A shroud pin for a gas turbine engine shroud

Abstract

A shroud assembly for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction is provided. The shroud assembly includes a shroud segment extending substantially along the circumferential direction and including a shroud wall defining a shroud attachment opening, a hanger assembly including a hanger wall defining a hanger attachment opening, and an attachment pin assembly including a first member defining an interference fit with the hanger wall through the hanger attachment opening and including a shoulder contacting the hanger wall, the first member further extending through the shroud attachment opening and defining a hollow core, and a second member extending through the hollow core of the first member, the second member extending between a first end and a second end, the second member including a rim at the first end and an auxiliary attachment member at the second end.

Description

[0001] Federal government-funded research

[0002] This invention was made with government support under Contract No. FA8626-16-C-2138 granted by the Department of Defense. The U.S. government may have certain rights to this invention. Technical Field

[0003] This topic generally relates to gas turbine engines. More specifically, this topic relates to shielding assemblies for gas turbine engines. Background Technology

[0004] The performance and efficiency of gas turbine engines can be improved by increasing the combustion gas temperature. However, increased combustion temperature can negatively impact gas turbine engine components, for example, by increasing the likelihood of material failure. Therefore, high-temperature materials such as ceramic matrix composites (CMCs) are used in various engine components. In particular, shroud assemblies that define the outer boundary of the engine's working gas flow path and circumferentially surround the rotor blades of various compressors and / or turbine stages can be formed from CMC materials. For example, shroud sections can be formed from SiC / Si-SiC (fiber / matrix) CMC materials. Attached Figure Description

[0005] The complete and feasible disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, for those skilled in the art, wherein:

[0006] Figure 1 This is a schematic cross-sectional view of an exemplary gas turbine engine according to various embodiments of this subject matter.

[0007] Figure 2 yes Figure 1 The diagram shows cross-sectional views of the compressor section, combustion section, and high-pressure turbine section of a gas turbine engine.

[0008] Figure 3 The exemplary aspects of this disclosure include the attachment pin component. Figure 2 A partial side cross-sectional view of the protective shield assembly.

[0009] Figure 4 yes Figure 3 Close-up view of the protective cover assembly and the attached pin assembly.

[0010] Figure 5 It is along Figure 4 A view of the longitudinal centerline of the attached pin assembly. Detailed Implementation

[0011] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerals and letter designations to refer to features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to refer to similar or analogous portions of the present disclosure.

[0012] The term "exemplary" as used herein means "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior or better than other implementations. Furthermore, unless specifically stated otherwise, all embodiments described herein should be considered exemplary.

[0013] The singular forms “one,” “a,” and “the” include plural references unless the context clearly indicates otherwise.

[0014] In a context such as “at least one of A, B and C”, the term “at least one” means only A, only B, only C, or any combination of A, B and C.

[0015] The term "turbine" refers to a machine that includes one or more compressors, a heating section (e.g., a combustion section), and one or more turbines, which together produce torque output.

[0016] The term "gas turbine engine" refers to an engine that has a turbine as its power source, either entirely or partially. Exemplary gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid versions of one or more of these engines.

[0017] The term "combustion section" refers to any heat addition system used in a turbine. For example, the term "combustion section" can refer to a section that includes one or more of a knock combustion assembly, a rotary detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assemblies. In some exemplary embodiments, the combustion section may include an annular burner, a canister burner, a tubular burner, a vortex burner (TVC), or other suitable combustion systems, or combinations thereof.

[0018] When used with compressors, turbines, shafts, or spools, the terms “low” and “high,” or their respective degrees of comparison (e.g., higher, lower, where applicable), each refer to a relative speed within the engine, unless otherwise specified. For example, “low turbine” or “low-speed turbine” defines a component configured to operate at a speed (e.g., the maximum permissible speed) lower than that of a “high turbine” or “high-speed turbine” at the engine.

[0019] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0020] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction in which the fluid flows.

[0021] As used herein, ceramic matrix composites, or “CMC,” refers to a class of materials that include reinforcing materials (e.g., reinforcing fibers) surrounded by a ceramic matrix phase. Typically, the reinforcing fibers provide structural integrity to the ceramic matrix. Some examples of matrix materials for CMCs may include, but are not limited to, non-oxide silicon-based materials (e.g., silicon carbide, silicon nitride, or mixtures thereof), oxide ceramics (e.g., silicon oxycarbide, silicon oxynitride, alumina (Al₂O₃), silicon dioxide (SiO₂), aluminosilicates, or mixtures thereof), or mixtures thereof. Optionally, ceramic particles (e.g., oxides of Si, Al, Zr, Y, and combinations thereof) and inorganic fillers (e.g., pyrophyllite, wollastonite, mica, talc, kyanite, and montmorillonite) may also be included within the CMC matrix.

[0022] Some examples of CMC reinforcing fibers may include, but are not limited to, non-oxide silicon-based materials (e.g., silicon carbide, silicon nitride, or mixtures thereof), non-oxide carbon-based materials (e.g., carbon), oxide ceramics (e.g., silicon oxycarbonate, silicon oxynitride, alumina (Al2O3), silicon dioxide (SiO2), aluminosilicates such as mullite, or mixtures thereof) or mixtures thereof.

[0023] Typically, a particular CMC can be referred to as a combination of its fiber type / matrix type. For example, C / SiC for carbon fiber reinforced silicon carbide; SiC / SiC for silicon carbide fiber reinforced silicon carbide; SiC / SiN for silicon carbide fiber reinforced silicon nitride; and SiC / SiC-SiN for silicon carbide fiber reinforced silicon carbide / silicon nitride matrix mixtures, etc. In other examples, a CMC may consist of a matrix and reinforcing fibers comprising oxide-based materials (e.g., alumina (Al₂O₃), silica (SiO₂), aluminosilicates, and mixtures thereof). Aluminosilicates may include crystalline materials such as mullite (3Al₂O₃·2SiO₂) and glassy aluminosilicates.

[0024] In some embodiments, the reinforcing fibers may be bundled and / or coated before being incorporated into the matrix. For example, the fiber bundles may form reinforcing tapes, such as unidirectional reinforcing tapes. Multiple tapes may be laid together to form a preform component. The fiber bundles may be impregnated with a slurry composition before or after the preform is formed. The preform may then be heat-treated, such as cured or burned off, to produce a high coke residue in the preform, and subsequently chemically treated, such as with silicon melt infiltration, to obtain a component formed from a CMC material having the desired chemical composition.

