaced apart from the first radial wall and located on the opposite side of the fuel supply conduit 254, and a circumferential wall 294 extending between the first radial wall 290 and the second radial wall 292. The first radial wall 290 may extend generally radially outward from the outer surface of the flow sleeve 110 to the circumferential wall 294. In other words, the first radial wall 290 may be in contact with the outer surface of the flow sleeve 110 in a coplanar manner and located on the first side of the fuel supply conduit 254. The second radial wall 292 may extend generally radially outward from the outer surface of the flow sleeve 110 to the circumferential wall 294. In other words, the second radial wall 292 may be in contact with the outer surface of the flow sleeve 110 in a coplanar manner and located on the second side of the fuel supply conduit 254. The first radial wall 290, the second radial wall 292, the circumferential wall 294, and the flow sleeve 110 may collectively surround the forward portion 272 of the fuel supply conduit 254 so that the first flow path 276 is defined around the forward portion 272 of the fuel supply conduit 254 (for example, they may collectively extend 360 degrees around the fuel supply conduit 254).

[0050] In many embodiments, as shown, both the front tube shield 268 and the rear tube shield can extend axially from their respective front ends 310, 314 to their respective rear ends 312, 316, thereby defining the terminations of the shields 268, 270 in the axial direction A. For example, the front tube shield 268 can extend axially from a front end 310 adjacent to the mounting flange 269 to a rear end 312 positioned in front of the impingement sleeve 112. Similarly, the rear tube shield 270 can extend axially from a front end 314 to a rear end 316. More specifically, as will be described later, the rear tube shield 270 may include roof portions 280 and floor portions 282 that connect to each other and collectively enclose a portion of the fuel supply conduit 254, defining a second flow path 277. In such embodiments, the roof portion 280 may extend from a front end 314 to a rear end 316, and the floor portion 282 may extend separately from a front end 315 to a rear end 317. As shown in Figure 4, the front end 315 of the floor portion 282 is axially offset from the front end 314 of the roof portion 280, defining an inlet 285 to the second flow path 277.

[0051] In various embodiments, as best shown in Figure 4, the front tube shield 268 can be spaced apart from the rear tube shield 270 and can overlap the rear tube shield 270 axially. For example, the front end 314 of the rear tube shield 270 can extend axially into the front tube shield 268 (e.g., without contacting the front tube shield 268 to allow space for compressed air 15 to enter the first flow path 276). In particular, the tube shields 268 and 270 overlap each other axially but do not contact each other. For example, the rear end 312 of the front tube shield 268 may be completely spaced apart from the rear tube shield 270, thereby advantageously allowing compressed air 15 to enter uniformly into the first flow path 276 defined by the front tube shield 268 and the flow sleeve 110 at the rear end 312 of the front tube shield 268.

[0052] In many embodiments, the front tube shield 268 may define a first inlet 318 at the front end 310 of the front tube shield 268, a second inlet 320 at the rear end 312 of the front tube shield 268, and a third inlet 322 between the front end 310 and the rear end 312 of the front tube shield 268. For example, the third inlet 322 may be defined in the first radial wall 290, the second radial wall 292, or the circumferential wall 294 at a location between the front end 310 and the rear end 312 of the front tube shield. In an exemplary embodiment, as shown in Figure 4, the third inlet 322 may be defined in the second radial wall 292 behind the fuel sweep opening 260 such that the compressed air 15 entering the third inlet 322 flows toward the fuel sweep opening 260 in the opposite direction to axial A.

[0053] Each of the inlets 318, 320, and 322 can provide a separate inlet for compressed air 15 from the high-pressure plenum 66 to flow into the first passage 276. In certain embodiments, all of the compressed air 15 in the first passage 276 can flow toward the fuel sweep opening 260. For example, compressed air 15 entering the first inlet 318 can flow axially A toward the fuel sweep opening 260. Conversely, compressed air 15 entering the second inlet 320 or the third inlet 322 can flow toward the fuel sweep opening 260 in the opposite direction to axial A. In this way, the fuel sweep opening 260 can guide airflow in the opposite direction into the forward tube shield 268.

