Exhaust diffuser assembly with stress relief opening at parting line

Abstract

An exhaust diffuser assembly (100) and a gas turbine (10) are provided. The exhaust diffuser assembly (100) includes at least two diffuser sections (102A, 102B) coupled to each other and collectively forming an exhaust diffuser (34) extending from a front end (76) to a rear end (78). The at least two diffuser sections (102A, 102B) include a first diffuser section (102A) having a first sleeve portion (202) extending to a first circumferential edge (207). The two diffuser sections (102A, 102B) also include a second diffuser section (102B) having a second sleeve portion (206) extending to a second circumferential edge (208). The first circumferential edge (207) is joined to the second circumferential edge (208) at the parting line (200). The weld joint (210) extends along a portion of the parting line (200) to a weld end (212, 272). The first sleeve portion (202) and the second sleeve portion (206) define a stress relief opening (214, 270A, 270B) disposed at least partially at a weld end (212, 272) of the weld joint (210).

Description

Technical Field

[0001] The present disclosure generally relates to an exhaust diffuser having one or more segments joined at a split line. In particular, the present disclosure relates to structures and openings that reduce local stress at the split line. Background Art

[0002] Turbines are used for energy transfer purposes in various industries and applications. For example, a gas turbine engine typically 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 the compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed in the combustion section and burned in the combustion chamber to generate high-pressure and high-temperature combustion gases. The combustion gases flow from the combustion section into the turbine section, where the combustion gases expand to do work. For example, the expansion of the combustion gases in the turbine section can rotate a rotor shaft connected to, for example, a generator to generate electricity. The combustion gases are then discharged from the turbine section through an exhaust diffuser positioned downstream of the turbine section.

[0003] The exhaust diffuser typically includes an inner liner and an outer liner that is radially separated from the inner liner to form an exhaust flow channel through the diffuser. One or more diffuser struts of generally airfoil shape extend between the inner liner and the outer liner within the exhaust flow channel to provide structural support to the outer liner and / or a rear bearing of the support shaft. The exhaust diffuser typically includes one or more sections (such as a top section and a bottom section) that are joined together at a split line (e.g., via a weld joint).

[0004] Operation of a turbine for power generation can result in frequency oscillations (i.e., pressure pulsations or vibrations) within the exhaust diffuser that may cause damage to various components of the exhaust diffuser over time or may result in an unplanned or premature shutdown of the turbine. For example, the split line may be exposed to these vibrations, which may damage the weld joint connecting the top section and the bottom section. In particular, existing split line designs may experience high stresses at the joint between the top section and the bottom section due to the operation of the turbine.

[0005] Therefore, an improved exhaust diffuser having one or more structures and / or openings at a split line that improves the robustness of the split line to operational vibrations is desirable and would be appreciated in the art. Summary of the invention

[0006] Various aspects and advantages of exhaust diffuser assemblies and gas turbines according to the present disclosure will be set forth in part in the following description, or may be obvious from the description, or may be learned through practice of the technology.

[0007] According to one embodiment, an exhaust diffuser assembly is provided. The exhaust diffuser assembly includes at least two diffuser sections, which are connected to each other and together form an exhaust diffuser extending from a front end to a rear end. The at least two diffuser sections include a first diffuser section having a first sleeve portion extending to a first circumferential edge in at least two diffuser sections. The two diffuser sections also include a second diffuser section having a second sleeve portion extending to a second circumferential edge. The first circumferential edge is joined to the second circumferential edge at a dividing line. The weld joint extends along a portion of the dividing line to the weld end. The first sleeve portion and the second sleeve portion define a stress relief opening at least partially disposed at the weld end of the weld joint.

[0008] According to another embodiment, a gas turbine is provided. The gas turbine includes a compressor segment, a combustion segment downstream of the compressor segment, and a turbine segment downstream of the combustion segment. The gas turbine segment also includes an exhaust diffuser assembly having an exhaust diffuser downstream of the turbine segment. The exhaust diffuser assembly includes at least two diffuser sections, which are connected to each other and together form an exhaust diffuser extending from the front end to the rear end. The at least two diffuser sections include a first diffuser section having a first sleeve portion extending to a first circumferential edge in at least two diffuser sections. The two diffuser sections also include a second diffuser section having a second sleeve portion extending to a second circumferential edge. The first circumferential edge is joined to the second circumferential edge at a dividing line. The weld joint extends to a weld end along a portion of the dividing line. The first sleeve portion and the second sleeve portion define a stress relief opening at least partially disposed at the weld end of the weld joint.

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

[0010] This specification sets forth a complete and enabling disclosure of the exhaust diffuser assembly and gas turbine of the present invention, including the best mode of making and using the systems and methods of the present invention, to one of ordinary skill in the art, with reference to the accompanying drawings, wherein:

[0011] Figure 1 is a schematic diagram of a turbine according to an embodiment of the present disclosure;

[0012] Figure 2 schematically illustrates an enlarged cross-sectional view of an exhaust diffuser assembly according to an embodiment of the present disclosure;

[0013] Figure 3 shows a cross-sectional, partially exploded view of an exhaust diffuser according to an embodiment of the present disclosure;

[0014] Figure 4 The embodiment according to the present disclosure is shown Figure 3 a cross-sectional assembly view of the exhaust diffuser shown;

