Seal assembly for a rotary machine with flexible joints

Abstract

A rotary machine includes a stator and a rotor configured to rotate relative to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. The rotary machine also includes a seal assembly located at the rotor-stator interface. The seal assembly includes a seal rotor, a seal stator, a seal slider, and a seal defined by the rotor face of the seal rotor and a slider face of the seal slider. Further, the seal assembly includes a flexible joint connected between the slider face of the seal slider and a primary seal body. The flexible joint is configured to locally decouple movement of the slider face from the seal slider to allow the slider face to track movement of the rotor away from the primary seal body.

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to rotary machines, and more particularly, to a seal assembly between components in a rotary machine. BACKGROUND

[0002] Gas turbine engines generally include a turbine section downstream of a combustion section, which can rotate with the compressor section to rotate and operate the gas turbine engine to generate power, such as propulsive thrust. Generally, the turbine section defines a high pressure turbine in a serial flow arrangement with a mid-pressure turbine and / or a low pressure turbine. The high pressure turbine includes an inlet or nozzle guide vane between the combustion section and a high pressure turbine rotor. The nozzle guide vane is generally used to accelerate a flow of combustion gases exiting the combustion section to more closely match or exceed a high pressure turbine rotor speed in a tangential or circumferential direction. Thereafter, the turbine section generally includes successive rows or stages of stationary and rotating airfoils or vanes and blades, respectively.

[0003] Additionally, rotary machines, such as gas turbine engines, have seals between rotating components (e.g., rotors) and corresponding stationary components (e.g., stators). These seals can help reduce fluid leakage between the rotors and stators. The seals can additionally or alternatively help separate fluids having different pressures and / or temperatures, respectively. The sealing characteristics of the seals can not only affect the amount of leakage and / or separation of fluids, but also the overall operation and / or operational efficiency of the rotary machine. An example seal in a gas turbine engine is a non-contacting film ride suction face seal of a rotor. BRIEF DESCRIPTION OF DRAWINGS

[0004] 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 best mode is included herein, in the description of the drawings, and of which the best mode is included herein, in the claims. The disclosure of the patent document is not to be considered exhaustive or complete, and the present disclosure should not be limited by the embodiments discussed herein.

[0005] Figure 1 A schematic cross-sectional view of an exemplary rotary machine including a gas turbine engine is shown in accordance with an embodiment of the present disclosure;

[0006] Figure 2A A schematic perspective view of an exemplary seal assembly disposed adjacent to a rotor of a turbine engine is shown in accordance with an embodiment of the present disclosure;

[0007] Figure 2B Another schematic perspective view of an exemplary seal assembly disposed adjacent to a rotor of a turbine engine is shown in accordance with an embodiment of the present disclosure;

[0008] Figure 3 A schematic side view of an exemplary seal assembly is shown in accordance with an embodiment of the present disclosure;

[0009] Figure 4This is a perspective view of an embodiment of a sealing assembly having an aspirating face seal according to the present disclosure;

[0010] Figure 5 yes Figure 4 A partial front view of the suction surface seal shown;

[0011] Figure 6 This is a partial perspective view of an embodiment of a sealing assembly having a suction surface seal with a flexible joint according to the present disclosure; and

[0012] Figure 7 This is a partial cross-sectional view of an embodiment of a sealing assembly with a flexible joint according to the present disclosure.

[0013] Reference numerals used repeatedly in this specification and drawings are intended to indicate the same or similar features or elements of this disclosure. Detailed Implementation

[0014] Reference will now be made in detail to embodiments of the present disclosure, one or more examples of which are illustrated in the accompanying drawings. Each example is provided as an explanation of the present disclosure and not as a limitation thereof. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made to the present disclosure without departing from the scope or spirit thereof. For example, features shown or described as part of one embodiment may be used with another embodiment to produce yet another embodiment. Therefore, the present disclosure is intended to cover such modifications and variations falling within the scope of the appended claims and their equivalents.

[0015] The term "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 superior or better than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0016] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0017] In a context such as “at least one of A, B and C”, the term “at least one” means only A, only B, only C, or any combination of A, B and C.

[0018] The term "turbine" refers to a machine that includes one or more compressors, a heating section (e.g., a combustion section), and one or more turbines that together generate torque output.

[0019] The term "gas turbine engine" refers to an engine that has a turbine as its power source, in whole or in part. Examples of gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid electric versions of one or more of these engines.

[0020] The term "combustion section" refers to any heat addition system used in a turbine. For example, the term combustion section can refer to a section including one or more of a knock combustion assembly, a rotating detonation combustion assembly, a pulse detonation combustion assembly, or other suitable heat addition assemblies. In some example embodiments, the combustion section may include an annular burner, a can burner, a tubular burner, a trap vortex burner (TVC), or other suitable combustion systems, or combinations thereof.

[0021] 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).

[0022] As used herein, the term "stator" refers to any component of a rotating machine (such as a turbine engine) that has a coaxial configuration and arrangement with the rotor of the rotating machine. The stator may be arranged radially inward or radially outward relative to at least a portion of the rotor along a radial axis. Additionally or alternatively, the stator may be axially arranged adjacent to at least a portion of the rotor.

[0023] Unless otherwise stated, when used with compressors, turbines, shafts, or spool components, the terms “low” and “high” or their respective comparatives (e.g., “lower” and “higher”, if applicable) refer to relative speeds within the engine. For example, “low-speed turbine” or “low-turbine” defines a component constructed to operate at speeds (such as maximum permissible speeds) lower than those of the engine’s “high-speed turbine” or “high-turbine”.

[0024] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle, and specifically to the normal operating posture of the gas turbine engine or vehicle. For example, in the case of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0025] 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.

[0026] As used herein, the terms "axial" and "axially" refer to a direction and orientation that extends substantially parallel to the centerline of the gas turbine engine. Furthermore, the terms "radial" and "radially" refer to a direction and orientation that extends substantially perpendicular to the centerline of the gas turbine engine. Additionally, as used herein, the terms "circumferential" and "circumferentially" refer to a direction and orientation that extends in an arc around the centerline of the gas turbine engine.

[0027] Unless otherwise stated herein, the terms “connection,” “fixed,” “attached to,” etc., refer to both direct connection, fixation, or attachment, and indirect connection, fixation, or attachment via one or more intermediate components or features.

[0028] As used herein, the terms “first,” “second,” “third,” etc., are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the components.

[0029] As used in this document when referring to two walls and / or surfaces, the term "adjacent" means that the two walls and / or surfaces are in contact with each other, or that the two walls and / or surfaces are separated only by one or more unstructured layers, and that the two walls and / or surfaces are in series contact with one or more unstructured layers (i.e., the first wall / surface is in contact with one or more unstructured layers, and one or more unstructured layers are in contact with the second wall / surface).

[0030] As used herein, the terms "monolithic," "single," or "integral" used to describe a structure mean that the structure is formed monolithically from a continuous material or group of materials, without seams, connections, 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.