[0054] In exemplary embodiments, the shielding assembly 102 may further include a venturi nozzle 296 having a circumferentially converging portion 297 and a circumferentially expanding portion 298. In particular, the venturi nozzle 296 may be defined by a forward tube shield 268 immediately behind the fuel sweep opening 260. As shown, the circumferentially converging portion 297 may converge circumferentially inward while extending downstream (or axially). In other words, in the circumferentially converging portion 297, the first radial wall 290 and the second radial wall 292 may taper toward each other or converge as they extend axially A. For example, the circumferential distance between walls 290, 292 may decrease axially A in the circumferentially converging portion 297.

[0055] Conversely, the circumferential extension portion 298 may branch outward circumferentially while extending downstream (or axially). In other words, in the circumferential extension portion 298, the first radial wall 290 and the second radial wall 292 may taper toward each other or expand toward each other as they extend axially A. For example, the circumferential distance between walls 290 and 292 may increase axially A in the circumferential extension portion 298. In many embodiments, the circumferential extension portion 298 may extend directly from the circumferential converging portion 297 so that a throat 299 can be defined between the circumferential converging portion 297 and the circumferential extension portion 298. The throat 299 can define the minimum circumferential length (and minimum cross-sectional area) of the forward tube shield 268.

[0056] In this way, the circumferential converging portion 297 and the circumferential expanding portion 298 can collectively define the venturi nozzle 296, which favorably ensures that all of the compressed air 15 in the forward tube shield 268 is directed toward one of the fuel sweep openings 260 by generating a pressure difference within the first flow path 276 (and ensuring that the air does not flow beyond the fuel sweep opening 260).

[0057] During operation, the fuel sweep opening 260 can function to guide the flow of compressed air 15 into the first passage 276, which can favorably sweep and remove any fuel leaks in the fuel supply conduit 254 during the operation of the combustor 17. In certain embodiments, the fuel supply conduit 254 may include a welded joint 255 (for example, if parts of the fuel supply conduit are joined together). The welded joint 255 may be positioned close to the fuel sweep opening 260 so that any fuel leaks from the welded joint 255 can be favorably swept and removed by the compressed air 15. For example, the flow of compressed air 15 in the forward tube shield 268 can carry leaked fuel from the fuel supply conduit 254 (particularly from the forward portion 272 of the fuel supply conduit 254) through the first passage 276, the fuel sweep opening 260, to the annular section 47. In this way, leaked fuel from the forward portion 272 of the fuel supply conduit 254 can be carried away (or swept away) by a first flow of compressed air 300 for use in one or more fuel nozzles 40. For example, leaked fuel from the fuel supply conduit 254 flows into the first passage 276, is swept away by the flow of compressed air 15, and thereby moves to one or more fuel nozzles 40 for use in the primary combustion zone 72. Thus, at least one fuel sweep opening 260 and the forward tube shield 268 ensure that leaked fuel from the forward portion 272 of the fuel supply conduit 254 does not move to the hot components of the combustor 17 (otherwise it could cause automatic ignition of the leaked fuel and damage the combustor 17).

[0058] In certain embodiments, the rear tube shield 270 may include a roof portion 280 and a floor portion 282 that collectively define the boundary of the second flow path 277. Both the roof portion 280 and the floor portion 282 may be radially spaced apart from the impingement sleeve 112. Although the roof portion 280 and the floor portion 282 are shown as two separate components that collectively form the rear tube shield 270, in some embodiments, the rear tube shield 270 may be a single component that surrounds the rear portion 274 of the fuel supply conduit 254.

