Integrated front panel for burners

Abstract

The present invention is entitled "Integrated front panel for burner". The present invention discloses a gas turbine engine (10) comprising a compressor (14) and a turbine (26) and a burner (22) and a combustor (24) between the compressor (14) and the turbine (26). The burner (22) is downstream of the compressor (14) and upstream of the turbine (26). The burner (22) is connected to the combustor (24) at a front panel (100) of the burner (22). The front panel (100) comprises a frame (102), an edge (112) extending around a central aperture (114) in the frame (102), and a sealing segment (116). The frame (102), the edge (112) and the sealing segment (116) are all integrally formed as a single unitary body.

Description

Technical Field

[0001] The subject matter disclosed herein relates to burners for turbomachines. More particularly, the present disclosure relates to a front panel of an integrally formed burner. Background Art

[0002] A turbine (such as a gas turbine engine) typically includes an inlet section, a compression section, one or more burners, a combustion chamber, and a turbine section. The inlet section may include a series of filters, cooling coils, moisture separators, and / or other equipment to purify and otherwise condition the working fluid (e.g., air) entering the gas turbine. The working fluid flows downstream from the inlet section to the compressor section, where kinetic energy is gradually imparted to the working fluid to produce a compressed working fluid in a highly energized state. In one or more burners, the compressed working fluid is mixed with fuel from a fuel supply to form a combustible mixture. The combustible mixture is burned by one or more burners to provide combustion gases with high temperature and pressure to the combustion chamber. The combustion gases flow through the turbine of the turbine section, where energy (kinetic energy and / or thermal energy) is transferred from the combustion gases to the rotor blades, causing the shaft to rotate and produce work. For example, the rotation of the shaft may drive the compressor to produce a compressed working fluid. Alternatively or in addition, the shaft may connect the turbine to a generator for generating electricity. Exhaust from the turbine flows through the exhaust section, which connects the turbine to an exhaust pipe downstream of the turbine. The exhaust section may include, for example, a heat recovery steam generator for cleaning the exhaust gas and extracting additional heat from the exhaust gas before releasing it to the environment.

[0003] The burner of such a turbine usually adjoins the combustion chamber via a front panel of the burner. The front panel may also include damping features. The sealing segment may be attached and welded to the front panel of the burner. The sealing segment may be used to connect the front panel of the burner to the membrane seal and the internal carrier to form the burner chamber.

[0004] Constructing and assembling the sealing segment and the front panel of the separate part may introduce restrictions in the design of the burner chamber. For example, the sealing segment may conflict with or constrain the possible location of damping features on some front panels.

[0005]

[0006] Therefore, it is recognized in the art that there is a need for an improved front panel for a burner nozzle that provides both sealing and damping features. Summary of the invention

[0006] Various aspects and advantages are set forth in the following description, or may be obvious from the description, or may be learned through practice of the invention.

[0007] In an exemplary embodiment of the present disclosure, a front panel for a burner of a turbine is provided. The turbine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending around the axial direction. The front panel includes a frame including an outer portion extending from a first side portion to a second side portion in a circumferential direction. The frame also includes an inner portion spaced apart from the outer portion by a first side portion and a second side portion in a radial direction. The inner portion of the frame extends from the first side portion to the second side portion in a circumferential direction. The front panel also includes an edge extending around a central orifice in the frame. The edge extends from the frame in an axial direction and is configured to engage with a downstream end of the burner. The front panel also includes a sealing segment connected to the inner portion of the frame. The frame, the edge, and the sealing segment are all integrally formed as a single, unitary body.

[0008] In another exemplary embodiment of the present disclosure, a turbine is provided. The turbine defines an axial direction, a radial direction perpendicular to the axial direction, and a circumferential direction extending around the axial direction. The turbine includes a compressor, a turbine, a combustor disposed downstream of the compressor and upstream of the turbine, and a burner disposed downstream of the compressor and upstream of the turbine. The burner is connected to a front panel. The front panel of the burner includes a frame, the frame including an outer portion extending from a first side portion to a second side portion in a circumferential direction. The frame also includes an inner portion spaced apart from the outer portion by a first side portion and a second side portion in a radial direction. The inner portion of the frame extends from the first side portion to the second side portion in a circumferential direction. The front panel also includes an edge extending around a central aperture in the frame. The edge extends from the frame in an axial direction and is configured to engage with a downstream end of the burner. The front panel also includes a sealing segment connected to the inner portion of the frame. The frame, the edge, and the sealing segment are all formed integrally as a single monolithic body.

