Sleeve assembly and method for manufacturing the same

Abstract

To provide sleeve assemblies for use with a combustor.SOLUTION: A sleeve assembly (120) for a combustion system includes a first duct (148) including a first circumferential surface (168) and a second duct (146) including a second circumferential surface (163). The first circumferential surface (168) radially overlaps the second circumferential surface (163) such that the first duct (148) and the second duct (146) collectively define a continuous combustion chamber therein. The continuous combustion chamber is configured to receive high temperature gases flowing therethrough. The sleeve assembly (120) further includes a wear insert (166) removably coupled to the first circumferential surface (168) and extending radially from the first circumferential surface (168) to engage the second circumferential surface (163).SELECTED DRAWING: Figure 3

Description

Technical Field

[0001] The field of the present disclosure generally relates to sleeve assemblies, and more particularly to sleeve assemblies for use with combustors.

Background Art

[0002] At least some known turbine assemblies include a compressor, a combustor, and a turbine coupled together in a series flow arrangement. The gas flowing into the compressor is compressed and discharged into the combustor, where it is mixed with fuel. The resulting mixture is ignited to produce combustion gases, which are sent from the combustor through the turbine. The gas drives the turbine, which can then supply power to a generator coupled to the turbine.

[0003] At least some known combustors include a sleeve assembly that includes a liner and a transition duct that collectively define a combustion chamber, in which a mixture of fuel and compressed gas is ignited before being supplied to a turbine coupled to the transition duct. Known sleeve assemblies generally allow for axial movement between the transition duct and the liner relative to each other to accommodate thermal expansion / movement during operation. As a result, at least some such assemblies may be prone to wear at the interface defined between the liner and the transition duct.

[0004] To reduce the impact of movement within the sleeve assembly, at least some known sleeve assemblies include an anti-friction wear coating applied to the transition duct and / or the liner. More specifically, at least some known wear coatings are applied in the form of a spray coating. However, applying these spray coatings generally requires a fair amount of preparation of the surface to be coated prior to the application of the spray coating. Further, if maintenance is required on either the liner or the transition duct, the coating needs to be manually removed before a new wear coating can be applied. Removing such coatings can be a time-consuming and laborious task.

[0005] Accordingly, it would be desirable to provide a sleeve assembly that enables a more simple and robust, and more easily replaceable, wear insert. SUMMARY OF THE INVENTION

[0006] In one aspect, a sleeve assembly for a combustion system is provided. The sleeve assembly includes a first duct including a first circumferential surface and a second duct including a second circumferential surface. The first circumferential surface radially overlaps the second circumferential surface such that the first duct and the second duct collectively define an interior continuous combustion chamber. The continuous combustion chamber is configured to receive high temperature gases flowing therethrough. The sleeve assembly further includes a wear insert removably coupled to the first circumferential surface and extending radially from the first circumferential surface to engage the second circumferential surface.

[0007] In another aspect, a turbine assembly is provided. The turbine assembly includes a compressor section, a turbine section coupled downstream of the compressor section, and a combustor. The combustor includes a plurality of cans coupled in fluid communication between the compressor section and the turbine section. The first can of the plurality of cans includes a sleeve assembly. The sleeve assembly includes a first duct including a first circumferential surface and a second duct including a second circumferential surface. The first circumferential surface radially overlaps the second circumferential surface such that the first duct and the second duct collectively define an internal continuous combustion chamber. The continuous combustion chamber is configured to receive the high-temperature gas flowing therethrough. The sleeve assembly further includes a wear insert removably coupled to the first circumferential surface and extending radially from the first circumferential surface to engage the second circumferential surface.

[0008] In yet another aspect, a method of assembling a sleeve assembly for a combustion system is provided. The method includes providing a first duct including a first circumferential surface. The method also includes removably coupling a wear insert to the first circumferential surface. The method further includes positioning a second duct including a second circumferential surface adjacent to the first duct such that the first circumferential surface radially overlaps the second circumferential surface and the wear insert engages the second circumferential surface. The first duct and the second duct collectively define an internal continuous combustion chamber configured to receive the high-temperature gas flowing therethrough.

Brief Description of the Drawings

[0009]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

[0010] Unless otherwise specified, the drawings provided herein are meant to illustrate features of embodiments of the present disclosure. These features are considered to be applicable to a variety of systems that include one or more embodiments of the present disclosure. Accordingly, the drawings are not meant to include all conventional features known to those skilled in the art that are necessary for the practice of the embodiments disclosed herein.