[0025] These materials, along with certain monolithic ceramics (i.e., ceramic materials without reinforcement), are particularly well-suited for high-temperature applications. Furthermore, these ceramic materials are lighter than superalloys while still providing strength and durability for components made from them. Therefore, the use of such materials in many gas turbine components used in the high-temperature sections of gas turbine engines, such as airfoils (e.g., turbines and blades), combustors, shields, and other similar parts, is currently under consideration; these components would benefit from the lighter weight and higher temperature capabilities these materials can offer.

[0026] While CMC material is used in some components of the shield assembly, the shield assembly can include mounting elements (e.g., hangers) formed from other materials. Thermal expansion mismatch between the mounting elements and the shield section may necessitate relatively complex and large mounting elements that occupy more space in the engine than desired and add additional weight and cost. Therefore, an improved shield assembly for gas turbines is needed.

[0027] This disclosure generally relates to a shield assembly for a gas turbine engine, defined in axial, radial, and circumferential directions. The shield assembly includes a shield segment extending substantially in the circumferential direction and including a shield wall. The shield wall defines a shield attachment opening. The shield assembly further includes a hanger assembly and an attachment pin assembly, the hanger assembly having a hanger wall defining a hanger attachment opening. The attachment pin assembly includes a first member defining an interference fit with the hanger wall through the hanger attachment opening. The first member includes a shoulder that contacts the hanger wall, extends through the shield attachment opening, and defines a hollow core.

[0028] The attachment pin assembly further includes a second member extending through the hollow core of the first member. The second member extends between the first end and the second end, and includes an edge at the first end and an auxiliary attachment member at the second end. For example, the edge may define a diameter larger than the diameter of the hanger attachment opening, and the auxiliary attachment member may define a diameter larger than the diameter of the hollow core.

[0029] In this way, the attachment pin assembly can include a dual attachment configuration, which is less complex and lighter than previous designs. For example, the attachment pin assembly includes a first attachment via an interference fit between a first member and a hanger wall, and a second attachment via compression between the shoulder of the first member and the edge of the second member.

[0030] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of a gas turbine engine 100 according to an exemplary embodiment of the present disclosure. More specifically, for Figure 1 In one embodiment, the gas turbine engine 100 is an aviation high-bypass turbofan jet engine, which is configured (e.g., underwing or tail-mounted) to be mounted on an aircraft. Figure 1 As shown, the gas turbine engine 100 defines an axial direction A (extending parallel to or coaxial with the longitudinal centerline 102 for reference), a radial direction R, and a circumferential direction C (i.e., the direction extending about the axial direction A; see also...). Figure 3 Typically, a gas turbine engine 100 includes a fan section 104 and a turbine 106 disposed downstream of the fan section 104.

[0031] The depicted exemplary turbine 106 typically includes a generally tubular outer casing 108 defining an annular inlet 110. The casing 108 surrounds, in a series flow relationship: a compressor section 112, including a first turbocharger or LP compressor 114 and a second HP compressor 116; a combustion section 118; a turbine section 120, including a first HP turbine 122 and a second LP turbine 124; and an injection exhaust nozzle section 126. An HP shaft or spool 128 drives the HP turbine 122 to the HP compressor 116. An LP shaft or spool 130 drives the LP turbine 124 to the LP compressor 114. The compressor section, combustion section 118, turbine section, and injection exhaust nozzle section 126 together define a working gas flow path 132 through the turbine 106.

[0032] Still referencing Figure 1In one embodiment, fan section 104 includes a variable-pitch fan 134 having a plurality of fan blades 136 circumferentially spaced and coupled to disk 138. As shown, the fan blades 136 extend outward from disk 138 generally along a radial direction R. Each fan blade 136 is operably coupled to a suitable actuating member 140 by means of the fan blades 136, allowing each fan blade 136 to rotate relative to disk 138 about a pitch axis P, the actuating member 140 being configured to collectively, for example, uniformly change the pitch of the fan blades 136. The fan blades 136, disk 138, and actuating member 140 rotate together about a longitudinal centerline 102 via LP shaft 130 across a power gearbox 142. The power gearbox 142 includes a plurality of gears for progressively reducing the rotational speed of LP shaft 130 to a more efficient fan rotation speed.

[0033] Still referencing Figure 1 In an exemplary embodiment, the disk 138 is covered by a rotatable forward nacelle 144 having an aerodynamic profile to facilitate airflow through a plurality of fan blades 136. Additionally, the exemplary fan section 104 includes an annular fan housing or outer nacelle 146 circumferentially surrounding at least a portion of the fan 134 and / or turbine 106. Furthermore, in the depicted embodiment, the nacelle 146 is supported relative to the turbine 106 by a plurality of circumferentially spaced outlet guide vanes 148. Further, a downstream section 150 of the nacelle 146 extends over an outer portion of the turbine 106 to define a bypass airflow passage 152 therebetween.

[0034] During operation of the gas turbine engine 100, a volume of air 154 enters the gas turbine engine 100 through the nacelle 146 and / or the associated inlet 156 of the fan section 104. As the volume of air 154 passes through the fan blades 136, a first portion of the air 154, as indicated by arrow 158, is directed or directed into the bypass airflow passage 152, and a second portion of the air 154, as indicated by arrow 160, is directed or directed into the LP compressor 114. The second portion 160 of air then increases as it is directed through the high-pressure (HP) compressor 116 and into the combustion section 118.

[0035] See still Figure 1A second portion 160 of compressed air from the compressor section is mixed with fuel and burned in the combustion section 118 to provide combustion gas 162. The combustion gas 162 is guided from the combustion section 118 through the HP turbine 122 along the hot gas path 174, where a portion of the thermal and / or kinetic energy from the combustion gas 162 is extracted via a sequential stage of HP turbine stator blades 164 coupled to the housing 108 and HP turbine rotor blades 166 coupled to the HP shaft or spool 128, thus causing the HP shaft or spool 128 to rotate, thereby supporting the operation of the HP compressor 116. Combustion gas 162 is then guided through LP turbine 124, where a second portion of the thermal and kinetic energy from combustion gas 162 is extracted via a sequential stage of LP turbine stator blades 168 connected to housing 108 and LP turbine rotor blades 170 connected to LP shaft or spool 130, thus causing LP shaft or spool 130 to rotate, thereby supporting the operation of LP compressor 114 and / or fan 134.

