Turbine engine seal for turbine engine

Abstract

A turbine engine seal configured for use between a turbine engine rotor and a turbine engine static component of a turbine engine may include a sealing structure having a negative thermal expansion (NTE) layer on one or both of the turbine engine rotor and the turbine engine static component. The NTE layer may include an NTE reactive feature composed of a material having a negative coefficient of thermal expansion. When the turbine engine rotor rubs against the turbine engine static component, heat is generated, and the NTE reactive component experiences a temperature rise from a first temperature to a second temperature. The increase in temperature results in a reduction in size of the NTE-reactive component, thereby forming a hydrodynamic pouch that can be used to generate a lift that propels the separation between the turbine engine rotor and the turbine engine static component. The sealing structure may include a lattice compliant layer.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to sealing assemblies for rotary machines, and more particularly, to seals for rotary machines, such as turbine engines, and methods of manufacturing the sealing assemblies and methods of facilitating separation between a turbine engine rotor and a turbine engine static component. BACKGROUND

[0002] Rotary machines, such as gas turbine engines, have seals between a rotating component (e.g., a rotor) and a corresponding stationary component (e.g., a stator). These seals help reduce fluid leakage between the rotor and the stator. Transient operating conditions and / or abnormal movement of the rotor can cause leakage of the seals. Excessive leakage of the seals in the rotary machine can significantly reduce the operational efficiency of the rotary machine. Transient operating conditions and / or abnormal movement of the rotor can also cause increased friction and / or contact between the seals and the rotor. This friction and / or contact between the seals and the rotor can cause premature wear and / or reduced operational efficiency of the rotary machine. Accordingly, it would be desirable to provide improved sealing assemblies for rotary machines, such as turbine engines, and improved methods of sealing an interface between a rotor and a stator of a rotary machine. BRIEF DESCRIPTION OF DRAWINGS

[0003] A complete and enabling disclosure is set forth in the specification of this patent document, including the best mode for carrying out the application, of which the following examples are representative, in which:

[0004] Figure 1 A schematic cross-sectional view of an exemplary turbine engine is shown;

[0005] Figure 2 A schematic view of an exemplary sealing assembly disposed between a turbine engine rotor and a turbine engine static component is shown;

[0006] Figure 3A A schematic view of an exemplary sealing structure of a sealing assembly at a first temperature is shown;

[0007] Figure 3B A schematic view of an exemplary sealing structure of a sealing assembly at a first temperature is shown;

[0008] Figure 4A A schematic view of an exemplary sealing structure of a sealing assembly at a second temperature is shown;

[0009] Figure 4B A schematic view of an exemplary sealing structure of a sealing assembly at a second temperature is shown;

[0010] Figure 5 A schematic view of another exemplary sealing structure at a first temperature is shown;

[0011] Figure 6 a second temperature is shown. Figure 6 a schematic view of an exemplary seal structure;

[0012] Figure 7 a schematic view of another exemplary seal structure having a lattice compliant layer is shown.

[0013] Figure 8 a schematic view of another exemplary seal structure having a lattice compliant layer is shown.

[0014] Figure 9 a schematic view of an annular arrangement of multiple segments of an exemplary seal structure is shown.

[0015] Figure 10 a method of operating a turbine engine having a seal structure is shown; and

[0016] Figure 11 a method of making a seal structure having a lattice compliant layer is shown.

[0017] Reference numbers repeated in the description and drawings are intended to refer to the same or like parts or elements throughout the present disclosure. DETAILED DESCRIPTION

[0018] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the present disclosure and is not meant as a limitation of the present disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the present disclosure. For instance, features illustrated or described as part of one embodiment, can be used with another embodiment to yield still a further embodiment. Thus, it is intended that the present disclosure cover all such modifications and variations of this disclosure.

[0019] The word "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations. Furthermore, unless otherwise indicated, all embodiments described herein are to be considered exemplary.

[0020] As used herein, the terms "first," "second," and "third" can be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

[0021] The terms “upper,” “lower,” “right,” “left,” “vertical,” “horizontal,” “top,” “bottom,” “lateral,” “longitudinal,” and the like shall relate to the present disclosure as it is oriented in the drawings. However, it is to be understood that the present disclosure can assume various alternative orientations, unless otherwise specified or clear from context. It is also to be understood that the specific devices illustrated in the attached drawings, and described in the following specification, are simply exemplary embodiments of the present disclosure. Hence, specific dimensions and other physical characteristics related to the embodiments disclosed herein are not to be considered as limiting.

[0022] The terms “forward” and “aft” refer to relative positions within a turbine engine, with forward referring to a position closer to an engine inlet and aft referring to a position closer to an engine nozzle or exhaust.

[0023] The terms “upstream” and “downstream” refer to the relative direction with respect to fluid flow in a fluid path. For example, “upstream” refers to the direction from which fluid flows, and “downstream” refers to the direction to which fluid flows.

[0024] The singular forms “a,” “an,” and “the” include plural references unless the context clearly dictates otherwise.

[0025] Unless otherwise stated herein, the terms “coupled,” “fixed,” “attached to,” and the like, mean either directly coupled, fixed, or attached by one or more intermediate components or features.

[0026] Approximating language as used herein throughout the description and claims is applied to modify any quantitative representation that could possibly vary depending on a specific implementation scenario. Accordingly, a value modified by a term or terms, such as “about,” “approximately,” and “substantially,” are not limited to the exact value specified. In at least some instances, an approximate language can correspond to the precision of an instrument for measuring the value, or the precision of the method or machine for constructing or manufacturing the component and / or system. For example, an approximate language can refer to within a 1%, 2%, 4%, 10%, 15%, or 20% margin of error.

[0027] Herein and throughout the specification and claims, range limitations are combined and interchanged, such ranges are identified and include all the sub-ranges included therein unless context or language indicates otherwise. For example, a range of “between A and B” is identified as including all values of A and B unless context or language indicates otherwise.

