Coupling assembly for a turbine engine

Abstract

A coupling assembly for a turbine engine. The coupling assembly includes a cold side component, a hot side component, and a fastening mechanism. The cold side component and the hot side component together at least partially form a combustion chamber. The fastening mechanism couples the hot side component to the cold side component. The fastening mechanism includes a stud disposed through the cold side component and a cap positioned on the stud. The cap defines a hollow interior and includes one or more first cap cooling holes. The one or more first cap cooling holes are operable to direct cooling air into the hollow interior such that the hollow interior provides a cushion of air between the combustion chamber and the stud.

Description

Technical Field

[0001] This disclosure generally relates to coupling components for turbine engines. Background Technology

[0002] The turbine engine may include a combustion section with a combustor that generates hot combustion gases that are discharged into the turbine section of the turbine engine. The combustion section may include cold-side and hot-side components connected together by a coupling assembly. Attached Figure Description

[0003] The foregoing and other features and advantages will become apparent from the more specific description of the various exemplary embodiments below, as shown in the accompanying drawings, wherein similar reference numerals generally denote the same, functionally similar and / or structurally similar elements.

[0004] Figure 1 It is a schematic cross-sectional view of a turbine engine taken along the centerline axis of the turbine engine according to the present disclosure.

[0005] Figure 2 Based on this disclosure Figure 1 A schematic partial cross-sectional view of an exemplary combustion section of a turbine engine.

[0006] Figure 3 It is a section taken at the centerline axis of the turbine engine according to this disclosure for use Figure 1 A schematic partial cross-sectional view of a portion of the connecting assembly of the combustion section of a turbine engine.

[0007] Figure 4 It is based on this disclosure in isolation from Figure 3 A top view of the gasket of the connecting component.

[0008] Figure 5 It is a section taken at the centerline axis of the turbine engine according to another embodiment for... Figure 1 A schematic partial cross-sectional view of a portion of the connecting assembly of the combustion section of a turbine engine.

[0009] Figure 6 It is a section taken at the centerline axis of the turbine engine according to another embodiment for... Figure 1 A schematic partial cross-sectional view of a portion of the connecting assembly of the combustion section of a turbine engine.

[0010] Figure 7 It is a section taken at the centerline axis of the turbine engine according to another embodiment for... Figure 1 A schematic partial cross-sectional view of a portion of the connecting assembly of the combustion section of a turbine engine.

[0011] Figure 8AIt is a section taken at the centerline axis of the turbine engine according to another embodiment for... Figure 1 A schematic partial cross-sectional view of a portion of the connecting assembly of the combustion section of a turbine engine.

[0012] Figure 8B It is based on this disclosure in isolation from Figure 8A A top view of the multiple flexible plates of the connecting components.

[0013] Figure 9A It is a section taken at the centerline axis of the turbine engine according to another embodiment for... Figure 1 A schematic partial cross-sectional view of a portion of the connecting assembly of the combustion section of a turbine engine.

[0014] Figure 9B It is isolated from another embodiment Figure 9A A top view of the multiple flexible plates of the connecting components. Detailed Implementation

[0015] Additional features, advantages, and embodiments of this disclosure will become apparent or apparent from consideration of the following detailed description, accompanying drawings, and claims. Furthermore, the foregoing summary and the following detailed description of this disclosure are exemplary and intended to provide further explanation without limiting the scope of the claimed disclosure.

[0016] Various embodiments of this disclosure are discussed in detail below. Although specific embodiments are discussed, they are for illustrative purposes only. Those skilled in the art will recognize that other components and constructions can be used without departing from the spirit and scope of this disclosure.

[0017] As used herein, the terms “first,” “second,” “third,” and “fourth” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

[0018] 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 from which the fluid flows.

[0019] The terms "front" and "rear" refer to relative positions within a turbine engine or carrier, and specifically to the normal operating posture of the turbine engine or carrier. For example, for a 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] Unless otherwise stated herein, the terms “connection,” “fixation,” “attachment,” “linkage,” etc., refer to both direct connection, fixation, attachment, or linking, and indirect connection, fixation, attachment, or linking through one or more intermediate components or features.

[0021] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0022] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends arcuately around the centerline of the turbine engine.

[0023] As used in this article, "hot side" is the side of a turbine engine's combustion section that is exposed to or otherwise oriented toward the combustion chamber facing the combustion section.

[0024] As used in this article, the "cold side" is the side of the combustion section of a turbine engine that is not exposed to or otherwise oriented toward the combustion chamber.

[0025] This disclosure provides a coupling assembly for a combustion section of a turbine engine. The combustion section includes a cold-side component and a hot-side component coupled to the cold-side component. The cold-side component and the hot-side component may be parts of a bushing and / or annular dome assembly of the combustion section. For example, the cold-side component may be a housing of a bushing, while the hot-side component may be a heat shield including tiles or panels coupled to the housing. In some embodiments, the cold-side component is an annular dome assembly, and the hot-side component is a deflector assembly including tiles or panels coupled to the annular dome assembly. The hot-side component protects or shields the cold-side component from the hot combustion gases inside the combustion chamber of the combustion section. The coupling assembly includes one or more fastening mechanisms positioned around the cold-side component to fasten and secure the hot-side component to the hot-side component.

[0026] When assembling cold-side and hot-side components, one or more fastening mechanisms may be exposed to hot combustion gases. For example, one or more fastening mechanisms may include studs that are part of a panel, and these studs may experience damage due to insufficient cooling. Therefore, the combustion section may experience thermal damage around the fastening mechanisms due to their proximity to hot combustion gases and the lack of adequate cooling around them. In some cases, thermal damage around the fastening mechanisms may lead to fatigue, failure, or wear of a portion of the combustion section surrounding the fastening mechanisms. Therefore, embodiments of this disclosure provide improved coupling assemblies and cooling arrangements for the fastening mechanisms around the combustion section, compared to combustion sections that do not benefit from this disclosure, to improve the durability and lifespan of such combustion sections.

[0027] This disclosure avoids direct exposure of hot combustion gases to studs by providing hollow studs and / or hollow caps positioned on the studs. Cooling air is directed through the hollow studs and / or through the hollow caps. This disclosure provides various arrangements for attaching the hollow caps to the studs. This disclosure also provides for avoiding exposure of hot combustion gases by shifting the position of the stud head from the hot side of the panel to the housing. Embodiments of this disclosure also include a plate for holding the panel to a cold-side component without using a rigid bolt connection. The plate may include multi-finger-like protrusions or projections that engage with the panel to hold the panel to the cold-side component without direct contact with the fastening mechanism of the panel. The plate may be made of a ceramic matrix composite or metal. Cooling air is directed through the plate. Therefore, compared to connection assemblies that do not benefit from this disclosure, this disclosure provides for reducing thermal gradients and preventing stress concentration in the area surrounding the fastening mechanism by promoting cooling of the panel through the caps and / or through the plate.

[0028] Now refer to the attached diagram, Figure 1 This is a schematic cross-sectional view of the turbine engine 10 taken along the centerline axis of the turbine engine 10 according to an embodiment of the present disclosure. Figure 1 As shown, the turbine engine 10 defines an axial direction A (extending parallel to the longitudinal centerline axis 12 provided for reference) and a radial direction R orthogonal to the axial direction A. Typically, the turbine engine 10 includes a fan section 14 and a core turbine engine 16 disposed downstream of the fan section 14.

[0029] The core turbine engine 16 shown typically includes a housing 18, which is substantially tubular and defines an annular inlet 20. Figure 1As schematically shown, the housing 18 surrounds the following components in a series flow relationship: a compressor section 21, which includes a turbocharger or low-pressure (LP) compressor 22, followed downstream by a high-pressure (HP) compressor 24; a combustion section 26; a turbine section 27, which includes a high-pressure (HP) turbine 28, followed downstream by a low-pressure (LP) turbine 30; and an exhaust nozzle section 32. A high-pressure (HP) shaft 34 or spool drives the HP turbine 28 to the HP compressor 24 so that the HP turbine 28 and HP compressor 24 rotate in unison. A low-pressure (LP) shaft 36 drives the LP turbine 30 to the LP compressor 22 so that the LP turbine 30 and LP compressor 22 rotate in unison. The compressor section 21, combustion section 26, turbine section 27, and exhaust nozzle section 32 together define the core airflow path.

[0030] for Figure 1 In the embodiment depicted, fan section 14 includes a fan 38 (e.g., a variable pitch fan) having a plurality of fan blades 40 spaced apart and coupled to disk 42. Figure 1 As shown, fan blades 40 extend outward from disk 42 generally in the radial direction R. Each fan blade 40 is operably coupled to an actuation member 44 by means of the fan blades 40, and the actuation member 44 is configured to uniformly change the pitch of the fan blades 40 relative to disk 42. The fan blades 40, disk 42, and actuation member 44 can rotate together via a fan shaft 45 about a centerline axis 12, which is powered by an LP shaft 36 across a power gearbox (also referred to as gearbox assembly 46). The gearbox assembly 46 is located in... Figure 1 The diagram is schematically shown. The gearbox assembly 46 includes a plurality of gears for adjusting the rotational speed of the fan shaft 45, and thus adjusting the rotational speed of the fan 38 relative to the LP shaft 36.

[0031] Still referencing Figure 1 In an exemplary embodiment, disk 42 is covered by a rotatable fan hub 48, which is aerodynamically shaped to facilitate airflow through a plurality of fan blades 40. Furthermore, fan section 14 includes an annular fan housing or nacelle 50 circumferentially surrounding at least a portion of fan 38 and / or core turbine engine 16. Nacelle 50 is supported relative to core turbine engine 16 by a plurality of circumferentially spaced outlet guide vanes 52. Additionally, a downstream section 54 of nacelle 50 extends above the outer portion of core turbine engine 16 to define a bypass airflow passage 56 therebetween.

[0032] During operation of the turbine engine 10, a certain amount of air 58 enters the turbine engine 10 through the inlet 60 of the nacelle 50 and / or fan section 14. As the certain amount of air 58 passes through the fan blades 40, a first portion of air 62 is directed or directed into the bypass airflow passage 56, while a second portion of air 64 is directed or directed into the upstream section of the core airflow path, or more specifically, into the annular inlet 20 of the LP compressor 22. The ratio between the first portion of air 62 and the second portion of air 64 is generally referred to as the bypass ratio. The pressure of the second portion of air 64 is then increased to form compressed air 65, and the compressed air 65 is directed through the HP compressor 24 and into the combustion section 26, where the compressed air 65 is mixed with fuel and burned to provide combustion gases 66.

[0033] Combustion gas 66 is directed into and expands through HP turbine 28, where a portion of the thermal and / or kinetic energy from the combustion gas 66 is extracted via a sequential stage of HP turbine stator blades 68 connected to housing 18 and HP turbine rotor blades 70 connected to HP shaft 34, thus rotating HP shaft 34 to support the operation of HP compressor 24. Combustion gas 66 is then directed into and expands through LP turbine 30. Here, a second portion of thermal and kinetic energy is extracted from the combustion gas 66 via a sequential stage of LP turbine stator blades 72 connected to housing 18 and LP turbine rotor blades 74 connected to LP shaft 36, thus rotating LP shaft 36 to support the operation of LP compressor 22 and the rotation of fan 38 via gearbox assembly 46.

[0034] Combustion gas 66 is then directed through the injection exhaust nozzle section 32 of the core turbine engine 16 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 62 increases significantly as it is directed through the bypass airflow passage 56 before exiting from the fan nozzle exhaust section 76 of the turbine engine 10, also providing propulsive thrust. The HP turbine 28, LP turbine 30, and injection exhaust nozzle section 32 at least partially define a hot gas path 78 for guiding combustion gas 66 through the core turbine engine 16.

[0035] Figure 1The turbine engine 10 depicted is merely an example. In other exemplary embodiments, the turbine engine 10 may have any other suitable configuration. For example, in other exemplary embodiments, the fan 38 may be constructed in any other suitable manner (e.g., as a fixed-pitch fan) and may also be supported using any other suitable fan frame configuration. Furthermore, in other exemplary embodiments, any other suitable number or configuration of compressors, turbines, shafts, or combinations thereof may be provided. In other exemplary embodiments, aspects of this disclosure may be incorporated into any other suitable turbine engine, such as a turbofan engine, propeller fan engine, turbojet engine, turboprop engine, and / or turboshaft engine.

[0036] Figure 2 It is based on the turbine engine 10 disclosed herein. Figure 1 This is a schematic partial cross-sectional view of a portion of an exemplary combustion section 26. Various embodiments of the combustion section 26 may further specifically define a rich-burner burner. However, other embodiments may define a lean-burner configuration. In an exemplary embodiment, the combustion section 26 includes an annular burner. Those skilled in the art will understand that the burner can be any other burner, including but not limited to a single-annular burner or a double-annular burner, a can-shaped burner, or a can-annular burner.

[0037] Figure 2 A combustion section 26 is shown, defining an axial direction A and a radial direction R orthogonal to the axial direction A. The combustion section 26 includes an outer liner 202 and an inner liner 204 disposed between an outer burner housing 206 and an inner burner housing 208. The outer liner 202 and the inner liner 204 are radially spaced apart such that a combustion chamber 210 is defined therebetween. An outer channel 212 is formed therebetween by the outer liner 202 and the outer burner housing 206, and an inner channel 214 is formed therebetween by the inner liner 204 and the inner burner housing 208. Each of the outer liner 202 and the inner liner 204 includes a housing 203 and a heat shield 205. In an exemplary embodiment, the outer liner 202 and the inner liner 204 (e.g., housing 203 and heat shield 205) are generally cylindrical, but any known shape for burner bushings may be used.

[0038] The heat shield 205 includes one or more tiles or panels 207 disposed on and connected to the hot side of the housing 203. That is, the panels 207 of the heat shield 205 are connected to the side of the housing 203 that is directly exposed to the combustion chamber 210. Figure 2Three panels 207 of the heat shield 205 are depicted, but the heat shield 205 may include any number of panels 207 as needed. The housing 203 is made of, for example, a non-ceramic material (such as metal). The panels 207 of the heat shield 205 are made of, for example, a ceramic material. In some embodiments, the panels 207 are ceramic matrix composites (CMC). Therefore, the heat shield 205 provides shielding for the housing 203, improving the lifespan of the housing 203, thereby improving the lifespan of the outer liner 202 and the inner liner 204.

[0039] Combustion section 26 may also include a burner assembly 218, which includes an annular dome assembly 220 mounted upstream of combustion chamber 210. The burner assembly 218 is configured to connect to the front ends of outer liner 202 and inner liner 204. More specifically, the burner assembly 218 includes an inner annular dome 222 attached to the front end of inner liner 204 and an outer annular dome 224 attached to the front end of outer liner 202.

