Integrated fuel nozzle connector

Abstract

A gas turbine includes a compressor, a turbine, and a combustor disposed downstream of the compressor and upstream of the turbine. The combustor includes an end cap. The combustor also includes a flange. The flange includes an internal fluid passage defined within the flange, and the flange is connected to an internal face of the end cap. A fuel port is integrally joined with the flange. The fuel port extends through the end cap between the flange and an inlet positioned outside of the end cap. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.

Description

Technical Field

[0001] The present disclosure generally relates to an integrated fuel coupling for supplying fuel to a fuel nozzle assembly of a turbomachine. Background Art

[0002] Gas turbines generally operate by burning a fuel and air mixture in one or more combustors to form high-energy combustion gases that pass through the turbine, thereby rotating the turbine's rotor shaft. The rotational energy of the rotor shaft can be converted into electrical energy via a generator connected to the rotor shaft. Each combustor typically includes a fuel nozzle that provides premixing of fuel and air upstream of the combustion zone as a means of keeping nitrogen oxide (NOx) emissions low.

[0003] Gaseous fuels, such as natural gas, are commonly used as the combustible fluid in gas turbine engines used to generate electricity. A typical fuel supply system for providing gaseous fuel to the fuel nozzles of a combustor includes a sealed coupling positioned within the head end of the combustor so that if the seal fails or otherwise permits fuel to escape from the coupling within the head end, a flame can be maintained within the head end of the combustor. Summary of the Invention

[0004] Various aspects and advantages are set forth in the following description, or may be obvious from the description, or may be learned through practice.

[0005] According to one embodiment, a gas turbine is provided. The gas turbine includes a compressor, a turbine, and a combustor positioned downstream of the compressor and upstream of the turbine. The combustor includes an end cover. The combustor also includes a flange. The flange includes an internal fluid passage defined therein and is connected to an inner surface of the end cover. A fuel port is integrally engaged with the flange. The fuel port extends through the end cover between the flange and an inlet positioned outside the end cover. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.

[0006] According to another embodiment, a combustor for a turbine is provided. The combustor includes an end cover. The combustor also includes a flange. The flange includes an internal fluid passage defined therein and is connected to an interior surface of the end cover. A fuel port is integrally engaged with the flange. The fuel port extends through the end cover between the flange and an inlet positioned outside the end cover. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.

[0007] In addition to the above embodiments, the present disclosure also provides the following technical solutions:

[0008] Technical Solution 1. A gas turbine comprising:

[0009] compressor;

[0010] turbine;

[0011] a combustor disposed downstream of the compressor and upstream of the turbine, the combustor comprising:

[0012] end caps;

[0013] a flange including an internal fluid passage defined therein, the flange being connected to an interior face of the end cap; and

[0014] A fuel port is integrally engaged with the flange, the fuel port extending through the end cover between the flange and an inlet positioned externally of the end cover, the inlet of the fuel port being in fluid communication with the internal fluid passage of the flange.

[0015] Technical Solution 2. According to the gas turbine described in Technical Solution 1, the flange extends between a first side and a second side relative to the first side, the first side of the flange is adjacent to the inner surface of the end cover, and further includes a fluid conduit extending between the second side of the flange and the fuel nozzle.

[0016] Technical Solution 3. In the gas turbine according to Technical Solution 2, the fuel port extends between the inlet and the first side of the flange.

[0017] Technical Solution 4. The gas turbine according to Technical Solution 1 further includes a filter positioned within the fuel port, so that the inlet of the fuel port is fluidically connected to the internal fluid channel of the flange through the filter.

[0018] Technical Solution 5. The gas turbine according to Technical Solution 1 further includes an orifice fitting connected to the inlet of the internal fluid channel of the flange, so that the inlet of the fuel port is fluidically connected to the internal fluid channel of the flange through the orifice fitting.

[0019] Technical Solution 6. The gas turbine according to Technical Solution 5 further includes a filter upstream of the orifice fitting, so that the inlet of the fuel port is fluidically connected to the internal fluid channel of the flange through the filter and the orifice fitting.

[0020] Technical Solution 7. The gas turbine according to Technical Solution 5 further includes a filter integrally coupled to the orifice fitting, the filter being positioned within the fuel port upstream of the orifice fitting so that the inlet of the fuel port is fluidically connected to the internal fluid channel of the flange through the filter and the orifice fitting.