[0028] Additionally, unless otherwise stated, the terms "low," "high," or their respective comparatives (e.g., lower, higher, if applicable) refer to relative speeds within the engine. For example, a "low-pressure turbine" operates at pressures typically lower than those of a "high-pressure turbine." Alternatively, unless otherwise stated, the above terms may be understood in their superlative sense. For example, a "low-pressure turbine" may refer to the turbine with the lowest maximum pressure within turbine section 126, while a "high-pressure turbine" may refer to the turbine with the highest maximum pressure within turbine section 126.

[0029] The term “turbine” or “turbomachinery” refers to a machine that includes one or more compressors, a heating section (e.g., a burner section), and one or more turbines that together generate torque output.

[0030] As used herein, the term "turbo engine" refers to an engine that includes a turbine as its power source, in whole or in part. Examples of turbo engines include gas turbine engines, as well as hybrid electric turbine engines, such as turbofan engines, turboprop engines, turbojet engines, turboshaft engines, etc.

[0031] As used herein, the term "rotor" refers to any component of a rotating machine (such as a turbine engine) that rotates about an axis of rotation. As an example, a rotor may include a shaft or spool of a rotating machine (such as a turbine engine).

[0032] As used herein, the term "stator" refers to any component of a rotating machine (such as a turbine engine) that has a coaxial construction and arrangement with the rotor of the rotating machine. The stator may be stationary or may rotate about an axis of rotation. The stator may be arranged radially inward or radially outward relative to the rotor along a radial axis.

[0033] One or more components of the turbine engine described below can be manufactured or formed using any suitable process, such as additive manufacturing (e.g., 3D printing). Using such a process allows the component to be integrally formed as a single, monolithic part, or any suitable number of sub-parts. In particular, additive manufacturing processes can allow the integral formation of such components and include a variety of features that are not achievable using existing manufacturing methods. For example, the additive manufacturing methods described herein can allow the manufacture of channels, conduits, cavities, openings, housings, manifolds, double walls, heat exchangers, or other components, or the specific positioning and integration of these components, which may have unique features, constructions, thicknesses, materials, densities, fluid passages, manifolds, and mounting structures that may not be achievable or practical using existing manufacturing methods. Some of these features are described herein.

[0034] Suitable additive manufacturing technologies according to this disclosure include, for example, selective laser melting (SLM), direct metal laser melting (DMLM), fused deposition modeling (FDM), selective laser sintering (SLS), 3D printing such as by inkjet, laser jetting and binder jetting, stereolithography (SLA), direct selective laser sintering (DSLS), electron beam sintering (EBS), electron beam melting (EBM), laser engineered net forming (LENS), laser net forming manufacturing (LNSM), direct metal deposition (DMD), digital light processing (DLP), direct selective laser melting (DSLM), and other known processes.

[0035] Suitable powder materials for manufacturing the structures provided herein as a single, monolithic structure include metal alloys, polymers, or ceramic powders. Exemplary metal powder materials are stainless steel alloys, cobalt-chromium alloys, aluminum alloys, titanium alloys, nickel-based superalloys, and cobalt-based superalloys. Additionally, suitable alloys may include those engineered to have good oxidation resistance, referred to as “superalloys” that have acceptable strength at elevated operating temperatures in turbine engines, such as Hastelloy, Inco nickel alloys (e.g., IN 738, IN 792, IN 939), Rene alloys (e.g., Rene N4, Rene N5, Rene 80, Rene 142, Rene 195), Haines alloys, Mar M, CM 247, CM 247LC, C263, 718, X-850, ECY768, 282, X45, PWA 1483, and CMSX (e.g., CMSX-4) single-crystal alloys. The manufactured objects disclosed herein can be formed from one or more selected crystal microstructures, such as directional solidification (“DS”) or single crystals (“SX”)).

[0036] As used herein, the terms "monolithic," "single," or "integral" used to describe a structure mean that the structure is formed integrally from a continuous material or group of materials without seams, joints, etc. The monolithic single structure described herein can be formed to have the structure by additive manufacturing, or alternatively by casting or the like.

[0037] This disclosure generally provides a sealing assembly for rotating machines. The sealing assembly disclosed herein can be used in any rotating machine. Exemplary embodiments may be particularly suitable for turbines, such as turbine engines. The sealing assembly disclosed herein includes a membrane-riding seal that provides a fluid film between one side of a seal and one side of a rotor. The sealing assembly may be located at the interface between a turbine engine rotor and a static component of a turbine engine. The sealing assembly may include a sealing structure.

[0038] Currently disclosed sealing assemblies are generally considered non-contact seals because fluid bearings inhibit contact between the sealing surface and the rotor surface. Additionally, currently disclosed sealing assemblies include sealing structures configured to float or actuate along the axis of motion in response to prime movers caused by transient operating conditions of the rotating machine and / or abnormal rotor movement. This structure includes the features described herein that provide an improved response to transient operating conditions and / or abnormal rotor movement. Currently disclosed sealing structures can accommodate a wider range of operating conditions and / or provide improved operational performance, including improved sealing assembly performance and / or improved rotating machine performance. Additionally or alternatively, currently disclosed sealing assemblies can provide a lower probability of continuous contact between the turbine rotor and turbine static components during transient conditions, thereby improving the durability and / or service life of the sealing assembly, turbine rotor, turbine static components, and / or related components of the rotating machine.

[0039] Exemplary embodiments of this disclosure will now be described in more detail. References Figure 1 An exemplary turbine engine 100 will be described. In some embodiments, the currently disclosed sealing assembly may be included in a rotating machine such as turbine engine 100. The exemplary turbine engine 100 may be mounted to an aircraft, such as in an underwing configuration or a tail-mounted configuration. It will be understood that Figure 1 The turbine engine 100 shown is provided as an example and does not constitute a limitation, and the subject matter of this disclosure can be implemented with other types of turbine engines and other types of rotating machines.

[0040] Generally, the turbine engine 100 may include a fan section 102 and a core engine 104 disposed downstream of the fan section 102. The fan section 102 may include a fan 106 having any suitable configuration, such as a single-stage configuration with variable pitch. The fan 106 may include a plurality of fan blades 108 spaced apart and coupled to a fan disk 110. The fan blades 108 may extend generally radially outward from the fan disk 110. The core engine 104 may be directly or indirectly coupled to the fan section 102 to provide torque for driving the fan section 102.