[0059] In many embodiments, the rear tube shield 270 may be spaced apart from both the flow sleeve 110 and the rear portion 274 of the fuel supply conduit 254 to define a second flow path 277. For example, the rear tube shield 270 can annularly surround the rear portion 274 of the fuel supply conduit 254 and can extend generally axially together with both the impingement sleeve 112 and the rear portion 274 of the fuel supply conduit 254. In various embodiments, the rear tube shield 270 defines an inlet 285 at its front end to a second flow path 277 between the roof portion 280 and the floor portion 282, thereby enabling direct fluid communication with the high-pressure plenum 66. Compressed air 15 in the second flow path 277 can flow from the inlet 285 toward the fuel injector 100.

[0060] In various embodiments, the fuel injection assembly 80 may further include an inlet flow regulator 288 that generally surrounds the fuel injector 100. The inlet flow regulator 288 may define a number of holes 289 that regulate the compressed air 15 before it enters the fuel injector 100, which favorably increases the mixture of air and fuel in the fuel injector 100. As shown in Figure 4, the front end of the inlet flow regulator 288 may axially overlap and contact the roof portion 280 of the rear tube shield 270 to ensure that any fuel leaks in the rear portion 274 of the fuel supply conduit 254 pass safely into the fuel injector 100.

[0061] In an exemplary embodiment, compressed air 15 from the high-pressure plenum 66 can enter a second passage 277 at the inlet 285 and exit the second passage 277 at the fuel injector 100. For example, the compressed air 15 in the second passage 277 can flow axially A toward the fuel injector 100. In this way, leaked fuel in the rear portion 274 of the fuel supply conduit 254 can be swept away and removed by the compressed air 15 in the second passage 277 for final use in the fuel injector 100.

[0062] During operation, the fuel injector 100 can partially function to guide the flow of compressed air 15 into the second passage 277, which can favorably sweep and remove any fuel leaks in the fuel supply conduit 254 during the operation of the combustor 17. For example, the compressed air 15 in the second passage 277 can carry leaked fuel from the fuel supply conduit 254 (particularly from the rear portion 274 of the fuel supply conduit 254) to the fuel injector 100 for injection into the secondary combustion zone 74. Thus, the rear tube shield 270 ensures that leaked fuel from the rear portion 274 of the fuel supply conduit 254 does not move to the hot components of the combustor 17 (otherwise it could cause the leaked fuel to automatically ignite and damage the combustor 17).

[0063] In various embodiments, the front tube shield 268 may include one or more flanges 273 that connect directly to the flow sleeve 210. For example, in some embodiments, the flanges 273 may define slots through which one or more bolts 275 can extend, allowing the flanges 273 to be connected to the flow sleeve 210 with threaded fasteners. In other embodiments, the flanges 273 may be welded or fixed to the flow sleeve 210. In exemplary embodiments, the flanges 273 may be formed integrally with the front tube shield 268 so that the front tube shield 268 and the flanges 273 constitute a single component.

[0064] Similarly, the rear tube shield 270 may include one or more mounting flanges 278 that can connect the rear tube shield 270 to the impingement sleeve 112. As shown in Figures 3 and 4, the mounting flanges 278 may be formed integrally with the rear tube shield 270 as a single component. The mounting flanges 278 can support the rear tube shield 270 and be connected to the impingement sleeve 112 (e.g., via bolts and screws, welding, or other suitable coupling means).

[0065] This specification discloses the present invention, including its best mode, and uses examples to enable any person skilled in the art to practice the invention, including the fabrication and use of any device or system and the implementation of any incorporated method. The patentable scope of the present invention is defined by the claims and may include other embodiments that a person skilled in the art may conceive. Such other embodiments are intended to be within the claims if they include structural elements that are not different from the language of the claims, or equivalent structural elements that do not substantially differ from the language of the claims.

[0066] Further aspects of the present invention are provided by the subject matter of the following clauses.