[0031] As used herein throughout the specification and claims, approximate language is applied to modify any quantitative expression that may allow for variation without altering its underlying function. Therefore, values ​​modified by terms such as “about,” “approximate,” and “substantially” are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value, or the precision of the method or machine used to construct or manufacture the component and / or system. For example, approximate language may refer to margins of 1%, 2%, 4%, 10%, 15%, or 20%. These approximate margins may apply to a single value, to either end of a range defining a numerical value, or to margins between two ends, and / or between the ends.

[0032] Throughout this specification and claims, scope limitations are combined and interchanged, and unless the context or language otherwise indicates otherwise, such scopes are identified and include all subscopes contained herein. For example, all scopes disclosed herein include endpoints, and endpoints may be combined independently of each other.

[0033] This disclosure generally relates to sealing assemblies for rotating machines. The sealing assemblies disclosed herein can be used in any rotating machine. Exemplary embodiments may be particularly suitable for turbines, such as turbine engines. The sealing assemblies disclosed herein include a suction seal that provides a fluid film between one side of the seal and one side of the rotor. The fluid film may be provided by one or more suction conduits that allow fluid (such as pressurized air or gas in a turbine engine) to flow from a higher pressure region on one side of the sealing assembly to a lower pressure region on the other side of the sealing assembly. The fluid flowing through the suction conduits provides a pressurized fluid film between the sealing surface and the rotor surface. The pressurized fluid film can act as a fluid bearing, such as a gas bearing, to inhibit contact between the seal and the rotor. For example, the fluid bearing may be a hydrostatic bearing, an air hydrostatic bearing, a pneumatic bearing, or a combination of air hydrostatic and pneumatic characteristics, referred to as a hybrid bearing.

[0034] Therefore, the currently disclosed sealing assemblies are generally considered to be non-contact seals because the fluid bearing inhibits contact between the sealing surface and the rotor surface. The currently disclosed sealing assemblies include a primary seal defined by the rotor surface of the sealing rotor and the sliding surface of the sealing slide. The primary seal can be configured as a suction surface seal, a fluid bearing, a gas bearing, etc. Additionally or alternatively, the primary seal can be configured as a radial diaphragm riding seal, an axial diaphragm riding seal, an axial brush seal, a radial brush seal, a radial carbon seal, an axial carbon seal, etc.

[0035] In certain embodiments, for example, the sealing assembly of this disclosure generally includes a sealing rotor, a sealing stator, a sealing slide, and a seal defined by a rotor face of the sealing rotor and a slide face of the sealing slide. Furthermore, the sealing assembly includes a flexible joint connecting the slide face of the sealing slide and a primary seal to allow the slide face to track axial movement of the rotor without affecting the primary seal, thereby decoupling the movement of the slide face from the sealing slide.

[0036] In conventional sealing arrangements, the entire sliding element acts as a rigid body tracking the movement of the rotor, making it more susceptible to friction and damage. Furthermore, in conventional arrangements, the sliding face of the seal is rigidly connected to the sliding element, thus lacking sufficient flexibility to engage with the rotor. In contrast, the sealing assembly of this disclosure includes a flexible structure that engages the sliding face to the sliding body. Therefore, this structure is described herein as capable of partially decoupling the movement of the sliding face from the sealing sliding element, allowing the sliding face to track the movement of the rotor away from the sliding body. Thus, the flexible structure / joint described herein allows at least a portion of the sliding face to deform, tilt, and / or otherwise move while the rotor separates and disperses from the remainder of the sliding body, because at least for small rotor axial movements (e.g., such as a taper of up to 5°, preferably up to 1°, more preferably up to 0.25°), this portion of the sliding face itself will be able to track the rotor without affecting the remainder of the sliding body. Therefore, the flexible structure / joint of this disclosure provides improved flexibility to engage with the rotor and maintain a substantially constant air gap. In some embodiments, to improve flexibility, the sliding surface may also be segmented into multiple segments, which allows the movement of the sliding surface to be partially decoupled from the sealing sliding element.

[0037] Now for reference Figure 1 A schematic cross-sectional view of a gas turbine engine 100 is provided according to an example embodiment of this disclosure. Specifically, Figure 1 A turbofan engine with a rotor assembly having single-stage non-ducted rotor blades is provided. In this way, the rotor assembly may be referred to herein as a "non-ducted fan," or the entire engine 100 may be referred to herein as a "non-ducted turbofan engine." Furthermore, Figure 1 The engine 100 includes a third flow that extends from the compressor section to the rotor assembly flow path above the turbine, as will be explained in more detail below.

[0038] For reference, engine 100 defines an axial direction A, a radial direction R, and a circumferential direction C. Furthermore, engine 100 defines an axial centerline or longitudinal axis 112 extending along the axial direction A. Typically, the axial direction A extends parallel to the longitudinal axis 112, the radial direction R extends outward and inward from the longitudinal axis 112 in a direction perpendicular to the axial direction A, and the circumferential direction extends 360° around the longitudinal axis 112. Engine 100 extends, for example, between a front end 114 and a rear end 116 along the axial direction A.

[0039] Engine 100 includes a turbine 120 and a rotor assembly (also referred to as a fan section 150) positioned upstream therefrom. Typically, turbine 120 includes a compressor section, a combustion section, a turbine section, and an exhaust section in a sequential flow order. Specifically, as...Figure 1 As shown, turbine 120 includes a core shroud 122 defining an annular core inlet 124. The core shroud 122 also at least partially surrounds a low-pressure system and a high-pressure system. For example, the shown core shroud 122 at least partially surrounds and supports a booster or low-pressure (“LP”) compressor 126 for pressurizing air entering turbine 120 through core inlet 124. A high-pressure (“HP”) multi-stage axial compressor 128 receives pressurized air from the LP compressor 126 and further increases the air pressure. The pressurized air flows downstream to a combustor 130 in the combustion section, where fuel is injected into the pressurized air flow and ignited to increase the temperature and energy level of the pressurized air.

[0040] It should be understood that, as used herein, the terms “high / low speed” and “high / low pressure” are used interchangeably with respect to high-pressure / high-speed systems and low-pressure / low-speed systems. Furthermore, it should be understood that the use of the terms “high” and “low” in the same context to distinguish between two systems does not imply any absolute speed and / or pressure values.

[0041] High-energy combustion products flow downstream from combustor 130 to HP turbine 132. HP turbine 132 drives HP compressor 128 via HP shaft 136. In this respect, HP turbine 132 is drivably coupled to HP compressor 128. High-energy combustion products then flow to LP turbine 134. LP turbine 134 drives components of LP compressor 126 and fan section 150 via LP shaft 138. In this respect, LP turbine 134 is drivably coupled to components of LP compressor 126 and fan section 150. In this example embodiment, LP shaft 138 is coaxial with HP shaft 136. After driving each of turbines 132 and 134, combustion products exit turbine 120 through turbine exhaust nozzle 140.

[0042] Therefore, turbine 120 defines a working gas flow path or core duct 142 extending between core inlet 124 and turbine exhaust nozzle 140. Core duct 142 is an annular duct positioned approximately inside core casing 122 in the radial direction R. Core duct 142 (e.g., through the working gas flow path of turbine 120) may be referred to as a second flow.