[0041] The core engine 104 may include an engine housing 114 that surrounds one or more portions of the core engine 104, including a compressor section 122, a combustor section 124, and a turbine section 126. The engine housing 114 may define a core engine inlet 116, an exhaust nozzle 118, and a core airflow path 120 between them. The core airflow path 120 may pass through the compressor section 122, combustor section 124, and turbine section 126 in a series flow relationship. The compressor section 122 may include a first turbocharger or low-pressure (LP) compressor 128 and a second high-pressure (HP) compressor 130. The turbine section 126 may include a first high-pressure (HP) turbine 132 and a second low-pressure (LP) turbine 134. The compressor section 122, combustor section 124, turbine section 126, and exhaust nozzle 118 may be arranged in a series flow relationship and may each define a portion of the core airflow path 120 through the core engine 104.

[0042] The core motor 104 and fan section 102 can be coupled to a shaft driven by the core motor 104. As an example, such as... Figure 1 As shown, the core engine 104 may include a high-pressure (HP) shaft 136 and a low-pressure (LP) shaft 138. The HP shaft 136 can drive the HP turbine 132 to the HP compressor 130. The LP shaft 138 can drive the LP turbine 134 to the LP compressor 128. In other embodiments, such as in the case of a turbine engine 100 including an intermediate-pressure turbine, the turbine engine 100 may have three shafts. The shafts of the core engine 104, together with the rotating portions of the core engine 104, may sometimes be referred to as "spools". The HP shaft 136, the rotating portion of the HP compressor 130 coupled to the HP shaft 136, and the rotating portion of the HP turbine 132 coupled to the HP shaft 136 may be collectively referred to as the high-pressure (HP) spool 140. The LP shaft 138, the rotating portion of the LP compressor 128 coupled to the LP shaft 138, and the rotating portion of the LP turbine 134 coupled to the LP shaft 138 may be collectively referred to as the low-pressure (LP) spool 142.

[0043] In some embodiments, fan section 102 may be directly coupled to the shaft of core engine 104, such as directly coupled to LP shaft 138. Alternatively, as Figure 1 As shown, fan section 102 and core engine 104 can be connected to each other via a power gearbox 144 (such as a planetary reduction gearbox, a rotary gearbox, etc.). For example, power gearbox 144 can connect LP shaft 138 to fan 106, such as fan disc 110 connected to fan section 102. Power gearbox 144 may include multiple gears for reducing the rotational speed of LP shaft 138 to a more efficient rotational speed for fan section 102.

[0044] Still referencing Figure 1 The fan section 102 of the turbine engine 100 may include a fan housing 146, which at least partially surrounds the fan 106 and / or a plurality of fan blades 108. The fan housing 146 may be supported by the core engine 104, for example, by a plurality of circumferentially spaced and substantially radially extending outlet guide vanes 148. The turbine engine 100 may include a nacelle 150. The nacelle 150 may be fixed to the fan housing 146. The nacelle 150 may include one or more sections at least partially surrounding the fan section 102, the fan housing 146, and / or the core engine 104. For example, the nacelle 150 may include a nosecowl, a fan shroud, an engine shroud, a thrust reverser, etc. The inner portions of the fan housing 146 and / or the nacelle 150 may circumferentially surround the outer portion of the core engine 104. The inner portions of the fan housing 146 and / or the nacelle 150 may define a bypass passage 152. The bypass passage 152 may be arranged in a ring between the outer portion of the core engine 104 and the inner portion of the fan casing 146 and / or the nacelle 150 surrounding the outer portion of the core engine 104.

[0045] During operation of the turbine engine 100, inlet airflow 154 enters the turbine engine 100 through inlet 156 defined by nacelle 150 (such as the front shroud of nacelle 150). Inlet airflow 154 passes through fan blades 108. Inlet airflow 154 splits into core airflow 158, which flows into and passes through core airflow path 120 of the core engine 104, and bypass airflow 160, which flows through bypass passage 152. Core airflow 158 is compressed by compressor section 122. The pressurized air from compressor section 122 flows downstream to combustor section 124, where fuel is introduced to generate combustion gases, indicated by arrow 162. Combustion gases exit combustor section 124 and flow through turbine section 126, generating torque that rotates compressor section 122 to support combustion and also rotates fan section 102. Rotation of fan section 102 causes bypass airflow 160 to flow through bypass passage 152, generating propulsive thrust. The core airflow leaving the exhaust nozzle 118 generates additional thrust.

[0046] In some exemplary embodiments, the turbine engine 100 may be a relatively large power-stage turbine engine 100, which can generate a relatively large thrust. For example, the turbine engine 100 may be configured to generate a thrust of about 300 kilonewtons (kN) to about 700 kN, such as a thrust of about 300 kN to about 500 kN, such as a thrust of about 500 kN to about 600 kN, or such as a thrust of about 600 kN to about 700 kN. However, it will be understood that, with reference to Figure 1The various features and properties of the turbine engine 100 described are provided by way of example only and do not constitute a limitation. In fact, this disclosure can be implemented with respect to any desired turbine engine, including those turbine engines having properties or features that differ from the turbine engine 100 described herein in one or more respects.

[0047] Still referencing Figure 1 The turbine engine 100 includes sealing assemblies at multiple locations throughout the turbine engine 100, and any one or more of the sealing assemblies can be constructed according to this disclosure. The currently disclosed sealing assemblies can be disposed in the turbine engine 100 at any location, including interfaces with rotating portions of the turbine engine 100, such as interfaces with rotating portions of the core engine 104 or spools. For example, the sealing assembly may be included at an interface with a portion of the LP spool 142 and / or at an interface with the HP spool 140. In some embodiments, the sealing assembly may be included at an interface between a spool (such as the LP spool 142 or HP spool 140) of the core engine 104 and a stationary portion. Additionally or alternatively, the sealing assembly may be included at an interface between the LP spool 142 and the HP spool 140. Additionally or alternatively, the sealing assembly may be included at an interface between the stationary portion of the core engine 104 and the LP spool 138 or HP spool 136, and / or at an interface between the LP spool 138 and the HP spool 136.