[0015] Figure 5 shows an isometric view of an exhaust diffuser assembly having an exhaust diffuser according to an embodiment of the present disclosure;

[0016] Figure 6 shows an enlarged view of an exhaust diffuser of an exhaust diffuser assembly including a split line according to an embodiment of the present disclosure;

[0017] Figure 7 shows an enlarged view of an exhaust diffuser of an exhaust diffuser assembly including a dividing line according to another exemplary embodiment of the present disclosure;

[0018] Figure 8 An enlarged view of an exhaust diffuser of an exhaust diffuser assembly having a connection block disposed at a split line according to an embodiment of the present disclosure is shown; and

[0019] Fig. 9 FIG. 1 shows a cross-sectional view taken along line 9-9 according to an embodiment of the present disclosure. Figure 8 A cross-sectional view of the exhaust diffuser assembly is shown. DETAILED DESCRIPTION

[0020] Reference will now be made in detail to embodiments of the exhaust diffuser assembly and gas turbine of the present invention, one or more examples of which are shown in the accompanying drawings. Each example is provided by way of explanation of the present invention technology, rather than limitation of the present invention technology. In fact, it will be apparent to those skilled in the art that modifications and variations can be made in the present invention technology without departing from the scope or essence of the present invention technology protected by the claims. For example, features illustrated or described as part of one embodiment may be used in 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.

[0021] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. In addition, unless otherwise specifically stated, all embodiments described herein should be considered exemplary.

[0022] The detailed description uses numbers and letter names to refer to the features in the drawings. Similar or similar names in the drawings and description have been used to refer to similar or similar parts of the present 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 position or importance of the various components.

[0023] The term "fluid" may be a gas or a liquid. The term "fluid communication" means that two or more regions defining a flow channel are joined to each other so that a fluid can form a connection (ie flow) between the designated regions.

[0024] As used herein, the terms "upstream" (or "front") and "downstream" (or "rear") refer to relative directions with respect to the flow of a fluid in a fluid passage. For example, "upstream" refers to the direction from which the fluid is flowing, and "downstream" refers to the direction toward which the fluid is flowing. Thus, the term "front" generally refers to the compressor end of a gas turbine engine, while the term "rear" refers to the exhaust end of a gas turbine engine.

[0025] The term "radially" refers to relative directions that are substantially perpendicular to the axial centerline of a particular component; the term "axially" refers to relative directions that are substantially parallel and / or coaxially aligned with the axial centerline of a particular component; and the term "circumferentially" refers to relative directions that extend around the axial centerline of a particular component.

[0026] Terms with approximate meanings (such as "about", "approximately", "substantially" and "substantially") are not limited to the exact values ​​specified. In at least some cases, approximate language may correspond to the accuracy of an instrument used to measure a value, or the accuracy of a method or machine used to construct or manufacture a component and / or system. In at least some cases, approximate language may correspond to the accuracy of an instrument used to measure a value, or the accuracy of a method or machine used to construct or manufacture a component and / or system. For example, approximate language may refer to a tolerance of 1%, 2%, 4%, 5%, 10%, 15% or 20% in an individual value, a range of values ​​and / or an end value of a range of defined values. When used in the context of an angle or direction, such terms are included within ten degrees greater than or less than the angle or direction. For example, "substantially vertical" includes directions within ten degrees of vertical in any direction (e.g., clockwise or counterclockwise).

[0027] Unless otherwise indicated herein, the terms "coupled," "fixed," "attached to," and the like refer to both direct coupling, fixing, or attachment, as well as indirect coupling, fixing, or attachment through one or more intermediate components or features. The terms "directly coupled," "directly fixed," "directly attached to," and the like mean that two components are engaged in contact with one another and there are no intermediate components or features present.

[0028] As used herein, the terms "includes," "comprising," "having," or any other variation thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, article, or apparatus that includes a list of features is not necessarily limited to only those features but may include other features not expressly listed or inherent to such process, method, article, or apparatus. In addition, unless expressly specified otherwise, "and / or" refers to a condition that is satisfied by any of the following: A is true (or exists) and B is false (or does not exist); A is false (or does not exist) and B is true (or exists); and both A and B are true (or exist).

[0029] Here and throughout the specification and claims, where range limitations are combined and interchanged, such ranges are identified and include all sub-ranges contained therein unless context or language indicates otherwise. For example, all ranges disclosed herein are inclusive of the endpoints, and the endpoints are independently combinable with each other.

[0030] Now referring to the accompanying drawings, Figure 1 A schematic diagram of one embodiment of a turbomachine is shown, which in the illustrated embodiment is a gas turbine engine 10. Although an industrial or land-based gas turbine engine is shown and described herein, the present disclosure is not limited to industrial and / or land-based gas turbine engines unless otherwise indicated in the claims. For example, the present invention as described herein may be used for any type of turbomachine, including but not limited to a steam turbine, an aircraft gas turbine, or a marine gas turbine.

[0031] As shown, the gas turbine engine 10 generally includes a compressor section 12. The compressor section 12 includes a compressor 14. The compressor section 12 includes an inlet 16 disposed at the upstream end of the gas turbine engine 10. The gas turbine engine 10 also includes a combustion section 18 having one or more combustors 20 disposed downstream of the compressor section 12. The gas turbine engine 10 also includes a turbine section 22 located downstream of the combustion section 18. A shaft 24 generally extends axially through the gas turbine engine 10.