[0067] A combustor comprising an end cover, and at least one fuel nozzle extending from the end cover and at least partially enclosed by a combustion liner, wherein the combustion liner extends from the at least one fuel nozzle toward a rear frame, and the combustion liner defines a combustion chamber having a primary combustion zone downstream of the at least one fuel nozzle and a secondary combustion zone downstream of the primary combustion zone, and an outer sleeve spaced apart from the combustion liner and surrounding the combustion liner such that an annular portion is defined between them, and a fuel injection assembly, wherein the fuel injection assembly comprises the outer sleeve, the annular portion, and the combustion liner A combustor comprising a fuel injector extending through a na to the secondary combustion zone, a fuel supply conduit positioned outside the outer sleeve, the fuel supply conduit extending to the fuel injector, and a shielding assembly coupled to the outer sleeve and at least partially enclosing the fuel supply conduit, the shielding assembly including a venturi nozzle having a circumferentially converging portion and a circumferentially expanding portion, at least one fuel sweep opening defined in the outer sleeve immediately ahead of the venturi nozzle, the at least one fuel sweep opening, and a fuel injection assembly comprising a shielding assembly positioned within the shielding assembly.

[0068] The combustor according to one or more of these clauses, wherein the shielding assembly comprises a front tube shield and a rear tube shield, and the venturi nozzle is defined by the front tube shield.

[0069] The combustor according to one or more of these provisions, wherein the front tube shield is spaced apart from the rear tube shield and overlaps the rear tube shield in the axial direction.

[0070] The combustor according to one or more of these provisions, wherein the forward tube shield is coupled to the flow sleeve of the outer sleeve, and the forward tube shield and the flow sleeve collectively define a first flow path that communicates with the fuel sweep opening.

[0071] A combustor according to one or more of these provisions, wherein the front tube shield defines a first inlet at the front end of the front tube shield, a second inlet at the rear end of the front tube shield, and a third inlet between the front end and the rear end of the front tube shield.

[0072] The combustor according to one or more of these provisions, wherein the outer sleeve comprises a flow sleeve and an impingement sleeve coupled to each other, the flow sleeve extending between the front casing and the impingement sleeve, and the impingement sleeve extending between the flow sleeve and the rear frame of the combustor.

[0073] The combustor according to one or more of these clauses, wherein the shielding assembly further comprises a forward tube shield coupled to the flow sleeve, the forward tube shield and the flow sleeve collectively enclose the forward portion of the fuel supply conduit such that a first flow path is defined by the forward tube shield, and the fuel sweep opening is located within the forward tube shield.

[0074] The combustor according to one or more of these clauses, further comprising a rear tube shield that annularly surrounds the rear portion of the fuel supply conduit such that a second flow path is defined by the rear tube shield.

[0075] A combustor according to one or more of these clauses, wherein the compressed air in the first passage moves toward the at least one fuel sweep opening, and the compressed air in the second passage moves toward the fuel injector.

[0076] The combustor according to one or more of these clauses, wherein the shielding assembly further comprises a floor portion and a roof portion that are coupled to each other and collectively define the second flow path.

[0077] A turbomachinery comprising a compressor section, a turbine section, and a combustor located downstream of the compressor section and upstream of the turbine section, wherein the combustor comprises an end cover and at least one fuel nozzle extending from the end cover and at least partially enclosed by a combustion liner, the combustion liner extending from the at least one fuel nozzle toward a rear frame, the combustion liner defining a combustion chamber having a primary combustion zone downstream of the at least one fuel nozzle and a secondary combustion zone downstream of the primary combustion zone, an outer sleeve spaced apart from the combustion liner and surrounding the combustion liner such that an annular portion is defined between them, and a fuel injection assembly, the fuel injection A turbomachinery comprising a combustor comprising an assembly comprising an outer sleeve, an annular portion, and a fuel injector extending through a combustion liner to the secondary combustion zone, a fuel supply conduit positioned outside the outer sleeve, the fuel supply conduit extending to the fuel injector, and a shielding assembly coupled to the outer sleeve and at least partially enclosing the fuel supply conduit, the shielding assembly comprising a venturi nozzle having a circumferentially converging portion and a circumferentially expanding portion, at least one fuel sweep opening defined in the outer sleeve immediately ahead of the venturi nozzle, the at least one fuel sweep opening, and a fuel injection assembly comprising a shielding assembly disposed within the shielding assembly.