[0048] As an example, Figure 1Some exemplary locations of the sealing assembly are shown. As an example, the sealing assembly may be located at or near bearing chamber 164. A sealing assembly located at or near bearing chamber 164 may sometimes be referred to as a bearing chamber seal. Such a bearing chamber seal may be configured to inhibit airflow (such as core airflow 158) from entering the bearing chamber of the turbine engine 100, such as the bearing chamber located at the interface between the LP shaft 138 and the HP shaft 136. As another example, the sealing assembly may be located at or near the compressor section 122 of the turbine engine 100. In some embodiments, the sealing assembly may be located at or near, for example, the compressor discharge port 166 of the HP compressor 130. A sealing assembly located at or near the compressor discharge port 166 may sometimes be referred to as a compressor discharge pressure seal. Such a compressor discharge pressure seal may be configured to maintain pressure downstream of the compressor section 122 and / or provide bearing thrust balance. Additionally or alternatively, the sealing assembly may be located between adjacent compressor stages 168 of the compressor section 122. A sealing assembly located between adjacent compressor stages 168 may sometimes be referred to as an interstage compressor seal. Such compressor stage seals can be configured to restrict air recirculation within compressor section 122. As another example, the sealing assembly can be located at or near turbine section 126 of turbine engine 100. In some embodiments, the sealing assembly can be located at or near turbine inlet 170, such as HP turbine 132 or LP turbine 134. A sealing assembly located at or near turbine inlet 170 may sometimes be referred to as a front turbine seal. Such a front turbine seal can be configured to receive high-pressure cooling air for HP turbine 132 and / or LP turbine 134 (such as for their turbine disks and turbine blades). Additionally or alternatively, the sealing assembly can be located at or near one or more turbine disk edges 172. A sealing assembly located at or near turbine disk edges 172 may sometimes be referred to as a turbine disk edge seal. Such a turbine disk edge seal can be configured to inhibit the intake of hot gas into the disk edge region. Additionally or alternatively, the sealing assembly can be located between adjacent turbine stages 174 of turbine section 126. A sealing assembly located between adjacent turbine stages 174 may sometimes be referred to as an inter-stage seal. This turbine stage seal can be configured to restrict air recirculation within the turbine section 126.

[0049] The sealing assemblies at these or other locations of the turbine engine 100 may be constructed in accordance with this disclosure. Additionally or alternatively, the turbine engine 100 may include the currently disclosed sealing assemblies at one or more other locations of the turbine engine 100. It should also be understood that the currently disclosed sealing assemblies may also be used in other rotating machines, and references are made to… Figure 1 The turbine engine 100 described is provided as an example and does not constitute a limitation.

[0050] Now for reference Figure 2 An exemplary sealing assembly is further described below. Figure 2 As shown, a rotating machine 200 (such as a turbine engine 100) may include a sealing assembly 202 configured to provide a sealed interface between the turbine engine rotor 204 and the turbine engine static component 205 of the rotating machine 200. The sealing assembly 202 can be integrated into any rotating machine 200 (such as reference 100). Figure 1 In the aforementioned turbine engine 100). For example... Figure 2 As shown, the sealing assembly 202 can separate the inlet chamber 206 from the outlet chamber 208. The inlet chamber 206 can define a region of the rotating machine 200 that includes a relatively high pressure fluid volume (p_high). The inlet chamber 206 can be located at a distal position relative to the axis of rotation 210 of the rotor 204. The outlet chamber 208 can define a region of the rotating machine 200 that includes a relatively low pressure fluid volume (p_low). The outlet chamber 208 can be located at a proximal position relative to the axis of rotation 210 of the rotor 204. The axis of rotation 210 can coincide with and / or extend parallel to the longitudinal axis of the rotating machine 200 (such as the turbine engine 100). The sealing assembly 202 can be configured as a membrane riding seal that provides a non-contact sealing interface that inhibits contact between the turbine engine static component 205 and the turbine engine rotor 204, for example, a fluid bearing, gas bearing, etc. located at the interface between the turbine engine static component 205 and the turbine engine rotor 204.

[0051] Considering the various locations where the sealing assembly 202 may be suitable for use discussed above, any one or both of the turbine engine static component 205 and turbine engine rotor 204 that can be used with the sealing assembly 202 can take various forms. In one embodiment, the turbine engine static component 205 can take the form of a turbine engine housing (e.g., a compressor housing, turbine housing, etc.). In alternative and / or additional embodiments, the turbine engine rotor 204 can take the form of a turbine rotor and / or a compressor rotor. In the illustrated embodiment, the sealing assembly 202 is located on each of the turbine engine static component 205 and turbine engine rotor 204. In some embodiments, the sealing assembly 202 may be included with only one of the turbine engine static component 205 and turbine engine rotor 204. Furthermore, in additional and / or alternative embodiments, any one or both of the turbine engine static component 205 and turbine engine rotor 204 may include multiple sealing assemblies 202 positioned at different locations.

[0052] The sealing assembly 202 includes a sealing structure 212 integrated with the turbine rotor 204 and the turbine static component 205. As described above, in some forms, the sealing structure 212 may be included together with only one of the turbine rotor 204 and the turbine static component 205. Thus, one or more sealing structures 212 may be located at the interface 207 between the turbine rotor 204 and the turbine static component 205, wherein it will be understood that the “interface” may include the connection of one or more sealing structures 212 to any one or both of the turbine rotor 204 and the turbine static component 205.