[0043] Fan section 150 includes fan 152, which is a primary fan in this example embodiment. For Figure 1 In the embodiment shown, fan 152 is an open rotor or non-ducted fan 152. In this way, engine 100 can be referred to as an open rotor engine.

[0044] As shown in the figure, fan 152 includes an array of fan blades 154. Figure 1(Only one is shown). The fan blade 154 is, for example, rotatable about the longitudinal axis 112. As described above, the fan 152 is drivenly connected to the LP turbine 134 via the LP shaft 138. For Figure 1 In the embodiment shown, the fan 152 is connected to the LP shaft 138 via a reduction gearbox 155, for example, in an indirect drive or gear drive configuration.

[0045] Furthermore, the array of fan blades 154 can be arranged at equal intervals around the longitudinal axis 112. Each fan blade 154 has a root and a tip, as well as a span defined between them. Each fan blade 154 defines a central blade axis 156. In this embodiment, each fan blade 154 of the fan 152 can rotate about its central blade axis 156, for example, in unison with each other. One or more actuators 158 are provided to facilitate this rotation and are therefore used to change the pitch of the fan blades 154 about their respective central blade axes 156.

[0046] Fan section 150 also includes a fan guide vane array 160, which includes fan guide vanes 162 arranged around a longitudinal axis 112. Figure 1 (Only one is shown in the image). In this embodiment, the fan guide vane 162 is not rotatable about the longitudinal axis 112. Each fan guide vane 162 has a root and a tip, and a span defined between them. The fan guide vane 162 can be as follows: Figure 1 The fan guide vane 162 shown is not obscured, or alternatively, it can be obscured, for example, by an annular shroud spaced outward from the tip of the fan guide vane 162 in the radial direction R or attached to the fan guide vane 162.

[0047] Each fan guide vane 162 defines a central blade axis 164. In this embodiment, each fan guide vane 162 of the fan guide vane array 160 can rotate about its respective central blade axis 164, for example, in unison with each other. One or more actuators 166 are provided to facilitate this rotation and are therefore used to change the pitch of the fan guide vane 162 about its respective central blade axis 164. However, in other embodiments, each fan guide vane 162 may be fixed or unable to pitch about its central blade axis 164. The fan guide vanes 162 are mounted to the fan shroud 170.

[0048] like Figure 1As shown, in addition to the non-ductless fan 152, a ducted fan 184 is also included behind fan 152, such that engine 100 includes both ducted and non-ducted fans, both used to generate thrust by the movement of air without passing through at least a portion of turbine 120 (e.g., in the depicted embodiment, without passing through HP compressor 128 and combustion chamber). The ducted fan 184 is rotatable about the same axis as fan blades 154 (e.g., longitudinal axis 112). In the depicted embodiment, the ducted fan 184 is driven by LP turbine 134 (e.g., coupled to LP shaft 138). In the described embodiment, as described above, fan 152 may be referred to as the primary fan, and ducted fan 184 may be referred to as the secondary fan. It should be understood that these terms "primary" and "secondary" are convenient terms and do not imply any particular importance, right, etc.

[0049] The duct fan 184 includes multiple fan blades arranged in a single stage (in Figure 1 (Not separately marked), so that the duct fan 184 can be referred to as a single-stage fan. The fan blades of the duct fan 184 can be arranged at equal intervals around the longitudinal axis 112. Each blade of the duct fan 184 has a root and a tip and a span defined between them.

[0050] The fan shroud 170 annularly surrounds at least a portion of the core shroud 122 and is generally positioned radially R outside at least a portion of the core shroud 122. Specifically, a downstream section of the fan shroud 170 extends over the front portion of the core shroud 122 to define a fan duct flow path, or simply fan duct 172. According to this embodiment, the fan duct flow path or fan duct 172 can be understood as forming at least a portion of the third flow of the engine 100.

[0051] Incoming air enters through fan duct inlet 176, passes through fan duct 172, and is exhausted through fan exhaust nozzle 178 to generate propulsive thrust. Fan duct 172 is an annular duct positioned radially R approximately outside core duct 142. Fan shroud 170 and core shroud 122 are connected together and are supported by a plurality of substantially radially extending, circumferentially spaced stationary struts 174. Figure 1(Only one support is shown in the image.) The stationary support 174 may each have an aerodynamic profile to guide airflow therefrom. Other supports besides the stationary support 174 may be used to connect and support the fan shroud 170 and / or the core shroud 122. In many embodiments, the fan duct 172 and the core duct 142 may extend at least partially together (generally axially) on opposite sides (e.g., opposite radial sides) of the core shroud 122. For example, the fan duct 172 and the core duct 142 may each extend directly from the leading edge 144 of the core shroud 122 and may extend generally axially and partially together on opposite radial sides of the core shroud 122.

[0052] Engine 100 also defines or includes an inlet duct 180. The inlet duct 180 extends between engine inlet 182 and core inlet 124 / fan duct inlet 176. Engine inlet 182 is generally defined at the front end of fan shroud 170 and positioned in the axial direction A between fan 152 and fan guide vane array 160. Inlet duct 180 is an annular duct positioned in the radial direction R inside fan shroud 170. Air flowing downstream along inlet duct 180 is diverted by the fan duct splitter or leading edge 144 of core shroud 122 into core duct 142 and fan duct 172, and is not necessarily uniform. In the depicted embodiment, inlet duct 180 is wider in the radial direction R than core duct 142. Inlet duct 180 is also wider in the radial direction R than fan duct 172.

[0053] It is worth noting that, for the depicted embodiment, engine 100 includes one or more features to increase third-flow thrust Fn. 3S (For example, the efficiency of thrust generated by the airflow through the fan duct 172 exiting through the fan exhaust nozzle 178, which is at least partially generated by the duct fan 184). Specifically, the engine 100 also includes an array of inlet guide vanes 186 positioned in the inlet duct 180, upstream of the duct fan 184 and downstream of the engine inlet 182. The array of inlet guide vanes 186 is arranged about a longitudinal axis 112. In this embodiment, the inlet guide vanes 186 are not rotatable about the longitudinal axis 112. Each inlet guide vane 186 defines a central blade axis (not shown for clarity) and is rotatable about its respective central blade axis, for example, in unison with each other. In this way, the inlet guide vanes 186 can be considered variable geometry components. One or more actuators 188 are provided to facilitate this rotation and can therefore be used to change the pitch of the inlet guide vanes 186 about their respective central blade axes. However, in other embodiments, each inlet guide vane 186 may be fixed or not pitchable about its central blade axis.

[0054] Furthermore, downstream of the ducted fan 184 and upstream of the fan duct inlet 176, the engine 100 includes an array of outlet guide vanes 190. Like the array of inlet guide vanes 186, the array of outlet guide vanes 190 is not rotatable about the longitudinal axis 112. However, in the illustrated embodiment, unlike the array of inlet guide vanes 186, the array of outlet guide vanes 190 is configured as fixed-pitch outlet guide vanes.