[0040] Combustion section 26 can be configured to start from turbine engine 10 ( Figure 1 HP compressor 24 ( Figure 1 The outlet of the annular dome assembly 220 receives compressed air 65. To aid in guiding the compressed air 65, the annular dome assembly 220 may further include an inner shroud 228 and an outer shroud 230, which may be coupled to the upstream ends of the inner liner 204 and outer liner 202, respectively. In this respect, an annular opening 232 formed between the inner shroud 228 and the outer shroud 230 allows compressed fluid (e.g., compressed air 65) to enter the combustion section 26 through a diffuser opening in a direction generally indicated by the flow direction 234. The compressed air 65 can enter a cavity 236 defined at least partially by the annular dome assembly 220. In various embodiments, the cavity 236 is more specifically defined between the inner annular dome 222 and the outer annular dome 224, and between the inner shroud 228 and the outer shroud 230. As will be discussed in more detail below, a portion of the compressed air 65 in the cavity 236 can be used for combustion, while another portion can be used to cool the combustion section 26.

[0041] In addition to directing air into cavity 236 and combustion chamber 210, inner shroud 228 and outer shroud 230 may direct a portion of compressed air 65 around the outside of combustion chamber 210 to facilitate cooling of outer liner 202 and inner liner 204. For example, as Figure 2 As shown, a portion of the compressed air 65 can flow around the combustion chamber 210, as indicated by the outer channel flow direction 238 and the inner channel flow direction 240, to provide cooling air to the outer channel 212 and the inner channel 214, respectively.

[0042] In some exemplary embodiments, the inner annular dome 222 may be integrally formed as a single annular component, and similarly, the outer annular dome 224 may also be integrally formed as a single annular component. In yet other embodiments, the inner annular dome 222 and the outer annular dome 224 may be formed together as a single integral component. In various embodiments, an annular dome assembly 220 including one or more of the inner annular dome 222, the outer annular dome 224, the outer liner 202, or the inner liner 204 may be formed as a single integral component. In other exemplary embodiments, the inner annular dome 222 or the outer annular dome 224 may alternatively be formed from one or more components joined in any suitable manner. For example, with respect to the outer annular dome 224, in some exemplary embodiments, the outer cover 230 may be formed separately from the outer annular dome 224 and attached to the front end of the outer annular dome 224 using, for example, welding, mechanical fasteners, adhesives or bonding agents, or composite layup processes. Additionally or alternatively, the inner annular dome 222 may have a similar construction.

[0043] The combustor assembly 218 also includes a plurality of mixer assemblies 242 circumferentially spaced between the outer annular dome 224 and the inner annular dome 222. In this respect, the annular dome assembly 220 defines an opening in which a cyclone, vortex, or mixer assembly 242 is mounted, attached, or otherwise integrated to introduce an air / fuel mixture into the combustion chamber 210. Notably, compressed air 65 can be directed from the combustion section 26 into or through one or more mixer assemblies 242 to support combustion in the upstream end of the combustion chamber 210.

[0044] Liquid or gaseous fuel is delivered to combustion section 26 via a fuel distribution system (not shown), wherein the liquid or gaseous fuel is introduced from the front end of the burner in the form of a highly atomized spray from a fuel nozzle. In an exemplary embodiment, each mixer assembly 242 defines an opening for receiving fuel injectors 246 (details omitted for clarity). The fuel injectors 246 inject fuel in a generally axial direction A and a generally radial direction R, wherein the fuel swirls together with incoming compressed air 65. Thus, each mixer assembly 242 receives compressed air 65 from an annular opening 232 and fuel from the corresponding fuel injector 246. The fuel and pressurized air swirl and mix together through the mixer assembly 242, and the resulting fuel / air mixture is discharged into combustion chamber 210 for its combustion. The mixer assembly 242 and the fuel injector 246 may, as needed, comprise any type of mixer assembly and fuel injector, respectively.

[0045] Combustion section 26 may also include an ignition assembly (e.g., one or more igniters extending through liner 202) suitable for igniting the fuel-air mixture. For clarity, Figure 2 Details of the fuel injectors and ignition assembly are omitted. Once ignited, the resulting hot combustion gases can flow through the combustion chamber 210 in a generally axial direction A, and enter and pass through the turbine engine 10 ( Figure 1 Turbine section 27 () Figure 1 In turbine section 27, a portion of the thermal or kinetic energy from the combustion gas 66 is extracted, as described above. More specifically, the combustion gas 66 may flow into an annular first-stage turbine nozzle 248. As generally understood, the first-stage turbine nozzle 248 is defined by an annular flow passage comprising a plurality of radially extending, circularly spaced nozzle blades 250 that deflect the gas, causing it to flow at an angle and impinge on the HP turbine 28. Figure 1 HP turbine rotor blades 70 ( Figure 1 )superior.

[0046] Each dome (e.g., inner annular dome 222 and outer annular dome 224) has a heat shield, such as a deflector assembly 260, which thermally insulates the annular dome assembly 220 from the extremely high temperatures (e.g., with combustion gases 66) generated in the combustion chamber 210 during engine operation. The inner annular dome 222, outer annular dome 224, and deflector assembly 260 may define a plurality of openings 244 for receiving the mixer assembly 242. As shown, in one embodiment, the plurality of openings 244 are circular. In other embodiments, the plurality of openings 244 are oval, elliptical, polygonal, rectangular, or other non-circular cross-sections. The deflector assembly 260 is mounted on the combustion chamber side (e.g., the hot side) of the annular dome assembly 220.

[0047] The deflector assembly 260 includes one or more tiles or panels 261 arranged on and connected to the hot side of the annular dome assembly 220. That is, the panel 261 of the deflector assembly 260 is connected to the side of the annular dome assembly 220 that is directly exposed to the combustion chamber 210. Figure 2 Two panels 261 of the deflector assembly 260 are depicted, but the deflector assembly 260 may include any number of panels 261 as needed. The panels 261 of the deflector assembly 260 are made of, for example, a ceramic material. In some embodiments, the panels 261 are ceramic matrix composites (CMC). Thus, the deflector assembly 260 provides shielding for the annular dome assembly 220, thereby improving the lifetime of the annular dome assembly 220.

[0048] Figures 3 to 9B The description of the turbine engine 10 ( Figure 1 The section taken at the centerline axis of the turbine engine 10 ( Figure 1 Combustion section 26 ( Figure 1 and Figure 2Various embodiments of the connecting components. Figures 3 to 9B The connecting components can be used for the outer liner 202 ( Figure 2 ), lining 204 ( Figure 2 ), Annular dome assembly 220 ( Figure 2 ), and / or combustion section 26 or any other component of the turbine engine 10. Each of the coupling assemblies detailed herein includes coupling a hot-side component to a cold-side component. As used herein, "hot-side" refers to combustion section 26 ( Figure 2 The "cold side" is the side of combustion section 26 that is exposed to or otherwise oriented toward the combustion chamber 210, while the "cold side" is the side of combustion section 26. Figure 2 The cold-side component is not exposed to or otherwise oriented toward the side facing the combustion chamber 210. In an exemplary embodiment, the cold-side component is the outer liner 202 ( Figure 2 ) or lining 204 ( Figure 2 ) outer shell 203 ( Figure 2 The heat-side component is heat shield 205. Figure 2 In some embodiments, the cold-side component is an inner annular dome 222. Figure 2 ) and / or outer annular dome 224 ( Figure 2 The hot-side component is the deflector assembly 260. Figure 2 ). Figures 3 to 9B It includes many identical or similar parts and functions. Unless otherwise stated, similar reference numerals indicate similar features and functions between the figures. Further details are provided below. Figures 3 to 9B Examples of implementations.

[0049] Figure 3 According to this disclosure, in the turbine engine 10 ( Figure 1 The section taken at the centerline axis of the turbine engine 10 ( Figure 1 The combustion section () Figure 1 and Figure 2 A schematic partial cross-sectional view of a portion of the connecting component 300. Figure 3 A coupling assembly 300 is shown, which includes a cold-side component 302 and a hot-side component 304. The hot-side component 304 includes one or more tiles or panels 306 disposed on and connected to the hot side of the cold-side component 302. That is, the panel 306 of the hot-side component 304 is connected to the side of the cold-side component 302 exposed to the combustion chamber 210. Figure 3 A panel 306 is depicted, but the hot-side component 304 may include any number of panels 306 as needed.

[0050] The cold-side component 302 includes one or more cold-side component cooling holes 308, and the hot-side component 304 includes one or more hot-side component cooling holes 310. In this way, cooling air 380 (e.g., Figure 2 Compressed air (65) can pass through the cold-side component 302 and can pass through the hot-side component 304, as further detailed below. One or more cold-side component cooling holes 308 are impingement cooling holes configured to pass generally radially through the cold-side component 302. One or more hot-side component cooling holes 310 are thin-film cooling holes configured to pass through the hot-side component 304 at an angle. The one or more cold-side component cooling holes 308 and the one or more hot-side component cooling holes 310 may each comprise any number of cooling holes formed in any orientation relative to the cold-side component 302 and the hot-side component 304. In some embodiments, the one or more cold-side component cooling holes 308 and the one or more hot-side component cooling holes 310 are also circumferentially angled to operatively guide the cooling air tangentially.

[0051] The coupling assembly 300 includes one or more fastening mechanisms 320 for attaching and connecting the cold-side component 302 to the hot-side component 304 (e.g., each of the panels 306 of the hot-side component 304). That is, the hot-side component 304 is coupled to the cold-side component 302 via one or more fastening mechanisms 320. Although Figure 3 A fastening mechanism 320 is shown, but one or more fastening mechanisms 320 may be included in any number as needed. A gap or space 322 is formed between the cold-side component 302 and the hot-side component 304. For example, a space 322 is formed between the radially outer surface of the hot-side component 304 and the radially inner surface of the cold-side component 302.

[0052] One or more fastening mechanisms 320 include a stud 324 and a cap 326. The one or more fastening mechanisms 320 may include any type of known fastening mechanism, such as a bolt, screw, nut, rivet, etc. The stud 324 includes a generally cylindrical body defining the stud 324. The cap 326 includes a generally truncated conical shape having a hollow interior 328, such that the cap 326 includes an outer surface 330 and an inner surface 332. The outer surface 330 and the inner surface 332 together form a thin wall 333, such that the hollow interior 328 includes a shape generally corresponding to the shape of the cap 326. In this way, the hollow interior 328 is a closed hollow interior 328. Therefore, the hollow interior 328 defines the space in the turbine engine 10 ( Figure 1During operation, a reservoir filled with cooling air is provided, as further detailed below. The stud 324 and cap 326 can include any shape and / or any size as needed. The cap 326 and the hollow interior 328 each include a diameter larger than the outer diameter of the stud 324. The stud 324 is inserted through a first fastening mechanism orifice 334 of the cold-side component 302, and the cap 326 is engaged with the stud 324. When the cap 326 is engaged with the stud 324, the cap 326 is inserted and positioned in a second fastening mechanism orifice 336 of the hot-side component 304. In this way, the cap 326 seals the second fastening mechanism orifice 336, preventing hot combustion gases in the combustion chamber 210 from leaking through the second fastening mechanism orifice 336. The cap 326 is positioned between the stud 324 and the combustion chamber 210, such that the stud 324 is insulated from the combustion chamber 210. In this way, the stud 324 is not directly exposed to the combustion chamber 210. For example, the stud 324 is radially spaced from the combustion chamber 210.

[0053] The cap 326 is connected to the stud 324 via a first threaded connection 338. In some embodiments, the cap 326 is press-fitted to the stud 324 without using a threaded connection. In some embodiments, the cap 326 and the stud 324 are integrally formed, such that the cap 326 and the stud 324 form a single integral component. One or more fastening mechanisms 320 also include a nut 340 connected to the stud 324 on the cold side of the stud 324. The nut 340 is connected to the stud 324 via a second threaded connection 342. In some examples, the nut 340 is press-fitted to the stud 324. When the nut 340 is tightened, the second threaded connection 342 pulls the stud 324 and the cap 326 through a second fastening mechanism orifice 336, thereby tightening and securing the fastening mechanism 320 to securely connect the hot-side component 304 to the cold-side component 302.

[0054] The cap 326 includes a stud receiving portion 344, which defines a stud opening 346 for receiving a portion of the stud 324. The stud receiving portion 344 and the stud opening 346 are sized and shaped to receive the stud 324. Figure 3 A stud receiving portion 344 is shown, comprising a solid annular body surrounding a stud 324. In some embodiments, a cap 326 may define a radial clearance or radial space around the stud receiving portion 344 for additional cooling, as described below. Figure 5 Further details: The stud receiving portion 344 extends from the cold side of the inner surface 332 and enters the hollow interior 328 of the cap 326. The stud receiving portion 344 is spaced apart from the hot side of the inner surface 332. In this way, the hollow interior 328 surrounds the stud receiving portion 344.

[0055] Cap 326 may include cap insert 348, which is threaded onto stud 324 at a first threaded connection 338. The stud opening 346 is sized and shaped to receive cap insert 348 for engaging cap 326 to stud 324. For example, cap 326 is press-fitted onto cap insert 348. In some embodiments, cap insert 348 is integrally formed with cap 326, such that cap insert 348 and cap 326 form a single integral part. In some embodiments, cap insert 348 is welded, brazed, or otherwise attached to cap 326 and / or stud 324. In some embodiments, cap insert 348 is press-fitted onto stud 324. In some embodiments, cap insert 348, cap 326, and stud 324 are integrally formed together, such that cap insert 348, cap 326, and stud 324 form a single integral part. In some embodiments, cap 326 is directly engaged to stud 324 without using a cap insert. For example, the size and shape of the stud receiving portion 344 and the stud opening 346 of the cap 326 can be designed to directly receive the stud 324. In some embodiments, the stud receiving portion 344 includes threads such that the cap 326 is threaded to engage the cap 326 to the stud 324 at a first threaded connection 338 via the threads of the stud receiving portion 344.

[0056] The cap 326 includes one or more first cap cooling holes 350 extending therethrough, and one or more second cap cooling holes 352 extending therethrough. Each of the one or more first cap cooling holes 350 and one or more second cap cooling holes 352 extends from the outer surface 330 of the cap 326 through a thin wall 333 to the inner surface 332 of the cap 326. When one or more fastening mechanisms 320 are secured, the one or more first cap cooling holes 350 are disposed in the space 322. In this manner, the one or more first cap cooling holes 350 provide fluid communication from the space 322 to the hollow interior 328 of the cap 326. The one or more second cap cooling holes 352 are disposed on the hot side of the cap 326. In this manner, the one or more second cap cooling holes 352 provide fluid communication from the hollow interior 328 of the cap 326 to the combustion chamber 210. In some embodiments, the one or more first cap cooling holes 350 and / or the one or more second cap cooling holes 352 are circumferentially angled to operatively guide cooling air tangentially to the hollow interior 328 or the combustion chamber 210, respectively.

[0057] The connecting assembly 300 also includes a washer 360 disposed in a space 322 between the cold-side component 302 and the hot-side component 304. The washer 360 includes a first washer surface 362 and a second washer surface 364 opposite to the first washer surface 362. The washer 360 is a flexible washer, such that it can bend or otherwise buckle with movement of the cold-side component 302 and / or the hot-side component 304. The washer 360 includes a flat portion 366 and a curved portion 368. The flat portion 366 includes a generally straight, flat portion of the washer 360. The curved portion 368 includes one or more bends and defines a generally frustoconical shape around a portion of a cap 326 within the space 322.