[0053] Now go to Figure 3A and Figure 3B An embodiment of a sealing structure 212 that may be included in a sealing assembly 202 is shown. Figure 3A A side view of a sealing structure 212 extending in the circumferential direction C and having thickness in the radial direction R is shown. As will be understood, the circumferential direction C extends circumferentially around the annular shape of the turbine engine 100, while the radial direction R is perpendicular to the axis of rotation 210. Figure 2 (As shown in the diagram) The sealing structure 212 includes a sealing body 214 having a thickness extending in the radial direction between a first sealing side 216 and a second sealing side 218. Typically, depending on any given application, the first sealing side 216 of the sealing structure 212 is coupled to the turbine rotor 204 or the turbine static component 205.

[0054] The seal 214 also includes a negative thermal expansion (NTE) layer 220 having an NTE base 222 extending radially between a first base side 224 and a second base side 226. The NTE base 222 may be integral with the seal 214 (e.g., it may be a monolithic material cast or additively printed) or may be integrated with the seal 214 by any suitable mechanism (including metallurgical bonding, chemical bonding, etc.).

[0055] NTE layer 220 includes NTE reactive components 228 disposed in a channel 230 defined between a first channel sidewall 232 and a second channel sidewall 234 in NTE base 222. Channel 230 may also include a sidewall bridge 240 extending between the first channel sidewall 232 and the second channel sidewall 234. Although channel 230 is depicted as linear in the cross-sectional shape defined by the first channel sidewall 232, the second channel sidewall 234, and the sidewall bridge 240, other embodiments may include different cross-sectional shapes.

[0056] The NTE reactive component 228 is composed of a material having a negative coefficient of thermal expansion, such that the size of the NTE reactive component 228 is inversely proportional to temperature. For example, as the temperature of the NTE reactive component 228 increases from a first temperature to a second temperature, the NTE reactive component 228 will decrease from a first size to a second size. The NTE reactive component 228 may include a form of zirconium oxide. For example, the NTE reactive component 228 may include a zirconium oxide alloy. The NTE reactive component 228 may be partially stabilized zirconium oxide. In a non-limiting embodiment, the NTE reactive component 228 may be ZrV2O7. In some forms, the negative coefficient of thermal expansion of the NTE reactive component 228 is -10 micrometers / Kelvin. In additional and / or alternative forms, the negative coefficient of thermal expansion may be any negative coefficient of thermal expansion less than zero. For example, the negative coefficient of thermal expansion may be in the range of -7 micrometers / Kelvin to -11 micrometers / Kelvin.

[0057] although Figure 3A and Figure 3B The embodiments illustrate multiple channels 230, but it will be understood that in some forms, a single channel 230 may be provided in the NTE layer 220.

[0058] Figure 3B A view of the sealing structure 212 in the radial direction R is shown, wherein the channel 230 is depicted as adjacent channels 230 axially separated from adjacent channels 230. The channel 230 extends in the circumferential direction. Figure 3B Only a portion of it is depicted. The channel 230 may take the form of a herringbone or V-shape. In the illustrated embodiment, each channel 230 includes a leg 236, which together form a piecewise linear shape in the circumferential direction. The shape of the channel 230 as observed in the radial direction (e.g., as shown in the diagram) Figure 3B (As shown) can be repeated throughout the entire circumferential range of the sealing structure 212.

[0059] Figure 3A and Figure 3B The embodiment of NTE layer 220 depicted is shown with respect to a first temperature relative to the NTE reactive component 228 and the NTE base 222. The NTE reactive component 228 and the NTE base 222 are also shown at a second temperature. Figure 4A and Figure 4B The figure shows that the second temperature is higher than Figure 3A and Figure 3B The first temperature in it. From Figure 3A and Figure 3B The first temperature in Figure 4A and Figure 4BThe temperature rise in the second temperature range can be caused by friction between the turbine rotor 204 and the turbine static component 205. It will be understood that the friction between the turbine rotor 204 and the turbine static component 205 can be caused by an imbalance in the turbine rotor 204 and / or the shaft to which the turbine rotor 204 is attached. Figure 3A and Figure 3B The first temperature in Figure 4A and Figure 4B The increase in temperature of the second temperature will cause the NTE layer 220 to change shape, and in particular, the NTE reactive component 228 to change shape.

[0060] When with Figure 3A When comparing the descriptions in the text, Figure 4A The effect of temperature rise on the NTE reactive component 228 is illustrated, where the NTE reactive component 228 undergoes a reduction in size, particularly a reduction in depth in the illustrated embodiment, as this is related to the radial depth of the channel 230. In one form, the coefficient of thermal expansion of the NTE base 222 is positive, which contributes to a significant reduction in the depth of the NTE reactive component 228. This reduction in depth of the NTE reactive component 228 can form a hydrodynamic pocket 238 defined between the NTE reactive component 228 and the first channel sidewall 232 and the second channel sidewall 234 of the channel 230. The size of the hydrodynamic pocket 238 depends on the temperature of the NTE reactive component 228 and the NTE layer 220 at any given time.

[0061] The formation of a hydrodynamic pocket 238, caused by temperature rise due to friction between the turbine rotor 204 and the turbine static component 205, can contribute to the generation of local hydrodynamic lift. Adjustment of the hydrodynamic lift caused by the growth and / or formation of the hydrodynamic pocket 238 can be used to balance the rotor to an equilibrium position, thereby reducing and / or eliminating friction between the turbine rotor 204 and the turbine static component 205. As used with respect to the hydrodynamic pocket, the term "growth" refers to an increase in the volume of the hydrodynamic pocket.

[0062] Now go to Figure 5 and Figure 6 NTE layer 220 can adopt the same as Figure 3A and Figure 4A The different cross-sectional forms depicted in the text. Figure 3A and Figure 4A The embodiment depicting the channel 230 and NTE reactive component 228 is portrayed as having a straight cross-sectional shape, wherein the NTE reactive component 228 has a constant radial thickness within the axial range of the channel 230. In contrast, Figure 5 andFigure 6 The NTE reactive component 228 is characterized by a profile having the shape of a channel 230. This profile shape of the NTE reactive component 228 results in a generally constant thickness of the NTE reactive component 228 along the first channel sidewall 232 and the second channel sidewall 234, as well as the sidewall bridge 240 between the first channel sidewall 232 and the second channel sidewall 234. In other forms, the profile may not be of constant thickness, but still provide a hydrodynamic pocket 238.