DETAILED DESCRIPTION OF THE INVENTION

[0011] The exemplary systems and methods described herein overcome at least some of the drawbacks of known sleeve assemblies by providing a wear insert removably coupled to at least one duct of the sleeve assembly and facilitating a reduction in friction resistance at a slide interface within the sleeve assembly. More specifically, embodiments described herein include a first duct having a first circumferential surface, a second duct having a second circumferential surface, and a wear insert extending circumferentially between the two duct surfaces. More specifically, the first circumferential surface radially overlaps the second circumferential surface such that the first and second ducts collectively define an internal continuous combustion chamber. In one embodiment, the wear insert is removably coupled to the first circumferential surface and extends radially from the first circumferential surface to engage the second circumferential surface. In some embodiments, the wear insert is a single-piece integral structure. In some embodiments, the first duct includes a groove recessed radially from the first circumferential surface, and the wear insert is seated within the groove.

[0012] Unless otherwise specified, words expressing approximation such as "generally", "substantially", and "approximately" as used herein indicate that the term so modified may be applied only to the extent recognized by those skilled in the art, not to an absolute or complete degree. Thus, values modified by terms such as "approximately", "about", and "substantially" are not limited to the exact values specified. In at least some instances, words expressing approximation can correspond to the accuracy of the equipment for measuring the value. Here, and throughout the specification and claims, the limits of a range may be specified. Such ranges are combinable and / or replaceable and include all sub-ranges included herein unless the context or language specifically indicates otherwise. Additionally, unless otherwise specified, terms such as "first", "second", etc. are used herein merely as labels and are not intended to impose an order, position, or hierarchical requirement on the items they refer to. Further, for example, a reference to a "second" item does not require, or exclude, the presence of a "first" or smaller numbered item, or a "third" or larger numbered item.

[0013] FIG. 1 is a schematic view of an exemplary turbine assembly 100. In an exemplary embodiment, the turbine assembly 100 is an industrial gas turbine assembly including a compressor section 102, a combustor section 104, and a turbine section 106 coupled in series flow communication with each other within a casing 108 along a centerline axis 110. During operation, working gas 112 flows into the compressor section 102, where it is compressed and then sent into the combustor section 104. The compressed gas 114 is mixed with fuel (not shown) and ignited in the combustor section 104 to generate combustion gas 115, which is sent through the turbine section 106 and then discharged from the turbine section 106 as exhaust gas 116.

[0014] In an exemplary embodiment, the combustor section 104 includes a plurality of combustion cans 118. Each combustion can 118 has a sleeve assembly 120 that defines a combustion chamber 122. A fuel delivery system 124 is coupled to each combustion can 118 and includes a fuel injector 126 located at the front end of the combustion can 118. A mixture of fuel and compressed gas is axially injected into the combustion chamber 122 through the fuel injector 126.

[0015] FIG. 2 is a schematic view of an exemplary sleeve assembly 120 that can be used with the turbine assembly 100. In an exemplary embodiment, the sleeve assembly 120 has a front end 134 coupled to the compressor discharge casing 101 (shown in FIG. 1) and an opposite rear end 136 fluidly coupled to the nozzle 109 (shown in FIG. 1) of the turbine section 106. The sleeve assembly 120 defines a combustion chamber 122 between the front end 134 and the rear end 136, respectively.

[0016] In an exemplary embodiment, a crossfire tube 138 is coupled to the sleeve assembly 120. The crossfire tube 138 is coupled to the sleeve assembly 120 such that the tube 138 extends into the combustion zone 140 of the combustion chamber 122. In an alternative embodiment, the crossfire tube 138 can extend into any other zone defined within the combustion chamber 122. In an exemplary embodiment, during operation of the turbine assembly 100, a mixture of fuel and compressed gas is injected into the combustion chamber 122 through the fuel injector 126. The mixture is ignited in the combustion zone 140 of the combustion chamber 122, thereby generating combustion gases 115 that flow through the turbine section 106 (shown in FIG. 1).