[0058] When the connecting assembly 300 is assembled, the cold side of the outer surface 330 of the cap 326 contacts the second washer surface 364 at the flat portion 366 of the washer 360, such that the washer 360 is positioned and secured between the cold-side component 302 and the cap 326. A curved portion 368 bends from the flat portion 366, extending to the cold side of the hot-side component 304. In this manner, the first washer surface 362 contacts the cold-side component 302, while the second washer surface 364 contacts the cap 326 (e.g., at the flat portion 366) and the hot-side component 304 (e.g., at the curved portion 368). Therefore, the washer 360 maintains the space 322 between the cold-side component 302 and the hot-side component 304, such that the washer 360 prevents the hot-side component 304 from being in the combustion zone 26 ( Figure 2 During operation, it comes into contact with the cold side component 302.

[0059] Washer 360 includes a washer stud hole 370 for receiving a stud 324 passing through it. In this manner, washer 360 is secured by fastening mechanism 320 when fastening mechanism 320 is assembled and fastened as described above. Washer 360 includes one or more washer cooling holes 372, each extending from a first washer surface 362 through washer 360 to a second washer surface 364. One or more washer cooling holes 372 are disposed in a curved portion 368 of washer 360. When coupling assembly 300 is assembled, one or more washer cooling holes 372 are disposed within space 322. In this manner, cooling air 380 is operably guided from space 322 through washer 360 and between washer 360 and cap 326, as further detailed below. The one or more washer cooling holes 372 may include any number of cooling holes as needed.

[0060] In operation, cooling air 380 is operably allowed to flow from the cold side of the cold-side component 302 through one or more cold-side component cooling holes 308 and into the space 322. In an exemplary embodiment, the cooling air 380 is compressed air 65 received from the compressor section of the turbine engine. Figure 2However, cooling air 380 can be supplied from any source as needed. Cooling air 380 is operably guided from space 322 through one or more gasket cooling holes 372, and between gasket 360 and cap 326. Simultaneously, cooling air 380 is operably guided from space 322 through one or more hot-side component cooling holes 310 and enters combustion chamber 210 for thin-film cooling of hot-side component 304. Cooling air 380 is operably guided from between gasket 360 and cap 326 through one or more first cap cooling holes 350 and enters the hollow interior 328 of cap 326. In this way, cooling air 380 fills the hollow interior 328. Cooling air 380 is operably guided from the hollow interior 328 through one or more second cap cooling holes 352 and enters combustion chamber 210 for thin-film cooling of cap 326.

[0061] Therefore, the cap 326 with a hollow interior 328, one or more first cap cooling holes 350, and one or more second cap cooling holes 352 provide a cooling arrangement that prevents the stud 324 from being directly exposed to the hot combustion gases in the combustion chamber 210. Cooling air 380 in the hollow interior 328 provides a buffer between the combustion chamber 210 and the stud 324. Thin-film cooling of the cap 326 provides a layer of cooling air 380 between the hot side of the outer surface 330 of the cap 326 and the hot airflow (e.g., hot combustion gases). Thin-film cooling thus protects the cap 326, and the buffer of cooling air 380 in the hollow interior 328 of the cap 326 protects the stud 324 from exposure to hot combustion gases and provides additional cooling for the stud 324. Therefore, the thermal gradient in the region of one or more fasteners 320 is reduced, thereby reducing stress concentration on one or more fasteners 320. Therefore, the coupling assembly 300 provides to reduce damage to the hot-side component 304 and / or the cold-side component 302 and / or reduce failure of the hot-side component 304 and / or the cold-side component 302 in the area surrounding one or more fastening mechanisms 320.

[0062] Figure 4 It is based on the present disclosure isolated from the connection component 300 ( Figure 3 A top view of the washer at 360 degrees. Figure 4 A washer 360 is shown in an unbent orientation, causing the washer 360 to flatten. The washer 360 can be bent or otherwise deformed to form... Figure 3The washer 360 is generally truncated conical in shape. In the unbent configuration, the washer 360 defines a generally circular shape. The washer 360 can include any shape and / or any size as needed. The washer 360 includes an outer edge 474 defining the outer periphery of the washer 360. The washer stud hole 370 is located at the radial center of the washer 360. One or more washer cooling holes 372 are disposed radially outward from the washer stud hole 370 and circumferentially around the washer 360. In this way, one or more washer cooling holes 372 are located between the outer edge 474 and the washer stud hole 370.

[0063] The gasket 360 also includes one or more gasket grooves 476 circumferentially disposed around the outer edge 474. Each gasket groove 476 extends radially inward from the outer edge 474 to a corresponding gasket cooling hole 372. In this way, the one or more gasket grooves 476 allow the gasket 360 to bend in the region surrounding the outer edge 474, such that the gasket 360 fits into the cold-side component 302. Figure 3 ) and hot-side component 304 ( Figure 3 Between. The bending of the gasket 360 allows the gasket 360 to buckle or compress, so that the hot side component 304 can move radially relative to the cold side component 302 and prevents the hot side component 304 from contacting the cold side component 302.

[0064] Figure 5 According to another embodiment, in turbine engine 10 ( Figure 1 The section taken at the centerline axis of the turbine engine 10 ( Figure 1 The combustion section () Figure 1 and Figure 2 A schematic partial cross-sectional view of a portion of the coupling assembly 500. The coupling assembly 500 and... Figure 3 The coupling assembly 300 is substantially similar. For example, the coupling assembly 500 includes one or more fastening mechanisms 520, which include a stud 324 and a cap 526. The cap 526 includes a generally truncated conical shape having a hollow interior 528, such that the cap 526 includes an outer surface 530 and an inner surface 532. The outer surface 530 and the inner surface 532 together form a thin wall 533, such that the hollow interior 528 includes a shape generally corresponding to the shape of the cap 526. In this way, the hollow interior 528 is a closed hollow interior 528. Therefore, the hollow interior 528 is defined in the turbine engine 10 ( Figure 1During operation, a reservoir filled with cooling air is provided, as further detailed below. The cap 526 and the hollow interior 528 each include a diameter larger than the outer diameter of the stud 324. The cap 526 is positioned between the stud 324 and the combustion chamber 210 such that the stud 324 is insulated from the combustion chamber 210. In this way, the stud 324 is not directly exposed to the combustion chamber 210. For example, the stud 324 is radially spaced from the combustion chamber 210. The cap 526 also includes one or more first cap cooling holes 550 and one or more second cap cooling holes 552. However, the cap 526 differs from... Figure 3 Hat 326.

[0065] Cap 526 includes a stud receiving portion 544 that defines a stud opening 546 for receiving a portion of stud 324. Cap 526 defines a radial clearance or radial space 547 around stud receiving portion 544. Radial space 547 extends radially from an outer surface 530 of stud receiving portion 544 to another portion of the outer surface 530 of cap 526. For example, outer surface 530 defines a generally U-shaped portion in the region of radial space 547. Radial space 547 may include any size and / or any shape as needed. When coupling assembly 500 is assembled, stud receiving portion 544 abuts washer 360. Cap 526 also includes one or more third cap cooling holes 553 in the generally U-shaped portion of outer surface 530. A portion of the cold side of outer surface 530 of cap 526 is spaced apart from washer 360.

[0066] In operation, cooling air 380 is operably guided between the washer 360 and the cold side of the outer surface 530 of the cap 526, and into the radial space 547 to cool the stud receiving portion 544, thereby cooling the stud 324. Cooling air 380 is operably guided from the radial space 547 through one or more third cap cooling holes 553 and into the hollow interior 528. In this way, cooling air 380 fills the hollow interior 528 to provide a buffer between the combustion chamber 210 and the stud 324. Cooling air 380 is operably guided from the hollow interior 528 through one or more second cap cooling holes 552 and into the combustion chamber 210 to provide thin-film cooling, as described above regarding... Figure 3 Detailed. Therefore, the radial space 547 provides additional cooling around the stud receiving portion 544, thereby providing additional cooling around the stud 324. The radial space 547 also provides additional flexibility, allowing the cap 526 to buckle or compress in the region surrounding the radial space 547. Therefore, if hot combustion gases cause the cap 526 to move, the stress and strain on the stud 324 are reduced due to the movement of the cap 526.

[0067] Figure 6 According to another embodiment, in turbine engine 10 ( Figure 1The section taken at the centerline axis of the turbine engine 10 ( Figure 1 Combustion section 26 ( Figure 1 and Figure 2 A schematic partial cross-sectional view of a portion of the coupling assembly 600. The coupling assembly 600 includes a cold-side component 302 and a hot-side component 604. The hot-side component 604 includes one or more tiles or panels 606 disposed on and connected to the hot side of the cold-side component 302. Figure 6 A panel 606 is depicted, but the hot-side component 604 may include any number of panels 606 as needed. The coupling assembly 600 includes one or more fastening mechanisms 620 for attaching and connecting the hot-side component 604 to the cold-side component 302. The hot-side component 604 includes one or more hot-side component cooling holes 610.

[0068] Each panel 606 of the hot-side component 604 includes a recessed portion 612 in a region surrounding each of one or more fastening mechanisms 620. The recessed portion 612 includes a portion of the respective panel 606 that is hot-side recessed relative to the hot-side component 604. For example, the recessed portion 612 may extend from the hot-side component 604 toward the cold-side component 302. The recessed portion 612 may be the same as or substantially similar to the recess described in U.S. Application No. 17 / 812,897, the contents of which are incorporated herein by reference in their entirety. The respective fastening mechanism 620 may be centrally located in the recessed portion 612 such that the respective fastening mechanism 620 is hot-side recessed or otherwise retracted relative to the hot-side component 604. The respective fastening mechanism 620 may be located anywhere within the recessed portion 612 as needed. Furthermore, while the recessed portion 612 in the exemplary embodiment is generally circular in shape, the recessed portion 612 surrounding each fastening mechanism 620 may include any shape or size as needed. A gasket 360 is connected between the hot side of the cold-side component 302 and the cold side of the recess 612. The gasket 360 has a diameter larger than the diameter of the recess 612, such that the gasket 360 circumferentially surrounds the recess 612. The recess 612 includes one or more recess cooling holes 614 extending therethrough. The one or more recess cooling holes 614 extend from the cold side of the recess 612 to the hot side of the recess 612.

[0069] The recessed portion 612 also includes a stud receiving portion 616 defining a gap or space, the size and shape of which are designed to receive a stud 624 of a corresponding fastening mechanism 620. One or more fastening mechanisms 620 include a stud 624 and a cap 626. The stud 624 includes one or more stud cooling holes 625 extending therethrough. The one or more stud cooling holes 625 extend longitudinally from the cold side of the stud 624 through the length of the stud 624 to the hot side of the stud 624. In this way, the one or more stud cooling holes 625 provide fluid communication from the cold side of the cold side component 302 to the hollow interior 628 of the cap 626, as further detailed below. The stud 624 also includes a cap receiving portion 627, the size and shape of which are designed to receive part of the cap 626, as detailed below.

[0070] The cap 626 includes a generally truncated conical shape with a hollow interior 628, such that the cap 626 includes an outer surface 630 and an inner surface 632. The outer surface 630 and the inner surface 632 together form a thin wall 633, such that the hollow interior 628 includes a shape generally corresponding to the shape of the cap 626. In this way, the hollow interior 628 is a closed hollow interior 628. Therefore, the hollow interior 628 is defined in the turbine engine 10 ( Figure 1 The reservoir is filled with cooling air during operation, as further detailed below. The stud 624 and cap 626 can include any shape and / or any size as needed. The cap 626 and the hollow interior 628 each include a diameter larger than the outer diameter of the stud 624. The cap 626 is engaged with the stud 624. When the cap 626 is engaged with the stud 624, the cap 626 is inserted into and positioned within a recessed space 636 defined by a recessed portion 612 of the hot-side component 604. A portion of the cap 626 is spaced apart from the cold side of the recessed portion 612, such that a gap or space 647 is defined between the cap 626 and the recessed portion 612. The cap 626 is positioned between the stud 624 and the combustion chamber 210 such that the stud 624 is insulated from the combustion chamber 210. In this way, the stud 624 is not directly exposed to the combustion chamber 210. For example, the stud 624 is radially spaced from the combustion chamber 210.

[0071] The cap 626 includes a cap extension 644, which is sized and shaped to fit into a cap receiving portion 627 of the stud 624. The cap extension 644 extends from the cold side of the outer surface 630 of the cap 626. The cap extension 644 is inserted through an aperture in the recess 612 and received by the cap receiving portion 627 of the stud 624. When assembled, the cold side of the outer surface 630 of the cap 626 abuts the hot side of the recess 612. The hot side of the outer surface 630 of the cap 626 is substantially flush with or substantially in line with the hot side of the hot side member 604. In some embodiments, the cap 626 may extend beyond (e.g., radially inward) the hot side of the hot side member 604. In some embodiments, the cap 626 extends to a radially outward position from the hot side of the hot side member 604.

[0072] The recessed portion 612 includes an insert 648 disposed within the stud receiving portion 616 for connecting the stud 624 and the cap 626. The stud 624 includes threads such that it is connected to the insert 648 at a first threaded connection 638 via a corresponding thread on the insert 648. The stud 624 also includes threads such that it is connected to the nut 640 at a second threaded connection 642 via a corresponding thread on the nut 640. The cap 626 includes threads such that it is connected to the insert 648 at a third threaded connection 645 via a corresponding thread on the insert 648. For example, the cap 626 is connected to the insert 648 via threads on a cap extension 644. In some embodiments, the stud 624 and / or the cap 626 are press-fitted into the insert 648 without using a threaded connection. Any threaded connection may include other types of connections, such as press fit, welding, brazing, adhesive, etc. In some embodiments, the coupling assembly 600 does not include the insert 648 and the cap 626 is directly coupled to the stud 624.

[0073] The cap 626 includes one or more first cap cooling holes 650 extending therethrough, one or more second cap cooling holes 652 extending therethrough, and one or more third cap cooling holes 653 extending therethrough. Each of the one or more first cap cooling holes 650, one or more second cap cooling holes 652, and one or more third cap cooling holes 653 extends from the outer surface 630 of the cap 626 through a thin wall 633 to the inner surface 632 of the cap 626. When one or more fastening mechanisms 620 are secured, the one or more first cap cooling holes 650 are disposed in a space 647. In this manner, the one or more first cap cooling holes 650 provide fluid communication from the space 647 to the hollow interior 628 of the cap 626. The one or more second cap cooling holes 652 are disposed on the hot side of the cap 626. In this manner, the one or more second cap cooling holes 652 provide fluid communication from the hollow interior 628 of the cap 626 to the combustion chamber 210. The one or more third cap cooling holes 653 extend through the cap extension 644 and are aligned with one or more stud cooling holes 625. In this manner, one or more third cap cooling holes 653 provide fluid communication from one or more stud cooling holes 625 to the hollow interior 628 of the cap 626. In some embodiments, one or more first cap cooling holes 650, one or more second cap cooling holes 652 and / or one or more third cap cooling holes 653 are circumferentially angled to operatively guide cooling air tangentially into the hollow interior 628 or the combustion chamber 210, respectively.