[0055] Furthermore, it should be understood that, for the depicted embodiment, the fan exhaust nozzle 178 of the fan duct 172 is also configured as a variable geometry exhaust nozzle. In this way, the engine 100 includes one or more actuators 192 for regulating the variable geometry exhaust nozzle. For example, the variable geometry exhaust nozzle can be configured to change the total cross-sectional area (e.g., the area of ​​the nozzle in a plane perpendicular to the longitudinal axis 112) to regulate the thrust generated based on one or more engine operating conditions (e.g., the temperature, pressure, mass flow rate, etc. of the airflow through the fan duct 172). A fixed geometry exhaust nozzle may also be used.

[0056] The combination of an array of inlet guide vanes 186 located upstream of the duct fan 184, an array of outlet guide vanes 190 located downstream of the duct fan 184, and a fan exhaust nozzle 178 can result in a third-flow thrust Fn during one or more engine operating conditions. 3S More efficient generation. Furthermore, by introducing variability into the geometry of the inlet guide vane 186 and the fan exhaust nozzle 178, the engine 100 can operate under a relatively wide range of engine operating conditions (including takeoff and climb, which typically require maximum total engine thrust Fn). Total And cruise (which typically requires a smaller amount of total engine thrust Fn) Total This generates a more effective third-flow thrust Fn. 3S .

[0057] In addition, still refer to Figure 1 In an exemplary embodiment, the air passing through fan duct 172 may be relatively colder (e.g., at a lower temperature) than one or more fluids used in turbine 120. In this way, one or more heat exchangers 194 may be positioned in thermal communication with fan duct 172. For example, one or more heat exchangers 194 may be disposed within fan duct 172 and used to cool one or more fluids from the core engine, wherein the air passing through fan duct 172 serves as a source for removing heat from the fluid (e.g., compressor bleed air, oil, or fuel).

[0058] Although not depicted, heat exchanger 194 may be an annular heat exchanger extending approximately 360 degrees (e.g., at least 300 degrees, such as at least 330 degrees) within fan duct 172. In this way, heat exchanger 194 can effectively utilize air passing through fan duct 172 to cool one or more systems of engine 100 (e.g., lubrication system, compressor bleed air, electrical components, etc.). Heat exchanger 194 uses air passing through fan duct 172 as a radiator and correspondingly raises the temperature of air downstream of heat exchanger 194 and exiting fan exhaust nozzle 178.

[0059] As an example, Figure 1 Some exemplary locations 196 of the sealing assembly are shown. For example, such a sealing assembly may be particularly suitable for applications as described herein and Figure 2A The rotor-stator interface 201 is shown. As an example, the sealing assembly may be located at or near the bearing housing. A sealing assembly located at or near the bearing housing is sometimes referred to as a bearing housing seal. Such a bearing housing seal may be configured to inhibit airflow (such as core airflow) from entering the bearing housing of the engine 100, such as the bearing housing located at the interface between the LP shaft 138 and the HP shaft 136.

[0060] As another example, the sealing assembly may be located at or near the compressor section of engine 100. In some embodiments, the sealing assembly may be located at or near the compressor discharge port of, for example, HP compressor 128. A sealing assembly located at or near the compressor discharge port 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 and / or provide bearing thrust balance. Additionally or alternatively, the sealing assembly may be located between adjacent compressor stages of the compressor section. A sealing assembly located between adjacent compressor stages may sometimes be referred to as an interstage compressor seal. Such an interstage compressor seal may be configured to restrict air recirculation within the compressor section.

[0061] As another example, the sealing assembly may be located at or near the turbine section of engine 100. In some embodiments, the sealing assembly may be located at or near the turbine inlet of, for example, HP turbine 132 or LP turbine 134. A sealing assembly located at or near the turbine inlet may sometimes be referred to as a front turbine seal. Such a front turbine seal may 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 may be located at or near one or more turbine disk edges. A sealing assembly located at or near the turbine disk edges may sometimes be referred to as a turbine disk edge seal. Such a turbine disk edge seal may be configured to inhibit the intake of hot gas into the disk edge region. Additionally or alternatively, the sealing assembly may be located between adjacent turbine stages in the turbine section. A sealing assembly located between adjacent turbine stages may sometimes be referred to as an inter-turbine stage seal. Such an inter-turbine stage seal may be configured to restrict air recirculation within the turbine section.

[0062] The sealing assemblies at any one or more of these or other locations of engine 100 can be constructed according to this disclosure. Additionally or alternatively, engine 100 may include the sealing assemblies currently disclosed at one or more other locations of engine 100. It should also be understood that the sealing assemblies of this disclosure can also be used in other rotating machines, and references... Figure 1 The engine 100 described is provided as an example only and does not constitute a limitation.

[0063] Now for reference Figure 2A-2B Further, an exemplary sealing assembly is described. As shown, a rotating machine 200 (such as engine 100) may include a sealing assembly 202 configured to provide a sealing interface with a rotor 204, such as providing a sealing interface between the rotor 204 and the stator 206 of the rotating machine 200. The sealing assembly 202 can be integrated into any rotating machine 200 (such as reference 100). Figure 1 The engine 100 described herein. For example... Figure 2A As shown, the sealing assembly 202 can space the inlet chamber 208 and the outlet chamber 210. The inlet chamber 208 can define a region of the rotating machine 200 including a relatively high-pressure fluid volume. The outlet chamber 210 can define a region of the rotating machine 200 including a relatively low-pressure fluid volume. The sealing assembly 202 can have an annular configuration. In some embodiments, the sealing assembly 202 can include a plurality of annular elements that can be assembled to provide the sealing assembly 202. Additionally or alternatively, the sealing assembly 202 can include a plurality of semi-annular elements that can be assembled to provide the sealing assembly 202 having an annular configuration.

[0064] In some embodiments, such asFigure 2A As shown, the sealing assembly 202 can provide a sealed interface between the HP spool 205 of the core engine 104 and the stationary portion 209. For example, the rotor 204 may include a portion of the HP spool 205. Additionally or alternatively, the rotor 204 may include an HP spool cone 212 defining a portion of the HP spool 205. In some embodiments, the stator 206 may include a turbine center frame 214. The sealing assembly 202 can provide a sealed interface between the HP spool cone 212 and the turbine center frame 214. Additionally or alternatively, in some embodiments, such as... Figure 2B As shown, sealing assembly 202 can provide a sealed interface between rotating bodies (such as between HP spool 205 and LP spool 207). Rotor 204 may include a portion of LP spool 207. For example, as Figure 2B As shown, rotor 204 may include an LP spool cone 218 defining a portion of LP spool 207. Additionally or alternatively, sealing assembly 202 may be coupled to HP spool cone 212. For example, sealing stator 224 may be coupled to HP spool 205, such as to HP spool cone 212. Sealing rotor 222 may be coupled to LP spool 207, such as to LP spool cone 218. Sealing assembly 202 may define a sealing interface between HP spool cone 212 and LP spool cone 218. In some embodiments, such as Figure 2B As shown, the inner extension 220 can connect the sealing assembly 202 to the HP spool taper 212.

[0065] The sealing assembly 202 may be configured as a suction seal providing a non-contact sealing interface that inhibits contact between the sealing stator 224 and the sealing slide 226. As an example, the sealing assembly 202 may include or be configured as a suction face seal, a fluid bearing, a gas bearing, etc. During operation, fluid within the inlet chamber 208 may flow (e.g., be suctioned) through one or more paths of the sealing assembly 202 to the outlet chamber 210. In some embodiments, the fluid may include pressurized air, gas, and / or steam. In other embodiments, the fluid may include a liquid.