[0017] In an exemplary embodiment, the sleeve assembly 120 extends axially 142 and circumferentially 144 within the combustion chamber 122. As used herein, the term "axial" (or any variation thereof) refers to a dimension that extends along the center of any suitable shape (e.g., square, rectangle, triangle, etc.) and is not limited to a dimension that extends along the center of a circular shape. Similarly, as used herein, the term "radial" (or any variation thereof) refers to a dimension that extends outward from the center of any suitable shape (e.g., square, rectangle, triangle, etc.) and is not limited to a dimension that extends outward from the center of a circular shape. Additionally, as used herein, the term "circumferential" (or any variation thereof) refers to a dimension that extends around the center of any suitable shape (e.g., square, rectangle, triangle, etc.) and is not limited to a dimension that extends around the center of a circular shape.

[0018] In an exemplary embodiment, the sleeve assembly 120 includes a transition duct 148, or more generally, a first duct, and a liner 146, or more generally, a second duct. In an exemplary embodiment, the transition duct 148 has a unitary structure of a single piece and includes an outer surface 150 that extends from a front end 152 adjacent to the liner 146 to an opposite rear end 154. In particular, in an exemplary embodiment, the transition duct 148 is positioned to circumscribe at least a portion of the liner 146. In an alternative embodiment, the liner 146 is positioned to circumscribe at least a portion of the transition duct 148. In another alternative embodiment, the transition duct 148 is manufactured using any other suitable process and may include any suitable number of components that enable the sleeve assembly 120 to function as described herein (e.g., the transition duct 148 may not have a unitary structure of a single piece). The transition duct 148 may have any suitable level of rigidity or flexibility.

[0019] In an exemplary embodiment, the liner 146 is a single-piece integral structure having a front end 156, an adjacent fuel injector 126, and a rear end (not shown) sized to be received within the transition duct 148. In an exemplary embodiment, the liner 146 includes a body 158, and the body 158 has an outer surface 160 and a seal 162 coupled to the outer surface 160 and extending axially from the body 158 into the transition duct 148. In an exemplary embodiment, the liner 146 is generally cylindrical. In an alternative embodiment, the liner 146 may be any other shape that enables the liner 146 to function as described herein.

[0020] FIG. 3 is a schematic exploded view of a portion of the sleeve assembly 120 shown in FIG. 2. FIG. 4 is a schematic cross-sectional view of a portion of the sleeve assembly 120 shown in FIG. 3. In an exemplary embodiment, the transition duct 148 is coupled to the liner 146 via an interface assembly 164. The interface assembly 164 includes a seal 162 and an insert 166 sized to contact the seal 162 directly when the transition duct 148 is coupled to the liner 146. More specifically, in an exemplary embodiment, the seal 162 is fixedly secured to the outer surface 160 of the liner 146 such that the seal extends axially into the transition duct 148. In an alternative embodiment, the seal 162 extends axially between the liner 146 and the transition duct 148 in any manner that enables the sleeve assembly 120 to function as described herein. For example, without limitation, in some alternative embodiments, the seal 162 may be integrally formed with the liner 146 or the transition duct 148. In an exemplary embodiment, the seal 162 slidably engages the transition duct 148 and permits relative axial movement and / or expansion (e.g., due to thermal expansion during operation) of the liner 146 and / or the other of the transition duct 148. In each embodiment, the seal 162 facilitates coupling the liner 146 to the transition duct 148 in any manner that enables the sleeve assembly 120 to function as described herein.

[0021] In an exemplary embodiment, the transition duct 148 includes an inner surface 168 (or more broadly, a first circumferential surface) that defines an internal cavity 170 of the transition duct 148 sized and oriented to receive combustion gas 115 (shown in FIG. 2) from the liner 146. In an alternative embodiment, the sleeve assembly 120 includes one or more inner sleeves (not shown), the inner sleeves being used to convey the combustion gas 115 (shown in FIG. 2) and defining one or more cooling paths (not shown) that extend between the transition duct 148 and the liner 146 (e.g., radially outward from the inner sleeve). For example, in some such embodiments, a cooling flow (not shown) flows through one or more cooling paths (not shown) to facilitate cooling of the inner surface 168, and the combustion gas 115 (shown in FIG. 2) does not contact the inner surface 168 of the transition duct 148.