[0063] The contour characteristics of the NTE reactive component 228 result in the formation of a hydrodynamic pocket 238 defined by a groove 242. The groove 242 is defined by a first groove sidewall 244 of the NTE reactive component 228, a second groove sidewall 246 of the NTE reactive component 228, and a groove bridge 248 extending between the first groove sidewall 244 and the second groove sidewall 246. When the NTE reactive component 228 increases in temperature from a first temperature to a second temperature, as... Figure 6 When the variable shown is smaller, the fluid dynamics bag 238 can also be further defined by the first channel sidewall 232 and the second channel sidewall 234.

[0064] Figure 5 and Figure 6 The NTE layer 220 shown may include Figure 3B and Figure 4B Any axial and circumferential variations of the NTE layer 220 depicted (e.g., a herringbone pattern repeating along the circumferential direction of the sealing structure 212).

[0065] Figure 5 and Figure 6 The embodiments also depict a fluid dynamics bag 238 that can be formed before the temperature rises. Figure 5 The relative dimensions of the fluid dynamics bag 238 at the first temperature of the NTE reactive component 228 are depicted, while Figure 6 The fluid dynamics of the NTE reactive component 228 at a second temperature, where the second temperature is higher than the first temperature, are depicted. Figure 5 The first temperature described in the text can correspond to a standard daily temperature similar to the ambient temperature conditions before operating the turbine engine 100. Figure 6 The second temperature described herein can correspond to the operating temperature of the turbine engine 100. Furthermore, Figure 6 The second temperature depicted can correspond to the temperature generated by friction between the turbine rotor 204 and the static turbine component 205. Due to the negative thermal expansion coefficient of the NTE reactive component 228, Figure 5 The fluid dynamics bag 238 shown in the first temperature is greater than Figure 6The fluid dynamics bag 238 is shown at a higher second temperature. As the temperature of the NTE reactive component 228 increases from... Figure 5 The first temperature in the middle rises to Figure 6 At the second temperature, the size of the NTE reactive component 228 (e.g., the thickness measured relative to the first channel sidewall 232) decreases from the first size to the second size. As described above, the size of the fluid dynamics bag 238 depends on the temperature of the NTE reactive component 228 and the NTE layer 220 at any given time.

[0066] The growth of the hydrodynamic pocket 238 caused by the temperature rise due to friction between the turbine rotor 204 and the turbine static component 205 can help generate increased local hydrodynamic lift. Adjustment of the hydrodynamic lift caused by the growth of the hydrodynamic pocket 238 can be used to balance the rotor to an equilibrium position, thereby reducing and / or eliminating friction between the turbine rotor 204 and the turbine static component 205.

[0067] Now go to Figure 7 Another embodiment of the sealing structure 212 is depicted, which further includes a wear-resistant base layer 250 connecting the first sealing side 216 and the NTE layer 220. The wear-resistant base layer 250 may be made of a material that resists wear caused by contact with relatively moving parts. For example, if Figure 7 The sealing structure depicted is coupled to the turbine engine rotor 204, and the wear-resistant base layer 250 may include a material that resists wear when the sealing structure rubs against the turbine engine static component 205. The wear-resistant base layer 250 may be composed of materials such as chromium nitride or titanium nitride. In some embodiments, the wear-resistant base layer 250 may be integral with the NTE base 222. For example, the wear-resistant base layer 250 may be made of the same material as the NTE base 222 and may be formed simultaneously with the NTE base 222. In other embodiments, the wear-resistant base layer 250 may be integrated with the NTE base 222, such as through any suitable bonding operation (e.g., metallurgical bonding, chemical bonding, mechanical fastening, etc.). In some embodiments, the wear-resistant base layer 250 may serve as a bonding coating and manage thermal mismatch between the NTE layer 220 and the seal 214. Figure 7 The NTE layer 220 may include any variation of the NTE layer 220 discussed above, including those related to Figures 3A-6 Variations of the discussion.

[0068] What will be understood is... Figure 7 The sealing body 214 depicted may include, according to the above, the seal 214. Figures 3A-6 The channel 230 and NTE reactive component 228 formed in any of the depicted embodiments.

[0069] It is worth noting that,Figure 7 The embodiments also include a lattice compliant layer 252 disposed between the first seal 214a and the second seal 214b (collectively referred to as "seal 214"). In the illustrated embodiment, the radial thickness of the first seal 214a may be greater than the radial thickness of the second seal 214b. Other embodiments may include the first seal 214a and the second seal 214b having the same radial thickness, or may include a second seal 214b with a radial thickness greater than that of the first seal 214a.

[0070] The lattice compliance layer 252 extends radially between the first compliance layer side 262 and the second compliance layer side 264. The lattice compliance layer 252 is configured to provide additional structural compliance to the seal 214 relative to a monolithic seal 214 or seal 214 lacking the lattice compliance layer 252 in any other manner. When the turbine rotor 204 and the turbine stationary component 205 come into contact, the additional compliance present in the seal 214, including the lattice compliance layer 252, improves the durability and performance of the seal structure 212 by providing flexibility to the seal structure 212. This contact can be circumferential friction as described above, but can also include axial contact, such as that caused by thrust along the axial direction A during operation of the turbine engine 100. The lattice compliance layer 252 can provide axially related compliance. For example, in some forms, the lattice compliance layer 252 can provide axial compliance, radial compliance, and circumferential compliance that differ from each other. The lattice compliant layer 252 can be integrally formed with the first seal 214a and the second seal 214b, for example, by additive manufacturing.