[0021] Technical Solution 8. According to the gas turbine of Technical Solution 1, the fuel port passes through the hole of the end cover, and further includes a sealing groove surrounding the hole of the end cover.

[0022] Technical Solution 9. In the gas turbine according to Technical Solution 1, the fuel port is offset from the hole of the end cover so that an annular channel is defined between the fuel port and the hole of the end cover.

[0023] Technical Solution 10. In the gas turbine according to Technical Solution 1, the flange comprises a heat shield, and the internal fluid passage of the flange is at least partially defined in the heat shield.

[0024] Technical Solution 11. A combustor for a turbine, comprising:

[0025] end caps;

[0026] a flange including an internal fluid passage defined therein, the flange being connected to an inner side of the end cap; and

[0027] A fuel port is integrally engaged with the flange, the fuel port extending through the end cover between the flange and an inlet positioned externally of the end cover, the inlet of the fuel port being in fluid communication with the internal fluid passage of the flange.

[0028] Technical Solution 12. According to the combustor of Technical Solution 11, the flange extends between a first side and a second side relative to the first side, the first side of the flange is adjacent to the end cover, and further includes a fluid conduit extending between the second side of the flange and the fuel nozzle.

[0029] Technical Solution 13. In the burner according to Technical Solution 12, the fuel port extends between the inlet and the first side of the flange.

[0030] Technical Solution 14. The burner according to Technical Solution 11 further includes a filter positioned within the fuel port, so that the inlet of the fuel port is fluidically connected to the internal fluid channel of the flange through the filter.

[0031] Technical Solution 15. The burner according to Technical Solution 11 further includes an orifice fitting connected to the inlet of the internal fluid channel of the flange, so that the inlet of the fuel port is fluidically connected to the internal fluid channel of the flange through the orifice fitting.

[0032] Technical Solution 16. The burner according to Technical Solution 15 further includes a filter upstream of the orifice fitting, so that the inlet of the fuel port is fluidically connected to the internal fluid channel of the flange through the filter and the orifice fitting.

[0033] Technical Solution 17. The burner according to Technical Solution 15 further includes a filter integrally engaged with the orifice fitting, and the filter is positioned in the fuel port upstream of the orifice fitting, so that the inlet of the fuel port is fluidically connected to the internal fluid channel of the flange through the filter and the orifice fitting.

[0034] Technical Solution 18. According to the burner of Technical Solution 11, the fuel port passes through the hole of the end cover, and further includes a sealing groove surrounding the hole of the end cover.

[0035] Technical Solution 19. In the burner according to Technical Solution 11, the fuel port is offset from the hole of the end cover so that an annular channel is defined between the fuel port and the hole of the end cover.

[0036] Technical Solution 20. In the burner according to Technical Solution 11, the flange includes a heat shield, and the internal fluid channel of the flange is at least partially defined in the heat shield.

[0037] Those skilled in the art will better understand the features and aspects of these and other embodiments from a reading of this specification. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] A full and enabling disclosure of various embodiments, including the best mode known to those skilled in the art, is more particularly set forth in the remainder of the specification and with reference to the accompanying drawings, in which:

[0039] Figure 1 is a functional block diagram of an exemplary gas turbine that may incorporate various embodiments of the present disclosure;

[0040] Figure 2 is a simplified cross-sectional side view of an exemplary combustor as may be incorporated into various embodiments of the present disclosure;

[0041] Figure 3 yes Figure 2 a cross-sectional side view of a portion of a burner;

[0042] Figure 4 yes Figure 3 an enlarged view of a portion of;

[0043] Figure 5 yes Figure 4an enlarged view of a portion of;

[0044] Figure 6 yes Figure 4 A magnified view of a portion of the . DETAILED DESCRIPTION

[0045] Reference will now be made in detail to the present embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. Numerals and letter designations are used in the detailed description to refer to features in the drawings. The same or similar reference numerals are used in the drawings and the description to refer to the same or similar parts of the present disclosure.

[0046] As used herein, the terms "first," "second," and "third" are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the respective components. The terms "upstream" and "downstream" refer to relative directions relative to the flow of a fluid in a fluid path. For example, "upstream" refers to the direction from which the fluid is flowing, while "downstream" refers to the direction to which the fluid is flowing. The term "radially" refers to a relative direction that is substantially perpendicular to the axial centerline of a particular component, the term "axially" refers to a relative direction that is substantially parallel to and / or coaxially aligned with the axial centerline of a particular component, and the term "circumferentially" refers to a relative direction that extends around the axial centerline of a particular component.