[0078] The turbomachinery according to one or more of these clauses, wherein the shielding assembly comprises a forward tube shield and a rear tube shield, and the venturi nozzle is defined by the forward tube shield.

[0079] The turbomachinery according to one or more of these clauses, wherein the forward tube shield is spaced apart from the rear tube shield and overlaps the rear tube shield in the axial direction.

[0080] The turbomachinery according to one or more of these provisions, wherein the forward tube shield is coupled to the flow sleeve of the outer sleeve, and the forward tube shield and the flow sleeve collectively define a first flow path that communicates fluid with the fuel sweep opening.

[0081] A turbomachinery according to one or more of these provisions, wherein the forward tube shield defines a first inlet at the forward end of the forward tube shield, a second inlet at the rear end of the forward tube shield, and a third inlet between the forward end and the rear end of the forward tube shield.

[0082] The turbomachinery according to one or more of these provisions, wherein the outer sleeve comprises a flow sleeve and an impingement sleeve coupled to each other, the flow sleeve extending between the forward casing and the impingement sleeve, and the impingement sleeve extending between the flow sleeve and the rear frame of the combustor.

[0083] The turbomachinery according to one or more of these clauses, wherein the shielding assembly further comprises a forward tube shield coupled to the flow sleeve, the forward tube shield and the flow sleeve collectively enclose the forward portion of the fuel supply conduit such that a first flow path is defined by the forward tube shield, and the fuel sweep opening is located within the forward tube shield.

[0084] The turbomachinery according to one or more of these provisions, wherein the shielding assembly further comprises a rear tube shield that annularly surrounds the rear portion of the fuel supply conduit such that a second flow path is defined by the rear tube shield.

[0085] A turbomachinery according to one or more of these clauses, wherein the compressed air in the first passage moves toward the at least one fuel sweep opening, and the compressed air in the second passage moves toward the fuel injector.

[0086] The turbomachinery according to one or more of these provisions, wherein the shielding assembly further comprises a floor portion and a roof portion that are coupled to each other and collectively define the second flow path. [Explanation of symbols]

[0087] 10 Heavy Duty Gas Turbines 12 Entrance Section 14 Compressor Section 15 Compressed air 16. Combustor Section 17 Combustor 18 Turbine Section 20 Exhaust Section 22 shafts 24 Rotor Discs 26 rotor blades 27 Combustion gases 28 Rotor Discs 30 rotor blades 31 Outer casing 32 High-temperature gas pathway 34 Combustion gases 37 Fuel 38 Fuel supply line 40 Fuel Nozzles 42 End cover 44 caps 46 Combustion Liner 47 Ring section 48 Outer sleeve 50 Front casing 60 Compressor discharge casing 66 High-pressure plenum 70 Combustion chamber 72 Primary Combustion Zone 74 Secondary combustion zone 80 Fuel injection assembly 100 fuel injector 102 Shielding Assembly 110 Flow Sleeve 112 Impingement Sleeve 118 Rear frame 122 Head-end air plenum 158 Impingement opening 160 columns 162 Impingement opening 170 Axial centerline 254 Fuel supply conduit 255 Welded joints 256 Entrance 260 Fuel sweep opening 268 Front tube shield 269 ​​Mounting flange 270 Rear Tube Shield 272 Front part 273 Flange 274 Rear part 275 volts 276 First channel 277 Second channel 278 Mounting flange 280 Roof section 282 Floor part 285 Entrance 286 Opening 288 Inlet flow regulator 289 holes 290 First radial wall 292 Second radial wall 294 Circumferential wall 296 Venturi Nozzle 297 Circumferential convergence section 298 Circumferential extension portion 299 Throat 300 compressed air 310 Front end 312 Rear end 314 Front end 315 Front end 316 Rear end 317 Rear end 318 First Entrance 320 Second entrance 322 The third entrance A-axis C Circumferential direction R Radial direction