[0032] The compressor segment 12 may generally include a plurality of rotor disks 21 and a plurality of rotor blades 23 extending radially outward from each rotor disk 21 and connected to each rotor disk. Each rotor disk 21 may in turn be coupled to or form a portion of a shaft 24 extending through the compressor segment 12. The rotor blades 23 of the compressor segment 12 may include a turbine airfoil defining an airfoil shape (e.g., having a leading edge, a trailing edge, and a sidewall extending between the leading edge and the trailing edge). In addition, the compressor segment 12 includes stator vanes disposed between the rotor blades to define a series of compression stages. The stator vanes may extend from and be coupled to the compressor housing.

[0033] The turbine segment 22 may generally include a plurality of rotor disks 27 and a plurality of rotor blades 28 extending radially outward from each rotor disk 27 and interconnected to each rotor disk. Each rotor disk 27, in turn, may be coupled to or form a portion of a shaft 24 extending through the turbine segment 22. The turbine segment 22 also includes an outer casing 32 that circumferentially surrounds a portion of the shaft 24 and the rotor blades 28. The turbine segment 22 may include a fixed nozzle 26 extending radially inward from the outer casing 32. The rotor blades 28 and the fixed nozzles 26 may be arranged in an alternating manner along the axial centerline 30 of the gas turbine 10. Both the rotor blades 28 and the fixed nozzles 26 may include a turbine airfoil defining an airfoil shape (e.g., having a leading edge, a trailing edge, and a sidewall extending between the leading edge and the trailing edge).

[0034] In operation, ambient air 36 or other working fluid is drawn into the inlet 16 of the compressor 14 and is gradually compressed to provide compressed air 38 to the combustion section 18. The compressed air 38 flows into the combustion section 18 and mixes with the fuel to form a combustible mixture. The combustible mixture is burned within the combustion chamber 40 of the combustor 20, thereby generating combustion gases 42 that flow from the combustion chamber 40 into the turbine section 22. Energy (kinetic energy and / or thermal energy) is transferred from the combustion gases 42 to the rotor blades 28, causing the shaft 24 to rotate and produce mechanical work.

[0035] The gas turbine engine 10 may define a cylindrical coordinate system having an axial direction A extending along the axial centerline 30 , a radial direction R perpendicular to the axial centerline 30 , and a circumferential direction C extending about the axial centerline 30 .

[0036] The combustion gases 42 exit the turbine section 22 and flow through the exhaust diffuser 34 across a plurality of struts 44 disposed within the exhaust diffuser 34. During various operating conditions of the gas turbine engine 10, such as during part load operation, the combustion gases 42 flowing from the turbine section 22 into the exhaust diffuser 34 are imparted with a high level of swirl caused by the rotating turbine rotor blades 28. Such swirl can cause pressure fluctuations, frequency oscillations, or acoustic vibrations.

[0037] Figure 2 A cross-sectional view of an exhaust diffuser assembly 100 (which includes an exhaust diffuser 34) according to an embodiment of the present disclosure is shown. As shown, the exhaust diffuser 34 generally includes an inner liner 46 and an outer liner 48 radially spaced apart from the inner liner 46. The inner liner 46 may extend generally axially along an axial centerline 50 of the exhaust diffuser 34. The axial centerline 50 of the exhaust diffuser 34 may be coaxial with the axial centerline 30 of the gas turbine engine 10. The inner liner 46 is generally annular and may at least partially surround a rotating component. For example, the inner liner 46 may surround or encase a portion of the shaft 24.

[0038] In many embodiments, the outer liner 48 may be radially separated from the inner liner 46 such that the exhaust flow channel 52 is defined between the inner liner 46 and the outer liner 48. In a specific embodiment, the inner liner 46 is concentrically and coaxially aligned within the outer liner 48 relative to the axial centerline 50. In certain embodiments, the diffuser shell 56 may be radially spaced from and annularly surround the outer liner 48 such that a fluid plenum 58 is defined between the diffuser shell 56 and the outer liner 48. A stream of compressed air (or other working fluid) may flow within the fluid plenum 58 to cool various components of the exhaust diffuser 34 (such as the outer liner 48 and the struts 44). A plurality of support connectors 300 connect the diffuser shell 56 to the outer liner 48, which may be circumferentially spaced and disposed in the fluid plenum 58. The present disclosure is not limited to any particular size, shape, material, or other physical characteristics of the inner liner 46, the outer liner 48, and / or the diffuser shell 56, unless stated in the claims.

[0039] Each of the diffuser struts 44 may extend between the inner liner 46 and the outer liner 48 and within the exhaust flow passage 52 defined therebetween. The diffuser struts 44 are spaced circumferentially around the inner liner 46, and the diffuser struts 44 may orient, align, or otherwise center the inner liner 46 within the outer liner 48. Furthermore, the diffuser struts 44 may provide structural support between the inner liner 46 and the outer liner 48. Figure 1 As shown, the diffuser struts 44 are positioned relative to the flow direction 60 of the spent combustion gases 42 flowing out of the turbine section 22 of the gas turbine engine 10. Figure 3 As shown, each diffuser strut 44 generally includes a root portion 62 connected to the inner liner 46 and a tip portion 64 radially separated from the root portion 62 and connected to the outer liner 48 .