[0022] In an exemplary embodiment, when the liner 146 is coupled to the transition duct 148 (e.g., as shown in FIG. 4), the seal 162 is sized in axial length such that the seal 162 extends axially between the liner 146 and the transition duct 148 and radially overlaps at least a portion of the inner surface 168 of the transition duct 148. In an alternative embodiment, the seal 162 is fixedly secured to be fixable to the transition duct 148 and extends axially to radially overlap a portion of the outer surface 160 of the liner 146. In an exemplary embodiment, the seal 162 is a spring seal, or more specifically, a fla-seal. The seal 162 provides a substantially airtight seal at the interface defined between the liner 146 and the transition duct 148. The seal 162 includes a plurality of axially extending slits 172 defined therein and circumferentially spaced around the seal 162. The slits 172 allow for contraction and expansion of the seal 162 such that when the transition duct 148 is coupled to the liner 146, the transition duct 148 engages the seal 162 to compress the seal 162, thereby squeezing or sealing the slits 172 to provide the airtight seal 162. More specifically, in an exemplary embodiment, the insert 166 compresses the seal 162 when the liner 146 is coupled to the transition duct 148. In an exemplary embodiment, the seal 162 is a fla-seal 162. In an alternative embodiment, the seal 162 is any other seal that allows the sleeve assembly 120 to function as described herein.

[0023] Referring to FIG. 4, in an exemplary embodiment, the insert 166 is fixedly secured to the inner surface 168 and extends radially from the inner surface 168 to engage the outer surface 163 (or more generally, the second circumferential surface) of the seal 162, facilitating wear protection to the operating transition duct 148 and the seal 162. As shown in FIG. 4, the insert 166 is enlarged for purposes of clarity. In particular, in an exemplary embodiment, the insert 166 extends radially a height H 1 from the inner surface 168 of the transition duct 148, which in an exemplary embodiment is from approximately 1 / 1000 inch to approximately 1 / 10 inch. More specifically, in an exemplary embodiment, H1 is generally approximately 10 / 1000 inch to approximately 15 / 1000 inch. In an alternative embodiment, the height H of the insert 166 1 can be any size that allows the sleeve assembly 120 to function as described herein.

[0024] In an exemplary embodiment, the insert 166 is a one-piece integral structure that extends circumferentially around the inner surface 168 of the transition duct 148. The insert 166 has an axial length L 1 extending thereto. The length L 1 is selected to be sufficient to shield (i.e., directly inhibit) the inner surface 168 from the seal 162 such that during operation, the seal 162 contacts the insert 166 directly and does not contact the inner surface 168 of the transition duct 148 directly. In particular, during operation, the sliding contact between the seal 162 and the inner surface 168 of the transition duct 148 can occur as a result of at least one of the expansion and / or movement of the liner 146 or the transition duct 148 relative to each other. Such sliding contact may result in wear (i.e., material degradation) of the inner surface 168 over time. In an exemplary embodiment, the seal 162 contacts the insert 166 in a sliding manner and does not contact the inner surface 168 of the transition duct 148. In other words, in an exemplary embodiment, the insert 166, rather than the transition duct 148, is subject to wear resulting from frictional contact between the liner 146 and the transition duct 148. In an alternative embodiment, for example, as described above, when the seal 162 is fixedly coupled to the transition duct 148, the insert 166 is coupled to the inner surface 174 of the liner 146 and extends radially between the inner surface 174 and the seal 162. In yet a further alternative embodiment, the insert 166 can be coupled to either the liner 146 or the transition duct 148 in any other manner that allows the sleeve assembly 120 to function as described herein.

[0025] In an exemplary embodiment, the insert 166 is fixedly secured to the inner surface 168 of the transition duct 148 such that it can be fixed via a plurality of weld joints 176. More specifically, the insert 166 is spot welded to the inner surface 168 via the weld joints 176 along a first radial edge 178 of the insert 166 and along a second radial edge 180. In an exemplary embodiment, the weld joints 176 are disposed substantially equidistantly around the circumference of the insert 166 along the first radial edge 178 and along the second radial edge 180. In an alternative embodiment, the insert 166 is fixedly secured to the inner surface 168 in any manner that enables the sleeve assembly 120 to function as described herein. For example, without limitation, in some alternative embodiments, the transition duct 148 includes at least one opening (not shown) defined therein that extends between the inner surface 168 and the outer surface 182 of the transition duct 148 (e.g., by drilling a hole radially through the transition duct 148). In such an embodiment, the insert 166 is welded to the transition duct 148 via the at least one opening.

[0026] In an exemplary embodiment, the weld joints 176 enable the insert 166 to be easily removed from the inner surface 168 as a single-piece unit (i.e., the insert 166 can be removed and remain substantially intact as a single unit). For example, in contrast to other known sleeve assemblies that use spray-on wear coatings, in an exemplary embodiment, during maintenance operations, for example, to replace the insert 166, an operator can easily remove the insert 166 from the inner surface 168 by simply cutting the weld joints 176.