[0047] The technical terms used herein are used only to describe specific embodiments and are not intended to be limiting. As used herein, the singular forms "a / an" and "the" are also intended to include the plural forms, unless the context clearly indicates otherwise. It should be further understood that when used in this specification, the terms "comprises and / or comprising" specify the presence of the features, integers, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or groups thereof.

[0048] Each example is provided by way of explanation and not limitation. Indeed, modifications and variations can be made to the present invention without departing from the scope or spirit of the invention, as will be apparent to those skilled in the art. For example, features illustrated or described as part of one embodiment may be used on another embodiment to produce yet another embodiment. Therefore, it is intended that this disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents.

[0049] Although exemplary embodiments of the present disclosure will generally be described in the context of land-based power generation gas turbine combustors for illustrative purposes, those skilled in the art will readily appreciate that embodiments of the present disclosure may be applied to any style or type of turbine combustor and are not limited to combustors or combustion systems for land-based power generation gas turbines unless specifically recited in the claims.

[0050] Referring now to the accompanying drawings, Figure 1 A schematic diagram illustrates an exemplary gas turbine 10. The gas turbine 10 generally includes an inlet section 12, a compressor 14 positioned downstream of the inlet section 12, at least one combustor 16 positioned downstream of the compressor 14, a turbine 18 positioned downstream of the combustor 16, and an exhaust section 20 positioned downstream of the turbine 18. Additionally, the gas turbine 10 may include one or more shafts 22 connecting the compressor 14 to the turbine 18.

[0051] During operation, air 24 flows through the inlet section 12 and into the compressor 14, where it is gradually compressed, thereby providing compressed air 26 to the combustor 16. At least a portion of the compressed air 26 is mixed with fuel 28 within the combustor 16 and combusted to produce combustion gases 30. From the combustor 16, the combustion gases 30 flow into the turbine 18, where energy (kinetic and / or thermal energy) is transferred from the combustion gases 30 to rotor blades (not shown), thereby causing the shaft 22 to rotate. The mechanical rotational energy can then be used for various purposes, such as to power the compressor 14 and / or generate electricity. The combustion gases 30 that exit the turbine 18 can then be discharged from the gas turbine 10 via the exhaust section 20.

[0052] like Figure 2 As shown in FIG, the combustor 16 may be at least partially surrounded by a housing 32, such as a compressor discharge casing. The housing 32 may at least partially define a high pressure plenum 34 that at least partially surrounds the various components of the combustor 16. The high pressure plenum 34 may be coupled to the compressor 14 ( Figure 1 ) to receive compressed air 26 from the compressor. An end cover 36 may be connected to the outer casing 32. In some embodiments, the end cover 36 may be a separate component that is connected, e.g., fastened, to the outer casing 32. In other embodiments, the end cover 36 may be adjacent to the outer casing 32, e.g., the combustor 16 may be completely enclosed within the outer casing 32 and the end cover 36 may be a portion of the outer casing 32. In some embodiments, the outer casing 32 and the end cover 36 may at least partially define a head end volume or portion 38 of the combustor 16.

[0053] In some embodiments, the head end portion 38 is in fluid communication with the high pressure plenum 34 and / or the compressor 14. One or more bushings or conduits 40 can at least partially define a combustion chamber or zone 42 for combusting a fuel-air mixture, and / or can at least partially define a hot gas path 44 through the combustor 16 for directing the combustion gases 30 toward the inlet to the turbine 18.

[0054] In various embodiments, the combustor 16 includes at least one fuel nozzle assembly 50. As shown in Figure 2 , the fuel nozzle assembly 50 is disposed within the outer casing 32, downstream of the end cover 36 and / or axially spaced from the end cover 36 relative to an axial centerline 46 of the combustor 16, and upstream of the combustion chamber 42. In particular embodiments, the fuel nozzle assembly 50 can be in fluid communication with the gaseous fuel supply 48 via one or more fluid conduits 52. In some embodiments, the fluid conduit 52 can be fluidly connected and / or coupled to the end cover 36 at one end.