[0071] Now go to Figure 8 And continue to refer to Figure 7 An embodiment of a lattice compliant layer 252 is shown. The lattice compliant layer 252 includes a plurality of lattice ligaments 254 that together define a plurality of cavities 256, such as... Figure 8 The straight lines depicted in the diagram. Lattice ligament 254 can be... Figure 8 The nodes 257 are depicted as points extending between each other. Although the lattice ligaments 254 and nodes 257 are depicted as lines and points, it will be understood that this depiction is for ease of reference and is not intended to imply that only these constructions exist. For example, the lattice ligaments 254 may exhibit curved and / or discontinuous shapes. Furthermore, a node 257 may simply be a combination between intersecting lattice ligaments 254, or a combination between an intersecting lattice ligament 254 and one or the other of the first compliant layer side 262 and the second compliant layer side 264, regardless of whether such combination forms a point shape as depicted.

[0072] Depending on the application, the lattice compliant layer 252, and especially the cavity 256, can be oriented in any particular direction. Figure 8The illustration shows a cavity 256 defined on the axial anterior and axial posterior sides by adjacent non-intersecting ligaments 254. The cavity 256 may also be radially defined by the ligament 254 located between the first lattice layer 258 and the second lattice layer 260, or by one or the other of the first compliant layer side 262 and the second compliant layer side 264. It will be understood that in the illustrated embodiment, the cavity 256 may extend in the circumferential direction. In other embodiments, the cavity 256 may be oriented to extend in the radial direction, and in a further embodiment, the cavity 256 may be oriented to extend in the axial direction.

[0073] Figure 8 The cavity 256 depicted is arranged in the first lattice layer 258, radially offset from the second lattice layer 260. The first lattice layer 258 includes a plurality of cavities 256 defined by ligaments 254 in a trapezoidal shape (e.g., a trapezoidal shape) and a first compliant layer side 262, while the second lattice layer 260 includes a plurality of cavities 256 defined by ligaments 254 in a triangular shape (e.g., a triangular shape) and a second compliant layer side 264. The difference in the arrangement of ligaments in the first lattice layer 258 compared to the arrangement of ligaments in the second lattice layer 260, and therefore the difference in the shape of the cavity 256, can provide a difference in compliance between the first lattice layer 258 and the second lattice layer 260. Therefore, the compliance of the lattice compliant layer 252 can be tuned to provide variable compliance in the thickness of the lattice compliant layer 252 between the first seal 214a and the second seal 214b. In one configuration, the compliance of the first lattice layer 258 is greater than that of the second lattice layer 260 to provide greater deflection under load on the first lattice layer 258.

[0074] Now go to Figure 9 The circumferential arrangement of multiple segments 266 of the sealing structure 212 is depicted. Figure 8 The arrangement is viewed along the axial direction. Generally, a total of twelve different segments 266 are depicted, each segment 266 defining an arc 267 extending in the circumferential direction. Therefore, features within the sealing structure 212 can also be defined by arcs 267. For example, cavity 256 can be arranged to extend circumferentially along segment 266. When assembled together, the entire circumferential arc forms an annular shape.

[0075] Now for reference Figure 10 This describes an exemplary method of operating a turbine engine seal. In some embodiments, the seal structure 212 may be coupled to any one or both of the turbine engine rotor 204 and the turbine engine static component 205. Figure 10As shown, an exemplary method 268 for operating a turbine engine seal may include, at step 270, operating a turbine engine 100 having a sealing structure 212 at an interface 207 between a turbine engine rotor 204 and a turbine engine static component 205, the turbine engine sealing structure 212 having an NTE layer 220 including an NTE reactive component 228. The NTE reactive component 228 may be located in a channel 230 formed in the NTE layer 220, wherein the channel 230 may extend circumferentially. The operation method may include, at step 272, raising the temperature of the NTE layer 220 due to friction against the turbine engine rotor 204 against the turbine engine static component 205. Friction may be a result of an unbalanced state of the turbine engine rotor 204 and / or a movement of the axis of rotation of the turbine engine rotor 204. At step 274, the method may further include reducing the size of the NTE reactive component 228 as the temperature of the sealing structure 212 increases. The method may further include, at step 276, forming a fluid dynamic pouch 238 as the size of the NTE reactive component 228 decreases. This formation of the fluid dynamic pouch 238 may be the creation of the fluid dynamic pouch 238 if the original configuration at the first temperature does not provide it, or the growth of an existing fluid dynamic pouch 238 if the original configuration at the second temperature already provides it. At step 278, the method may further include generating a fluid dynamic force from the fluid dynamic pouch 238 to resist contact between the turbine rotor 204 and the turbine static component 205. The formation of the fluid dynamic pouch 238 may include forming a fluid dynamic pouch extending circumferentially along the NTE layer 220. The formation at step 272 may further include increasing the volume of the fluid dynamic pouch 238 from a first pouch size to a second pouch size as the temperature of the NTE layer increases from a first temperature to a second temperature.

[0076] Now for reference Figure 11 This describes an exemplary method for manufacturing turbine engine seals. In some embodiments, one or more portions of the turbine engine seal may be manufactured using additive manufacturing techniques. Additionally or alternatively, one or more portions of the turbine engine seal may be additively manufactured using other techniques such as casting, forging, machining, extrusion, etc. Figure 11As shown, an exemplary method 280 for manufacturing a turbine engine seal may include, at block 282, printing via additive manufacturing a lattice-compliant layer 252 of a sealing structure 212 configured for use at an interface 207 between a turbine engine rotor 204 and a turbine engine static component 205. At step 284, method 280 further includes forming the lattice-compliant layer 252 between a first sealing side 216 and a second sealing side 218 of a seal body 214 due to printing. The lattice-compliant layer 252 may have structural compliance that varies with the thickness of the lattice-compliant layer 252 between the first sealing side 216 and the second sealing side 218. Method 280 may further include, at step 286, attaching a negative thermal expansion (NTE) layer 220 to the second sealing side 218 of the seal body 214. The NTE layer 220 may include an NTE reactive component 228 composed of a material having a negative coefficient of thermal expansion. As the temperature increases from a first temperature to a second temperature, the size of the NTE reactive component 228 can be reduced from a first size to a second size. Method 280 may further include forming a plurality of ligaments 254 forming a lattice compliant layer 252. The ligaments 254, combined with either a first compliant layer side 262 or a second compliant layer side 264, can form a plurality of cavities 256.