[0040] Figure 3 shows a cross-sectional, partially exploded view of an exhaust diffuser 34 according to an embodiment of the present disclosure, and Figure 4 is shown a cross-sectional assembly view of the exhaust diffuser 34. As shown, the exhaust diffuser 34 includes at least two diffuser sections 102A, 102B that are coupled to one another and collectively form the exhaust diffuser 34. As shown, the at least two diffuser sections 102A, 102B may include a first diffuser section 102A (or top diffuser section) and a second diffuser section 102B (or bottom diffuser section).

[0041] Although Figure 3 and Figure 4An exhaust diffuser 34 having two diffuser sections 102A, 102B is shown, but it should be understood that the exhaust diffuser 34 may have more than two diffuser sections joined together using similar structures and techniques described herein. Unless specifically stated in the claims, the present disclosure should not be specifically limited to two diffuser sections.

[0042] At least two diffuser sections 102A, 102B may each include a sleeve portion, such as an inner sleeve portion 104A, 104B and an outer sleeve portion 106A, 106B. The inner sleeve portions 104A, 104B may be joined together at an inner split line 108 to form the inner sleeve 46, and the outer sleeve portions 106A, 106B may be joined together at an outer split line 110 to form the outer sleeve 48. Specifically, as shown, the first diffuser section 102A may include a first inner sleeve portion 104A and a first outer sleeve portion 106A. Similarly, the second diffuser section 102B may include a second inner sleeve portion 104B and a second outer sleeve portion 106B.

[0043] The first inner sleeve portion 104A may be coupled to the second inner sleeve portion 104B at the inner split line 108, and the first outer sleeve portion 106A may be coupled to the second outer sleeve portion 106B at the outer split line 110. More specifically, the first inner sleeve portion 104A may each extend circumferentially between first inner circumferential edges 112, and the second inner sleeve portion 104B may extend circumferentially between second inner circumferential edges 114. The first inner circumferential edges 112 may each be joined to respective second inner circumferential edges 114 at the inner split line 108. Similarly, the first outer sleeve portion 106A may each extend circumferentially between first outer circumferential edges 116, and the second outer sleeve portion 106B may extend circumferentially between second outer circumferential edges 118. The first outer circumferential edges 116 may each be joined to respective second outer circumferential edges 118 at the outer split line 110.

[0044] Figure 5 An isometric view of an exhaust diffuser assembly 100 having an exhaust diffuser 34 is shown. As described above, the exhaust diffuser 34 may include an inner liner 46, an outer liner 48, and a plurality of struts 44 extending (e.g., radially) between the inner liner 46 and the outer liner 48. The exhaust diffuser 34 may include a first diffuser section 102A and a second diffuser section 102B joined together at an inner dividing line 108 and an outer dividing line 110. Additionally, the exhaust diffuser 34 may extend axially between a forward end 76 and a rearward end 78.

[0045] like Figure 5As shown, a plurality of support connector assemblies 300 are attached to the outer liner 48, some of which are arranged in circumferential groups 310 (e.g., groups of three). Each support connector assembly 300 in the group 310 of support connector assemblies 300 may be approximately (e.g., ±5%) circumferentially equidistantly spaced from the other support connectors 300 in the group 310. Figure 5 As shown, each of the plurality of struts 44 defines an interior 86 that extends between an outer opening 88 defined in the outer liner 48 and an inner opening 90 defined in the inner liner 46. In such embodiments, the support connector assemblies 300 attached to the outer liner 48 may be disposed between circumferentially adjacent outer openings 88. Specifically, one or more groups 310 may be circumferentially disposed between two adjacent outer openings 88. In addition, a single split line support connector assembly 300 may be disposed between the outer split line 110 and the outer opening 88 closest to the outer split line 110. Although the circumferential group 310 is shown as having three support connector assemblies 300, other numbers (e.g., two or more) of support connector assemblies 300 may be used.

[0046] Now refer to Figure 6 and Figure 7 According to an embodiment of the present disclosure, a partition line 200 (which may be the above reference Figure 4 and Figure 5 108 or the outer dividing line 110 discussed above). As shown, the exhaust diffuser 34 may include at least two diffuser sections 102A, 102B that are coupled to each other and together form the exhaust diffuser 34 extending from the front end 76 to the rear end 78. The at least two diffuser sections 102A, 102B may include a first diffuser section 102A of the at least two diffuser sections having a first sleeve portion 202 extending to a first circumferential edge 207. The first sleeve portion 202 may be a first sleeve portion 202 as described above with reference to FIG. Figure 3 and Figure 4 One of the first inner sleeve 104A and / or the first outer sleeve 106A is discussed.

[0047] Additionally, at least two diffuser segments 102A, 102B may further include a second diffuser segment 102B having a second sleeve portion 206 extending to a second circumferential edge 208. The first circumferential edge 207 may be joined to the second circumferential edge 208 at the split line 200. For example, the weld joint 210 may extend from a first (or front) weld end 212 to a second (or rear) weld end 272 along a portion of the split line 200. Additionally, the first sleeve portion 202 and the second sleeve portion 206 may define a front stress relief opening 214 disposed at least partially at the first weld end 212. The front stress relief opening 214 may extend from the front end 76 of the exhaust diffuser 34 to (and partially beyond) the first weld end 212 of the weld joint 210.