Claims

1. A combustor (17), wherein the combustor (17) is End cover (42) and At least one fuel nozzle (40) extending from the end cover (42) and at least partially enclosed by a combustion liner (46), wherein the combustion liner (46) extends from the at least one fuel nozzle (40) toward the rear frame (118), and the combustion liner (46) defines a combustion chamber (70) having a primary combustion zone (72) downstream of the at least one fuel nozzle (40) and a secondary combustion zone (74) downstream of the primary combustion zone (72), An outer sleeve (48) that is spaced apart from the combustion liner (46) and surrounds the combustion liner (46), and an annular portion (47) is defined between the outer sleeve (48) and the combustion liner (46), Fuel injection assembly (80) and The fuel injection assembly (80) is equipped with A fuel injector (100) extends through the outer sleeve (48), the annular portion (47), and the combustion liner (46) to the secondary combustion zone (74), A fuel supply conduit (254) positioned outside the outer sleeve (48), wherein the fuel supply conduit (254) extends to the fuel injector (100), A shielding assembly (102) coupled to the outer sleeve (48) and at least partially enclosing the fuel supply conduit (254), wherein the shielding assembly (102) includes a venturi nozzle (296) having a circumferential converging portion (297) and a circumferential expanding portion (298), and at least one fuel sweep opening (260) is defined in the outer sleeve (48) immediately in front of the venturi nozzle (296), and the at least one fuel sweep opening (260) is located within the shielding assembly (102), and A combustion device (17) is provided with this.

2. The combustor (17) according to claim 1, wherein the shielding assembly (102) comprises a front tube shield (268) and a rear tube shield (270), and the venturi nozzle (296) is defined by the front tube shield (268).

3. The combustor (17) according to claim 2, wherein the front tube shield (268) is spaced apart from the rear tube shield (270) and overlaps with the rear tube shield (270) in the axial direction.

4. The combustor (17) according to claim 2, wherein the forward tube shield (268) is coupled to the flow sleeve (110) of the outer sleeve (48), and the forward tube shield (268) and the flow sleeve (110) collectively define a first flow path (276) that is in fluid communication with the fuel sweep opening (260).

5. The combustor (17) according to claim 4, wherein the front tube shield (268) defines a first inlet (318) at the front end (310) of the front tube shield (268), defines a second inlet (320) at the rear end (312) of the front tube shield (268), and defines a third inlet (322) between the front end (310) and the rear end (312) of the front tube shield (268).

6. The combustor (17) according to claim 1, wherein the outer sleeve (48) comprises a flow sleeve (110) and an impingement sleeve (112) coupled to each other, the flow sleeve (110) extending between the front casing (50) and the impingement sleeve (112), and the impingement sleeve (112) extending between the flow sleeve (110) and the rear frame (118) of the combustor (17).

7. The combustor (17) according to claim 6, wherein the shielding assembly (102) comprises a forward tube shield (268) coupled to the flow sleeve (110), the forward tube shield (268) and the flow sleeve (110) collectively surround the forward portion (272) of the fuel supply conduit (254) such that a first flow path (276) is defined by the forward tube shield (268), and the at least one fuel sweep opening (260) is located within the forward tube shield (268).

8. The combustor (17) according to claim 7, wherein the shielding assembly (102) comprises a rear tube shield (270) that annularly surrounds the rear portion (274) of the fuel supply conduit (254), and the rear tube shield (270) defines a second flow path (277).

9. The combustor (17) according to claim 8, wherein the compressed air (15) in the first passage (276) moves toward the at least one fuel sweep opening (260), and the compressed air (15) in the second passage (277) moves toward the fuel injector (100).

10. The combustor (17) according to claim 8, wherein the shielding assembly (102) further comprises a floor portion (282) and a roof portion (280) that are connected to each other to collectively define the second flow path (277).

11. Compressor section (14) and Turbine section (18) and A combustor section (16) located downstream of the compressor section (14) and upstream of the turbine section (18), wherein the combustor section (16) comprises a combustor (17) according to any one of claims 1 to 10. A turbomachinery (10) equipped with the above.

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