[0074] In operation, besides regarding Figure 3 In addition to the detailed cooling arrangement, cooling air 380 is operably guided through one or more gasket cooling holes 372 into the space between gasket 360 and recess 612. Cooling air 380 is operably guided from the space between gasket 360 and recess 612 through one or more recess cooling holes 614 and into the space 647 between recess 612 and cap 626. Cooling air 380 is operably guided from space 647 through one or more first cap cooling holes 650 and into the hollow interior 628 of cap 626. In this way, cooling air 380 fills the hollow interior 628. Cooling air 380 is then operably guided from the hollow interior 628 through one or more second cap cooling holes 652 and into combustion chamber 210 to provide thin-film cooling on the hot side of cap 626. Simultaneously, cooling air 380 is operably guided through one or more stud cooling holes 625, through one or more third cap cooling holes 653, into the hollow interior 628, through one or more second cap cooling holes 652, and into the combustion chamber 210. Meanwhile, cooling air 380 is guided from space 647 into the combustion chamber 210 to provide additional cooling in the area surrounding cap 626.

[0075] The coupling assembly 600 provides an improved cooling arrangement to reduce the thermal gradient in the region surrounding one or more fastening mechanisms 620, as detailed above. For example, a recessed portion 612 is provided to move the stud 624 away from the hot side of the hot-side component 604, such that the stud 624 is radially spaced from the combustion chamber 210, and a cap 626 provides the aforementioned... Figure 3 The improved cooling is detailed below. For example, cooling air 380 in the hollow interior 628 provides a buffer between the combustion chamber 210 and the stud 324. The cap 626 also serves to fill abrupt steps in the hot-side member 604 formed by the recess 612 (e.g., filling the recess space 636). In this way, the cap 626 provides a surface flush with the hot side of the hot-side member 604, keeping the hot side of the hot-side member 604 substantially flush and substantially smooth, thereby providing an improved cooling arrangement in the area surrounding one or more fastening mechanisms 620.

[0076] Figure 7 According to another embodiment, in turbine engine 10 ( Figure 1 The section taken at the centerline axis of the turbine engine 10 ( Figure 1 Combustion section 26 ( Figure 1 and Figure 2 A schematic partial cross-sectional view of a portion of the coupling assembly 700. The coupling assembly 700 includes a cold-side component 302 and a hot-side component 704. The hot-side component 704 includes one or more tiles or panels 706 disposed on and connected to the hot side of the cold-side component 302. Figure 7 A panel 706 is depicted, but the hot-side component 704 may include any number of panels 706 as needed. The coupling assembly 700 includes one or more fastening mechanisms 720 for attaching and connecting the hot-side component 704 to the cold-side component 302. The hot-side component 704 includes one or more hot-side component cooling holes 710.

[0077] The hot-side component 704 is basically similar to Figure 6 The hot-side component 604. For example, the hot-side component 704 includes a recessed portion 712 in a region surrounding each of one or more fastening mechanisms 720. Figure 7 As shown, washer 360 does not contact recess 712. Washer 360 has a diameter larger than the diameter of recess 712, such that washer 360 circumferentially surrounds recess 712. Recess 712 includes one or more recess cooling holes 714 extending therethrough. The one or more recess cooling holes 714 extend from the cold side of recess 712 to the hot side of recess 712. Recess 712 also includes a stud receiving portion 716 defining a gap or space, the size and shape of which are designed to receive a stud 724 of a corresponding fastening mechanism 720.

[0078] One or more fastening mechanisms 720 include a stud 724 and a cap 726. Although not shown, one or more fastening mechanisms 720 may also include a nut, as detailed above. The stud 624 includes a stud head 725 disposed in a stud receiving portion 716 of a recess 712. The stud head 725 extends from the cold side of the recess 612 to the hot side of the recess 612 such that the stud head 725 is flush with both the cold and hot sides of the recess 612. The cap 726 is positioned between the stud 724 and the combustion chamber 210 such that the stud 724 is insulated from the combustion chamber 210. In this way, the stud 724 is not directly exposed to the combustion chamber 210. For example, the stud 724 is radially spaced from the combustion chamber 210.

[0079] The cap 726 includes a generally truncated conical shape with a hollow interior 728, such that the cap 726 includes an outer surface 730 and an inner surface 732. The outer surface 730 and the inner surface 732 together form a thin wall 733, such that the hollow interior 728 includes a shape generally corresponding to the shape of the cap 726. In this way, the hollow interior 728 is a closed hollow interior 728. Therefore, the hollow interior 728 is defined in the turbine engine 10 ( Figure 1 The reservoir is filled with cooling air during operation, as further detailed below. The stud 724 and cap 726 can include any shape and / or any size as needed. The cap 726 and the hollow interior 728 each include a diameter larger than the outer diameter of the stud 724. The cap 726 is attached to the stud 724. For example, the cold side of the cap 726 is attached to the stud head 725. The cap 726 can be attached to the stud 724, for example, by welding, brazing, adhesive, etc. In some embodiments, the cap 726 is integrally formed with the stud 724, such that the stud 724 and the cap 726 form a single integral component. When the cap 726 is attached to the stud 724, the cap 726 is inserted and positioned in a second fastening mechanism orifice 736 defined by a recess 712 of the hot-side component 704. A portion of the cap 726 is spaced apart from the cold side of the recess 712, such that a gap or space 747 is defined between the cap 726 and the recess 712.

[0080] The cap 726 includes one or more first cap cooling holes 750 extending therethrough and one or more second cap cooling holes 752 extending therethrough. The one or more first cap cooling holes 750 and the one or more second cap cooling holes 752 each extend from the outer surface 730 of the cap 726 through a thin wall 733 to the inner surface 732 of the cap 726. When one or more fastening mechanisms 720 are secured, the one or more first cap cooling holes 750 are disposed in a space 747. In this manner, the one or more first cap cooling holes 750 provide fluid communication from the space 747 to the hollow interior 728 of the cap 726. The one or more second cap cooling holes 752 are disposed on the hot side of the cap 726. In this manner, the one or more second cap cooling holes 752 provide fluid communication from the hollow interior 728 of the cap 726 to the combustion chamber 210. In some embodiments, the one or more first cap cooling holes 750 and / or the one or more second cap cooling holes 752 are circumferentially angled to operatively guide cooling air tangentially to the hollow interior 728 or the combustion chamber 210, respectively. Similar to about Figure 6 The described coupling assembly 600 allows cooling air 380 to be operably guided through the coupling assembly 700. For example, the cooling air 380 is operably guided into the hollow interior 728 of the cap 726 to provide a buffer for the cooling air 380 between the combustion chamber 210 and the stud 324.

[0081] Figure 8A According to another embodiment, in turbine engine 10 ( Figure 1 The section taken at the centerline axis of the turbine engine 10 ( Figure 1 Combustion section 26 ( Figure 1 and Figure 2 A schematic partial cross-sectional view of a portion of the connecting component 800. Figure 8A A coupling assembly 800 is shown, which includes a cold-side component 802 and a hot-side component 804. The hot-side component 804 includes one or more tiles or panels 806 disposed on and connected to the hot side of the cold-side component 802. That is, the panel 806 of the hot-side component 804 is connected to the side of the cold-side component 802 exposed to the combustion chamber 210. Figure 8A A panel 806 is depicted, but the hot-side component 804 may include any number of panels 806 as needed.

[0082] The cold-side component 802 includes one or more cold-side component cooling holes 808, and the hot-side component 804 includes one or more hot-side component cooling holes 810. In this way, cooling air 380 (e.g., Figure 2The compressed air 65 shown can pass through the cold-side component 802 and can pass through the hot-side component 804, as further detailed below. One or more cold-side component cooling holes 808 and one or more hot-side component cooling holes 810 may each comprise any number of cooling holes formed in any orientation relative to the cold-side component 802 and the hot-side component 804. In some embodiments, one or more cold-side component cooling holes 808 and one or more hot-side component cooling holes 810 are also circumferentially angled to operatively guide the cooling air tangentially.

[0083] The coupling assembly 800 includes a plurality of fastening mechanisms 820 for attaching and connecting the cold-side component 802 and the hot-side component 804 (e.g., each of the panels 806 of the hot-side component 804). That is, the hot-side component 804 is coupled to the cold-side component 802 via the plurality of fastening mechanisms 820. Figure 8A Multiple fastening mechanisms 820 are shown, including a first fastening mechanism 820a and a second fastening mechanism 820b. The second fastening mechanism 820b is positioned axially downstream of the first fastening mechanism 820a. Although Figure 8A Two fastening mechanisms 820 are shown, but multiple fastening mechanisms 820 may be included as needed, in any number. A gap or space 822 is formed between the cold-side component 802 and the hot-side component 804. For example, space 822 is formed between the radially outer surface (e.g., cold side) of the hot-side component 804 and the radially inner surface (e.g., hot side) of the cold-side component 802.

[0084] Each of the multiple fastening mechanisms 820 includes a stud 824 and a nut 840 connected together by a threaded connection. The multiple fastening mechanisms 820 can include any type of known fastening mechanism, such as bolts, screws, nuts, rivets, etc. The stud 824 includes a generally cylindrical body defining the stud 824. The stud 824 can include any shape and / or any size as needed. The stud 824 is inserted through a fastening mechanism orifice 834 of the cold-side component 802. For example, the stud 824 of the first fastening mechanism 820a is inserted through the first fastening mechanism orifice 834a, while the stud 824 of the second fastening mechanism 820b is inserted through the second fastening mechanism orifice 834b. The stud 824 also includes a stud head 825 disposed on the hot side of the cold-side component 802. In this way, the stud head 825 is positioned away from the hot-side component 804, such that the stud 824 and the stud head 825 are insulated from the hot combustion gases in the combustion chamber 210. Figure 8A In this configuration, stud 824 does not directly connect the hot-side component 804 and the cold-side component 802. Instead, the connection assembly 800 includes a plurality of flexible plates 850 connecting the hot-side component 804 to the cold-side component 802, as further detailed below. The plurality of flexible plates 850 may be made of metal, ceramic, or a combination thereof. In some embodiments, the plurality of flexible plates 850 are made of CMC.

[0085] The hot-side component 804 includes a plurality of flanges 812, and a plurality of flexible plates 850 engage or otherwise hold the plurality of flanges 812 to connect the hot-side component 804 to the cold-side component 802. The plurality of flanges 812 includes a first flange 812a and a second flange 812b. The second flange 812b is positioned downstream of the first flange 812a. In other words, the first flange 812a is positioned upstream of the second flange 812b.

[0086] Each of the plurality of flanges 812 includes a radial flange portion 814 extending substantially radially from the hot-side component 804. For example, the radial flange portion 814 extends radially from the cold side of the hot-side component 804 toward the cold-side component 802. A first flange 812a includes a first radial flange portion 814a, and a second flange 812b includes a second radial flange portion 814b. The radial flange portion 814 of each flange 812 defines an axial end of a corresponding panel 806 of the hot-side component 804. For example, the first radial flange portion 814a is positioned at a first axial end of the panel 806, and the second radial flange portion 814b is positioned at a second axial end of the panel 806 opposite the first axial end. Each radial flange portion 814 is substantially axially aligned with a corresponding fastening mechanism 820 such that the panel 806 extends axially between the first fastening mechanism 820a and the second fastening mechanism 820b. When panel 806 is attached to cold-side component 802, this arrangement provides a balance for panel 806, as described in further detail below. However, panel 806 may include any axial length as required.

[0087] Each of the plurality of flanges 812 further includes an axial flange portion 816 extending axially from the radial flange portion 814. A first flange 812a includes a first axial flange portion 816a, and a second flange 812b includes a second axial flange portion 816b. The first axial flange portion 816a extends axially downstream from the first radial flange portion 814a. The second axial flange portion 816b extends axially upstream from the second radial flange portion 814b. Thus, a gap or space 818 is defined between the first flange 812a and the second flange 812b. The space 818 extends axially between the first flange 812a and the second flange 812b, and radially between the cold side of the hot-side component 804 and the axial flange portion 816 of each flange 812.

[0088] Multiple flexible plates 850 extend between the fastening mechanism connecting portion 852 and the flange connecting portion 854. The fastening mechanism connecting portion 852 includes a fastening mechanism orifice 862. Figure 8B This causes the corresponding fastening mechanism 820 to be inserted through the fastening mechanism orifice 862. Figure 8BIn this manner, the corresponding flexible plate 850 is connected to the corresponding fastening mechanism 820. For example, the first flexible plate 850a is connected to the first fastening mechanism 820a, and the second flexible plate 850b is connected to the second fastening mechanism 820b. The first flexible plate 850a extends from the first fastening mechanism 820a to the second flange 812b of the panel 806. In this manner, the first flexible plate 850a extends in both the radial and axial directions. For example, the first flexible plate 850a extends radially inward from the first fastening mechanism 820a toward the second flange 812b at a certain angle, and extends axially downstream from the first fastening mechanism 820a to the second flange 812b. The first flexible plate 850a radially overlaps the second flexible plate 850b at approximately the axial center of the first flexible plate 850a and the second flexible plate 850b. In this manner, the first flexible plate 850a is disposed in the space 822 between the cold-side component 802 and the hot-side component 804 and extends through the space 818.

[0089] Similarly, the second flexible plate 850b extends from the second fastening mechanism 820b to the first flange 812a of the panel 806. In this manner, the second flexible plate 850b extends in both the radial and axial directions. For example, the second flexible plate 850b extends radially inward at an angle from the second fastening mechanism 820b toward the first flange 812a, and extends axially upstream of the second fastening mechanism 820b to the first flange 812a. In this manner, the second flexible plate 850b is disposed in the space 822 between the cold-side member 802 and the hot-side member 804, and extends through the space 818.

[0090] Each flexible plate 850 is connected to a corresponding flange 812 via a flange connection portion 854. For example, the flange connection portion 854 includes one or more first protrusions 856 and one or more second protrusions 858 separated at the flange connection portion 854, as further detailed below. The one or more second protrusions 858 pass through one or more slots 857 (…). Figure 8B The first protrusion 850a is separated from the flange connecting portion 854 and engages the cold side of the axial flange portion 816. The second protrusion 858 is bent to form the flange connecting portion 854 and engages the hot side of the axial flange portion 816. In this way, the first protrusion 850a and the second protrusion 858 together hold or connect the respective axial flange portions 816. For example, the axial flange portion 816 is press-fitted between the first protrusion 856 and the second protrusion 858. Thus, the first flexible plate 850a and the second flexible plate 850b together connect and secure the hot side component 804 (e.g., panel 806) to the cold side component 802.

[0091] Each of the plurality of flexible plates 850 includes one or more flexible plate cooling holes 860 extending therethrough. The one or more flexible plate cooling holes 860 extend from the cold side to the hot side of the plurality of flexible plates 850 to provide fluid communication through the plurality of flexible plates 850. When the coupling assembly 800 is assembled, the one or more flexible plate cooling holes 860 are disposed in a space 822. In this manner, the one or more flexible plate cooling holes 860 provide fluid communication from the space 822 to one or more hot-side component cooling holes 810. The one or more flexible plate cooling holes 860 may be angled radially and / or circumferentially through the plurality of flexible plates 850 to operatively guide cooling air tangentially through the plurality of flexible plates 850.