[0036] Combustion gas 162 is then directed through the injection exhaust nozzle section 126 of turbine 106 to provide propulsive thrust. Simultaneously, as a first portion 158 of air is directed through bypass airflow passage 152 before exiting from the fan nozzle exhaust section 172 of gas turbine engine 100, the pressure of the first portion 158 of air increases significantly, also providing propulsive thrust. HP turbine 122, LP turbine 124, and injection exhaust nozzle section 126 at least partially define a hot gas path 174 for directing combustion gas 162 through turbine 106.

[0037] It should be understood that Figure 1 The exemplary gas turbine engine 100 depicted herein is merely an example, and in other exemplary embodiments, the gas turbine engine 100 may have any other suitable configuration. For example, the gas turbine engine may include any suitable number and / or configuration of compressors, turbines, shafts, or spools, etc. Furthermore, although depicted as including a variable-pitch fan 124 and a power gearbox 142, in other embodiments, the gas turbine engine may include a fixed-pitch fan, a direct-drive configuration, etc. Additionally or alternatively, aspects of this disclosure may be used with any other suitable aero gas turbine engine, such as a turboshaft engine, a turboprop engine, a turbojet engine, etc. Furthermore, aspects of this disclosure may also be used with any other land-based gas turbine engine, such as a power generation gas turbine engine, or any aero-derivative gas turbine engine, such as a marine gas turbine engine.

[0038] Now for reference Figure 2 , Figure 2 Provided Figure 1A side cross-sectional view of the compressor section 112, combustion section 118, and turbine section 120 of the turbine 106. More specifically, the rear end of the HP compressor 116, the combustion section 118, and the front end of the HP turbine 122 are shown.

[0039] Compressed air 176 exits the HP compressor 116 through a diffuser 178 located at the rear end or outlet of the HP compressor 116 and diffuses into the combustion section 118. The combustion section 118 of the turbine 106 is annularly surrounded by a radially inner burner housing 180 and a radially outer burner housing 182. Both the radially inner burner housing 180 and the radially outer burner housing 182 extend generally along the axial direction A and surround the burner assembly 184 in an annular ring. The inner burner housing 180 and the outer burner housing 182 are joined together at the annular diffuser 178 at the front end of the combustion section 118.

[0040] As shown in the figure, the burner assembly 184 typically includes an inner liner 186 and an outer liner 192. The inner liner 186 extends generally along an axial direction A between a rear end 188 and a front end 190, and the outer liner 192 also extends generally along an axial direction A between a rear end 194 and a front end 196. The inner liner 186 and the outer liner 192 together define at least partially a combustion chamber 198 therebetween. The inner liner 186 and the outer liner 192 are each attached to or integrally formed with an annular dome. More specifically, the annular dome includes an inner dome section 200 integrally formed with the front end 190 of the inner liner 186 and an outer dome section 202 generally formed with the front end 196 of the outer liner 192. Furthermore, the inner dome section 200 and the outer dome section 202 may each be integrally formed (or alternatively may be formed by multiple components attached in any suitable manner) and may each extend along a circumferential direction C to define an annular shape. However, it should be understood that in other embodiments, the burner assembly 184 may not include the inner dome section 200 and / or the outer dome section 202; it may include separately formed inner dome sections 200 and / or outer dome sections 202 attached to the respective inner liners 186 and outer liners 192; or it may have any other suitable configuration.

[0041] See still Figure 2The combustor assembly 184 further includes a plurality of fuel-air mixers 204 spaced apart along the circumferential direction C and at least partially positioned within an annular dome. More specifically, the plurality of fuel-air mixers 204 are at least partially disposed along the radial direction R between an outer dome section 202 and an inner dome section 200. Compressed air 176 from the compressor section 112 of the gas turbine engine 100 flows into or through the fuel-air mixers 204, where it mixes with fuel and is ignited to produce combustion gases 162 within the combustion chamber 198. The inner dome section 200 and the outer dome section 202 are configured to facilitate the flow of such compressed air 176 from the compressor section 112 into or through the fuel-air mixers 204.

[0042] As described above, combustion gas 162 flows from combustion chamber 198 into and through turbine section 120 of gas turbine engine 100, where a portion of the thermal and / or kinetic energy from combustion gas 162 is extracted via a successive stage of turbine stator blades and turbine rotor blades within HP turbine 122 and LP turbine 124. More specifically, as Figure 2 As shown, combustion gas 162 from combustion chamber 198 flows into HP turbine 122 immediately downstream of combustion chamber 198, where thermal and / or kinetic energy from combustion gas 162 is extracted in HP turbine 122 via a sequential stage of HP turbine stator blades 164 and HP turbine rotor blades 166.

[0043] like Figure 2 As shown, not all compressed air 176 flows into or directly through the fuel-air mixer 204 and into the combustion chamber 198. Some compressed air 176 is discharged into the chamber 206 surrounding the burner assembly 184. The chamber 206 is generally defined between the burner housings 180, 182 and the liners 186, 192. The outer burner housing 182 and the outer liner 192 define an outer chamber 208, which is generally arranged radially outward from the combustion chamber 198. The inner burner housing 180 and the inner liner 186 define an inner chamber 210, which is generally arranged radially inward relative to the combustion chamber 198. As the compressed air 176 is diffused by the diffuser 178, some of the compressed air 176 flows radially outward into the outer chamber 208, while some of the compressed air 176 flows radially inward into the inner chamber 210.

[0044] Compressed air 176, flowing radially outward into the outer chamber 208, generally flows axially toward the turbine section 120. Specifically, compressed air 176 flows above the HP turbine stator blades 164 and the HP turbine rotor blades 166. The outer chamber 208 may also extend to the LP turbine 124. Figure 1 ).

[0045] like Figure 2As further shown, the HP turbine 122 includes one or more shroud assemblies 300, each shroud assembly forming an annular shroud ring around an annular array of HP turbine rotor blades 166. In this example, the annular shroud ring is circumferentially arranged around the annular array of rotor blades 166 of the first stage 212 of the HP turbine 122, and the annular ring is circumferentially arranged around the annular array of turbine rotor blades 166 of the second stage 214. Typically, the shroud or shroud section of the shroud assembly 300 is radially spaced from the blade tip 216 of each rotor blade 166. The shroud assembly 300 typically reduces radial leakage into and out of the working gas flow path 132 and may also reduce axial leakage.