[0027] FIG. 5 is a partial cross-sectional view of an alternative sleeve assembly 320 for use with a turbine assembly 100 (shown in FIG. 1). In an exemplary embodiment, sleeve assembly 320 is substantially the same as sleeve assembly 120 described above with respect to FIGS. 1-4, except as described below. More specifically, in an exemplary embodiment, the transition duct 348 of sleeve assembly 120 defines a groove 384 that is radially recessed with respect to the inner surface 368 of transition duct 348. More specifically, in an exemplary embodiment, groove 384 is recessed with respect to inner surface 368 and is positioned radially outward from inner surface 368. In an alternative embodiment, groove 384 is defined on seal 362 and / or liner 346 and is recessed radially inward.

[0028] In an exemplary embodiment, insert 366 is received within groove 384. Insert 366 is substantially the same as insert 166 described above with respect to FIGS. 3 and 4, except as described below. More specifically, in an exemplary embodiment, insert 366 extends from groove 384 to a height H that is substantially the same as that of insert 166 (shown in FIG. 4) radially inward (i.e., upward) of inner surface 368. 1 In other words, in an exemplary embodiment, insert 366 extends to a greater overall radial height H than the overall radial height H of insert 166 and extends radially inward from inner surface 368. In an exemplary embodiment, groove 384 is sized such that insert 366 engages seal 362 when insert 366 is seated within groove 384. In an alternative embodiment, groove 384 and insert 366 are sized in any manner that allows sleeve assembly 320 to function as described herein. 1 greater than that shown by 2 and extends radially inward from inner surface 368. In an exemplary embodiment, groove 384 is sized such that insert 366 engages seal 362 when insert 366 is seated within groove 384. In an alternative embodiment, groove 384 and insert 366 are sized in any manner that allows sleeve assembly 320 to function as described herein.

[0029] In an exemplary embodiment, the insert 366 is coupled to the transition duct 348 via the groove 384. More specifically, unlike the sleeve assembly 120 described above with respect to FIGS. 1-4, in the exemplary embodiment, the insert 366 is not welded to the transition duct 348. Rather, in the exemplary embodiment, the groove 384 includes a first radially sidewall 386 and a second radially sidewall 388. The first radially sidewall 386 engages the first radially edge 378 of the insert 366, and the second radially sidewall 388 engages the second radially edge 380 of the insert 366, thereby inhibiting axial movement of the inner insert 366 when the insert 466 is received within the groove 384. Further, in the exemplary embodiment, the seal 362 applies a radially outward force to the insert 366 when the liner 346 is coupled to the transition duct 348 such that the seal 362 secures the insert 366 within the groove 384. As a result, in the exemplary embodiment, the insert 366 is secured in a predetermined position on the transition duct 348 without a fixable coupling (e.g., the welded joint 176 shown in FIG. 4) and can be easily removed and replaced, for example, during maintenance operations. In an alternative embodiment, the insert 366 is coupled to the transition duct 348 in any manner that allows the sleeve assembly 320 to function as described herein. For example, without limitation, in some alternative embodiments, the insert 366 is welded to the transition duct 348 after the insert 366 is seated in the groove 384. In a further alternative embodiment, one of the insert 366 and the groove 384 includes engagement features (e.g., a latch and a catch) to facilitate releasably coupling the insert 366 to the transition duct 348.

[0030] FIG. 6 is a flow diagram of an exemplary method of assembling a sleeve assembly 120 (shown in FIG. 2). Method 400 includes providing 402 a first duct (e.g., transition duct 148 shown in FIG. 4) that includes a first circumferential surface (e.g., inner surface 168 shown in FIG. 4). The method further includes removably coupling 404 a wear insert surface (e.g., insert 166 shown in FIG. 4) to the first circumferential surface. The method also includes positioning 406 a second duct (e.g., liner 146 shown in FIG. 4) that includes a second circumferential surface adjacent to the first duct such that the first circumferential surface radially overlaps a second circumferential surface (e.g., outer surface 163 shown in FIG. 4) and the wear insert engages the second circumferential surface, where the first duct and the second duct collectively define internally a continuous combustion chamber (e.g., combustion chamber 122 shown in FIG. 2) configured to receive high temperature gas (e.g., combustion gas 115 shown in FIG. 2) flowing therethrough.