[0009] These and other features, aspects and advantages of the present technology will become better understood with reference to the following description and appended claims.The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present technology and, together with the description, serve to explain the principles of the present technology. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] The remainder of this specification, including reference to the accompanying drawings, more particularly sets forth a complete and enabling disclosure of various embodiments, including the best mode apparent to those skilled in the art, in which:

[0011] Figure 1 A cross-sectional view of an exemplary gas turbine is shown that may incorporate various embodiments of the present disclosure.

[0012] Figure 2 A perspective view of a burner tip is shown with an exemplary front panel coupled thereto according to at least one embodiment of the present disclosure.

[0013] Figure 3 yes Figure 2 A perspective view of the front panel of the .

[0014] Figure 4 yes Figure 2 Cross-sectional view of the front panel and downstream portion of the burner.

[0015] Figure 5 yes Figure 4 An enlarged view of a portion of.

[0016] Figure 6 yes Figure 2 A perspective view of a portion of the front panel of FIG. DETAILED DESCRIPTION

[0017] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerical and letter designations to refer to the features in the drawings. Similar or similar designations in the drawings and the specification have been used to refer to similar or similar parts of the present disclosure.

[0018] 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 the various components. The terms "upstream" (or "upward") and "downstream" (or "downward") refer to relative directions relative to the flow of fluid in a fluid pathway. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction toward which the fluid flows. The term "radially" refers to a relative direction substantially perpendicular to an axial centerline of a particular component, the term "axially" refers to a relative direction substantially parallel and / or coaxially aligned with an axial centerline of a particular component, and the term "circumferentially" refers to a relative direction extending around the axial centerline of a particular component.

[0019] The terms used herein are only used for the purpose of describing specific embodiments and are not intended to be limiting. As used herein, the singular forms "a", "an" and "the" are intended to also include the plural forms, unless the context clearly indicates otherwise. It will be further understood that when used in the specification, the terms "comprise" and / or "comprising" specify the presence of stated features, integers, steps, operations, elements and / or parts, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, parts and / or their groups.

[0020] As used herein, approximate terms such as "substantially" or "about" include values ​​within ten percent greater or less than the stated value. When used in the context of an angle or direction, such terms include values ​​within ten degrees greater or less than the stated angle or direction. For example, "substantially vertical" includes directions within ten degrees of vertical in any direction (e.g., clockwise or counterclockwise).

[0021] Each example is provided by way of explanation and not limitation. In fact, it will be apparent to those skilled in the art that modifications and variations may be made without departing from the scope or spirit of the invention. For example, features shown or described as part of one embodiment may be used on another embodiment to produce yet another embodiment. Therefore, the present disclosure is intended to cover such modifications and variations that fall within the scope of the appended claims and their equivalents. Although for purposes of illustration, exemplary embodiments of the present disclosure will be generally described in the context of a combustion system for a land-based power generation gas turbine, it will be readily understood by those skilled in the art that embodiments of the present disclosure may be applied to any style or type of burner for a turbine, and are not limited to burners or combustion systems for land-based power generation gas turbines, unless specifically described in the claims.

[0022] Now referring to the accompanying drawings, Figure 1 A cross-sectional view of an exemplary gas turbine engine 10 that may incorporate various embodiments of the present invention is provided. As shown, the gas turbine engine 10 generally includes an inlet (not shown), a compressor 14 disposed downstream of the inlet, at least one burner 16 disposed downstream of the compressor 14, a combustor or combustion chamber 18 disposed downstream of the burner 16, a turbine 20 disposed downstream of the combustor 18, and an exhaust section 28 disposed downstream of the turbine 20. In addition, the gas turbine engine 10 may include one or more shafts 21 that couple the compressor 14 to the turbine 20. The shaft 21 may extend along an axial direction A and define the axial direction A. The gas turbine engine 10 may also define a radial direction R perpendicular to the axial direction A and a circumferential direction C ( Figure 2 and Figure 3 ).