[0055] Example embodiments of couplings for the fluid conduit 52 are described in Figure 3 . As shown in Figure 3 , in some example embodiments, the fluid conduit 52 can be part of a dual fuel system, such as can provide both a fuel port 60 for gaseous fuel and a liquid fuel conduit 61. However, in alternative embodiments, the fuel port 60 can be the only fuel coupling. Additionally, it should be appreciated that the fuel port 60 can be used to supply any suitable fuel and need not be limited to gaseous fuel.

[0056] As described in Figure 3 and 4 , embodiments can include a flange 54 that is connected to the interior face 37 of the end cover 36. As mentioned above, the head end portion 38, which is partially bounded by the end cover 36, can be in fluid communication with the compressor 14. In such embodiments, the pressure within the head end 38 can be significantly higher than the ambient pressure surrounding the gas turbine 10 Figure 1 . Thus, the interior face 37 of the end cover 36 is the surface of the end cover 36 that faces the head end 38 and is exposed to the compressed air 26. The flange 54 can be connected to the interior face 37 using bolts or other fasteners (not shown), as is understood in the art. The flange 54 can include a plurality of holes 82 for receiving the fasteners. The structure and intended function of such fasteners are generally understood by those skilled in the art and are not described in greater detail herein.

[0057] In certain embodiments, the flange 54 may extend between a first side 56 and a second side 58 opposite the first side 56. The first side 56 of the flange 54 may be positioned adjacent to the interior face 37 of the end cap 36, for example, when the flange 54 is connected to the end cap 37. In such embodiments, the adjacent surfaces, such as the first side 56 of the flange 54 and the interior face 37 of the end cap 36, may form a potential leakage path for the compressed air 26 to escape from the head end 38 into the surrounding environment. To prevent or minimize leakage of the compressed air 26 from the head end 38, a sealing member (not shown) may be provided within the sealing groove 76. As best shown in FIG. Figure 4 and 6 As seen in FIG. 1 , in the illustrated example embodiment, the sealing groove 76 is formed in the interior face 37 of the end cap 36, however, in alternative embodiments, the sealing groove 76 may be formed in the first side 56 of the flange 54. In some embodiments, for example, Figure 6 As illustrated in FIG, the first side 56 of the flange 54 may include a protruding sealing surface 57. The protruding sealing surface 57 may advantageously provide a more focused load transfer of the tightening load to the sealing member.

[0058] Still refer to Figure 3 and 4 , the flange 54 may include an internal fluid passage 64 defined within the flange 54. The internal fluid passage 64 may be connected to an inlet 63 ( Figure 6 ). The fluid conduit 52 may be in fluid communication with a corresponding one of the fuel nozzles 50. The internal fluid passage 64 may be in fluid communication with the fuel port 60.

[0059] Embodiments of the fuel nozzle coupling may be integrated in that the fuel port 60 may be integrally joined to the flange 54 such that the fuel port 60 and the flange 54 form a single, unitary piece. Figure 3 and 4As explained above, the fuel port 60 can be integrally joined with the flange 54, for example, by integrally joining the fuel port 60 with the flange 54. Integrating the fuel nozzle coupling can advantageously prevent or reduce leakage of the fuel 28 into the head end 38. The head end 38 can experience high temperatures such that if the fuel 28 escapes into the head end 38, it can cause flame holding. Thus, integrally joining the fuel port 60 with the flange 54 can advantageously prevent or reduce flame holding in the head end 38.

[0060] As best seen in Figure 4 and 5 The fuel port 60 can include an inlet 62 configured for coupling to a fuel supply, for example, the fuel supply 48 Figure 2 ) and providing fluid flow communication with an internal fluid passage 64 of the flange 54. With the inlet 62 positioned outside of the end cap 36, the fuel port 60 can extend through the end cap 36 between the flange 54 and the inlet 62. As shown above, the interior face 37 of the end cap 36 faces the head end 38, similarly, the inlet 62 can be positioned outside of the end cap 36 due to the inlet 62 being on an opposite side of the end cap 36 from the head end 38. Thus, it should be appreciated that as used herein with respect to the end cap 36, the term, for example, "interior" refers to a side of the end cap 36 adjacent to the head end 38, while the term, for example, "exterior" or "outside" refers to an opposite side of the end cap 36 distal from the head end 38.