[0092] Multiple flexible plates 850 provide flexibility, allowing the panel 806 of the hot-side component 804 to move relative to the cold-side component 802. For example, the multiple flexible plates 850 may be compressible or buckle, allowing the panel 806 to move relative to the cold-side component 802. The multiple flexible plates 850 are flexible in multiple degrees of freedom, allowing the panel 806 to move radially, axially, circumferentially, or in combinations thereof relative to the cold-side component 802. For example, the circumferentially spaced multiple flexible plates 850 provide additional circumferential flexibility compared to coupling components that do not benefit from this disclosure.

[0093] In operation, cooling air 880 is operably guided from the cold side of the cold-side component 802, through one or more cold-side component cooling holes 808, and into the space 822 between the hot side of the cold-side component 802 and the plurality of flexible plates 850. In an exemplary embodiment, the cooling air 880 is compressed air 65 (received from the compressor section of a turbine engine) Figure 2 However, cooling air 880 can be supplied from any source as needed. Cooling air 880 is operably guided from space 822 through one or more flexible plate cooling holes 860 and between the plurality of flexible plates 850 and the cold side of hot-side component 804. Cooling air 880 is then operably guided from space 822 through one or more hot-side component cooling holes 810 and into combustion chamber 210 for thin-film cooling of the hot side of hot-side component 804.

[0094] Figure 8B It is based on the isolation of the connection component 800 according to this disclosure ( Figure 8A A top view of multiple flexible panels 850. Figure 8B Multiple flexible plates 850 in an unbent orientation are shown, such that the multiple flexible plates are flattened. The multiple flexible plates 850 can be bent or otherwise deformed to form... Figure 8AThe shape is shown. In the unbent configuration, a plurality of flexible plates 850 each define a generally rectangular shape. The plurality of flexible plates 850 may include any shape and / or any size as needed. The plurality of flexible plates 850 are circumferentially spaced apart from each other. For example, a first flexible plate 850a is circumferentially spaced from a second flexible plate 850b and positioned circumferentially adjacent to the second flexible plate 850b. In one embodiment, the first flexible plate 850a is circumferentially positioned behind the second flexible plate 850b. The first flexible plate 850a and the second flexible plate 850b are generally axially aligned. In this way, the plurality of flexible plates 850 provide balance for the hot-side components in the circumferential direction as well as in the axial and radial directions. In some embodiments, the first flexible plate 850a is circumferentially positioned in front of the second flexible plate 850b.

[0095] Multiple flexible plates 850 extend from a proximal first end 851 to a distal second end 853 opposite to the first end 851. A fastening mechanism connecting portion 852 is located at the first end 851, and a flange connecting portion 854 is located at the second end 853. A fastening mechanism orifice 862 is located at the fastening mechanism connecting portion 852. One or more first protrusions 856 and one or more second protrusions 858 are located at the flange connecting portion 854. One or more flexible plate cooling holes 860 are axially located between the fastening mechanism connecting portion 852 and the flange connecting portion 854.

[0096] Each flexible plate 850 (e.g., a first flexible plate 850a and a second flexible plate 850b) includes one or more first bends 870, one or more second bends 872, one or more third bends 874, and one or more fourth bends 876. Figure 8B Each bend is depicted with dashed lines. One or more first bends 870 are defined at the fastening mechanism connection portion 852, such that the flexible plate 850 extends radially inward from the fastening mechanism connection portion 852. Figure 8A (As shown). One or more second bends 872 are defined at the flange connection portion 854. In this way, the flexible plate 850 defines a generally straight portion (e.g., without bends) between one or more first bends 870 and one or more second bends 872.

[0097] One or more second bends 872 may include bends of one or more first protrusions 856 in a first radial direction, and may include bends of one or more second protrusions 858 in a second radial direction. For example, one or more first protrusions 856 may bend radially outward at one or more second bends 872, and one or more second protrusions 858 may bend radially inward at one or more second bends 872. In this way, one or more first protrusions 856 and one or more second protrusions 858 are divided into different directions at one or more second bends 872 (e.g., Figure 8A (As shown). One or more third bends 874 are defined at one or more first protrusions 856 and one or more second protrusions 858. For example, one or more first protrusions 856 bend radially inward at one or more third bends 874, and one or more second protrusions 858 bend radially outward at one or more third bends 874 (as shown). Figure 8A (As shown). In this manner, one or more first protrusions 856 include portions engaging the cold side of the axial flange portion 816, and one or more second protrusions 858 include portions engaging the hot side of the axial flange portion 816. One or more fourth bends 876 are defined at one or more first protrusions 856 and one or more second protrusions 858. For example, one or more first protrusions 856 are radially outwardly bent at one or more fourth bends 876, and one or more second protrusions 858 are radially inwardly bent at one or more fourth bends 876. In this manner, one or more first protrusions 856 and one or more second protrusions 858 engage the axial flange portion 816 at one or more fourth bends 876 (as shown). Figure 8A (As shown). Therefore, the bends in the flange connection portion 854 allow one or more first protrusions 856 and one or more second protrusions 858 to engage and retain the panel 806 at the axial flange portion 816. Multiple flexible plates 850 may include any number of bends in any orientation as needed for engaging the axial flange portion 816 of the panel 806.

[0098] Refer again Figure 8A The coupling assembly 800 provides a cooling arrangement that prevents the multiple fastening mechanisms 820 from being directly exposed to hot combustion gases in the combustion chamber 210. The coupling assembly 800 separates the multiple fastening mechanisms 820 from the hot-side component 804, ensuring that the multiple fastening mechanisms 820 are not exposed to hot combustion gases. For example, the multiple fastening mechanisms 820 are insulated from the combustion chamber 210. Multiple flexible plates 850 engage the panel 806 of the hot-side component 804, allowing the hot-side component 804 to be coupled to the cold-side component 802 without requiring the fastening mechanisms 820 to directly contact the hot-side component 804. This reduces the thermal gradient in the areas of the multiple fastening mechanisms 820, thereby reducing stress concentration on the multiple fastening mechanisms 820. Compared to an arrangement where the fastening mechanisms 820 directly contact the hot-side component 804, the flexibility of the multiple flexible plates 850 allows the panel 806 to move while also reducing stress on the multiple fastening mechanisms 820. The protrusions of the flange connection portion 854 of the flexible plate 850 also include flexibility, such that the flange connection portion 854 provides frictional damping when the hot-side component 804 moves relative to the cold-side component 802. Therefore, the connection assembly 800 provides reduced damage and / or failure of the hot-side component 804 and / or the cold-side component 802 in the area surrounding the plurality of fastening mechanisms 820.

[0099] Figure 9A According to another embodiment, in turbine engine 10 ( Figure 1 The section taken at the centerline axis of the turbine engine 10 ( Figure 1 Combustion section 26 ( Figure 1 and Figure 2 A schematic partial cross-sectional view of a portion of the coupling assembly 900. The coupling assembly 900 and... Figure 8A The connecting assembly 800 is substantially similar. For example, the connecting assembly 900 includes a cold-side component 802, a hot-side component 804, a panel 806, multiple fastening mechanisms 820, and multiple flanges 812. However, the connecting assembly 900 includes multiple flexible plates 950, which are different from... Figure 8A and Figure 8B Multiple flexible panels, 850. Figure 9B It is based on the isolation of the connection component 900 according to this disclosure ( Figure 9A A top view of multiple flexible panels 950.

[0100] refer to Figure 9A and 9B A plurality of flexible plates 950 include a first flexible plate 950a and a second flexible plate 950b. The plurality of flexible plates 950 extend between a fastening mechanism connection portion 952 and a flange connection portion 954. The plurality of flexible plates 950 include a plurality of fastening mechanism orifices 962. For example, the fastening mechanism connection portion 952 includes a first fastening mechanism orifice 962a, such that a corresponding fastening mechanism 820 is inserted through the first fastening mechanism orifice 962a. In this manner, a corresponding flexible plate 950 is coupled to a corresponding fastening mechanism 820. For example, the first flexible plate 950a is coupled to the first fastening mechanism 820a and the second flexible plate 950b is coupled to the second fastening mechanism 820b. The flange connection portion 954 includes a second fastening mechanism orifice 962b. In this manner, multiple flexible plates 950 can be oriented such that a corresponding fastening mechanism 820 is inserted through a first fastening mechanism orifice 962a, or can be oriented such that a corresponding fastening mechanism 820 is inserted through a second fastening mechanism orifice 962b. This arrangement provides ease of manufacture when assembling the connecting assembly 900.

[0101] The first flexible plate 950a extends from the first fastening mechanism 820a to the second flange 812b of the panel 806, as detailed above. The first flexible plate 950a radially overlaps the second flexible plate 950b at approximately the axial center of the first flexible plate 950a and the second flexible plate 950b (e.g., Figure 9A(As shown). In this manner, the first flexible plate 950a is disposed in the space 822 between the cold-side component 802 and the hot-side component 804, and extends through the space 818. Similarly, the second flexible plate 950b extends from the second fastening mechanism 820b to the first flange 812a of the panel 806, as detailed above. In this manner, the second flexible plate 950b is disposed in the space 822 between the cold-side component 802 and the hot-side component 804, and extends through the space 818.

[0102] Each flexible plate 950 is connected to a corresponding flange 812 via a flange connection portion 954. However, the flange connection portion 954 is not related to... Figure 8A The detailed flange connection portion 854 similarly includes one or more protrusions. Instead, the flange connection portion 954 inserts into the space 818 to engage with the hot side of the axial flange portion 816, such that the flange connection portion 954 radially supports the panel 806 at the axial flange portion 816. The flange connection portion 954 is fixed to the axial flange portion 816 by, for example, welding, brazing, adhesive, etc. Thus, the first flexible plate 950a and the second flexible plate 950b together connect and fix the hot-side component 804 (e.g., panel 806) to the cold-side component 802, such that the plurality of fastening mechanisms 820 do not directly engage the hot-side component 804. In this way, the fastening mechanisms 820 are insulated from the combustion chamber 210.

[0103] Each of the plurality of flexible plates 950 includes one or more flexible plate cooling holes 960 extending therethrough. The one or more flexible plate cooling holes 960 extend from the cold side to the hot side of the plurality of flexible plates 950 to provide fluid communication through the plurality of flexible plates 950. When the coupling assembly 900 is assembled, the one or more flexible plate cooling holes 960 are disposed in the space 822. In this manner, the one or more flexible plate cooling holes 960 provide fluid communication from the space 822 to one or more hot-side component cooling holes 810. The one or more flexible plate cooling holes 960 may be angled radially and / or circumferentially through the plurality of flexible plates 950 to operatively guide cooling air tangentially through the plurality of flexible plates 950.

[0104] Figure 9B A first flexible plate 950a is shown circumferentially spaced from a second flexible plate 950b and positioned circumferentially adjacent to the second flexible plate 950b. For example, the first flexible plate 950a is circumferentially positioned behind the second flexible plate 950b. In this manner, a plurality of flexible plates 950 are circumferentially spaced from each other. The first flexible plate 950a and the second flexible plate 950b are generally axially aligned. In this manner, the plurality of flexible plates 950 provide a heat-side component 804 in the circumferential direction as well as in the axial and radial directions. Figure 9A The balance of the first flexible plate 950a is achieved by positioning it circumferentially in front of the second flexible plate 950b in some embodiments.

[0105] Multiple flexible plates 950 from the first end 951 near the end ( Figure 9B ) extends to the distal end 953 opposite to the first end 951 ( Figure 9B The fastening mechanism connecting portion 952 is located at the first end 951, and the flange connecting portion 954 is located at the second end 953. The first fastening mechanism orifice 962a is located at the fastening mechanism connecting portion 952, and the second fastening mechanism orifice 962b is located at the flange connecting portion 954. Figure 9B One or more flexible plate cooling holes 960 are shown axially positioned between the fastening mechanism connection portion 952 and the flange connection portion 954.

[0106] Each flexible plate 950 (e.g., a first flexible plate 950a and a second flexible plate 950b) includes a first bent portion 970 and a second bent portion 972. Figure 9B Each bend is depicted with dashed lines. The first bend 970 is defined at the fastening mechanism connection portion 952, such that the flexible plate 950 extends radially inward from the fastening mechanism connection portion 952 (e.g., Figure 9A (As shown). The second bend 972 is defined at the flange connection portion 954, such that the flexible plate 950 extends generally axially from the second bend 972. In this way, the flexible plate 950 defines a generally straight portion (e.g., no bend) between the first bend 970 and the second bend 972. The portion of the flexible plate 950 extending axially from the second bend 972 is inserted into the space 818 ( Figure 9A It engages the cold side of the axial flange portion 816 to support the panel 806 of the hot side component 804.

[0107] Multiple flexible plates 950 provide flexibility, allowing the panel 806 of the hot-side component 804 to move relative to the cold-side component 802. For example, the multiple flexible plates 950 can be compressed or buckled, allowing the panel 806 to move relative to the cold-side component 802. The multiple flexible plates 950 are flexible in multiple degrees of freedom, allowing the panel 806 to move radially, axially, circumferentially, or in combinations thereof relative to the cold-side component 802.

[0108] In operation, cooling air 880 is operably guided from the cold side of the cold-side component 802, through one or more cold-side component cooling holes 808, and into the space 822 between the hot side of the cold-side component 802 and the plurality of flexible plates 950. Cooling air 880 is operably guided from the space 822, through one or more flexible plate cooling holes 960, and between the plurality of flexible plates 950 and the cold side of the hot-side component 804. Cooling air 880 is then operably guided from the space 822 through one or more hot-side component cooling holes 810 and into the combustion chamber 210 to provide thin-film cooling to the hot side of the hot-side component 804. Figure 8A and Figure 8B Compared to multiple flexible plates 850, multiple flexible plates 950 provide manufacturing convenience. Since the flange connection portion 954 is connected to the axial flange portion 816 so that the flange connection portion 954 does not slide or move relative to the axial flange portion 816, the connection of multiple flexible plates 950 to the axial flange portion 816 reduces wear.

[0109] Embodiments of this disclosure provide an improved cooling arrangement such that one or more fastening mechanisms in the combustion zone are not directly exposed to hot combustion gases in the combustion chamber. Therefore, embodiments of this disclosure help reduce the thermal gradient in the region surrounding the fastening mechanism, thereby reducing stress concentration in that region. Consequently, embodiments of this disclosure provide reduced damage and / or failure of hot-side and / or cold-side components in the region surrounding the fastening mechanism.

[0110] Further details are provided by the following topics.

[0111] A coupling assembly for a turbine engine includes: a cold-side component; a hot-side component, the cold-side component and the hot-side component together at least partially forming a combustion chamber; and a fastening mechanism that couples the hot-side component to the cold-side component, the fastening mechanism including: a stud disposed through the cold-side component; and a cap positioned on the stud, the cap defining a hollow interior and including one or more first cap cooling holes operably directing cooling air into the hollow interior such that the hollow interior provides a buffer of cooling air between the combustion chamber and the stud.