[0048] The split line 200 may be an imaginary (although at least partially visible at the weld joint 210) axially extending line defined at the junction between the first sleeve portion 202 and the second sleeve portion 206. In an exemplary embodiment, the front stress relief opening 214 includes a slot portion 216 extending from the front end 76 of the exhaust diffuser 34 along the split line 200. The first circumferential edge 207 may be spaced apart from the second circumferential edge 208 to define the slot portion 216, such that the first circumferential edge 207 and the second circumferential edge 208 together define the slot portion 216. In other words, the slot portion 216 may be defined along a front portion of the exhaust diffuser between the first circumferential edge 207 and the second circumferential edge 208 and along the split line 200.

[0049] In some embodiments, such as Figure 6 and Figure 7 As shown, the front stress relief opening 214 may include branch portions 218A, 218B and main body portions 220A, 220B. The branch portions 218A, 218B may extend (substantially vertically) from the groove portion 216 to the main body portions 220A, 220B. Specifically, the first sleeve portion 202 may define a first branch portion 218A, which extends substantially vertically from the groove portion 216 at the first welding end 212 of the welding joint 210 to the first main body portion 220A. Similarly, the second sleeve portion 206 may define a second branch portion 218B extending from the groove portion 216 at the first welding end 212 of the welding joint 210 to the second main body portion 220B.

[0050] The first body portion 220A and the second body portion 220B may each be spaced apart from the weld joint 210 and may extend axially next to the front portion of the weld joint 210. As shown in the figure, in an exemplary embodiment, the first body portion 220A and the second body portion 220B may each be shaped as a circle or an ellipse. However, in other embodiments, the first body portion 220A and the second body portion 220B may have any suitable shape (such as a rectangular, square, triangular or other polygonal shape). In an embodiment, the first body portion 220A and the second body portion 220B are congruent shapes arranged symmetrically about the dividing line 200. As shown in FIG. Figure 6 As shown, each of the first body portion 220A and the second body portion 220B can be shaped as a circle, and the branch portions 218A, 218B can be tangent to the corresponding circular body portion. For example, the first branch portion 218A can be tangent to the frontmost side of the first body portion 220A, and the second branch portion 218B can be tangent to the frontmost side of the second body portion 220B. In this way, the first body portion 220A and the second body portion 220B can extend axially behind the first branch portion 218A and the second branch portion 218B.

[0051] For example, at least one of the first sleeve portion 202 and the second sleeve portion 206 (such as both) includes tabs 228A, 228B (e.g., front tabs) defined between the stress relief opening 214 and the weld joint 210. Specifically, the first sleeve portion 202 may define a first tab 228A between the front stress relief opening 214 and the weld joint 210, and the second sleeve portion 206 may define a second tab 228B between the front stress relief opening 214 and the weld joint 210.

[0052] Each of the tabs 228A, 228B may extend axially from the end wall 230A, 230B at the first weld end 212 of the weld joint 210 to a base 232A, 232B (as shown in phantom) at the axial terminal end of the front stress relief opening 214. For example, the first tab 228A may extend (e.g., axially) from the first end wall 230A to the first base 232A, and the second tab 228B may extend (e.g., axially) from the second end wall 230B to the second base 220B. The first end wall 230A and the second end wall 230B may be substantially perpendicular to the split line 200 and may be aligned with each other (e.g., in the axial direction) such that the first end wall 230A and the second end wall 230B form a single continuous surface (which may be flush or without protrusions / protrusions).

[0053] In an exemplary embodiment, each of the tabs 228A, 228B may diverge in width as the tabs 228A, 228B extend axially from the respective end walls 230A, 230B at the first weld end 212 of the weld joint 210 to the base 232A, 232B. For example, each of the tabs 228A, 228B may define a first width 234 at the end walls 230A, 230B and a second width 236 at the base 232A, 232B. The first width 234 may be defined between the weld joint 210 and the front stress relief opening 214 (specifically, the body portions 220A, 220B) at the end walls 230A, 230B. The second width 236 may be defined between the weld joint 210 and the front stress relief opening 214 (specifically, the rear end of the body portions 220A, 220B) at the base 232A, 232B. The second width 236 may be greater than the first width 234 (such as 20% greater, or such as 50% greater). The width of each of the tabs 228A, 228B may increase from the first width 234 to the second width 236 as the tabs extend axially from the end walls 230A, 230B to the bases 232A, 232B.

[0054] like Figure 6 As shown, the slot portion 216 may have a uniform width 217 in the circumferential direction C of the gas turbine 10 between the front end 76 and the branch portions 218A, 218B. However, in some embodiments, such as Figure 7 As shown, the slot portion 216 may have a varying width between the front end 76 and the branch portions 218A, 218B. Figure 7 As shown, the groove portion 216 may include a first section 222 having a first width 223, a second section 224 having a second width 225 greater than the first width 223, and a tapered section 226 tapered between the second width 225 and the first width 223. The first section 222 may extend from the front end 76 to the tapered section 226 along the dividing line 200. The tapered section 226 may extend from the first section 222 to the second section 224 along the dividing line 200. The second section 224 may extend from the tapered section 226 to the branch portions 218A, 218B along the dividing line 200.