[0066] As shown, the sealing assembly 202 may be positioned adjacent to the rotor 204. Furthermore, as shown, the sealing assembly 202 may include a sealing rotor 222, a sealing stator 224, and a sealing slide 226. The sealing rotor 222 may be coupled to the rotor 204, such as to another portion of the HP spool cone 212 or HP spool 205, or such as to another portion of the LP spool cone 218 or LP spool 207. In some embodiments, the sealing stator 224 may be coupled to a stationary portion of the core engine 104, such as to the turbine center frame 214. In some embodiments, the sealing stator 224 may be coupled to a rotating portion of the core engine 104, such as to another portion of the HP spool cone 212 or HP spool 205, or such as to another portion of the LP spool cone 218 or LP spool 207. Additionally or alternatively, the sealing stator 224 may be coupled to an inner extension 220, for example as... Figure 2B As shown. The sealing slide 226 can be slidably coupled to the sealing stator 224 at the sliding interface 228. The sealing rotor 222, sealing stator 224, and / or sealing slide 226 can each have annular configurations. Additionally or alternatively, the sealing rotor 222, sealing stator 224, and / or sealing slide 226 can each include multiple semi-annular elements that can be assembled to provide an annular assembly. The sealing assembly 202 can include a primary seal 230. The primary seal 230 can include or be configured as a suction face seal, a fluid bearing, a gas bearing, etc. The primary seal 230 can have an annular configuration defined by one or more annular or semi-annular components (such as the sealing slide 226 and / or the sealing rotor 222).

[0067] The sealing slider 226 may include a sliding face 232. The sealing rotor 222 may include a rotor face 234. The primary seal 230 may be at least partially defined by the sliding face 232 of the sealing slider 226 and the rotor face 234 of the sealing rotor 222. The sliding face 232 and the rotor face 234 may provide non-contact interfaces for suction face seals, fluid bearings, gas bearings, etc., that define the primary seal 230. The sealing slider 226 may be configured such that the sliding face 232 slidably engages and retracts relative to the rotor face 234. In some embodiments, the sealing assembly 202 may include a plurality of suction conduits 236 configured to supply fluid from the inlet gas chamber 208 to the primary seal 230. The plurality of suction conduits 236 may be defined by the integral structure of one or more components of the sealing assembly 202.

[0068] In some embodiments, the sealing slide 226 may include a plurality of suction conduits 236 configured to supply fluid from the inlet chamber 208 to the primary seal 230. The suction conduits 236 defined by the sealing slide 226 may sometimes be referred to as slide suction conduits 238. The slide suction conduits 238 may define internal conduits, paths, etc., through the sealing slide 226. The slide suction conduits 238 may be in fluid communication with both the inlet chamber 208 and the primary seal 230. The slide suction conduits 238 may, for example, discharge fluid from the inlet chamber 208 to the primary seal 230 at a plurality of openings in the slide face 232.

[0069] Additionally or alternatively, the suction conduit 236 defined by the sealed rotor 222 may sometimes be referred to as the rotor suction conduit 240. The rotor suction conduit 240 may define an internal conduit, path, etc., through the sealed rotor 222. The rotor suction conduit 240 may be in fluid communication with the inlet chamber 208 and the primary seal 230. The rotor suction conduit 240 may, for example, discharge fluid from the inlet chamber 208 to the primary seal 230 through multiple openings in the rotor face 234.

[0070] During operation, the sealing slider 226 can slide back and forth relative to the sealing stator 224 and the sealing rotor 222. The movement of the sealing slider 226 can be initiated at least in part by the pressure difference between the inlet chamber 208 and the outlet chamber 210. As an example, Figure 2A and Figure 2B The sealing slide 226 is shown in the retracted position, such that the primary seal 230 is relatively open. For example, when the rotating machine 200 is operating at idle, the sealing slide 226 may occupy the retracted position. As power output and / or rotational speed increase, for example, as the pressure difference between the inlet chamber 208 and the outlet chamber 210 increases, the sealing slide 226 may slide forward toward the sealing rotor 222. For example, when the rotating machine 200 is operating under nominal and / or rated operating conditions, the sealing slide 226 may occupy the engaged position. When the sealing slide 226 is in the engaged position, the sliding surface 232 and the rotor surface 234 become very close, and fluid such as that flowing from the inlet chamber 208 to the outlet chamber 210 through multiple suction conduits 236 can be confined between the sliding surface 232 and the rotor surface 234 by suction face seals, fluid bearings, gas bearings, etc., providing a non-contact interface.

[0071] The sealing assembly 202 may include a secondary seal 242. The secondary seal 242 may have an annular configuration defined by one or more annular or semi-annular components. The secondary seal 242 may exhibit elasticity during compression and / or expansion and rebound over at least a portion of the range of motion of the sealing slide 226. For example, the secondary seal 242 may inhibit or prevent fluid flow therethrough, such as inhibiting or preventing fluid from the inlet chamber 208 to the outlet chamber 210, while allowing the sealing slide 226 to slide back and forth relative to the sealing stator 224 and the sealing rotor 222 (e.g., between a retracted position and an engaged position) according to the operating conditions of the rotating machine 200.

[0072] In some embodiments, the secondary seal 242 may be configured to provide resistance to compressive loads. At least a portion of the compressive load on the secondary seal 242 may be activated as the seal slide 226 moves forward toward the seal rotor 222. Additionally or alternatively, the secondary seal 242 may exhibit at least some preload, such as at least some compressive preload. The secondary seal 242 may be configured to exhibit a force constant (e.g., under compressive loads) and is at least partially configured to provide resistance to compressive loads while exhibiting forward and / or backward displacements suitable for the operation of the primary seal 230 (e.g., under specified operating conditions of the rotating machine 200).

[0073] In some embodiments, in addition to or in lieu of a compressive load, the secondary seal 242 may be configured to provide resistance to a tension load. At least a portion of the tension load on the secondary seal 242 may be activated as the seal slide 226 moves forward toward the seal rotor 222. Additionally or alternatively, the secondary seal 242 may exhibit at least some preload, such as at least some tension preload. The secondary seal 242 may be configured to exhibit a force constant (e.g., under a tension load) and at least partially configured to provide resistance to the tension load while exhibiting forward and / or backward displacements suitable for the operation of the primary seal 230 (e.g., under specified operating conditions of the rotating machine 200). The forward and backward displacements of the secondary seal 242 may include compression and / or expansion of one or more secondary sealing elements 246 of the secondary seal 242. The specified operating conditions of the rotating machine 200 may include at least one of, for example, starting operating conditions, idling operating conditions, stopping operating conditions, nominal operating conditions, transient operating conditions, and abnormal operating conditions. The force vector (such as the compressive force vector) acting on the secondary seal 242 can apply a compressive load sufficient to move the seal slide 226 toward the seal rotor 222 and / or hold the seal slide 226 in a proper position (such as an engaged position) relative to the seal rotor 222.