[0046] Each shroud assembly 300 includes a shroud segment 302 and a hanger assembly 304. The shroud segment 302 is positioned radially outward from the blade tip 216 of each rotor blade 166 and at least partially defines a working gas flow path 132. Each shroud segment 302 includes an outer side 306 along the radial direction R and an inner side 308 along the radial direction R. The inner side 308 of each shroud segment 302 may include, for example, a ceramic-based abrasive material coated with an environmental barrier coating (EBC). However, alternatively, in other embodiments, any other suitable material and / or coating may be disposed on the inner side 308 of the shroud segment 302. Further, as will be explained in more detail below, each shroud segment 302 is coupled to a corresponding hanger assembly 304. The hanger assembly 304 couples each shroud segment 302 to structural components of the turbine 106, and more specifically, to the housing 182 in the illustrated embodiment.

[0047] It should be noted that the shield assembly 300 can be additionally used in the LP compressor 114, HP compressor 116, and / or LP turbine 124 in a similar manner. Therefore, the shield assembly 300 disclosed herein is not limited to use in the HP turbine 122, but can be used in any suitable section of the gas turbine engine 100 or more generally, a turbine engine.

[0048] For example, the following will refer to the example. Figure 4 To explain in more detail, the protective cover section 302 and the hanger assembly 304 each extend generally along the circumferential direction C (see...). Figure 2 The shroud assembly 300 may generally include multiple individual shroud segments 302 and hanger assemblies 304, which are arranged sequentially along the circumferential direction C to collectively form the circumferential shroud assembly 300.

[0049] Still referencing Figure 3 The shield assembly 300 will be explained in more detail. More specifically, Figure 3 A close-up schematic diagram of a shield assembly 300 installed inside a gas turbine engine is provided.

[0050] The shield section 302 generally includes a shield body 310 defining an outer side 306 and an inner side 308, wherein the inner side 308 at least partially defines the working gas flow path 132 of the gas turbine engine (see...). Figure 1 and 2 Furthermore, the shield section 302 includes a front shield wall 312 and a rear shield wall 314, which are spaced apart from each other along the axial direction A and together define a cavity 316 therebetween. Notably, each of the front shield wall 312 and the rear shield wall 314 extends generally outward from the shield body 310 along the radial direction R and further generally along the circumferential direction C (see...). Figure 2 It extends together with the main body 310 of the protective cover.

[0051] In short, it should be understood that cavity 316 is further defined by hanger assembly 304. During operation, cavity 316 may be supplied with cooling air from the compressor section bypassing the burner, for example through outer air chamber 208 (see...). Figure 2 This air cools the shroud section 302 and the hanger assembly 304, and is typically at a higher pressure than the gas in the flow path. For example, the pressure in cavity 316 can increase with engine operating speed as it receives this air from the compressor section (which generates higher-pressure air at higher speeds). This configuration helps prevent hot flow path gas from radially leaking outward into hanger assembly 304 and / or shroud section 302 (e.g., cavity 316 of the shroud assembly) and potentially damaging these components. Therefore, a seal is required between shroud section 302 and hanger assembly 304 to prevent uncontrolled escape of cooling air from cavity 316 into the flow path.

[0052] See still Figure 3 The hanger assembly 304 is connected to the shield section 302 and is further configured to mount the shield section 302 within the gas turbine engine to, for example, a structural component of the gas turbine engine (e.g., housing 182, as referenced above). Figure 2 More specifically, the hanger assembly 304 includes hanger attachments configured to attach the hanger assembly 304 to structural members of the gas turbine engine, and more specifically, includes a front hanger attachment 318 and a rear hanger attachment 320. In the illustrated embodiment, the front hanger attachment 318 and the rear hanger attachment 320 are each configured as a hook. However, in other exemplary embodiments, any other suitable mechanical fasteners (e.g., bolts, screws, etc.) may be used.

[0053] More specifically, for Figure 3In one embodiment, the front hanger attachment 318 and the rear hanger attachment 320 are connected to structural components of the gas turbine engine, and more specifically, to the housing 182 of the gas turbine engine, to mount the shield assembly 300 inside the gas turbine engine.

[0054] Furthermore, the hanger assembly 304 generally includes a front hanger wall 322 and a rear hanger wall 324. In the depicted embodiment, the front hanger wall 322 is coupled to the front protective wall 312 and the rear hanger wall 324 is coupled to the rear protective wall 314. Specifically, for Figure 3 In an exemplary embodiment, the front hanger wall 322 is connected to the front shroud wall 312 using a first attachment pin assembly 330A. The first attachment pin assembly 330A generally includes a first member 332 and a second member 334, and can provide a dual-redundant mechanical attachment from the front hanger wall 322 to the front shroud wall 312. Similar to... Figure 3 In the embodiment depicted, the rear hanger wall 324 is connected to the rear shield wall 312 using a second attachment pin assembly 330B. The second attachment pin assembly 330B also generally includes a first member 332 and a second member 334, and can provide a double redundant mechanical attachment from the rear hanger wall 324 to the rear shield wall 314.

[0055] More specifically, see also Figure 4 The diagram provides a close-up cross-sectional view of the second auxiliary pin assembly 330B that connects the rear hanger wall 324 to the rear cover wall 314. The pin assembly 330 extends generally along the longitudinal axis 331.

[0056] As described above, the second attachment pin assembly 330B includes a first member 332 and a second member 334. The rear guard wall 314 defines a guard attachment opening 336, and the rear hanger wall 324 assembly defines a hanger attachment opening 338.

[0057] The first member 332 includes a body having a first segment 344 and a second segment 346. Furthermore, the first member 332 includes a shoulder 342 between the first segment 344 and the second segment 346. More specifically, the first segment 344 defines a first segment diameter 348, the second segment 346 defines a second segment diameter 350, and the rear hanger wall 324 defines a hanger attachment opening diameter 352. Notably, the first segment diameter 348 can be substantially equal to the hanger attachment opening diameter 352 to facilitate an interference fit 340 as described below. The second segment diameter 350 is larger than the first segment diameter 348 and further larger than the hanger attachment opening diameter 352. In this way, the shoulder 342 prevents the second segment 346 of the first member 332 from inserting through the hanger attachment opening 338 (in...). Figure 4 (Inserted from right to left in the view of the embodiment).

[0058] When inserted into the hanger attachment opening 338 of the rear hanger wall 324, the first segment 344 is located within the hanger attachment opening 338 and defines an interference fit 340 with the rear hanger wall 324. The shoulder 342 contacts the rear hanger wall 324 at a position between the first segment 344 and the second segment 346, and as described above, prevents the second segment 346 of the first member 332 from inserting through the hanger attachment opening 338. The second segment 346 extends beyond the rear hanger wall 324.