[0055] like Figure 6 and Figure 7As shown, in addition to the front stress relief opening 214, the exhaust diffuser assembly 100 may also include rear stress relief openings 270A, 270B at the rear end 78. The weld joint 210 may extend continuously along the split line 200 from the first weld end 212 to the rear end 272 of the weld joint 210. As shown, the first rear stress relief opening 270A may be defined in the first sleeve portion 202, and the second rear stress relief opening 270B may be defined in the second sleeve portion 206. The rear stress relief openings 270A, 270B may each define a rear tab 274A, 274B. The first rear tab 274A may be defined between the weld joint 210, the rear end 78, and the first rear stress relief opening 270A. Similarly, the second rear tab 274B may be defined between the weld joint 210, the rear end 78, and the second rear stress relief opening 270B. As the tabs extend axially, the rear stress relief openings 270A, 270B may each converge in width, which may advantageously reduce stress at the weld joint 210. In an exemplary embodiment, as shown, the rear stress relief openings 270A, 270B may be shaped as a semicircle or a semi-ellipse, but in other embodiments, the rear stress relief openings 270A, 270B may have other shapes.

[0056] Now refer to Figure 8 According to an embodiment of the present disclosure, a partition line 200 (which may be the above reference Figure 4 and Figure 5 108 or the outer dividing line 110) of the exhaust diffuser assembly 100. In particular, Figure 8 Can be a reference Figure 7 The same embodiment shown and described, but Figure 8 The embodiment shown in FIG. 2 includes a connection block 240 positioned in the slot portion 216 and coupled to the first sleeve portion 202 and the second sleeve portion 206 .

[0057] The connection block 240 may extend axially between a first (or front) end 242 and a second (or rear) end 244. The connection block 240 may be longest in the axial direction A, and the connection block 240 may extend within the slot 216 such that a first portion of the connection block 240 is disposed on a radially inward surface of the exhaust diffuser 34, and a second portion of the connection block 240 is disposed on a radially outward surface of the exhaust diffuser 34. For example, the connection block 240 may extend within the second section 224 of the slot 216 (and / or at least partially within the tapered section 226 in some embodiments). In addition, the connection block 240 may at least partially overlap one or more portions of the stress relief opening 214. For example, as shown, the connection block 240 may overlap (e.g., completely overlap) the second section 224 of the slot 216. In addition, the connection block 240 may at least partially overlap the main body portions 220A, 220B of the front stress relief opening 214.

[0058] like Figure 8 As shown, the connection block 240 may include a V-shaped opening at the second end 244. The V-shaped opening may be defined by a first sloping wall 248 and a second sloping wall 250, each of which may extend to a junction or apex 252 at which the first sloping wall 248 and the second sloping wall 250 are connected. In many embodiments, the apex 252, which is located at the peak of the curved interface between the first sloping wall 248 and the second sloping wall 250, may be located along the split line 200. The first sloping wall 248 and the second sloping wall 250 may be inclined relative to the axial direction A, the split line 200, and the wall from which the first sloping wall 248 and the second sloping wall 250 extend. The apex 252 may be axially spaced from the end walls 230A, 230B, which advantageously allows the weld joint 210 to be accessed and welded upward from the rear end 78 to the first weld end 212 without having to disconnect the connection block 240. Additionally, as will be discussed in greater detail below, a locating pin 254 may extend through the connection block 240 and through the second sleeve portion 206 to couple the connection block 240 with the second sleeve portion 206 and to align the connection block 240 within the slot portion 216 .

[0059] See now Fig. 9, a cross-sectional view of the exhaust diffuser assembly 100 taken along line 9-9 is shown according to an embodiment of the present disclosure. As shown, the connection block 240 may include a first wall 256 disposed on (e.g., in contact with) a first outer side 255 of the first sleeve portion 202 and a second outer side 259 of the second sleeve portion 206. In addition, the connection block 240 may include a second wall 258 disposed on (e.g., in contact with) a first inner side 257 of the first sleeve portion 202 and a second inner side 261 of the second sleeve portion 206. In addition, the connection block 240 may include a crossbar 260 extending through the slot 216. In particular, the crossbar 260 may extend from the first wall 256 through the second section 224 of the slot 216 to the second wall 258, thereby providing the connection block 240 with a generally H-shaped cross section. The first wall 256 and the second wall 258 may be generally perpendicular to the crossbar 260. In addition, as shown, the locating pin 254 may extend through the first wall 256, the second sleeve portion 206, and the second wall 258. The locating pin 254 may extend completely through the first wall 256 and / or the second wall 258, such that the respective terminal ends of the locating pin 254 extend outwardly from at least one of the first wall 256 and the second wall 258. Alternatively, the locating pin 254 may extend partially through the first wall 256 and the second wall 258 (i.e., the locating pin 254 may terminate within the first wall 256 and the second wall 258). In many embodiments, the locating pin 254 may be welded to the connecting block 240 at one or both ends. For example, the locating pin 254 may be welded to the second wall 258 of the connecting block 240 via a weld joint 280 (which may be annular around the locating pin 254). In addition, as shown in FIG. Fig. 9 As shown, the locating pin 254 may include an angled end 282 that is flush with the arcuate outer wall 268, which improves the aerodynamic efficiency of the connection block 240. The angled end 282 may be ground flush with the arcuate outer wall 260 (eg, using a grinder or other device).