[0074] Additionally or alternatively, a force vector (such as a tension vector) acting on the secondary seal 242 may apply a tension load sufficient to move the sealing slide 226 toward the sealing rotor 222 and / or hold the sealing slide 226 in an appropriate position (such as an engaged position) relative to the sealing rotor 222. The force vector may include at least the pressure difference between the inlet chamber 208 and the outlet chamber 210. The force vector acting on the secondary seal 242 may cause the sealing slide 226 to occupy and / or maintain an engaged position relative to the sealing rotor 222, such that the slide surface 232 is at an appropriate distance from the rotor surface 234 to provide a suction face seal, fluid bearing, gas bearing, etc.

[0075] In some embodiments, the resistance to compressive loads provided by the secondary seal 242 can retract the sealing slide 226 away from the sealing rotor 222 and / or hold the sealing slide 226 in the retracted position relative to the sealing rotor 222. The secondary seal 242 may exhibit a rebound force sufficient to overcome the compressive load, retracting the sealing slide 226 and / or holding the sealing slide 226 in the retracted position. Additionally or alternatively, the resistance to tension loads provided by the secondary seal 242 can retract the sealing slide 226 away from the sealing rotor 222 and / or hold the sealing slide 226 in the retracted position relative to the sealing rotor 222. The secondary seal 242 may exhibit a rebound force sufficient to overcome the tension load, retracting the sealing slide 226 and / or holding the sealing slide 226 in the retracted position. For example, when the pressure difference between the inlet chamber 208 and the outlet chamber is below a threshold or decreases to below a threshold, the force constant of the secondary seal 242 can overcome the compressive force vector and / or tension vector acting on the secondary seal 242, thereby causing the sealing slide 226 to occupy and / or maintain a retracted position relative to the sealing rotor 222. Under specified operating conditions of the rotating machine 200 (including, for example, at least one of the following: start-up operating conditions, idle operating conditions, shutdown operating conditions, transient operating conditions, and abnormal operating conditions), the secondary seal 242 can retract and / or maintain the sealing slide 226 in the retracted position relative to the sealing rotor 222. In some embodiments, when the sealing slide 226 is in the retracted position relative to the sealing rotor 222, the sliding surface 232 of the primary seal 230 can be sufficiently separated from the rotor surface 234 of the sealing rotor 222 to provide disengagement from suction face seals, fluid bearings, gas bearings, etc.

[0076] In some embodiments, the sealing rotor 222 may be movable back and forth relative to the sealing slide 226 and / or the sealing stator 224. The sealing slide 226 may be configured to move back and forth in response to the movement of the sealing rotor 222. For example, the back and forth movement of the sealing slide 226 may track the back and forth movement of the sealing rotor 222. In some embodiments, the force vector acting on the secondary seal 242 may include at least the force applied by the sealing rotor 222. Additionally or alternatively, the sealing stator 224 may be movable back and forth relative to the sealing slide 226 and / or the sealing rotor 222. The sealing slide 226 may be configured to move back and forth in response to the movement of the sealing stator 224. For example, the back and forth movement of the sealing slide 226 may track the back and forth movement of the sealing stator 224. In some embodiments, the force vector acting on the secondary seal 242 may include at least the force applied by the sealing stator 224.

[0077] During operation, for example, in response to changes in one or more force vectors acting on the secondary seal 242, the secondary seal 242 can move through various stages of compression and rebound, and / or tension and rebound. Changes in one or more force vectors can include at least one of the following: changes in the pressure differential between the inlet chamber 208 and the outlet chamber 210, movement of the sealing rotor 222, and movement of the sealing stator 224. The secondary seal 242 can exhibit responsiveness to such changes in one or more force vectors sufficient to maintain the sealing slide 226 in an engaged position during specified operating conditions, such that the slide face 232 can maintain an appropriate distance from the rotor face 234 to provide a suction face seal, fluid bearing, gas bearing, etc. For example, during variable operating conditions falling within the range of operating variations, the secondary seal 242 can maintain the sealing slide 226 in the engaged position. Additionally or alternatively, during operating conditions outside the range of operational variation, the secondary seal 242 may retract the sealing slide to the retracted position and / or may maintain the sealing slide 226 in the retracted position. Operating conditions may be within the range of operational variation during at least one of the following: start-up operating conditions, idle operating conditions, shutdown operating conditions, transient operating conditions, and abnormal operating conditions.

[0078] The exemplary sealing assembly 202 may include a primary seal 230 having one or more primary sealing elements 244. Additionally or alternatively, the exemplary sealing assembly 202 may include a secondary seal 242 having one or more secondary sealing elements 246. The secondary sealing elements 246 may be coupled to a sealing stator 224 and / or a sealing slide 226. In some embodiments, the rotor-facing portion of the secondary sealing element 246 may be coupled to the sealing stator 224.

[0079] Additionally or alternatively, the stator-facing portion of the secondary sealing element 246 may be coupled to the sealing slide 226. In some embodiments, the stator-facing portion of the secondary sealing element 246 may be coupled to the sealing stator 224. Additionally or alternatively, the rotor-facing portion of the secondary sealing element 246 may be coupled to the sealing slide 226. One or more primary sealing elements 244 and / or one or more secondary sealing elements 246 may engage and / or disengage at least partially depending on the position of the sealing slide 226 relative to the sealing rotor 222 and / or the sealing stator 224. During operation, the engagement and / or disengagement of one or more primary sealing elements 244 and / or one or more secondary sealing elements 246 may depend at least partially on one or more forces acting on the secondary seal 242. Additionally or alternatively, in some embodiments, the exemplary sealing assembly 202 may include a third seal having one or more third sealing elements. One or more third sealing elements may engage and / or disengage, at least in part, depending on the position of the sealing slide 226 relative to the sealing rotor 222 and / or the sealing stator 224 (e.g., in response to one or more forces acting on the secondary seal 242).

[0080] Now for reference Figure 3The sealing slider 226 may include a primary seal 248. The primary seal 248 may include one or more slider surfaces 232. One or more slider surfaces 232 may respectively engage with one or more corresponding rotor surfaces 234, defining a primary seal 230 and / or one or more corresponding primary sealing elements 244. In some embodiments, the primary seal 248 may define a plurality of slider suction conduits 238. The sealing slider 226 may include a rotor-facing extension 250 projecting axially toward the sealing rotor 222. The rotor-facing extension 250 may axially overlap at least a portion of the sealing rotor 222 over at least a portion of the range of motion of the sealing slider 226. The rotor-facing extension 250 and the primary seal 248 may define corresponding portions of a single component (such as an integral component), or the rotor-facing extension 250 and the primary seal 248 may be coupled to each other. The sealing slider 226 may include a stator-facing extension 252 projecting axially toward the sealing stator 224. The stator-facing extension 252 may axially overlap the sealing stator 224 over at least a portion of the range of motion of the sealing slide 226. The stator-facing extension 252 and the primary seal 248 may define corresponding portions of a single component (such as an integral component), or the stator-facing extension 252 and the primary seal 248 may be coupled to each other. In some embodiments, the sealing stator 224 may be directly or indirectly coupled to the sealing slide 226 at the stator-facing extension 252. Additionally or alternatively, the sealing stator 224 may be directly or indirectly coupled to the sealing slide 226 at the primary seal 248. In some embodiments, the secondary seal 242 may be directly or indirectly coupled to the sealing slide 226. For example, the secondary seal 242 may be directly or indirectly coupled to the sealing slide 226 at the stator-facing extension 252 and / or at the primary seal 248. Additionally or alternatively, in some embodiments, the secondary seal 242 may be directly or indirectly coupled to the sealing stator 224.