[0059] See still Figure 4 The first member 332 defines a hollow core 354. The second member 334 extends through the hollow core 354 of the first member 332, and more specifically extends between the first end 356 and the second end 358.

[0060] The second component 334 includes a body having an edge 360 ​​at a first end 356, an auxiliary attachment member 362 at a second end 358, and a body 364 extending at least between the edge 360 ​​and the auxiliary attachment member 362. The auxiliary attachment member 362 is positioned outside a cavity 316 defined between the front shield wall 312 and the rear shield wall 314.

[0061] The edge 360 ​​of the second member 334 can prevent the second member 334 from extending all the way through the hollow core 354 (in the depicted) Figure 4 (From left to right in the view of the embodiment). More specifically, in the illustrated embodiment, edge 360 ​​defines an edge diameter 366, and the hollow core 354 of the first member 332 defines a hollow core diameter 368. In the illustrated embodiment, the edge diameter 366 is larger than the hollow core diameter 368 to prevent the second member 334 from extending all the way through the hollow core 354 of the first member 332.

[0062] Furthermore, in the illustrated embodiment, edge 360 ​​further defines an inner surface 370. The inner surface 370 of edge 360 ​​is positioned against the rear hanger wall 324 at a location surrounding the hanger attachment opening 338, and is positioned adjacent to the rear cover wall 314 on a side opposite to one side of the rear hanger wall 324. This further prevents the second attachment pin assembly 330B from being in contact with the depicted... Figure 4 In the view of the embodiment, the device slides from left to right through the hanger attachment opening 338.

[0063] Furthermore, in order to prevent the second component 334 of the second attached pin assembly 330B from being in the depicted Figure 4In the illustrated embodiment, sliding from right to left, the auxiliary attachment member 362 is disposed at the second end 358 of the second member 334. In the illustrated embodiment, the auxiliary attachment member 362 is positioned against the end of the first member 332. More specifically, the first member 332 similarly extends longitudinally between the first end 372 and the second end 374, and for the illustrated embodiment, the auxiliary attachment member 362 is positioned against the second end 374 of the first member 332. More specifically, for the illustrated embodiment, as described above, the hollow core 354 defines a hollow core diameter 368. The auxiliary attachment member 362 similarly defines an auxiliary attachment member diameter 376 larger than the hollow core diameter 368. The diameter 376 of the auxiliary attachment member 362 is larger than the hollow core diameter 368, which can prevent the second member 334 of the second attachment pin assembly 330B from sliding out of the first end of the first member 332 (i.e., in...). Figure 4 (From right to left in the view of the embodiment).

[0064] It is worth noting that in the illustrated embodiment, the diameter 376 of the auxiliary attachment member is smaller than the diameter 350 of the second segment. This configuration ensures that the rear guard wall 314 can move relative to the rear hanger wall 324 in a desired manner, as described in more detail below.

[0065] More specifically, the second member 334 of the attachment assembly further includes a body 364, wherein the auxiliary attachment member 362 is coupled to the body 364 at a second end 358 of the second member 334. The auxiliary attachment member 362 can be coupled to the body 364 in any suitable manner. For example, in at least some exemplary embodiments, the auxiliary attachment member 362 may include a forged connection, a welded connection (e.g., a spot welded connection), a rotary engagement connection (e.g., a threaded connection), or a combination thereof. Furthermore, the auxiliary attachment member 362 may include a grommets, rotary fasteners (e.g., having a threaded connector), or a combination having one or more of the above connections. More specifically, for the illustrated embodiment, the auxiliary attachment member 362 includes a grommets (i.e., including a welded connection) welded to the body 364 of the second member 334 of the second attachment pin assembly 330B.

[0066] In this manner, it should be understood that the second attachment pin assembly 330B includes at least two attachment devices for connection to the rear guard wall 314 and the rear hanger wall 324. More specifically, relative to the first member 332, a first segment 344 of the first member 332 defines an interference fit 340 between the first member 332 and the rear hanger wall 324 via a hanger attachment opening 338, thereby connecting the first member 332 to the rear hanger wall 324. Notably, relative to the first member 332, a shoulder 342 prevents the first member 332 from over-inserting into or through the hanger attachment opening 338. Furthermore, the second member 334 of the second attachment pin assembly 330B provides redundant connection for the second attachment pin assembly 330B. More specifically, the second member 334 is secured to the first member 332 by including an edge 360 ​​defining an edge diameter 366 larger than the diameter of the hollow core 368 (preventing the second member 334 from sliding through the second end 358 of the first member 332) and further by including an auxiliary attachment member 362 (preventing the second member 334 from sliding through the first end of the first member 332). Further, the second member 334 prevents the second attachment pin assembly 330B from sliding out of the hanger attachment opening 338 of the hanger wall 324 by including an edge 360 ​​defining an edge diameter 366 larger than the diameter of the hanger attachment opening 352, and more specifically, prevents the first member 332 of the second attachment pin assembly 330B from sliding out of the hanger attachment opening 338 of the hanger wall 324.

[0067] In this way, the second attachment pin assembly 330B can define a dual / redundant attachment mechanism with the hanger wall 324—for example, for the depicted embodiment: (1) an interference fit 340 and (2) a combination of shoulder 342 and edge 360 ​​(held in place with auxiliary attachment member 362).

[0068] It is worth noting that, in order to install the second attachment pin assembly 330B, the first segment 344 can be first pressed and fitted into the hanger attachment opening 338 (in Figure 4 The first member 332 is installed (from right to left in the view depicted) until the shoulder 342 is pressed against one side of the rear hanger wall 324 adjacent to the rear shield wall 314. Next, the second end 358 of the second member 334 can slide through the hollow core 354, starting at the first end 372 of the first member 332 (from left to right) until the edge 360 ​​is pressed against the first end 372 of the first member 332, the side of the rear hanger wall 324 opposite to the side of the adjacent rear shield wall 314, or both. An auxiliary attachment member 362 can then be positioned on the second end 358 of the second member 334 and secured to the body 364 of the second member 334.