[0023] In some embodiments, for example, Figure 1 As shown, the gas turbine engine 10 may include a sequential combustion system. In such an embodiment, the burner 16 may be a main burner 16, and the gas turbine engine 10 may also include a sequential burner 22. Moreover, the turbine 20 may be a high-pressure turbine 20, and a low-pressure turbine 26 may be disposed downstream of the sequential burner 24, wherein the sequential burner 24 receives combustion gases from the sequential burner 22. The low-pressure turbine 26 typically includes a greater number of stages than the high-pressure turbine 20; for example, Figure 1As shown, the high pressure turbine 20 includes a single stage having one nozzle or stator blade and one rotor blade downstream of one stator blade, while the low pressure turbine 26 includes, for example, three or more stages, such as at least three sets of stator blades and rotor blades.

[0024] During operation, air flows through the inlet and enters the compressor 14, where the air is gradually compressed, thereby providing compressed air to the burner 16. The burner 16 may be at least partially surrounded by an outer cylinder 34, such as a compressor discharge cylinder. The compressor discharge cylinder 34 may at least partially define a high pressure chamber that at least partially surrounds various components of the combustor 18. The compressor discharge cylinder 34 may be in fluid communication with the compressor 14 to receive compressed air therefrom.

[0025] At least a portion of the compressed air is mixed with fuel within the burner 16 and combusted to produce combustion gases 30. The combustion gases 30 flow from the burner 16 into and through the combustor 18 and to the turbine 20, where energy (kinetic energy and / or thermal energy) is transferred from the combustion gases 30 to one or more rotor blades (such as a single rotor blade in the illustrated example where the turbine 20 is a single-stage high-pressure turbine), thereby causing the shaft 21 to rotate. The mechanical rotational energy can then be used for various purposes, such as powering the compressor 14 and / or generating electricity. The combustion gases 30 exiting the turbine 20 can then, in some embodiments, be exhausted from the gas turbine engine 10 via the exhaust section 28, while in other embodiments, such as Figure 1 As shown, the combustion gases 30 exiting the high pressure turbine 20 may be mixed with additional fuel and combusted in the sequential burner 22 downstream of the high pressure turbine 20. For example, such additional fuel may be supplied to the sequential burner 22 via a retractable fuel lance 23. The sequential burner 22 may generate combustion gases 32 within the sequential combustor 24, which are directed to the low pressure turbine 26, as described above.

[0026] like Figure 2 As shown, the continuous burner 22 can be connected to the continuous burner 24 ( Figure 1 ).like Figure 2 As shown, the continuous burner 22 extends from an upstream end 36 to a downstream end 38 in an axial direction. The downstream end 38 of the continuous burner 22 can be connected to the front panel 100. For example, the downstream end 38 of the continuous burner 22 can be joined to the front panel 100, such as by welding the front panel 100 to the burner 22 at the downstream end 38 of the burner 22. For example, Figure 2 As shown, the front panel 100 may be joined to the downstream end 38 of the sequential burner 22 via a weld or seam 200 .

[0027] Figure 3 A perspective view of the front panel 100 is provided. Figure 3As can be seen in FIG. 1 , the front panel 100 includes a frame 102 and an edge 112 (e.g., a center edge 112) that surrounds and defines a center aperture 114. The frame 102 generally surrounds the edge 112, and the edge 112 is located in or near the approximate geometric center of the frame 102. The center edge 112 may include cooling features, such as cooling holes 120, as in the exemplary embodiment shown. As shown in FIG. Figure 3 As can be seen in FIG. 1 , the frame 102 includes an outer portion 104 extending from a first side portion 106 to a second side portion 108 along a circumferential direction C, and an inner portion 110 spaced apart from the outer portion 104 by the first side portion 106 and the second side portion 108 along a radial direction R. The first side portion 106 and the second side portion 108 extend from the inner portion 110 to the outer portion 104 along the radial direction R. The inner portion 110 extends from the first side portion 106 to the second side portion 108 along the circumferential direction C. Similarly, as shown in FIG. Figure 3 As shown, the central edge 112 of the front panel 100 extends away from the frame 102 along the axial direction A (e.g., in the axial upstream direction), so that when the front panel 100 is coupled to the burner 22, the central edge 112 extends from the frame 102 to the downstream end 38 of the continuous burner 22, as shown in FIG. Figure 2 shown.