[0060] In an exemplary embodiment, as shown, the connection block 240 may define a first channel 262 and a second channel 264. The first channel 262 may be defined between the first wall 256 and the second wall 258 on a first side of the crossbar 260. The second channel 264 may be defined between the first wall 256 and the second wall 258 on a second side of the crossbar 260. Each of the first channel 262 and the second channel 264 has a U-shaped cross section. The first sleeve portion 202 may extend into the first channel 262, and the second sleeve portion 206 may extend into the second channel 264.

[0061] The second wall 258 of the connection block 240 may be positioned within the exhaust gas flow (eg, as described above with reference to Figure 2In such an embodiment, the second wall 258 may include a curved outer wall 268, which may include a first tapered side and a second tapered side that each extend to an apex. The curved outer wall 268 may advantageously improve the aerodynamic efficiency of the exhaust diffuser 34 by preventing flow vortices that may otherwise be caused by objects in the exhaust flow channel 52.

[0062] This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any 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 those skilled in the art. If these other examples include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ substantially from the literal language of the claims, these other examples are intended to be within the scope of the claims.

[0063] Further aspects of the invention are provided by the subject matter of the following clauses:

[0064] An exhaust diffuser assembly comprises: at least two diffuser sections, which are connected to each other and together form an exhaust diffuser extending from a front end to a rear end, and the at least two diffuser sections include: a first diffuser section of the at least two diffuser sections, the first diffuser section having a first sleeve portion extending to a first circumferential edge; and a second diffuser section, the second diffuser section having a second sleeve portion extending to a second circumferential edge, the first circumferential edge being joined to the second circumferential edge at a dividing line; wherein a weld joint extends along a portion of the dividing line to a weld end, and wherein the first sleeve portion and the second sleeve portion define a stress relief opening at least partially disposed at the weld end of the weld joint.

[0065] An exhaust diffuser assembly according to any of the preceding clauses, wherein at least one of the first sleeve portion and the second sleeve portion includes a tab defined between the stress relief opening and the weld joint; and wherein the tab diverges in width as the tab extends axially from an end wall at the weld end of the weld joint to a base of the tab.

[0066] An exhaust diffuser assembly according to any of the preceding clauses, wherein the weld end is a first weld end disposed between the front end and the rear end of the exhaust diffuser; and wherein the stress relief opening comprises a slot portion extending along the split line from the front end of the exhaust diffuser to the first weld end.

[0067] An exhaust diffuser assembly as described in any preceding clause, wherein the stress relief opening further comprises a body portion spaced apart from the weld joint and extending axially alongside the first weld end of the weld joint.

[0068] An exhaust diffuser assembly as described in any preceding clause, wherein the body portion comprises a symmetrical circular shape.

[0069] An exhaust diffuser assembly according to any preceding clause, wherein the body portion comprises one of a circular shape or an oval shape.

[0070] An exhaust diffuser assembly as described in any preceding clause, wherein the slot portion comprises a first section having a first width and a second section having a second width, the second width being greater than the first width.

[0071] An exhaust diffuser assembly as described in any preceding clause, wherein the first circumferential edge and the second circumferential edge are spaced apart from one another to define the slot portion.

[0072] The exhaust diffuser assembly of any preceding clause, further comprising a connection block disposed in the slot portion and coupled to the first sleeve portion and the second sleeve portion.

[0073] According to the exhaust diffuser assembly described in any of the preceding clauses, the connecting block includes a first wall arranged on a first outer side of the first sleeve part and a second outer side of the second sleeve, a cross bar extending through the groove, and a second wall arranged on a first inner side of the first sleeve part and a second inner side of the second sleeve part.

[0074] An exhaust diffuser assembly as claimed in any preceding clause, wherein the connection block defines a first passage and a second passage, wherein the first sleeve portion extends into the first passage, and wherein the second sleeve portion extends into the second passage.

[0075] An exhaust diffuser assembly according to any preceding clause, wherein the stress relief opening is a first stress relief opening; wherein the weld joint extends to a second weld end at the rear end of the exhaust diffuser; and wherein a second stress relief opening is disposed at the rear end of the exhaust diffuser proximate to the second weld end.

[0076] The exhaust diffuser assembly of any preceding clause, wherein the second stress relief opening comprises a part-circular shape.

[0077] The exhaust diffuser assembly of any preceding clause, wherein the second stress relief opening comprises a semi-circular shape or a semi-stadium shape.

[0078] A gas turbine, the gas turbine comprising: a compressor section; a combustion section, the combustion section being located downstream of the compressor section; a turbine section, the turbine section being located downstream of the combustion section; and an exhaust diffuser assembly, the exhaust diffuser assembly having an exhaust diffuser located downstream of the turbine section, the exhaust diffuser assembly comprising: at least two diffuser sections that are coupled to each other and together form an exhaust diffuser extending from a front end to a rear end, the at least two diffuser sections comprising: a first diffuser section of the at least two diffuser sections, the first diffuser section having a first sleeve portion extending to a first circumferential edge; and a second diffuser section, the second diffuser section having a second sleeve portion extending to a second circumferential edge, the first circumferential edge being joined to the second circumferential edge at a split line; wherein the weld joint extends along a portion of the split line to a weld end, and wherein the first sleeve portion and the second sleeve portion define a stress relief opening at least partially disposed at the weld end of the weld joint.

[0079] A gas turbine according to any of the preceding clauses, wherein at least one of the first sleeve portion and the second sleeve portion includes a tab defined between the stress relief opening and the weld joint; and wherein the tab diverges in width as the tab extends axially from an end wall at the weld end of the weld joint to a base of the tab.