[0112] According to the connecting assembly described in the foregoing clause, the space is defined between the cold-side component and the hot-side component, and the stud is disposed in the space.

[0113] According to any of the preceding clauses, the cap is configured to pass through the hot-side component.

[0114] According to any of the preceding clauses, the cap is positioned between the stud and the combustion chamber.

[0115] According to any of the preceding clauses, the stud is radially spaced from the combustion chamber such that the stud is insulated from the combustion chamber.

[0116] According to any of the preceding clauses, the cap includes one or more second cap cooling holes that operatively guide cooling air from the hollow interior into the combustion chamber.

[0117] According to any of the preceding clauses, the hollow interior includes a diameter larger than the outer diameter of the stud.

[0118] According to any of the preceding clauses, the cap includes a thin wall defined by an inner surface and an outer surface, the thin wall defining the shape of the hollow interior.

[0119] According to any of the preceding clauses, the shape of the hollow interior generally corresponds to the shape of the cap.

[0120] The coupling assembly according to any of the foregoing clauses further includes a gasket disposed between the cold-side component and the hot-side component, the gasket being flexible to allow the hot-side component to move relative to the cold-side component, and the gasket preventing the hot-side component from contacting the cold-side component.

[0121] According to any of the preceding clauses, the gasket includes one or more gasket cooling holes that operatively direct cooling air toward the cap.

[0122] According to any of the preceding clauses, the gasket includes one or more gasket grooves that extend radially inward from the outer edge of the gasket to the one or more gasket cooling holes.

[0123] According to any of the preceding clauses, the one or more first cap cooling holes operably guide the cooling air from the space into the hollow interior.

[0124] According to any of the preceding clauses, the one or more caps include an outer surface and an inner surface, wherein one or more first cap cooling holes extend from the outer surface through the thin wall to the inner surface.

[0125] According to any of the preceding clauses, the cold-side component is the housing of the bushing of the turbine engine, and the hot-side component is a heat shield.

[0126] According to any of the preceding clauses, the cold-side component is an annular dome assembly, and the hot-side component is a deflector assembly.

[0127] According to any of the preceding clauses, the cold-side component includes one or more cold-side component cooling holes that are operable to direct cooling air from the cold side of the cold-side component to the space between the cold-side component and the hot-side component.

[0128] According to any of the preceding clauses, the cooling holes of the one or more cold-side components are impact cooling holes.

[0129] According to any of the preceding clauses, the hot-side component includes one or more hot-side component cooling holes that are operable to direct the cooling air from the space to the combustion chamber.

[0130] According to any of the preceding clauses, the cooling holes of the one or more hot-side components are thin-film cooling holes.

[0131] According to any of the preceding clauses, the stud is inserted through a first fastening mechanism orifice of the cold-side component, and the cap is inserted through a second fastening mechanism orifice of the hot-side component.

[0132] According to any of the preceding clauses, the hot-side component includes one or more panels that together form the hot-side component.

[0133] According to any of the preceding clauses, each of the one or more panels is connected to the cold-side component via one or more fastening mechanisms.

[0134] According to any of the preceding clauses, the cap is connected to the stud via a first threaded connection.

[0135] According to any of the preceding clauses, the cap is press-fitted onto the stud.

[0136] According to any of the preceding clauses, the cap is integrally formed with the stud.

[0137] According to any of the preceding clauses, the fastening assembly further includes a nut connected to the stud on the cold side of the stud.

[0138] According to any of the preceding clauses, the nut is connected to the stud via a second threaded connection.

[0139] According to any of the preceding clauses, the cap includes a stud receiving portion that defines a stud opening for receiving a portion of the stud.

[0140] According to any of the preceding clauses, the stud receiving portion extends from the cold side of the inner surface of the cap and enters the hollow interior.

[0141] According to any of the preceding clauses, in the connecting assembly, the stud receiving portion is spaced apart from the hot side of the inner surface of the cap.

[0142] According to any of the preceding clauses, the cap further includes a cap insert positioned in the stud opening.

[0143] According to any of the preceding clauses, the stud is connected to the cap via the cap insert.

[0144] According to any of the preceding clauses, the stud is connected to the cap insert via the first threaded connection.

[0145] According to any of the preceding clauses, the cap presses into the cap insert.

[0146] According to any of the preceding clauses, the cap insert is integrally formed with the cap.

[0147] According to any of the preceding clauses, the stud is press-fitted onto the cap insert.

[0148] According to any of the preceding clauses, the stud is integrally formed with the cap insert.

[0149] According to any of the preceding clauses, the stud is brazed or welded to the cap insert.

[0150] According to any of the preceding clauses, the gasket includes a flat portion that contacts the cold-side component and a curved portion that contacts the hot-side component.

[0151] According to any of the preceding clauses, the washer includes a washer stud hole for receiving the stud.

[0152] According to any of the preceding clauses, the one or more gasket cooling holes are provided in the curved portion of the gasket.

[0153] According to any of the preceding clauses, the one or more gasket cooling holes are disposed within the space between the cold-side component and the hot-side component.

[0154] According to any of the preceding clauses, the cap defines a radial space surrounding the stud receiving portion.

[0155] According to any of the preceding clauses, the radial space extends radially from the outer surface of the stud receiving portion to another portion of the outer surface of the cap.

[0156] According to any of the preceding clauses, the outer surface defines a generally U-shaped portion, which defines the radial space.

[0157] According to any of the preceding clauses, the stud receiving portion is adjacent to the washer in the connecting assembly.

[0158] According to any of the preceding clauses, the cap is radially spaced from the gasket, such that the cooling air is operably directed between the gasket and the cap and into the radial space.

[0159] According to any of the preceding clauses, the cap further includes one or more third cap cooling holes that are operable to guide the cooling air from the radial space into the hollow interior.

[0160] According to any of the preceding clauses, the hot-side component includes a recessed portion in the region surrounding the fastening mechanism.

[0161] According to any of the preceding clauses, the recessed portion is recessed relative to the hot side of the hot side component.

[0162] According to any of the preceding clauses, the recessed portion extends from the hot-side component toward the cold-side component in the connecting assembly.

[0163] According to any of the preceding clauses, the recessed portion defines a recessed space, and the cap is disposed in the recessed space.

[0164] According to any of the preceding clauses, the washer has a diameter greater than the diameter of the recess, such that the washer circumferentially surrounds the recess.

[0165] According to any of the preceding clauses, the recessed portion includes one or more recessed cooling holes that operatively guide cooling air from the space to the combustion chamber.

[0166] According to any of the preceding clauses, a portion of the cap is spaced apart from the cold side of the recess, thereby defining a space between the cap and the recess.

[0167] According to any of the preceding clauses, the cap further includes a cap extension that is inserted into the cap receiving portion of the stud.

[0168] According to any of the preceding clauses, the recessed portion includes a stud receiving portion for receiving the stud.

[0169] According to any of the preceding clauses, the stud includes one or more stud cooling holes that operatively guide cooling from the cold side of the cold-side component to the hollow interior of the cap.

[0170] According to any of the preceding clauses, the cold side of the cap is adjacent to the hot side of the recessed portion.

[0171] According to any of the preceding clauses, the cap is connected to the stud via the cap extension.

[0172] According to any of the preceding clauses, the hot side of the cap is substantially flush with the hot side of the hot side component.

[0173] According to any of the preceding clauses, the cap includes one or more third cap cooling holes that are operable to guide cooling air from the one or more stud cooling holes into the hollow interior.

[0174] According to any of the preceding clauses, the cold side of the cap is connected to the stud.

[0175] According to any of the preceding clauses, the stud includes a stud head, and the cap is coupled to the stud head.

[0176] According to any of the preceding clauses, the cap is attached to the stud by welding, brazing, or adhesive.

[0177] According to any of the preceding clauses, the cap is integrally formed with the stud.

[0178] A turbine engine includes: a combustion section including a combustion chamber; and a coupling assembly including: a cold-side component; a hot-side component, the cold-side component and the hot-side component together at least partially forming the combustion chamber; and a fastening mechanism coupling the hot-side component to the cold-side component, the fastening mechanism including: a stud disposed through the cold-side component; and a cap positioned on the stud, the cap defining a hollow interior and including one or more first cap cooling holes operably guiding cooling air into the hollow interior such that the hollow interior provides a buffer of cooling air between the combustion chamber and the stud.

[0179] According to the turbine engine described in the foregoing clause, the cap is configured to pass through the hot-side component.

[0180] According to any of the preceding clauses of the turbine engine, the cap is positioned between the stud and the combustion chamber.

[0181] In any of the preceding clauses of the turbine engine, the stud is radially spaced from the combustion chamber such that the stud is insulated from the combustion chamber.

[0182] According to any of the foregoing clauses, the turbine engine cap includes one or more second cap cooling holes that are operable to guide cooling air from the hollow interior into the combustion chamber.

[0183] According to any of the preceding clauses, the hollow interior includes a diameter larger than the outer diameter of the stud.

[0184] According to any of the preceding clauses, the cap includes a thin wall defined by an inner surface and an outer surface, the thin wall defining the shape of the hollow interior.

[0185] According to any of the preceding clauses, the shape of the hollow interior generally corresponds to the shape of the cap.

[0186] According to any of the foregoing clauses, in a turbine engine, a space is defined between the cold-side component and the hot-side component, and the stud is disposed in the space.

[0187] The turbine engine according to any of the foregoing clauses further includes a gasket disposed between the cold-side component and the hot-side component, the gasket being flexible to allow the hot-side component to move relative to the cold-side component, and the gasket preventing the hot-side component from contacting the cold-side component.

[0188] According to any of the foregoing clauses of the turbine engine, the gasket includes one or more gasket cooling holes that operatively direct cooling air toward the cap.

[0189] According to any of the preceding clauses of the turbine engine, the gasket includes one or more gasket grooves that extend radially inward from the outer edge of the gasket to the one or more cooling holes.

[0190] According to any of the foregoing clauses of the turbine engine, the one or more first cap cooling holes are operable to guide the cooling air from the space into the hollow interior.

[0191] According to any of the preceding clauses of the turbine engine, the one or more caps include an outer surface and an inner surface, and the one or more first cap cooling holes extend from the outer surface through the thin wall to the inner surface.

[0192] According to any of the foregoing clauses, the cold-side component is the housing of the turbine engine bushing, and the hot-side component is a heat shield.

[0193] According to any of the preceding clauses, the cold-side component is an annular dome assembly, and the hot-side component is a deflector assembly.

[0194] According to any of the preceding clauses of the turbine engine, the cold-side component includes one or more cold-side component cooling holes that are operable to direct cooling air from the cold side of the cold-side component to the space between the cold-side component and the hot-side component.

[0195] According to any of the preceding clauses, the cooling holes of the one or more cold-side components are impact cooling holes.

[0196] According to any of the preceding clauses of the turbine engine, the hot-side component includes one or more hot-side component cooling holes that are operable to direct the cooling air from the space to the combustion chamber.

[0197] According to any of the preceding clauses, the one or more hot-side component cooling holes are thin-film cooling holes.

[0198] According to any of the foregoing clauses of the turbine engine, the stud is inserted through a first fastening mechanism orifice of the cold-side component, and the cap is inserted through a second fastening mechanism orifice of the hot-side component.

[0199] According to any of the foregoing clauses, the hot-side component of the turbine engine includes one or more panels that together form the hot-side component.

[0200] According to any of the foregoing clauses, each of the one or more panels is connected to the cold-side component by one or more fastening mechanisms.

[0201] According to any of the foregoing clauses of the turbine engine, the cap is connected to the stud via a first threaded connection.

[0202] According to any of the foregoing clauses of the turbine engine, the cap is press-fitted onto the stud.

[0203] In any of the foregoing clauses of the turbine engine, the cap is integrally formed with the stud.

[0204] According to any of the foregoing clauses of the turbine engine, the fastening assembly further includes a nut connected to the stud on the cold side of the stud.

[0205] According to any of the foregoing clauses of the turbine engine, the nut is connected to the stud via a second threaded connection.

[0206] According to any of the preceding clauses, the cap includes a stud receiving portion that defines a stud opening for receiving a portion of the stud.

[0207] According to any of the foregoing clauses of the turbine engine, the stud receiving portion extends from the cold side of the inner surface of the cap and enters the hollow interior.

[0208] According to any of the foregoing clauses of the turbine engine, the stud receiving portion is spaced apart from the hot side of the inner surface of the cap.

[0209] According to any of the foregoing clauses of the turbine engine, the cap further includes a cap insert positioned in the stud opening.

[0210] According to any of the foregoing clauses of the turbine engine, the stud is connected to the cap via the cap insert.

[0211] According to any of the preceding clauses of the turbine engine, the stud is connected to the cap insert via the first threaded connection.

[0212] According to any of the foregoing clauses of the turbine engine, the cap is press-fitted onto the cap insert.

[0213] According to any of the foregoing clauses of the turbine engine, the cap insert is integrally formed with the cap.

[0214] According to any of the foregoing clauses of the turbine engine, the stud is press-fitted onto the cap insert.

[0215] In any of the foregoing clauses of the turbine engine, the stud and the cap insert are integrally formed.

[0216] According to any of the foregoing clauses of the turbine engine, the stud is brazed or welded to the cap insert.

[0217] According to any of the foregoing clauses of the turbine engine, the gasket includes a flat portion that contacts the cold-side component and a curved portion that contacts the hot-side component.

[0218] According to any of the preceding clauses of the turbine engine, the washer includes a washer stud hole for receiving the stud.

[0219] According to any of the preceding clauses of the turbine engine, the one or more gasket cooling holes are provided in the curved portion of the gasket.

[0220] According to any of the preceding clauses, in a turbine engine, the one or more gasket cooling holes are disposed within the space between the cold-side component and the hot-side component.

[0221] According to any of the foregoing clauses of the turbine engine, the cap defines a radial space surrounding the stud receiving portion.

[0222] According to any of the preceding clauses, the radial space extends radially from the outer surface of the stud receiving portion to another portion of the outer surface of the cap.

[0223] According to any of the preceding clauses, the outer surface defines a generally U-shaped portion, which defines the radial space.

[0224] In any of the foregoing clauses of the turbine engine, the stud receiving portion is adjacent to the washer.

[0225] According to any of the preceding clauses of the turbine engine, the cap is radially spaced from the gasket, such that the cooling air is operably directed between the gasket and the cap and into the radial space.

[0226] According to any of the foregoing clauses of the turbine engine, the cap further includes one or more third cap cooling holes that are operable to guide the cooling air from the radial space into the hollow interior.

[0227] According to any of the foregoing clauses, the hot-side component of the turbine engine includes a recessed portion in the region surrounding the fastening mechanism.

[0228] According to any of the preceding clauses, the recessed portion is recessed relative to the hot side of the hot side component.

[0229] According to any of the foregoing clauses of the turbine engine, the recessed portion extends from the hot-side component toward the cold-side component.

[0230] According to any of the preceding clauses of the turbine engine, the recessed portion defines a recessed portion space, and the cap is disposed in the recessed portion space.