[0081] In some embodiments, the sealed stator 224 may include a stator flange 258 and a sliding flange 260. The stator flange 258 may be coupled to the stator 206 of the rotating machine 200 (such as the turbine center frame 214). Figure 2A Or defined thereto. Additionally or alternatively, the stator flange 258 may be coupled to or defined thereto the rotor 204 of the rotating machine 200, such as to the HP spool taper 212 and / or the inner extension 220. Figure 2BThe sliding flange 260 may be configured to engage with the sealing slide 226. One or more sliding pins 254 may be defined by or coupled to the sliding flange 260. The sliding flange 260 may be coupled to the stator flange 258, or the sliding flange 260 and the stator flange 258 may define corresponding portions of a single component (such as an integral component).

[0082] In some embodiments, the sealing slide 226 may include a secondary sealing flange 262. The secondary sealing flange 262 may be coupled to the sealing slide 226, such as to a stator-facing extension 252 of the sealing slide 226. Alternatively, the secondary sealing flange 262 may define a portion of the sealing slide 226, such as a portion of the stator-facing extension 252. For example, the sealing slide 226 and the secondary sealing flange 262 may define corresponding portions of a single component (such as an integral component).

[0083] For example, such as Figure 3 As shown, a secondary seal 242 may be disposed between the sealing stator 224 and the sealing slide 226. In some embodiments, the secondary seal 242 may be coupled to the sealing stator 224. For example, the secondary seal 242 (such as the rotor-facing portion of the secondary seal 242) may be coupled to the slide flange 260 of the sealing stator 224. Additionally or alternatively, the secondary seal 242 may be coupled to the sealing slide 226. For example, the secondary seal 242 (such as the stator-facing portion of the secondary seal 242) may be coupled to the secondary sealing flange 262 of the sealing slide 226. As described herein, the secondary seal 242 may be configured to exhibit forward and backward displacement and / or compression and rebound (such as under compressive and / or tension loads) suitable for the operation of the primary seal 230 (such as under specified operating conditions of the rotating machine 200). Secondary seal 242 and / or one or more secondary sealing elements 246 may be configured to inhibit or prevent fluid flow through secondary seal 242, such as from inlet chamber 208 to outlet chamber 210.

[0084] In some embodiments, the secondary seal 242 and / or one or more of its secondary sealing elements 246 may be fluid-impermeable. Additionally or alternatively, the secondary seal 242 and / or one or more of its secondary sealing elements 246 may provide a fluid-impermeable seal, for example, at an interface with a portion of the sealing slide 226 (such as the secondary sealing flange 262) and / or at an interface with a portion of the sealing stator 224 (such as the slide flange 260). For example, the secondary seal 242 and / or secondary sealing element 246 may be coupled to the sealing slide 226, such as to the secondary sealing flange 262, for example, at the stator-facing portion of the secondary seal 242 and / or one or more of its secondary sealing elements 246. Additionally or alternatively, the secondary seal 242 and / or secondary sealing element 246 may be coupled to the sealing stator 224, such as to the slide flange 260, for example, at the rotor-facing portion of the secondary seal 242 and / or secondary sealing element 246. Secondary seals 242 and / or secondary sealing elements 246 may be connected to the sealing stator 224 and / or sealing slide 226 by welding, brazing, attachment hardware, etc. Alternatively or additionally, secondary seals 242 and / or secondary sealing elements 246 may be located in a recess or the like defined by the sealing slide 226 (such as by the secondary sealing flange 262), providing a fluid-impermeable seal therebetween. Alternatively or additionally, secondary seals 242 and / or secondary sealing elements 246 may be located in a recess or the like defined by the sealing stator 224 (such as by the slide flange 260), providing a fluid-impermeable seal therebetween. In some embodiments, secondary seals 242 and / or their secondary sealing elements 246 may be fluid-permeable while appropriately inhibiting fluid flow through them, such as from the inlet chamber 208 to the outlet chamber 210.

[0085] Now for reference Figure 3-7 The sealing assembly 202 also includes a flexible joint 256 connecting the sliding surface 232 of the sealing slide 226 and the primary seal 248. In such an embodiment, the flexible joint 256 is configured to partially decouple the movement of the sliding surface 232 from the sealing slide 226, allowing the sliding surface 232 to track the movement of the rotor 204 away from the primary seal 248.

[0086] More specifically, Figure 4 A perspective view of an embodiment of the sealing assembly 202 is shown, wherein the sliding surface 232 is segmented into a plurality of segments 264. Furthermore, as shown, the segments 264 of the sliding surface 232 are arranged adjacent to each other in a ring configuration.

[0087] In addition, and especially refer to Figure 6 and Figure 7The flexible joint 256 includes a plurality of flexible pivots 266 connecting the sliding surface 232 of the sealing slide 226 and the primary seal 248. For example, in one embodiment, one or more of the plurality of segments 264 include at least one of the flexible pivots 266, for example, to provide wavy and tapered deformation flexibility. In other embodiments, one or more of the plurality of segments 264 may include at least two flexible pivots 266, for example, to provide tapered flexibility. In certain embodiments, the flexible pivots 266 can be constructed using any suitable method, such as via additive manufacturing (e.g., wire-EDM, machining, etc.).

[0088] In addition, such as Figure 6 and Figure 7 As shown, adjacent flexible pivots 266 may be spaced apart to create one or more ventilation ports 268 in the flexible joint 256. Therefore, in the illustrated embodiment, the sealing assembly 202 includes a plurality of ventilation ports 268 formed by the plurality of flexible pivots 266. Thus, in such an embodiment, the flexible pivots allow ventilation and pressurization of the sealing assembly 202 through the ports. In additional embodiments, as... Figure 3 As shown, the sealing assembly 202 may also or optionally include one or more supply ports 270 on the rotor 204. In such embodiments, the supply port 270 may be used in conjunction with or in place of the ventilation port 268.

[0089] Further aspects of the currently disclosed topic are provided by the following clauses:

[0090] A rotating machine includes: a stator; a rotor configured to rotate relative to the stator, the rotor being arranged together with the stator at a rotor-stator interface; a sealing assembly located at the rotor-stator interface, the sealing assembly including a sealing rotor, a sealing stator, a sealing slide, and a seal defined by a rotor face of the sealing rotor and a sliding face of the sealing slide; and a flexible joint connecting the sliding face of the sealing slide and a primary seal. The flexible joint is configured to partially decouple movement of the sliding face from the sealing slide to allow the sliding face to track movement of the rotor away from the primary seal.

[0091] The rotating machine according to any of the foregoing clauses, wherein the sliding surface is segmented into multiple segments.