[0028] The frame 102, the edge 112, and the sealing segment 116 are all integrally formed as a single, unitary body. For example, in some embodiments, the frame 102, the edge 112, and the sealing segment 116 can be integrally formed as a single, unitary body by forming the components in an additive manufacturing process. In other embodiments, the frame 102, the edge 112, and the sealing segment 116 can be integrally formed as a single, unitary body using any suitable method, such as by casting the frame 102, the edge 112, and the sealing segment 116, or by forming the frame 102, the edge 112, and the sealing segment 116 using an additive manufacturing technique, such as, but not limited to, direct metal laser melting (DMLM), selective laser sintering (SLS), or other suitable techniques.

[0029] The front panel 100 may also include one or more dampers 118, such as resonators (such as Helmholtz resonators), disposed in and near the frame 102. For example, the dampers 118 may also be integrally formed with a single unitary body that also includes the frame 102, the edge 112, and the sealing section 116, as described above. Figure 4 and Figure 5As can be seen in the cross-sectional view of FIG. 1 , each damper 118 may include an interior volume 119 that is configured (e.g., sized and shaped) to reduce pressure oscillations that may propagate (e.g., circumferentially) within the combustor 24. The operation of such dampers 118 is generally understood in the art, and therefore, for the sake of brevity and clarity, will not be described in further detail herein.

[0030] like Figure 3 and Figure 4 As best seen in FIG. 1 , the one or more dampers 118 may include multiple dampers 118, such as a plurality of dampers 118. For example, in some embodiments, the plurality of dampers 118 may include a first plurality of dampers 118 in the top portion 104 of the frame 102, a second plurality of dampers 118 in the first side portion 106 of the frame 102, a third plurality of dampers 118 in the second side portion 108 of the frame 102, and a fourth plurality of dampers 118 in the inner portion 110 of the frame 102. In some embodiments, the first plurality of dampers 118 in the outer portion 104 of the frame 102 may include two rows of dampers 118 spaced apart along the radial direction R, such as an outer row of dampers 118 proximate the exterior of the frame 102 and an inner row of dampers 118 proximate the center edge 112. In some embodiments, the second plurality of dampers 118 in the first side portion 106 of the frame 102 may include two rows of dampers 118 spaced apart along the circumferential direction C, such as an outer row of dampers 118 near the outside of the frame 102 and an inner row of dampers 118 near the center edge 112, and the third plurality of dampers 118 in the second side portion 108 of the frame 102 may include two rows of dampers 118 spaced apart along the circumferential direction C, such as an outer row of dampers 118 near the outside of the frame 102 and an inner row of dampers 118 near the center edge 112.

[0031] Additionally, in at least some embodiments, the seal segment 116 may also include one or more dampers 118 integrated therewith, for example, the one or more dampers 118 may be directly integrated into the seal segment 116. For example, as in Figure 4 and Figure 5 As can be seen in FIG. 1 , the sealing section 116 may also include one or more internal volumes 119 therein, whereby the sealing section 116 may also function as a resonator (eg, a Helmholtz resonator), as described above. Figure 5As shown, each damper 118 may include an inlet 124 that enters (e.g., communicates with) the interior volume 119. It should be noted that the inlet 124 that enters the interior volume 119 of the damper 118 directly integrated into the sealing segment 116 is given by way of example only. Those skilled in the art will recognize that each damper 118 includes an inlet 124, and the inlet 124 and the interior volume 119 of each damper 118 may vary in shape and / or size, for example, to provide damping of a desired frequency or frequency range.

[0032] As in Figure 6 As best seen in FIG. 1 , the seal segment 116 can be discontinuous along the circumferential direction C. For example, the seal segment 116 can include a plurality of slits 121 extending along the axial direction A. For example, the slits 121 can be spaced apart along the circumferential direction C. Thus, the seal segment 116 can include a plurality of sub-segments 122 defined by and between the slits 121. In some embodiments, the slits 121 can have varying axial lengths, such as Figure 6 In addition, in some embodiments, one or more cooling holes 126 (e.g., a plurality of cooling holes 126) may be formed in the sealing segment 116. For example, Figure 6 As shown, the cooling holes 126 may be positioned at the axial endpoints of one or more (up to and including each) of the slots 121 in the seal segment 116. Such circumferential discontinuities (e.g., the slots 121 and / or the cooling holes 126) of the seal segment 116 may allow air to flow through the seal segment 116, such as between the sub-segments 122 thereof, thereby providing convective cooling to the seal segment 116.