[0231] According to any of the preceding clauses of the turbine engine, the washer has a diameter larger than the diameter of the recess, such that the washer circumferentially surrounds the recess.

[0232] According to any of the preceding clauses of the turbine engine, the recessed portion includes one or more recessed cooling holes that are operable to direct the cooling air from the space to the combustion chamber.

[0233] According to any of the preceding clauses of the turbine engine, a portion of the cap is spaced apart from the cold side of the recess, such that a space is defined between the cap and the recess.

[0234] According to any of the foregoing clauses of the turbine engine, the cap further includes a cap extension that is inserted into the cap receiving portion of the stud.

[0235] According to any of the preceding clauses of the turbine engine, the recessed portion includes a stud receiving portion for receiving the stud.

[0236] According to any of the preceding clauses of the turbine engine, the stud includes one or more stud cooling holes that operatively guide the cooling from the cold side of the cold-side component to the hollow interior of the cap.

[0237] According to any of the foregoing clauses of the turbine engine, the cold side of the cap is adjacent to the hot side of the recessed portion.

[0238] According to any of the foregoing clauses of the turbine engine, the cap is connected to the stud via the cap extension.

[0239] According to any of the preceding clauses of the turbine engine, the hot side of the cap is substantially flush with the hot side of the hot side component.

[0240] According to any of the foregoing clauses of the turbine engine, the cap includes one or more third cap cooling holes that are operable to guide cooling air from the one or more stud cooling holes into the hollow interior.

[0241] According to any of the foregoing clauses of the turbine engine, the cold side of the cap is connected to the stud.

[0242] According to any of the preceding clauses of the turbine engine, the stud includes a stud head, and the cap is coupled to the stud head.

[0243] According to any of the foregoing clauses of the turbine engine, the cap is attached to the stud by welding, brazing or adhesive.

[0244] In any of the foregoing clauses of the turbine engine, the cap is integrally formed with the stud.

[0245] A method for operably directing cooling air through a turbine engine. The method includes operably directing cooling air through a cold-side component of the turbine engine, a hot-side component being coupled to the cold-side component by a fastening mechanism including a stud and a cap disposed through the cold-side component, the cold-side component and the hot-side component together at least partially forming a combustion chamber. The method includes operably directing the cooling air through one or more first cap cooling holes in the cap into a hollow interior of the cap, such that the hollow interior provides a buffer for the cooling air between the combustion chamber and the stud.

[0246] The method described according to the foregoing clauses further includes operably guiding the cooling air through the hot-side component.

[0247] The method according to any of the foregoing clauses further includes operably guiding the cooling air from the hollow interior through one or more second cap cooling holes to the combustion chamber.

[0248] The method according to any of the foregoing clauses further includes operably directing the cooling air through one or more gasket cooling holes of a gasket disposed between the cold-side component and the hot-side component, the gasket being flexible such that the hot-side component moves relative to the cold-side component, and the gasket preventing the hot-side component from contacting the cold-side component.

[0249] The method according to any of the foregoing clauses further includes operably directing the cooling air through the one or more gasket cooling holes toward the cap.

[0250] The method according to any of the foregoing clauses further includes operably directing the cooling air through one or more cooling holes in the cold-side component and into the space defined between the cold-side component and the hot-side component.

[0251] The method according to any of the foregoing clauses further includes operably guiding the cooling air from the space into the hollow interior.

[0252] The method according to any of the foregoing clauses further includes operably directing the cooling air through one or more cooling holes in the hot-side components and into the combustion chamber.

[0253] The method according to any of the foregoing clauses further includes operably directing the cooling air into the radial space between the gasket and the cap.

[0254] The method according to any of the foregoing clauses further includes operably guiding the cooling air from the radial space into the hollow interior through one or more third cap cooling holes.

[0255] According to any of the foregoing clauses, the hot-side component includes a recessed portion, and the method further includes operably guiding the cooling air from the space through one or more recessed cooling holes in the recessed portion to the combustion chamber.

[0256] According to any of the foregoing clauses, the cap is disposed in a recessed space defined by the recessed portion, the method further comprising operably guiding the cooling air from the recessed space through the one or more first cap cooling holes and into the hollow interior of the cap.

[0257] According to any of the foregoing clauses, the stud includes one or more stud cooling holes, and the method further includes operably guiding the cooling air from the cold side of the cold-side component through the one or more stud cooling holes.

[0258] According to any of the foregoing clauses, the cap further includes one or more third cap cooling holes, and the method further includes operably guiding the cooling air from the one or more stud cooling holes through the one or more third cap cooling holes and into the hollow interior.

[0259] The method according to any of the foregoing clauses further includes operably directing the cooling air through the gasket and into the space between the gasket and the cap.

[0260] The method according to any of the foregoing clauses further includes operably directing the cooling air through the gasket and into the space between the gasket and the recess.

[0261] The method according to any of the foregoing clauses further includes thin-film cooling of the cap by operably guiding the cooling air from the hollow interior through the one or more second cap cooling holes and into the combustion chamber.

[0262] The method according to any of the foregoing clauses further includes impinging cooling of the hot-side component by operably guiding the cooling air from the cold side of the cold-side component through the one or more cold-side component cooling holes and into the space between the cold-side component and the hot-side component.

[0263] According to any of the foregoing descriptions, the cooling air is compressed air from the compressor section of the turbine engine.

[0264] According to any of the preceding clauses, the cold-side component is the housing of the bushing of the turbine engine, and the hot-side component is a heat shield.

[0265] According to any of the preceding clauses, the cold-side component is an annular dome assembly, and the hot-side component is a deflector assembly.

[0266] A coupling assembly for a turbine engine includes: a cold-side component; a hot-side component, the cold-side component and the hot-side component together at least partially forming a combustion chamber; a plurality of fastening mechanisms arranged through the cold-side component; and a plurality of flexible plates, each of the plurality of flexible plates being circumferentially spaced from each other and extending from a corresponding one of the plurality of fastening mechanisms to the hot-side component and engaging the hot-side component to couple the hot-side component to the cold-side component, such that the plurality of fastening mechanisms are insulated from the combustion chamber.

[0267] According to the connecting assembly described in the foregoing clause, each of the plurality of flexible plates includes one or more flexible plate cooling holes, which are operable to guide cooling air through the plurality of flexible plates.

[0268] According to any of the preceding clauses, the plurality of fastening mechanisms include a first fastening mechanism and a second fastening mechanism, and the plurality of flexible plates include a first flexible plate extending from the first fastening mechanism to the hot-side component and a second flexible plate extending from the second fastening mechanism to the hot-side component.

[0269] According to any of the preceding clauses, the first fastening mechanism is located upstream of the second fastening mechanism in the connecting assembly.

[0270] According to any of the preceding clauses, the first flexible plate extends downstream from the first fastening mechanism and extends to the hot-side component.

[0271] According to any of the preceding clauses, the second flexible plate extends upstream from the second fastening mechanism and extends to the hot-side component.

[0272] According to any of the preceding clauses, the hot-side component includes a plurality of flanges, each of the plurality of flexible plates engaging a corresponding one of the plurality of flanges to connect the hot-side component to the cold-side component.

[0273] According to any of the preceding clauses, each of the plurality of flanges includes a radial flange portion extending substantially radially from the hot-side component and an axial flange portion extending substantially axially from the radial flange portion.

[0274] According to any of the preceding clauses, each of the plurality of flexible plates engages a corresponding axial flange portion.

[0275] According to any of the preceding clauses, the plurality of flanges includes a first flange and a second flange positioned downstream of the first flange, and the plurality of flexible plates includes a first flexible plate and a second flexible plate, the first flexible plate engaging the second flange, and the second flexible plate engaging the first flange.

[0276] The coupling assembly according to any of the foregoing clauses further includes a space defined between the first flange and the second flange, each of the plurality of flexible plates extending into the space to couple the hot-side component to the cold-side component.

[0277] According to any of the preceding clauses, the first flange includes a first radial flange portion and a first axial flange portion, the first axial flange portion extending axially downstream from the first radial flange portion.

[0278] According to any of the preceding clauses, the second flange includes a second radial flange portion and a second axial flange portion, the second axial flange portion extending axially upstream from the second radial flange portion.

[0279] According to any of the preceding clauses, the hot-side component includes one or more panels connected to the cold-side component via the plurality of flexible plates.

[0280] According to any of the preceding clauses, each of the plurality of flexible plates includes a fastening mechanism orifice for receiving a respective fastening mechanism among the one or more fastening mechanisms.

[0281] According to any of the preceding clauses, each of the plurality of flexible plates includes a fastening connection portion connected to a respective fastening mechanism in one or more of the fastening mechanisms and a flange connection portion connected to a respective flange in one of the plurality of flanges.

[0282] According to any of the preceding clauses, the flange connection portion includes one or more first protrusions and one or more second protrusions separated at the flange connection portion, the one or more first protrusions and the one or more second protrusions engaging with a corresponding flange of the plurality of flanges.

[0283] According to any of the preceding clauses, the one or more first protrusions engage the hot side of the respective flange, and the one or more second protrusions engage the cold side of the respective flange.

[0284] According to any of the preceding clauses, the respective flange is press-fitted between the one or more first protrusions and the one or more second protrusions.

[0285] According to any of the preceding clauses, each of the plurality of flexible plates includes a first bend that is defined at the fastening mechanism connection portion, such that the plurality of flexible plates extend radially inward from the fastening mechanism connection portion.

[0286] According to any of the preceding clauses, each of the plurality of flexible plates includes one or more second bends defined at the flange connection portion, wherein the one or more first protrusions and the one or more second protrusions bend at the one or more second bends.

[0287] According to any of the preceding clauses, the one or more first protrusions bend radially outward at the one or more second bends, and the one or more second protrusions bend radially inward at the one or more second bends.

[0288] According to any of the preceding clauses, the one or more first protrusions and the one or more second protrusions are divided into different directions at the one or more second bends.

[0289] According to any of the preceding clauses, each of the plurality of flexible plates includes one or more first protrusions and one or more third bends at the one or more second protrusions.

[0290] According to any of the preceding clauses, the one or more first protrusions bend radially inward at the one or more third bends, and the one or more second protrusions bend radially outward at the one or more third bends.

[0291] According to any of the preceding clauses, each of the plurality of flexible plates includes one or more first protrusions and one or more fourth bends at the one or more second protrusions.

[0292] According to any of the preceding clauses, the one or more first protrusions bend radially outward at the one or more fourth bends, and the one or more second protrusions bend radially inward at the one or more fourth bends.

[0293] According to any of the preceding clauses, the one or more first protrusions and the one or more second protrusions engage the axial flange portion at the one or more fourth bends.

[0294] According to any of the preceding clauses, each of the plurality of flexible plates includes a first fastening mechanism orifice and a second fastening mechanism orifice.

[0295] According to any of the preceding clauses, the first fastening mechanism orifice is located at the fastening mechanism connection portion, and the second fastening mechanism orifice is located at the flange connection portion.

[0296] According to any of the preceding clauses, the flange connection portion engages the cold side of the axial flange portion.

[0297] According to any of the preceding clauses, each of the plurality of flexible plates includes a first bend at the fastening mechanism connection portion and a second bend at the flange connection portion.

[0298] According to any of the preceding clauses, the flange connection portion holds the hot-side component at the axial flange portion.

[0299] According to any of the preceding clauses, the flange connection portion is fixed to the axial flange portion by at least one of brazing, welding or adhesive.

[0300] According to any of the preceding clauses, the plurality of flexible plates are flexible in multiple degrees of freedom, such that the hot-side component can move axially, radially, or circumferentially relative to the cold-side component.

[0301] According to any of the preceding clauses, the first flexible plate is positioned circumferentially adjacent to the second flexible plate.

[0302] According to any of the preceding clauses, the first flexible plate is circumferentially rearward positioned relative to the second flexible plate in the connecting assembly.

[0303] According to any of the preceding clauses, the space is defined between the cold-side component and the hot-side component, and the plurality of plates are disposed in the space.

[0304] According to any of the preceding clauses, the one or more fastening mechanisms are disposed in the space between the cold-side component and the hot-side component.

[0305] According to any of the preceding clauses, the one or more fastening mechanisms include a stud and a stud head disposed on the hot side of the cold side component.

[0306] According to any of the preceding clauses, the stud head is disposed in the space between the cold-side component and the hot-side component.

[0307] According to any of the preceding clauses, the cold-side component is the housing of the bushing of the turbine engine, and the hot-side component is a heat shield.

[0308] According to any of the preceding clauses, the cold-side component is an annular dome assembly, and the hot-side component is a deflector assembly.

[0309] According to any of the preceding clauses, the cold-side component includes one or more cold-side component cooling holes that are operable to direct cooling air from the cold side of the cold-side component to the space between the cold-side component and the hot-side component.

[0310] According to any of the preceding clauses, the cooling holes of the one or more cold-side components are impact cooling holes.

[0311] According to any of the preceding clauses, the hot-side component includes one or more hot-side component cooling holes that are operable to direct the cooling air from the space to the combustion chamber.

[0312] According to any of the preceding clauses, the cooling holes of the one or more hot-side components are thin-film cooling holes.

[0313] According to any of the preceding clauses, the one or more fastening mechanisms each include a stud extending through the cold-side component.

[0314] According to any of the preceding clauses, the fastening assembly further includes a nut connected to the stud on the cold side of the stud.

[0315] According to any of the preceding clauses, the nut is connected to the stud via a second threaded connection.

[0316] A turbine engine includes: a combustion section including a combustion chamber; and a coupling assembly including: a cold-side component; a hot-side component, the cold-side component and the hot-side component together at least partially forming the combustion chamber; a plurality of fastening mechanisms arranged through the cold-side component; and a plurality of flexible plates, each of the plurality of flexible plates being circumferentially spaced from each other and extending from a respective one of the plurality of fastening mechanisms to the hot-side component and engaging the hot-side component to couple the hot-side component to the cold-side component, such that the plurality of fastening mechanisms are insulated from the combustion chamber.

[0317] According to any of the preceding clauses of the turbine engine, each of the plurality of flexible plates includes one or more flexible plate cooling holes that are operable to guide cooling air through the plurality of flexible plates.

[0318] According to any of the preceding clauses of the turbine engine, the hot-side component includes a plurality of flanges, each of the plurality of flexible plates engaging a corresponding one of the plurality of flanges to connect the hot-side component to the cold-side component.

[0319] According to any of the foregoing clauses, the plurality of fastening mechanisms include a first fastening mechanism and a second fastening mechanism, and the plurality of flexible plates include a first flexible plate extending from the first fastening mechanism to the hot-side component and a second flexible plate extending from the second fastening mechanism to the hot-side component.

[0320] According to any of the foregoing clauses, the first fastening mechanism is located upstream of the second fastening mechanism in the turbine engine.

[0321] According to any of the preceding clauses of the turbine engine, the first flexible plate extends downstream from the first fastening mechanism and extends to the hot-side component.

[0322] According to any of the foregoing clauses of the turbine engine, the second flexible plate extends upstream from the second fastening mechanism and extends to the hot-side component.