[0061] In some embodiments, the fuel port 60 can extend through a hole 39 defined in the end cap 36. In such embodiments, the seal groove 76 can surround the hole 39 of the end cap 36. As shown above, the seal groove 76 need not be formed in the interior face 37 of the end cap 36, the seal groove 76 can be provided, for example, in the first side 56 of the flange 54. In some embodiments, the fuel port 60 can be offset from the hole 39 of the end cap 36 such that an annular channel 78 is defined between the fuel port 60 and the hole 39 of the end cap 36. For example, an outer dimension of the fuel port 60, for example, a diameter of the fuel port 60 in embodiments where the fuel port 60 is cylindrical, can be less than a corresponding dimension of the hole 39 of the end cap 36.

[0062] As Figure 3 and 4As shown in FIG, the fuel port 60 may extend between the inlet 62 and the first side 56 of the flange 54. The fluid conduit 52 may extend between the second side 58 of the flange 54 and the fuel nozzle 50 ( Figure 2 ) extends between.

[0063] like Figure 4 , in some embodiments, the flange 54 can include a heat shield 66. In such embodiments, the internal fluid passage 64 of the flange 54 can be at least partially defined within the heat shield 66. The heat shield 66 acts as a thermal insulator between the elevated temperature of the compressed air 26 within the head end 38 and the relatively low temperature of the fuel 28 within the fuel ports 60 and the internal fluid passage 64 of the flange 54 (in this context, "relatively low temperature" means lower than the temperature of the compressed air 26). The heat shield 66 can advantageously prevent or minimize differential thermal expansion between, for example, the flange 54 and the end cover 36.

[0064] Still refer to Figure 4 , the filter 67 can be positioned within the fuel port 60 such that the inlet 62 of the fuel port 60 is in fluid communication with the internal fluid passage 64 of the flange 54 through the filter 67. For example, the filter 67 can be positioned and configured such that the fuel 28 flowing through the fuel port 60 must pass through the filter 67 before reaching the internal fluid passage 64. Figure 5 As illustrated in FIG, filter 67 may include one or more filter media 80. For example, filter media 80 may be a fine mesh, a membrane, or any other suitable filter media. The structure and intended function of such filter media are generally understood by those skilled in the art and are not described in further detail herein.

[0065] Still refer to Figure 4 , the orifice fitting 68 can be connected to the inlet 63 of the internal fluid passage 64 of the flange 54 so that the inlet 62 of the fuel port 60 is in fluid communication with the internal fluid passage 64 of the flange 54 through the orifice fitting 68. In some example embodiments, the orifice fitting 68 can include external threads and the inlet 63 of the internal fluid passage 64 in the flange 54 can include mating internal threads so that the orifice fitting 68 can be screwed into the inlet 63 of the internal fluid passage 64 in the flange 54. In some example embodiments, the orifice fitting 68 can include one or more orifices 70 defined therein. Figure 4 As illustrated in FIG, fuel 28 may flow into fuel port 60 at inlet 62. Filter 67 may be positioned upstream of orifice fitting 68. For example, filter 67 may divide the interior cavity 82 of fuel port 60 into a filtered portion 86 downstream of filter 67 and an unfiltered portion 84 upstream of filter 67. In some example embodiments, such as Figure 4As described in FIG. , the filter 67 may have a tapering shape, such as a conical shape. The one or more orifices 70 of the orifice fitting 68 may be in direct fluid communication with the filtered portion 86, such that the fuel 28 must pass through the filter 67 before reaching the orifice fitting 68 and passing through the one or more orifices 70 of the orifice fitting 68 into the internal fluid passage 64 of the flange 54. For example, Figure 4 , the filter 67 may define a tapered shape, and the orifice fitting 68 may include a plurality of orifices 70 arranged about the narrow end of the filter 67. In some example embodiments, the filter 67 may be a conical filter terminating at a point, and the orifice fitting may include a plurality of orifices 70 annularly arranged about the point of the conical filter.

[0066] In some example embodiments, the filter 67 may be integrally joined with the orifice fitting 68. For example, the filter 67 and orifice fitting 68 may be formed as a single piece as described above with respect to the fuel port 60 and flange 54, such as by casting or additive manufacturing.