[0069] Still refer to Figure 4As briefly mentioned above, the hanger assembly 304 may be formed of a metallic material and includes a shroud section 302 of the rear shroud wall 314 (see [link]). Figure 3 The housing can be formed from a ceramic matrix composite material. In this manner, a second attachment pin assembly 330B may be required to accommodate the relative thermal expansion between the housing section 302 and the hanger assembly 304. More specifically, in this manner, it should be understood that the second attachment pin assembly 330B is configured to provide alignment of the housing section 302 relative to the hanger assembly 304, but is not configured to rigidly secure the housing section 302 to the hanger assembly 304. More specifically, for the illustrated embodiment, the first member 332 defines a gap 378 with the rear housing wall 314 within the housing attachment opening 336. More specifically, the housing attachment opening 336 defines a housing attachment opening diameter 380, and a second segment 346 of the first member 332 defines a second segment diameter 350. The second segment diameter 350 is smaller than the housing attachment opening diameter 380 to define the gap 378 between the first member 332 and the housing section 302.

[0070] Furthermore, it should be understood that, for Figure 4 In some embodiments, the second attachment pin assembly 330B can be configured to match or substantially match the thermal expansion of the rear hanger wall 324 to maintain an interference fit 340 between, for example, the first member 332 and the rear hanger wall 324 through the hanger attachment opening 338. For example, the first member 332 and the second member 334 of the second attachment pin assembly 330B can be formed of a metallic material. In at least some exemplary aspects, the rear hanger wall 324 of the hanger assembly 304, the first member 332 of the second attachment pin assembly 330B, and the second member 334 of the second attachment pin assembly 330B can each be formed of a first metallic material. In this way, the rear hanger wall 324 of the hanger assembly 304, the first member 332 of the second attachment pin assembly 330B, and the second member 334 of the second attachment pin assembly 330B can each be formed of a common metallic material (as used herein, meaning a component made of the same metallic material). In this way, the second auxiliary pin assembly 330B can be configured to match the thermal expansion of the rear hanger wall 324 during operation of the gas turbine engine. Furthermore, by forming the first member 332 and the second member 334 of the second auxiliary pin assembly 330B with a common metallic material, the engagement of the first member 332 and the second member 334 of the second auxiliary pin assembly 330B can be maintained within the operating temperature range of the second auxiliary pin assembly 330B, for example, along the second auxiliary pin assembly 330B (i.e., along the longitudinal axis 331).

[0071] However, alternatively, it should be understood that the second attachment pin assembly 330B may be formed of a different metallic material than the rear hanger wall 324, and additionally or alternatively, the first member 332 and the second member 334 of the second attachment pin assembly 330B may be formed of different metallic materials. For example, in some exemplary embodiments, the first member 332 of the second attachment pin assembly 330B may be formed of a first metallic material defining a first coefficient of thermal expansion, the second member 334 of the second attachment pin assembly 330B may be formed of a second metallic material defining a second coefficient of thermal expansion, and the hanger wall may be formed of a third metallic material defining a third coefficient of thermal expansion.

[0072] In one exemplary embodiment, the first metal material may be different from the second metal material, and the first coefficient of thermal expansion may be greater than the second coefficient of thermal expansion. In this way, the second attachment pin assembly 330B can maintain the desired close fit between the first member 332 and the second member 334 along the longitudinal axis 331 of the second attachment pin assembly 330B within the operating temperature range of the second attachment pin assembly 330B.

[0073] Furthermore, in another exemplary embodiment, the first coefficient of thermal expansion may be greater than the third coefficient of thermal expansion. In this way, the first member 332 of the second attachment pin assembly 330B can maintain an interference fit 340 with the rear hanger wall 324 through the hanger attachment opening 338 within the operating temperature range of the second attachment pin assembly 330B.

[0074] As briefly discussed above, it should be understood that the shield assembly 300 (see Figure 3 This allows for the maintenance of a pressure differential between the hollow core 354 defined by the shroud section 302 and the cavities in front of and / or behind the shroud section 302. However, it is noteworthy that the second member 334, or more precisely, the body 364 of the second member 334, defines a gap 382 with the first member 332 within the hollow core 354. The gap 382 allows for, for example, relative thermal expansion. However, for this configuration, in order to maintain a fluid seal between the second attachment pin assembly 330B and the rear hanger wall 324, the edge 360 ​​of the second member 334 includes a sealing element 384 (see...). Figure 5 It is configured to contact the hanger wall 324 around the hanger attachment opening 338. More specifically, reference is now also made to... Figure 5 A schematic cross-sectional view is provided at the interface between the first end 356 of the first member 332 and the first end 356 of the second member 334 at the edge 360 ​​and the first end 356 of the first member 332. The rear hanger wall 324 is not included. Figure 5In the view shown, the sealing element 384 is a circumferential sealing element positioned on the inner surface 370 of the edge 360, outside the first segment diameter 348 of the first segment 344 of the first member 332. In this way, the edge 360 ​​of the second member 334 can form a fluid-tight seal with the rear hanger wall 324 on the side of the rear hanger wall 324 opposite to the side facing the rear cover wall 314.

[0075] Briefly return to the reference Figure 3 It should be understood that the above references Figure 4 and Figure 5 The second auxiliary pin assembly 330B discussed is configured to attach the rear hanger wall 324 to the rear shield wall 314. In the illustrated embodiment, it should be understood that the shield assembly 300 further includes a first auxiliary pin assembly 330A, as briefly noted above. The first auxiliary pin assembly 330A can be configured to attach the front hanger wall 322 to the front shield wall 312. The first auxiliary pin assembly 330A can be configured in substantially the same manner as the second auxiliary pin assembly 330B.

[0076] In this manner, the attachment pin assembly of this disclosure can include a dual attachment configuration, which is less complex and lighter than previous designs. For example, the attachment pin assembly includes a first attachment via an interference fit between a first member and a hanger wall, and a second attachment via compression between the shoulder of the first member and the edge of the second member (held in place by an auxiliary attachment member). Notably, this also facilitates a simpler installation process by allowing the edge of the second member to be positioned within a cavity between the front and rear guard walls (which may be difficult to access during installation).

[0077] Furthermore, it should be understood that this disclosure provides a method for attaching a protective section to a protective hanger. This method can be used in conjunction with one or more of the exemplary embodiments described above.

[0078] The method includes positioning a first member of the attachment pin assembly into a hanger attachment opening in a hanger wall and a cover attachment opening in a cover wall. In at least some exemplary aspects, positioning the first member into the hanger attachment opening includes pressing the first member into the hanger attachment opening. In this way, the first member can define an interference fit with the hanger wall through the hanger attachment opening.