[0092] The rotating machine according to any of the foregoing clauses, wherein the plurality of segments are arranged adjacent to each other in a ring configuration.

[0093] The rotating machine according to any of the foregoing clauses further includes one or more ventilation ports in the flexible joint.

[0094] The rotating machine according to any of the foregoing clauses, wherein the flexible joint includes a plurality of flexible pivots circumferentially spaced between the sliding surface of the sealing slide and the primary seal.

[0095] The rotating machine according to any of the foregoing clauses further includes a plurality of ventilation ports formed by the plurality of flexible pivots.

[0096] The rotating machine according to any of the foregoing clauses, wherein one or more of the plurality of segments include at least one of the plurality of flexible pivots.

[0097] The rotating machine according to any of the foregoing clauses, wherein one or more of the plurality of segments include at least two of the plurality of flexible pivots.

[0098] The rotating machine according to any of the foregoing clauses further includes one or more supply ports on the rotor.

[0099] In any of the preceding clauses of the rotating machine, the seal of the sealing assembly is configured as at least one of a suction face seal, a fluid bearing, or a gas bearing, the seal defining an air bearing surface on the rotor at the rotor-stator interface.

[0100] The rotating machine according to any of the foregoing clauses, wherein the rotating machine includes a gas turbine engine.

[0101] A gas turbine engine includes: a stator; a rotor configured to rotate relative to the stator, the rotor being arranged together with the stator at a rotor-stator interface; a sealing assembly located at the rotor-stator interface, the sealing assembly including a sealing rotor, a sealing stator, a sealing slide, and a suction face seal defined by a rotor face of the sealing rotor and a sliding face of the sealing slide; and a flexible joint connecting the sliding face of the sealing slide and a primary seal. The flexible joint is configured to partially decouple movement of the sliding face from the sealing slide to allow the sliding face to track movement of the rotor away from the primary seal.

[0102] In any of the preceding clauses of the gas turbine engine, the sliding surface is segmented into multiple segments.

[0103] A gas turbine engine according to any of the foregoing clauses, wherein the plurality of segments are arranged adjacent to each other in a ring configuration.

[0104] The gas turbine engine according to any of the foregoing clauses further includes one or more ventilation ports in the flexible joint.

[0105] According to any of the preceding clauses, in a gas turbine engine, the flexible joint includes a plurality of flexible pivots circumferentially spaced between the sliding surface of the sealing slide and the primary seal.

[0106] The gas turbine engine according to any of the foregoing clauses further includes a plurality of ventilation ports formed by the plurality of flexible pivots.

[0107] A gas turbine engine according to any of the foregoing clauses, wherein one or more of the plurality of segments include at least one of the plurality of flexible pivots.

[0108] A gas turbine engine according to any of the foregoing clauses, wherein one or more of the plurality of segments include at least two of the plurality of flexible pivots.

[0109] The gas turbine engine according to any of the foregoing clauses further includes one or more supply ports on the rotor.

[0110] A sealing assembly comprising: a sealing rotor, a sealing stator, a sealing slider, and a seal defined by a rotor face of the sealing rotor and a sliding face of the sealing slider; and a flexible joint connecting the sliding face of the sealing slider and a primary seal to allow the sliding face to track the movement of the rotor without affecting the primary seal, thereby decoupling the movement of the sliding face from the sealing slider.

[0111] 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 rotating machine, characterized in that, include: stator; A rotor configured to rotate relative to the stator, the rotor being arranged together with the stator at the rotor-stator interface; A sealing assembly located at the rotor-stator interface, the sealing assembly including a sealing rotor, a sealing stator, a sealing slider, and a seal defined by a rotor surface of the sealing rotor and a slider surface of the sealing slider; as well as A flexible joint is provided between the sliding surface of the sealing slide and the primary seal body. The flexible joint is configured to partially decouple the movement of the sliding surface from the sealing slide to allow the sliding surface to track the movement of the rotor away from the primary seal body.

2. The rotating machine according to claim 1, characterized in that, in, The sliding surface is divided into multiple segments.

3. The rotating machine according to claim 2, characterized in that, in, The multiple segments are arranged adjacent to each other in a ring structure.

4. The rotating machine according to claim 2, characterized in that, in, The flexible joint includes a plurality of flexible pivots, which are circumferentially spaced between the sliding surface of the sealing slider and the primary sealing body.

5. The rotating machine according to claim 4, characterized in that, It further includes multiple ventilation ports formed by the plurality of flexible pivots.

6. The rotating machine according to claim 4, characterized in that, in, One or more of the plurality of segments include at least one of the plurality of flexible pivots.

7. The rotating machine according to claim 6, characterized in that, in, One or more of the plurality of segments include at least two of the plurality of flexible pivots.

8. The rotating machine according to claim 1, characterized in that, It further includes one or more ventilation ports in the flexible joint.

9. The rotating machine according to claim 1, characterized in that, It further includes one or more supply ports on the rotor.

10. The rotating machine according to claim 1, characterized in that, in, The seal of the sealing assembly is configured as a suction surface seal.

11. The rotating machine according to claim 1, characterized in that, in, The seal of the sealing assembly is configured as a fluid bearing.

12. The rotating machine according to claim 1, characterized in that, in, The seal of the sealing assembly is configured as a gas bearing.

13. The rotating machine according to claim 1, characterized in that, in, The seal defines an air bearing surface on the rotor at the rotor-stator interface.

14. The rotating machine according to claim 1, characterized in that, in, The rotating machine includes a gas turbine engine.

15. A gas turbine engine, characterized in that, include: stator; A rotor configured to rotate relative to the stator, the rotor being arranged together with the stator at the rotor-stator interface and defining a rotor surface; A sealing assembly located at the rotor-stator interface, the sealing assembly including a sealing rotor, a sealing stator, a sealing slider, and a suction surface seal defined by the rotor surface of the sealing rotor and the slider surface of the sealing slider; as well as A flexible joint is provided between the sliding surface of the sealing slide and the primary seal body. The flexible joint is configured to partially decouple the movement of the sliding surface from the sealing slide to allow the sliding surface to track the movement of the rotor away from the primary seal body.

16. The gas turbine engine according to claim 15, characterized in that, in, The sliding surface is divided into multiple segments.

17. The gas turbine engine according to claim 16, characterized in that, in, The multiple segments are arranged adjacent to each other in a ring structure.

18. The gas turbine engine according to claim 16, characterized in that, in, The flexible joint includes a plurality of flexible pivots, which are circumferentially spaced between the sliding surface of the sealing slider and the primary sealing body.

19. The gas turbine engine according to claim 18, characterized in that, It further includes multiple ventilation ports formed by the plurality of flexible pivots.

20. The gas turbine engine according to claim 18, characterized in that, in, One or more of the plurality of segments include at least one of the plurality of flexible pivots.

21. The gas turbine engine according to claim 18, characterized in that, in, One or more of the plurality of segments include at least two of the plurality of flexible pivots.

22. The gas turbine engine according to claim 15, characterized in that, It further includes one or more ventilation ports in the flexible joint.

23. The gas turbine engine according to claim 15, characterized in that, It further includes one or more supply ports on the rotor.

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