[0080] A gas turbine according to any preceding clause, wherein the weld end is a first weld end disposed between the front end and the rear end of the exhaust diffuser; and wherein the stress relief opening comprises a groove portion extending along the dividing line from the front end of the exhaust diffuser to the first weld end.

[0081] A gas turbine according to any preceding clause, wherein the stress relief opening further comprises a body portion spaced apart from the weld joint and extending axially alongside the first weld end of the weld joint.

[0082] A gas turbine according to any preceding clause, wherein the slot portion comprises a first section having a first width and a second section having a second width, the second width being greater than the first width.

[0083] A gas turbine according to any preceding clause, wherein the first circumferential edge and the second circumferential edge are spaced apart from each other to define the slot portion.

[0084] A gas turbine according to any preceding clause, further comprising a connection block disposed in the slot portion and coupled to the first sleeve portion and the second sleeve portion.

[0085] According to a gas turbine described in any of the preceding clauses, the connecting block includes a first wall arranged on a first outer side of the first sleeve part and a second outer side of the second sleeve, a cross bar extending through the groove, and a second wall arranged on a first inner side of the first sleeve part and a second inner side of the second sleeve part.

[0086] A gas turbine according to any preceding clause, wherein the connection block defines a first passage and a second passage, wherein the first sleeve portion extends into the first passage, and wherein the second sleeve portion extends into the second passage.

[0087] A gas turbine according to any preceding clause, wherein the stress relief opening is a first stress relief opening; wherein the weld joint extends to a second weld end at the rear end of the exhaust diffuser; and wherein a second stress relief opening is arranged at the rear end of the exhaust diffuser near the second weld end.

Claims

1. An exhaust diffuser assembly (100), comprising: At least two diffuser sections (102A, 102B) are coupled to each other and together form an exhaust diffuser (34) extending from a front end (76) to a rear end (78), the at least two diffuser sections (102A, 102B) comprising: a first diffuser section (102A) having a first sleeve portion (202) extending to a first circumferential edge (207); and a second diffuser section (102B) having a second sleeve portion (206) extending to a second circumferential edge (208), the first circumferential edge (207) being joined to the second circumferential edge (208) at a split line (200); The weld joint (210) extends along a portion of the split line (200) to a weld end (212, 272), and the first sleeve portion (206) and the second sleeve portion (208) define a stress relief opening (214, 270A, 270B) at least partially disposed at the weld end (212, 272) of the weld joint (210).

2. The exhaust diffuser assembly (100) of claim 1, wherein at least one of the first sleeve portion (206) and the second sleeve portion (208) includes a tab (228A, 228B) defined between the stress relief opening (214) and the weld joint (210); and Wherein the tabs (228A, 228B) diverge in width as the tabs (228A, 228B) extend axially from the end walls (230A, 230B) at the weld end (212) of the weld joint (210) to the bases (232A, 232B) of the tabs (228A, 228B).

3. The exhaust diffuser assembly (100) of claim 1, wherein the weld end (212, 272) is a first weld end (212) disposed between the front end (76) and the rear end (78) of the exhaust diffuser (34); and wherein the stress relief opening (214) includes a groove portion (216) extending along the split line (200) from the front end (76) of the exhaust diffuser (34) to the first weld end (212).

4. The exhaust diffuser assembly (100) of claim 3, wherein the stress relief opening (214) further comprises a body portion (220A, 220B) spaced apart from the weld joint (210) and extending axially alongside the first weld end (212) of the weld joint (210).

5. The exhaust diffuser assembly (100) of claim 3, wherein the slot portion (216) includes a first section (222) having a first width (223) and a second section (224) having a second width (225), the second width (225) being greater than the first width (223).

6. The exhaust diffuser assembly (100) of claim 3, wherein the first circumferential edge (207) and the second circumferential edge (208) are spaced apart from one another to define the slot portion (216).

7. The exhaust diffuser assembly (100) of claim 3, further comprising a connection block (240) disposed in the slot portion (216) and coupled to the first sleeve portion (202) and the second sleeve portion (206).

8. The exhaust diffuser assembly (100) according to claim 7, wherein the connecting block (240) includes a first wall (256) disposed on a first outer side (255) of the first sleeve portion (202) and a second outer side (259) of the second sleeve portion (206), a cross bar (260) extending through the groove portion (216), and a second wall (258) disposed on a first inner side (257) of the first sleeve portion (202) and a second inner side (261) of the second sleeve portion (206).

9. The exhaust diffuser assembly (100) of claim 7, wherein the connection block (240) defines a first channel (262) and a second channel (264), wherein the first sleeve portion (202) extends into the first channel (262), and wherein the second sleeve portion (206) extends into the second channel (264).

10. The exhaust diffuser assembly (100) of claim 7, wherein the stress relief opening (214) is a first stress relief opening; wherein the weld joint (210) extends to a second weld end (272) at the rear end (78) of the exhaust diffuser (34); and wherein a second stress relief opening (270A, 270B) is disposed at the rear end (78) of the exhaust diffuser (34) proximate to the second weld end (272).

11. A gas turbine (10), comprising: Compressor section (12); a combustion section (18) located downstream of the compressor section (12); a turbine section (22) located downstream of the combustion section (18); as well as An exhaust diffuser assembly (100) according to any one of claims 1 to 10.

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