[0079] Furthermore, it should be understood that, in some exemplary aspects, positioning the first member into the hanger attachment opening may further include positioning the shoulder of the first member against the hanger wall.

[0080] The method further includes positioning the second member through the hollow core of the first member. Positioning the second member through the hollow core of the first member may include positioning the edge of the first member located at a first end of the first member against a hanger wall. It is worth noting that, in at least some exemplary aspects, positioning the second member through the hollow core includes sealing the edge of the first member with the hanger wall (e.g., by pressing a sealing element on the edge against the hanger wall).

[0081] The method further includes attaching an auxiliary attachment member to a second end of the first member. Attaching the auxiliary attachment member to the second end of the first member may include forging, welding, rotatably joining, etc., of the auxiliary attachment member to the second end of the first member.

[0082] Further aspects are provided by the following topics:

[0083] A shield assembly for a gas turbine engine, the shield assembly comprising: a shield segment extending substantially circumferentially and including a shield wall defining a shield attachment opening; a hanger assembly including a hanger wall defining a hanger attachment opening; and an attachment pin assembly including a first member comprising a first body defining a hollow core and having a first portion disposed within the hanger attachment opening and defining an interference fit between the first portion and the hanger wall, the first body further including a shoulder contacting the hanger wall, the first body further extending through the shield attachment opening; a second member including a second body extending between a first end and a second end and including an edge at the first end, the second body extending through the hollow core of the first member; and an auxiliary attachment member having the second body disposed thereon and adapted to retain the second body within the first body.

[0084] The shield assembly according to any one of the preceding clauses, wherein the first body includes a first segment having a first segment diameter, and the shoulder has a width greater than the first segment diameter.

[0085] The protective cover assembly according to any one of the preceding clauses, wherein the first member comprises a first segment and a second segment, wherein the first segment defines an interference fit with a hanger wall through the hanger attachment opening, and wherein the second segment extends through the protective cover attachment opening, wherein the first segment of the first member defines a first segment diameter, and wherein the edge of the second member defines an edge diameter larger than the diameter of the first segment.

[0086] The shield assembly according to any one of the preceding clauses, wherein the edge defines an inner surface, wherein the inner surface includes a circumferential sealing element positioned at a location outside the diameter of the first segment.

[0087] According to any one of the preceding clauses, in the protective cover assembly, the edge of the second member is defined as having an edge diameter greater than the diameter of the first segment, and the edge is positioned against the hanger wall.

[0088] According to any one of the preceding clauses, the edge of the second body defines an edge diameter larger than the diameter of the first segment.

[0089] The protective assembly according to any one of the preceding clauses, wherein the auxiliary attachment member is positioned against the second distal end of the first member.

[0090] The protective cover assembly according to any one of the preceding clauses, wherein the hollow core defines a hollow core diameter, and wherein the auxiliary attachment member defines an auxiliary attachment member diameter larger than the hollow core diameter.

[0091] The protective cover assembly according to any one of the preceding clauses, wherein the auxiliary attachment member includes a forged connection, a welded connection, a rotary joint connection, or a combination thereof.

[0092] The protective assembly according to any one of the preceding clauses, wherein the auxiliary attachment member includes a grommets, a swivel fastener, or both.

[0093] The protective cover assembly according to any one of the preceding clauses, wherein the protective cover section is formed of a ceramic matrix composite material, and wherein the hanger assembly, the first member of the attachment pin assembly, and the second member of the attachment pin assembly are formed of a metallic material.

[0094] The protective cover assembly according to any one of the preceding clauses, wherein the hanger wall, the first member of the attachment pin assembly, and the second member of the attachment pin assembly are each formed of a first metallic material.

[0095] The protective cover assembly according to any one of the preceding clauses, wherein the first and second components of the attached pin assembly are each formed of a first metallic material.

[0096] According to any one of the preceding clauses, the first member of the attached pin assembly is formed of a first metallic material defining a first coefficient of thermal expansion, the second member of the attached pin assembly is formed of a second metallic material defining a second coefficient of thermal expansion, and the first coefficient of thermal expansion is greater than the second coefficient of thermal expansion.

[0097] The shield assembly according to any one of the preceding clauses, wherein the first member defines a gap with the shield segment within the shield attachment opening.

[0098] The protective cover assembly according to any one of the preceding clauses, wherein the auxiliary attachment member includes a body extending through the hollow core of the first member, and wherein the body defines a gap with the first member within the hollow core.

[0099] The shield assembly according to any one of the preceding clauses, wherein the gas turbine engine includes a turbine section, and wherein the shield section is configured to be positioned within the turbine section.

[0100] An attachment pin assembly includes a first member comprising a first body defining a hollow core, the first body having a first portion adapted to be disposed within a hanger attachment opening in a hanger wall and to be interference-fitted with the hanger wall, the first body further including a shoulder, the first member being further adapted to extend through a shroud attachment opening in a shroud wall; and a second member comprising a second body extending between a first end and a second end and including an edge at the first end; wherein, when assembled, the second body extends through the hollow core of the first member, and the auxiliary attachment member is disposed on the second body and adapted to retain the second body within the first body.

[0101] The attachment pin assembly according to any one of the preceding clauses, wherein the first body includes a first segment having a first segment diameter, and the shoulder has a width greater than the first segment diameter.

[0102] The attachment pin assembly according to any one of the preceding clauses, wherein the first member comprises a first segment and a second segment, wherein the first segment defines an interference fit with the hanger wall through the hanger attachment opening, and wherein the second segment extends through the cover attachment opening, wherein the first segment of the first member defines a first segment diameter, and wherein the edge of the second member defines an edge diameter larger than the diameter of the first segment.

[0103] The attachment pin assembly according to any one of the preceding clauses, wherein the auxiliary attachment member is positioned against the second distal end of the first member.

[0104] The attachment pin assembly according to any one of the preceding clauses, wherein the first member of the attachment pin assembly is formed of a first metallic material defining a first coefficient of thermal expansion, wherein the second member of the attachment pin assembly is formed of a second metallic material defining a second coefficient of thermal expansion, and wherein the first coefficient of thermal expansion is greater than the second coefficient of thermal expansion.