[0033] Integrating the frame 102, the rim 112, the seal segment 116, and the damper 118 into a single, unitary body provides numerous advantages, many of which will be apparent to one of ordinary skill in the art. For example, such advantages include facilitating flexibility and cooling of the seal segment 116, e.g., the slits 121 may increase the flexibility of the seal segment 116 and thereby increase the life of the seal segment 116. Additionally, the integration of the various parts (including integrating one or more dampers 118 directly into the seal segment 116) may resolve or avoid potential conflicts with positioning multiple parts in the same or proximate locations, e.g., positioning the seal segment 116 where the damper 118 would be (or vice versa).

[0034] This written description uses examples to disclose the invention, including the best mode, and also enables any person skilled in the art to practice the invention, including making and using any device or system and performing any combined method. The patentable scope of the invention is defined by the claims and may include other examples that occur to one skilled in the art. For example, the aforementioned exemplary description of the inner corner of the rear frame may also be implemented at one or more outer corners of the rear frame as well as the inner corner or in place of the inner corner. If these other examples include structural elements that are not different from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims, these other examples are intended to be within the scope of the claims.

Claims

1. A front panel (100) for a burner (22) of a gas turbine engine (10), the gas turbine engine (10) defining an axial direction (A), a radial direction (R) perpendicular to the axial direction (A), and a circumferential direction (C) extending around the axial direction (A), the front panel (100) comprising: a frame (102), the frame comprising an outer portion (104) extending from a first side portion (106) to a second side portion (108) in the circumferential direction, an inner portion (110) spaced apart from the outer portion (104) by the first side portion (106) and the second side portion (108) in the radial direction, the inner portion (110) extending from the first side portion (106) to the second side portion (108) in the circumferential direction; a rim (112) extending around a central aperture (114) in the frame (102), the rim (112) extending from the frame (102) in the axial direction and configured to engage a downstream end of the burner (22); and a sealing segment (116) connected to the inner portion of the frame (102), wherein one or more dampers are directly integrated into the sealing segment; wherein the sealing segment includes one or more internal volumes therein, and each of the one or more dampers includes an inlet into the one or more internal volumes; and Wherein the frame (102), the rim (112), the one or more dampers and the sealing segment (116) are all integrally formed as a single unitary body.

2. The front panel (100) of claim 1, wherein the one or more dampers include a first plurality of dampers (118) integrally formed in the interior portion of the frame (102).

3. The front panel (100) of claim 2, wherein a second plurality of dampers (118) are integrally formed in the outer portion (104) of the frame (102).

4. The front panel (100) of claim 2, wherein a third plurality of dampers (118) are integrally formed in the first side portion (106) of the frame (102) and the second side portion (108) of the frame (102).

5. The front panel (100) according to claim 1, wherein the sealing segment (116) is discontinuous along the circumferential direction (C).

6. The front panel (100) according to claim 1, wherein the sealing section (116) comprises a plurality of slits (121) extending along the axial direction (A), and the slits in the plurality of slits (121) are spaced apart along the circumferential direction (C).

7. The front panel (100) of claim 1, further comprising at least one of a first plurality of cooling holes (126) formed in the sealing segment (116) or a second plurality of cooling holes (120) formed in the edge (112).

8. A gas turbine engine (10), the gas turbine engine defining an axial direction (A), a radial direction (R) perpendicular to the axial direction (A), and a circumferential direction (C) extending around the axial direction (A), the gas turbine engine (10) comprising: Compressor (14); Turbine (20, 26); a combustor disposed downstream of the compressor (14) and upstream of the turbine (20, 26); and A burner (16, 22) is arranged downstream of the compressor (14) and upstream of the turbine (20, 26), the burner (16, 22) being connected to a front panel (100) according to any one of claims 1 to 7.

9. A gas turbine engine (10) according to claim 8, wherein the turbine (20, 26) is a low-pressure turbine (26), the combustor is a sequential combustor (24), and the burners (16, 22) are sequential burners (22), and the gas turbine engine further comprises a high-pressure turbine (20) upstream of the sequential burner (22), a first burner (18) upstream of the high-pressure turbine (20), and an additional burner (16) upstream of the first burner (18).

10. The gas turbine engine (10) of claim 9, further comprising a retractable fuel lance (23) configured to provide fuel to the sequential burner (22).

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