[0323] According to any of the preceding clauses of the turbine engine, the hot-side component includes a plurality of flanges, the plurality of flexible plates engaging the plurality of flanges to connect the hot-side component to the cold-side component.

[0324] According to any of the foregoing clauses, the plurality of flanges includes a first flange and a second flange positioned downstream of the first flange, the first flexible plate engaging the second flange and the second flexible plate engaging the first flange.

[0325] According to any of the foregoing clauses, each of the plurality of flanges includes a radial flange portion extending substantially radially from the hot-side component and an axial flange portion extending substantially axially from the radial flange portion.

[0326] According to any of the foregoing clauses, the plurality of flexible plates engage the axial flange portion in the turbine engine.

[0327] According to any of the foregoing clauses of the turbine engine, the first flange includes a first radial flange portion and a first axial flange portion, the first axial flange portion extending axially downstream from the first radial flange portion.

[0328] According to any of the foregoing clauses of the turbine engine, the second flange includes a second radial flange portion and a second axial flange portion, the second axial flange portion extending axially upstream from the second radial flange portion.

[0329] The turbine engine according to any of the foregoing clauses further includes a space defined between the first flange and the second flange, into which the plurality of flexible plates extend.

[0330] According to any of the foregoing clauses, the hot-side component includes one or more panels connected to the cold-side component via the plurality of flexible plates.

[0331] According to any of the foregoing clauses, each of the plurality of flexible plates includes a fastening mechanism orifice for receiving a respective fastening mechanism among the one or more fastening mechanisms.

[0332] According to any of the foregoing clauses, each of the plurality of flexible plates includes a fastening connection portion connected to a respective fastening mechanism in one or more of the fastening mechanisms and a flange connection portion connected to a respective flange in one of the plurality of flanges.

[0333] According to any of the foregoing clauses, the turbine engine, the flange connection portion includes one or more first protrusions and one or more second protrusions separated at the flange connection portion, the one or more first protrusions and the one or more second protrusions engaging with a corresponding flange of the plurality of flanges.

[0334] According to any of the foregoing clauses of the turbine engine, the one or more first protrusions engage the hot side of the respective flange, and the one or more second protrusions engage the cold side of the respective flange.

[0335] According to any of the foregoing clauses of the turbine engine, the corresponding flange is press-fitted between the one or more first protrusions and the one or more second protrusions.

[0336] According to any of the preceding clauses of the turbine engine, each of the plurality of flexible plates includes a first bend defined at the fastening mechanism connection portion, such that the plurality of flexible plates extend radially inward from the fastening mechanism connection portion.

[0337] According to any of the preceding clauses, each of the plurality of flexible plates includes one or more second bends defined at the flange connection portion, wherein the one or more first protrusions and the one or more second protrusions bend at the one or more second bends.

[0338] According to any of the preceding clauses of the turbine engine, the one or more first protrusions are radially outwardly curved at the one or more second bends, and the one or more second protrusions are radially inwardly curved at the one or more second bends.

[0339] According to any of the preceding clauses of the turbine engine, the one or more first protrusions and the one or more second protrusions are divided into different directions at the one or more second bends.

[0340] According to any of the preceding clauses, each of the plurality of flexible plates includes one or more first protrusions and one or more third bends at the one or more second protrusions.

[0341] According to any of the preceding clauses of the turbine engine, the one or more first protrusions are radially inwardly curved at the one or more third bends, and the one or more second protrusions are radially outwardly curved at the one or more third bends.

[0342] According to any of the preceding clauses, each of the plurality of flexible plates includes one or more first protrusions and one or more fourth bends at the one or more second protrusions.

[0343] According to any of the preceding clauses, the one or more first protrusions bend radially outward at the one or more fourth bends, and the one or more second protrusions bend radially inward at the one or more fourth bends.

[0344] According to any of the preceding clauses, in a turbine engine, the one or more first protrusions and the one or more second protrusions engage the axial flange portion at the one or more fourth bends.

[0345] According to any of the foregoing clauses, the plurality of flexible plates each include a first fastening mechanism orifice and a second fastening mechanism orifice.

[0346] According to any of the foregoing clauses, the first fastening mechanism orifice is located at the fastening mechanism connection portion, and the second fastening mechanism orifice is located at the flange connection portion.

[0347] According to any of the foregoing clauses of the turbine engine, the flange connection portion engages the cold side of the axial flange portion.

[0348] According to any of the preceding clauses, the plurality of flexible plates each include a first bend at the fastening mechanism connection portion and a second bend at the flange connection portion.

[0349] According to any of the preceding clauses of the turbine engine, the flange connection portion holds the hot-side component at the axial flange portion.

[0350] According to any of the preceding clauses of the turbine engine, the flange connection portion is fixed to the axial flange portion by at least one of brazing, welding or adhesive.

[0351] According to any of the preceding clauses of the turbine engine, the plurality of flexible plates are flexible in multiple degrees of freedom, such that the hot-side component can move axially, radially, or circumferentially relative to the cold-side component.

[0352] According to any of the foregoing clauses of the turbine engine, the first flexible plate is positioned circumferentially adjacent to the second flexible plate.

[0353] According to any of the foregoing clauses of the turbine engine, the first flexible plate is circumferentially rearward positioned relative to the second flexible plate.

[0354] According to any of the foregoing clauses, the space of the turbine engine is defined between the cold-side component and the hot-side component, and the plurality of plates are disposed in the space.

[0355] According to any of the foregoing clauses, the one or more fastening mechanisms are disposed in the space between the cold-side component and the hot-side component of the turbine engine.

[0356] According to any of the preceding clauses, the one or more fastening mechanisms include a stud and a stud head, the stud head being disposed on the hot side of the cold-side component.

[0357] According to any of the foregoing clauses, the stud head is disposed in the space between the cold-side component and the hot-side component of the turbine engine.

[0358] According to any of the foregoing clauses, the cold-side component is the housing of the turbine engine bushing, and the hot-side component is a heat shield.

[0359] According to any of the preceding clauses, the cold-side component is an annular dome assembly, and the hot-side component is a deflector assembly.

[0360] According to any of the preceding clauses of the turbine engine, the cold-side component includes one or more cold-side component cooling holes that are operable to direct cooling air from the cold side of the cold-side component to the space between the cold-side component and the hot-side component.

[0361] According to any of the preceding clauses, the cooling holes of the one or more cold-side components are impact cooling holes.

[0362] According to any of the preceding clauses, the hot-side component includes one or more hot-side component cooling holes that are operable to direct cooling air from the space to the combustion chamber.

[0363] According to any of the preceding clauses, the one or more hot-side component cooling holes are thin-film cooling holes.

[0364] According to any of the foregoing clauses, the one or more fastening mechanisms each include a stud extending through the cold-side component.

[0365] According to any of the foregoing clauses of the turbine engine, the fastening assembly further includes a nut attached to the stud on the cold side of the stud.

[0366] According to any of the foregoing clauses of the turbine engine, the nut is connected to the stud via a second threaded connection.

[0367] A method for operably directing cooling air through a turbine engine. The method includes operably directing cooling air through a cold-side component of the turbine engine, a hot-side component being coupled to the cold-side component by a plurality of fastening mechanisms, the cold-side component and the hot-side component together at least partially forming a combustion chamber. The method includes operably directing the cooling air through one or more flexible plate cooling holes of a plurality of flexible plates, each of the plurality of flexible plates being circumferentially spaced from each other, and extending a corresponding one of the plurality of fastening mechanisms to the hot-side component and engaging the hot-side component to couple the hot-side component to the cold-side component, such that the plurality of fastening mechanisms are insulated from the combustion chamber.

[0368] The method described according to the foregoing clauses further includes operably guiding the cooling air through the hot-side component.

[0369] The method according to any of the foregoing clauses further includes operably directing the cooling air through one or more cooling holes in the cold-side component and into the space defined between the cold-side component and the hot-side component.

[0370] The method according to any of the foregoing clauses further includes operably guiding the cooling air from the space through one or more flexible plate cooling holes of the plurality of flexible plates.

[0371] The method according to any of the foregoing clauses further includes operably directing the cooling air between the plurality of flexible plates and the hot-side component.

[0372] The method according to any of the foregoing clauses further includes operably directing the cooling air through one or more cooling holes in the hot-side components and into the combustion chamber.

[0373] The method according to any of the foregoing clauses further includes thin-film cooling of the cap by operably guiding the cooling air from the hollow interior through the one or more second cap cooling holes and into the combustion chamber.

[0374] The method according to any of the foregoing clauses further includes impinging cooling of the hot-side component by operably guiding the cooling air from the cold side of the cold-side component through the one or more cold-side component cooling holes and into the space between the cold-side component and the hot-side component.

[0375] According to any of the foregoing descriptions, the cooling air is compressed air from the compressor section of the turbine engine.

[0376] According to any of the preceding clauses, the cold-side component is the housing of the bushing of the turbine engine, and the hot-side component is a heat shield.

[0377] According to any of the preceding clauses, the cold-side component is an annular dome assembly, and the hot-side component is a deflector assembly.

[0378] According to any of the foregoing clauses, the plurality of flexible plates include a first flexible plate and a second flexible plate, the method comprising operably guiding cooling air through the first flexible plate and the second flexible plate.

[0379] According to any of the foregoing provisions, the plurality of fastening mechanisms include a first fastening mechanism and a second fastening mechanism, and the plurality of flexible plates include a first flexible plate extending from the first fastening mechanism to the hot-side component and a second flexible plate extending from the second fastening mechanism to the hot-side component.

[0380] According to any of the methods described in the foregoing clauses, the first fastening mechanism is located upstream of the second fastening mechanism.

[0381] According to any of the foregoing provisions, the first flexible plate extends downstream from the first fastening mechanism and extends to the hot-side component.

[0382] According to any of the foregoing provisions, the second flexible plate extends upstream from the second fastening mechanism and extends to the hot-side component.

[0383] According to any of the preceding descriptions, the hot-side component includes a plurality of flanges, the plurality of flexible plates engaging the plurality of flanges to connect the hot-side component to the cold-side component.

[0384] According to any of the foregoing provisions, the plurality of flanges includes a first flange and a second flange positioned downstream of the first flange, wherein the first flexible plate engages the second flange and the second flexible plate engages the first flange.

[0385] Although preferred embodiments of the present disclosure have been described above, other variations and modifications will be apparent to those skilled in the art and can be made without departing from the spirit or scope of the present disclosure. Furthermore, features described in connection with one embodiment of the present disclosure may be used in conjunction with other embodiments, even if not explicitly stated above.

Claims

1. A coupling assembly for a turbine engine, characterized in that, The connection component includes: A cold-side component having a first fastening mechanism orifice through which a first fastening mechanism orifice is disposed; A hot-side component, wherein the cold-side component and the hot-side component together at least partially form a combustion chamber, wherein the hot-side component has a second fastening mechanism orifice through which it is disposed; and Fastening mechanism, which connects the hot-side component to the cold-side component, the fastening mechanism comprising: Studs, the studs being configured to pass through the first fastening mechanism orifice of the cold-side component; and A cap, positioned on the stud and within the second fastening mechanism orifice of the hot-side component, the cap defining a hollow interior and including one or more first cap cooling holes operably guiding cooling air into the hollow interior, such that the hollow interior provides a buffer of cooling air between the combustion chamber and the stud, wherein a portion of the stud is disposed within the hollow interior such that the hollow interior surrounds the stud.

2. The connecting component according to claim 1, characterized in that, in, The space is defined between the cold-side component and the hot-side component, and the stud is disposed in the space.

3. The connecting component according to claim 1, characterized in that, in, The cap is configured to pass through the heat-side component.

4. The connecting component according to claim 1, characterized in that, in, The cap is positioned between the stud and the combustion chamber.

5. The connecting component according to claim 1, characterized in that, in, The stud is radially spaced from the combustion chamber, thereby insulating the stud from the combustion chamber.

6. The connecting component according to claim 1, characterized in that, in, The cap includes one or more second cap cooling holes that are operable to guide cooling air from the hollow interior into the combustion chamber.

7. The connecting component according to claim 1, characterized in that, in, The hollow interior has a diameter larger than the outer diameter of the stud.

8. The connecting component according to claim 1, characterized in that, in, The cap includes a thin wall defined by an inner surface and an outer surface, the thin wall defining the shape of the hollow interior.

9. The connecting component according to claim 8, characterized in that, in, The shape of the hollow interior roughly corresponds to the shape of the cap.

10. The connecting component according to claim 1, characterized in that, The device further includes a gasket disposed between the cold-side component and the hot-side component, the gasket being flexible to allow the hot-side component to move relative to the cold-side component, and the gasket preventing the hot-side component from contacting the cold-side component.

11. The connection assembly according to claim 10, characterized in that, in, The gasket includes one or more gasket cooling holes that operably direct cooling air toward the cap.

12. The connecting assembly according to claim 11, characterized in that, in, The gasket includes one or more gasket grooves that extend radially inward from the outer edge of the gasket to the one or more gasket cooling holes.

13. The connecting component according to claim 1, characterized in that, in, The cap has a generally truncated conical shape with sloping sidewalls.

14. The connection assembly according to claim 13, characterized in that, in, The one or more first cap cooling holes extend through the inclined sidewall and are in fluid communication with the space defined between the cold side component and the hot side component, the one or more first cap cooling holes being operable to guide the cooling air from the space into the hollow interior.

15. A turbine engine, characterized in that, include: Combustion zone, the combustion zone including a combustion chamber; as well as The connection component includes: A cold-side component having a first fastening mechanism orifice through which a first fastening mechanism orifice is disposed; A hot-side component, wherein the cold-side component and the hot-side component together at least partially form the combustion chamber, wherein the hot-side component has a second fastening mechanism orifice through which it is disposed; and Fastening mechanism, which connects the hot-side component to the cold-side component, the fastening mechanism comprising: Studs, the studs being configured to pass through the first fastening mechanism orifice of the cold-side component; and A cap, positioned on the stud and within the second fastening mechanism orifice of the hot-side component, the cap defining a hollow interior and including one or more first cap cooling holes operably guiding cooling air into the hollow interior, such that the hollow interior provides a buffer of cooling air between the combustion chamber and the stud, wherein a portion of the stud is disposed within the hollow interior such that the hollow interior surrounds the stud.

16. The turbine engine according to claim 15, characterized in that, in, The cap is configured to pass through the heat-side component.

17. The turbine engine according to claim 15, characterized in that, in, The cap is positioned between the stud and the combustion chamber.

18. The turbine engine according to claim 15, characterized in that, in, The stud is radially spaced from the combustion chamber, thereby insulating the stud from the combustion chamber.

19. The turbine engine according to claim 15, characterized in that, in, The cap includes one or more second cap cooling holes that are operable to guide cooling air from the hollow interior into the combustion chamber.

20. The turbine engine according to claim 15, characterized in that, in, The hollow interior has a diameter larger than the outer diameter of the stud.

21. The turbine engine according to claim 15, characterized in that, in, The cap includes a thin wall defined by an inner surface and an outer surface, the thin wall defining the shape of the hollow interior.

22. The turbine engine according to claim 21, characterized in that, in, The shape of the hollow interior roughly corresponds to the shape of the cap.

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