[0031] The sleeve assembly described above allows for thermal expansion / movement between ducts of a combustor while at the same time allowing such ducts to be more easily serviced. In particular, the sleeve assembly described above includes a wear insert removably coupled to at least one duct of the sleeve assembly and facilitating a reduction in frictional wear at a slide interface within the sleeve assembly. The wear insert is removably coupled to a first circumferential surface of the first duct and extends radially to a second circumferential surface of the second duct. In some embodiments, the wear insert is removably coupled to the first duct via a plurality of weld joints. In other embodiments, the first duct defines a groove internally and the wear insert is seated in the groove. As a result, the sleeve assembly inhibits wear at the surfaces of the first and second ducts during operation of the turbine assembly. Rather, the wear insert absorbs material wear resulting from a sliding movement of one of the first and second ducts relative to the other.

[0032] Furthermore, unlike some known sleeve assemblies that may include spray-on wear coatings that must be removed and replaced over time, the wear inserts of the sleeve assemblies described above can be easily replaced by an operator as needed. For example, to remove the wear insert of the sleeve assembly described above that includes a welded joint coupling the wear insert to the first duct, the operator can remove the wear insert simply by severing the welded joint. Additionally, to remove the wear insert of the sleeve assembly described above that includes a groove sized to receive the wear insert, the operator can manually remove the wear insert from the groove. Accordingly, the sleeve assembly reduces the time and cost required to repair and maintain the sleeve assembly.

[0033] Exemplary technical effects of the methods, systems, and apparatuses described herein include at least one of (a) improved durability of the sleeve assembly, (b) reduced maintenance time required for repair of the sleeve assembly, (c) reduced material costs when assembling the sleeve assembly, and (d) improved lifespan of the sleeve assembly.

[0034] Exemplary embodiments of a sleeve assembly for a turbine assembly, and a method of assembling the sleeve assembly, have been described in detail above. The sleeve assembly is not limited to the specific embodiments described herein; rather, the elements of the sleeve assembly can be utilized separately and independently of the other elements described herein. For example, the elements of the sleeve assembly may also be used in combination with other turbine assemblies and are not limited to practice only with industrial gas turbine assemblies as described herein. Rather, the exemplary embodiments can be implemented and utilized in connection with many other turbine assembly applications.

[0035] The specific features of the various embodiments are shown in some of the drawings and may not be shown in others, but this is merely for convenience. Further, the reference to "one embodiment" in the above description is not intended to exclude the existence of additional embodiments incorporating the described features. According to the principles of the present disclosure, any feature in any drawing can be referenced and / or claimed in combination with any feature in any other drawing.

[0036] This specification uses several examples, including the best mode, to enable those skilled in the art to practice the present disclosure, which includes the fabrication and use of any device or system and the implementation of any related method. The patentable scope of the present disclosure is defined by the claims and can include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have 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.

Description of Reference Numerals

[0037] 100 Turbine assembly 101 Compressor discharge casing 102 Compressor section 104 Combustor section, combustor 106 Turbine section 108 Casing 109 Nozzle 110 Centerline axis 112 Working gas 114 Compressed gas 115 Combustion gas 116 Exhaust gas 118 Combustion can 120 Sleeve assembly 122 Combustion chamber 124 Fuel delivery system 126 Fuel injector 134 Front end 136 Rear end 138 Crossfire tube 140 Combustion zone 142 Axial direction 144 Circumferential direction 146 Liner / Second duct 148 Transition duct / First duct 150 Outer surface 152 Front end 154 Rear end 156 Front end 158 Body 160 Outer surface 162 Hermetic seal / Flange seal 163 Outer surface / Second circumferential surface 164 Interface assembly 166 Insert / Wear insert 168 Inner surface / First circumferential surface 170 Internal cavity 172 Slit 174 Inner surface 176 Weld joint 178 First radial edge 180 Second radial edge 182 Outer surface 320 Sleeve assembly 346 Liner 348 Transition duct 362 Seal 366 Insert 368 Inner surface 378 First radial edge 380 Second radial edge 384 Groove 386 First radial side wall / First radial surface 388 Second radial side wall / Second radial surface 400 Method 402 Step 404 Step 406 Step H 1 Radial height H 2 Radial height L 1 Axial length

Claims

1. A sleeve assembly (120) for a combustion system, the sleeve assembly (120) comprising: a first duct (148) having a first circumferential surface (168); a second duct (146) having a second circumferential surface, wherein the first circumferential surface (168) radially overlaps the second circumferential surface such that the first duct (148) and the second duct (146) collectively define an internal continuous combustion chamber, and the second duct (146) is configured to receive the high-temperature gas flowing therethrough; a wear insert (166) removably coupled to the first circumferential surface (168) and extending radially from the first circumferential surface (168) to engage the second circumferential surface; wherein the first duct (148) defines a groove (384) recessed radially from the first circumferential surface (168), and the wear insert (166) is seated within the groove (384). The sleeve assembly (120).