[0077] Further aspects of this disclosed subject matter are provided by the following provisions:

[0078] A turbine engine seal includes: a sealing structure configured to be positioned between a turbine engine rotor and a turbine engine static component, the sealing structure comprising: a sealing body having a thickness extending in a radial direction between a first sealing body side and a second sealing body side; and a lattice compliant layer disposed within the sealing body, between the first sealing body side and the second sealing body side.

[0079] According to the turbine engine seal described in the foregoing clause, the lattice compliant layer includes a plurality of lattice ligaments, each extending between adjacent nodes in a plurality of nodes.

[0080] According to any of the preceding clauses, the turbine engine seal, wherein the lattice compliant layer includes a plurality of cavities defined by the plurality of lattice ligaments.

[0081] According to any of the preceding clauses, the turbine engine seal has an annular structure, and the plurality of cavities extend circumferentially along the annular structure.

[0082] According to any of the preceding clauses, the turbine engine seal includes a first lattice layer and a second lattice layer, wherein the first lattice layer is positioned radially offset from the second lattice layer.

[0083] According to any of the preceding clauses, the turbine engine seal wherein the first lattice layer comprises a plurality of cavities having a trapezoidal shape.

[0084] According to any of the preceding clauses, the turbine engine seal wherein the first lattice layer comprises a plurality of cavities having a triangular shape.

[0085] According to any of the preceding clauses, the turbine engine seal has a first compliance in the axial direction on the first sealing side of the seal body and a second compliance in the axial direction on the second sealing side of the seal body.

[0086] The turbine engine seal according to any of the foregoing clauses, wherein the seal body comprises a plurality of layers, the plurality of layers including the lattice compliant layer.

[0087] According to any of the preceding clauses, the plurality of layers include a first seal and a second seal, wherein the lattice compliant layer is positioned between the first seal and the second seal.

[0088] According to any of the preceding clauses, the radial thickness of the first seal is greater than the radial thickness of the second seal.

[0089] According to any of the preceding clauses, the turbine engine seal is an integral component comprising a monolithic structure including the first compliant layer side and the second compliant layer side.

[0090] The turbine engine seal according to any of the foregoing clauses further includes a wear-resistant base layer coupled to a second sealing body side of the seal body, wherein the wear-resistant base layer has a thickness extending from a first wear-resistant side to a second wear-resistant side in the radial direction, the first wear-resistant side being coupled to the second sealing body side of the seal body, and wherein the second wear-resistant side includes a plurality of channels that partially extend into the thickness of the wear-resistant base layer.

[0091] According to any of the preceding clauses, the turbine engine seals include, respectively, a first channel sidewall and a second channel sidewall, the first channel sidewall being opposite to the second channel sidewall, and further include a negative thermal expansion (NTE) reactive component disposed in the plurality of channels and fixed to each of the first channel sidewall and the second channel sidewall.

[0092] According to any of the preceding clauses, the turbine engine seal wherein the NTE reactive component is composed of a material having a negative coefficient of thermal expansion.

[0093] According to any of the preceding clauses, the turbine engine seal wherein the NTE reactive component defines a groove having a first groove sidewall and a second groove sidewall, and wherein a hydrodynamic bag is formed between the first groove sidewall and the second groove sidewall.

[0094] According to any of the preceding clauses, the turbine engine seal wherein the hydrodynamic bag extends circumferentially along the wear-resistant base layer.

[0095] According to any of the preceding clauses, the turbine engine seal, wherein the hydrodynamic bag extends circumferentially in a herringbone shape.

[0096] A method of manufacturing a turbine engine seal includes: printing a lattice compliant layer via additive manufacturing to form a sealing structure for use at an interface between a turbine engine rotor and a turbine engine static component; forming the lattice compliant layer between a first sealing side and a second sealing side of the seal body due to the printing; and attaching a negative thermal expansion (NTE) layer to the second sealing side of the seal body.

[0097] According to the method described in the foregoing clause, the printing includes forming a plurality of ligaments of the lattice compliant layer.

[0098] This written description uses exemplary embodiments to describe the subject matter currently disclosed, including best practices, and also enables any person skilled in the art to practice such subject matter, including making and using any apparatus or system and methods of making any combination. The patentable scope of the subject matter currently disclosed is defined by the claims, and may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A turbine engine seal, characterized in that, include: A sealing structure configured to be positioned between a turbine engine rotor and static components of the turbine engine, the sealing structure comprising: A sealing body having a thickness extending in the radial direction between a first sealing body side and a second sealing body side; as well as A lattice compliant layer is disposed within the sealing body, between the first sealing body side and the second sealing body side.

2. The turbine engine seal according to claim 1, characterized in that, in, The lattice compliant layer includes multiple lattice ligaments, each extending between adjacent nodes in a plurality of nodes.

3. The turbine engine seal according to claim 2, characterized in that, in, The lattice compliant layer includes a plurality of cavities defined by the plurality of lattice ligaments.

4. The turbine engine seal according to claim 3, characterized in that, The sealing structure has an annular structure, wherein the plurality of cavities extend circumferentially along the annular structure.

5. The turbine engine seal according to claim 3, characterized in that, in, The plurality of cavities include a first lattice layer and a second lattice layer, wherein the first lattice layer is positioned radially offset from the second lattice layer.

6. The turbine engine seal according to claim 5, characterized in that, in, The first lattice layer includes multiple cavities having a trapezoidal shape.

7. The turbine engine seal according to claim 5, characterized in that, in, The first lattice layer includes multiple cavities with a triangular shape.

8. The turbine engine seal according to claim 1, characterized in that, in, The lattice compliant layer has a first compliance along the axial direction on the first sealing body side of the seal body, and a second compliance along the axial direction on the second sealing body side of the seal body.

9. The turbine engine seal according to claim 1, characterized in that, in, The sealing body comprises multiple layers, including the lattice compliant layer.

10. The turbine engine seal according to claim 9, characterized in that, The plurality of layers include a first sealing body and a second sealing body, wherein the lattice compliant layer is positioned between the first sealing body and the second sealing body.

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