[0105] A gas turbine engine defining axial, radial, and circumferential directions includes: a compressor section, a combustion section, and a turbine section, the compressor section, the combustion section, and the turbine section being in series flow relationship and together defining a working gas flow path; and a shield assembly positioned within at least one of the compressor section or the turbine section and at least partially defining the working gas flow path, the shield assembly including: a shield segment extending substantially in the circumferential direction and including a shield wall defining a shield attachment opening; A hanger assembly including a hanger wall defining a hanger attachment opening; an attachment pin assembly including a first member defining an interference fit with the hanger wall through the hanger attachment opening and including a shoulder contacting the hanger wall, the first member further extending through the guard attachment opening and defining a hollow core; and a second member extending through the hollow core of the first member, the second member extending between a first end and a second end, the second member including an edge at the first end and an auxiliary attachment member at the second end.

[0106] A method for attaching a protective section to a protective cover hanger, the method comprising: positioning a first member of an attachment pin assembly into a hanger attachment opening in a hanger wall and a protective cover attachment opening in a protective cover wall, wherein positioning the first member into the hanger attachment opening comprises pressing the first member into the hanger attachment opening; positioning a second member through the hollow core of the first member, wherein positioning the second member through the hollow core comprises positioning an edge of the first member located at a first end of the first member against the hanger wall; and attaching an auxiliary attachment member to a second end of the first member.

[0107] The method according to one or more of the preceding clauses, wherein positioning the first member into the hanger attachment opening further comprises positioning the shoulder of the first member against the hanger wall.

[0108] The method according to one or more of the preceding clauses, wherein positioning the second member through the hollow core includes sealing the edge of the first member with the hanger wall.

[0109] According to one or more of the preceding clauses of the method, wherein the hollow core defines a hollow core diameter, and wherein the auxiliary attachment member defines an auxiliary attachment member diameter larger than the hollow core diameter.

[0110] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and performing any incorporated methods. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A shroud assembly for a gas turbine engine, characterized by, The protective shield assembly includes: A protective section, the protective section extending substantially in a circumferential direction and including a protective wall, the protective wall defining a protective attachment opening; Hanger assembly, the hanger assembly including hanger wall defining a hanger attachment opening; and Attached pin assembly, the attached pin assembly includes A first component, the first component including a first body defining a hollow core and having a first portion disposed within the hanger attachment opening and defining an interference fit between the first portion and the hanger wall, the first body further including a shoulder contacting the hanger wall, the first body further extending through the cover attachment opening; A second component, the second component comprising a second body extending between a first end and a second end and including an edge at the first end, the second body extending through the hollow core of the first component; and An auxiliary attachment member is provided with a second body and is adapted to retain the second body within the first body.

2. The shroud assembly of claim 1, wherein, The first body includes a first segment having a first segment diameter, and the shoulder has a width greater than the first segment diameter.

3. The shroud assembly of claim 2, wherein, The edge defines an inner surface, wherein the inner surface includes a circumferential sealing element positioned at a location outside the diameter of the first segment.

4. The shroud assembly of claim 2, wherein, The edge of the second component is defined as having an edge diameter larger than that of the first segment, and the edge is positioned against the hanger wall.

5. The shroud assembly of claim 2, wherein, The edge of the second body is defined as having an edge diameter larger than that of the first segment.

6. The shroud assembly of claim 1, wherein, The auxiliary attachment member is positioned against the second distal end of the first member.

7. The shroud assembly of claim 1, wherein, The hollow core defines a hollow core diameter, and the auxiliary attachment member defines an auxiliary attachment member diameter larger than the hollow core diameter.

8. The shroud assembly of claim 1, wherein, The auxiliary attachment components include forged connections, welded connections, rotary joint connections, cable rings, rotary fasteners, or combinations thereof.

9. The shroud assembly of claim 1, wherein, The protective cover section is formed of a ceramic matrix composite material, and the hanger assembly, the first member of the attachment pin assembly, and the second member of the attachment pin assembly are formed of a metallic material.

10. The shroud assembly of claim 1, wherein, The hanger wall, the first component of the attachment pin assembly, and the second component of the attachment pin assembly are each formed of a first metallic material.

11. The shroud assembly of claim 1, wherein, The first and second components of the attached pin assembly are each formed of a first metallic material.

12. The shroud assembly of claim 1, wherein, The first component of the attached pin assembly is formed of a first metallic material that defines a first coefficient of thermal expansion, the second component of the attached pin assembly is formed of a second metallic material that defines a second coefficient of thermal expansion, and the first coefficient of thermal expansion is greater than the second coefficient of thermal expansion.

13. The shroud assembly of claim 1, wherein, The first component defines a gap between itself and the shield segment within the attachment opening of the shield.

14. The shroud assembly of claim 1, wherein, The auxiliary attachment member includes a body that extends through the hollow core of the first member, and wherein the body defines a gap with the first member within the hollow core.

15. The shroud assembly of claim 1, wherein, The gas turbine engine includes a turbine section, and the shield section is configured to be located within the turbine section.

16. An attachment pin assembly characterized by, include A first component, the first component including a first body defining a hollow core, the first body having a first portion adapted to be disposed within a hanger attachment opening in a hanger wall and to be interference-fitted with the hanger wall, the first body further including a shoulder, the first component being further adapted to extend through a cover attachment opening in a cover wall; and The second component includes a second body that extends between a first end and a second end and includes an edge at the first end; During assembly, the second body extends through the hollow core of the first member, and an auxiliary attachment member is provided with the second body and adapted to retain the second body within the first body.

17. The attachment pin assembly of claim 16, wherein, The first body includes a first segment having a first segment diameter, and the shoulder has a width greater than the first segment diameter.

18. The attachment pin assembly according to claim 16, characterized in that, The auxiliary attachment member is positioned against the second distal end of the first member.

19. The cotter pin assembly of claim 16, wherein, The first component of the attached pin assembly is formed of a first metallic material that defines a first coefficient of thermal expansion, the second component of the attached pin assembly is formed of a second metallic material that defines a second coefficient of thermal expansion, and the first coefficient of thermal expansion is greater than the second coefficient of thermal expansion.

20. A method of attaching a shroud segment to a shroud hanger, characterized by, The method includes: Positioning the first component of the attachment pin assembly into the hanger attachment opening of the hanger wall and the cover attachment opening of the cover wall, wherein positioning the first component into the hanger attachment opening includes pressing the first component into the hanger attachment opening; Positioning the second component through the hollow core of the first component, wherein positioning the second component through the hollow core includes positioning the edge of the first component located at a first end of the first component against the hanger wall; and The auxiliary attachment member is attached to the second end of the first member.

Images