2. The sleeve assembly (120) according to claim 1, wherein the wear insert (166) has a one-piece structure of a single part and is removable from the first circumferential surface (168) as a single part.

3. The first duct (148) further comprises a first radial surface (386) for engaging a first radial edge (378) of the wear insert (166) and a second radial surface (388), the groove (384) being defined axially between the first radial surface (386) and the second radial surface (388), and the second radial surface (388) being axially spaced from the first radial surface (386) to engage a second radial edge (380) of the wear insert (166) and inhibit axial movement of the wear insert (166) within the groove (384). The sleeve assembly (120) according to claim 1.

4. The sleeve assembly (120) according to claim 1, wherein the wear insert (166) is removably coupled to the first circumferential surface (168) via a plurality of weld joints (176).

5. The sleeve assembly (120) according to claim 1, wherein the wear insert (166) extends continuously circumferentially around the circumference of the first circumferential surface (168).

6. The second duct (146) further includes a body (158) and a seal (162) extending axially from the body (158), the sleeve assembly (120) according to claim 1, wherein the seal (162) has the second circumferential surface.

7. The sleeve assembly (120) according to claim 6, wherein the wear insert (166) inhibits direct contact between the first circumferential surface (168) and the second circumferential surface.

8. The sleeve assembly (120) according to claim 1, wherein the second circumferential surface is at least partially positioned radially within the first circumferential surface (168).

9. A turbine assembly (100), wherein the turbine assembly (100) has a compressor section (102); a turbine section (106) coupled downstream of the compressor section (102); a combustor (104) including a plurality of cans (118) coupled in fluid communication between the compressor section (102) and the turbine section (106), and a first can of the plurality of cans (118) has a first duct (148) having a first circumferential surface (168); a second duct (146) having a second circumferential surface, wherein the first circumferential surface (168) radially overlaps the second circumferential surface such that the first duct (148) and the second duct (146) collectively define an internal continuous combustion chamber, and the second duct (146) is configured to receive the high-temperature gas flowing therethrough; and a wear insert (166) removably coupled to the first circumferential surface (168) and extending radially from the first circumferential surface (168) to engage the second circumferential surface, a combustor (104) including a sleeve assembly (120); and the first duct (148) defines a groove (384) recessed radially from the first circumferential surface (168), and the wear insert (166) is seated within the groove (384), the turbine assembly (100).

10. The turbine assembly (100) according to claim 9, wherein the first duct (148) extends between the second duct (146) and the turbine section (106).

11. The turbine assembly (100) according to claim 9, wherein the wear insert (166) has a one-piece structure of a single component and is removable from the first circumferential surface (168) as a single component.

12. The first duct (148) further comprises a first radial surface (386) for engaging a first radial edge (378) of the wear insert (166) and a second radial surface (388), the groove (384) being defined axially between the first radial surface (386) and the second radial surface (388), the second radial surface (388) being axially spaced from the first radial surface (386) and engaging a second radial edge (380) of the wear insert (166) to inhibit axial movement of the wear insert (166) within the groove (384). The turbine assembly (100) according to claim 9.

13. A method (400) of assembling a sleeve assembly (120) for a combustion system, providing (402) a first duct (148) including a first circumferential surface (168), the first duct (148) defining a groove (384) recessed radially from the first circumferential surface (168); removably coupling (404) the wear insert (166) to the first circumferential surface (168) such that the wear insert (166) seats within the groove (384); positioning (406) a second duct (146) including the second circumferential surface adjacent to the first duct (148) such that the first circumferential surface (168) radially overlaps a second circumferential surface and the wear insert (166) engages the second circumferential surface, the first duct (148) and the second duct (146) collectively defining an internal continuous combustion chamber configured to receive high temperature gas flowing therethrough. (406) A method (400) comprising.

Images