[0067] The filter 67 can include a rim 81 extending around the upstream end of the filter 67. With the lip 74 defining an inner diameter that is smaller than the outer diameter of the rim 81 of the filter 67, the position of the filter 67 within the fuel port 60 can be limited by the inwardly protruding lip 74 formed within the fuel port 60. In some embodiments, the filter 67 can be installed in the fuel port 60 by passing the filter 67 through the inlet 62 of the fuel port 60 until the rim 81 of the filter 67 abuts the lip 74 of the fuel port 60. In some embodiments, a retaining ring 72 can be provided to hold the filter 67 in place. For example, the retaining ring 72 can snap fit into the recess 78 in the fuel port 60. Additionally, in embodiments where the filter 67 is integrally engaged with the orifice fitting 68, the filter 67 can be installed by passing the filter 67 and orifice fitting 68 from the inlet 62 of the fuel port 60 through the fuel port 60 until the orifice fitting 68 engages with the inlet 63 of the internal fluid passage 64, for example, until the external threads on the orifice fitting 68 contact the internal threads on the inlet 63 of the internal fluid passage, at which point the filter 67 and orifice fitting 68 (integrally engaged) can be screwed into the inlet 63 of the internal fluid passage 64 and secured in place by a retaining ring 72.

[0068] This written description uses examples to disclose the present technology, including the best mode, and also enables those skilled in the art to practice the present technology, including making and using any device or system and performing any incorporated method. The patentable scope of the present technology is defined by the claims and may include other examples that occur to those skilled in the art. If the structural elements of other such examples are the same as the literal meaning of the claims, or if the equivalent structural elements of such examples are not significantly different from the literal meaning of the claims, then such examples are intended to be within the scope of the claims.

Claims

1. A gas turbine comprising: compressor; turbine; burner, It is arranged downstream of the compressor and upstream of the turbine, and the combustor includes: end caps; a flange including an internal fluid passage defined therein, the flange being connected to an interior face of the end cap; a fuel port integrally engaged with the flange, the fuel port extending through the end cover between the flange and an inlet positioned external to the end cover, the inlet of the fuel port being in fluid communication with the internal fluid passage of the flange; an orifice fitting connected to an inlet of the internal fluid passage of the flange such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange through the orifice fitting; and A filter is integrally engaged with the orifice fitting, the filter being positioned within the fuel port upstream of the orifice fitting such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange through the filter and the orifice fitting.

2. The gas turbine according to claim 1, wherein: The flange extends between a first side and a second side opposite the first side, the first side of the flange abutting the interior face of the end cover, and further includes a fluid conduit extending between the second side of the flange and a fuel nozzle.

3. The gas turbine according to claim 2, wherein: The fuel port extends between the inlet and the first side of the flange.

4. The gas turbine according to claim 1, wherein: The fuel port passes through a hole in the end cover and further includes a sealing groove surrounding the hole in the end cover.

5. The gas turbine according to claim 1, wherein: The fuel port is offset from the bore of the end cover such that an annular channel is defined between the fuel port and the bore of the end cover.

6. The gas turbine according to claim 1, wherein: The flange includes a heat shield, the internal fluid passage of the flange being at least partially defined within the heat shield.

7. A combustor for a turbine, the combustor comprising: end caps; a flange including an internal fluid passage defined therein, the flange being connected to an inner side of the end cap; a fuel port integrally engaged with the flange, the fuel port extending through the end cover between the flange and an inlet positioned external to the end cover, the inlet of the fuel port being in fluid communication with the internal fluid passage of the flange; an orifice fitting connected to an inlet of the internal fluid passage of the flange such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange through the orifice fitting; as well as A filter is integrally engaged with the orifice fitting, the filter being positioned within the fuel port upstream of the orifice fitting such that the inlet of the fuel port is in fluid communication with the internal fluid passage of the flange through the filter and the orifice fitting.

8. The burner according to claim 7, characterized in that: The flange extends between a first side and a second side opposite the first side, the first side of the flange being adjacent to the end cover, and further includes a fluid conduit extending between the second side of the flange and a fuel nozzle.

9. The burner according to claim 8, characterized in that: The fuel port extends between the inlet and the first side of the flange.

10. The burner according to claim 7, characterized in that: The fuel port passes through a hole in the end cover and further includes a sealing groove surrounding the hole in the end cover.

11. The burner according to claim 7, characterized in that: The fuel port is offset from the bore of the end cover such that an annular channel is defined between the fuel port and the bore of the end cover.

12. The burner according to claim 7, characterized in that: The flange includes a heat shield, the internal fluid passage of the flange being at least partially defined within the heat shield.

Images