Turbine engine with rotor seal assembly

Abstract

A turbine engine includes an engine core having at least a compressor section, a combustor section, and a turbine section in an axial flow arrangement, the engine core defining an axial direction and an engine centerline. The turbine engine also has a rotor and a stator, a bracket assembly carried by the stator, and a seal assembly biased toward the rotor.

Description

[0001] This application is a divisional application of the patent application with the application number 202210570714.0 and the invention title "Turbine Engine with Rotor Seal Assembly" filed on May 24, 2022. Technical Field

[0002] The present disclosure generally relates to turbine engines, and more particularly, to rotor seal assemblies for gas turbine engines. Background Art

[0003] Turbine engines, particularly gas turbine engines, are rotary engines that extract energy from a working air flow that serially passes through a compressor section where the working air is compressed, a combustor section where fuel is added to the working air and ignited, and a turbine section where the combusted working air is expanded and work is extracted from the working air to drive the compressor section and other systems, and provide thrust in an aircraft implementation. Compressor stages and turbine stages include axially arranged pairs of rotating blades and stationary vanes. A gas turbine engine can be arranged as an engine core that includes at least a compressor section, a combustor section, and a turbine section in an axial flow arrangement, and defines at least one rotating element or rotor and at least one stationary component or stator. A seal assembly, particularly a labyrinth seal assembly, can be located between the stator and the rotor to reduce fluid leakage between the rotor and the stator. In a bypass turbofan implementation, an annular bypass air flow path is formed around the core, where the fan section is axially upstream of the compressor section. Summary of the Invention

[0004] In one aspect, the present disclosure relates to a turbine engine that includes: an engine core that includes at least a compressor section, a combustor section, and a turbine section in an axial flow arrangement, the engine core defining an axial direction and an engine centerline, and defining a rotor and a stator; a bracket assembly carried by the stator and having a seal seat that defines a seal cavity; and a seal assembly having a floating seal body and a biasing element, the floating seal body at least partially located within the seal cavity and having a first sealing surface facing the rotor, the biasing element located within the seal cavity and biasing the floating seal body such that the sealing surface is biased toward the rotor. Brief Description of the Drawings

[0005] A complete and enabling disclosure of the present specification, including the best mode thereof, for one of ordinary skill in the art, is set forth in the specification, with reference to the accompanying drawings, in which:

[0006] Figure 1 is a schematic cross-sectional view of a gas turbine engine for an aircraft.

[0007] Figure 2 isFigure 1 Schematic cross-sectional view of a gas turbine engine, further including a rotor and a stator, with a rotor seal assembly disposed therebetween.

[0008] Figure 3A is Figure 2 Enlarged schematic cross-sectional view of the rotor seal assembly of, further including a bracket assembly, a seal assembly, and a biasing element in a first position relative to the rotor.

[0009] Figure 3B is Figure 2 Enlarged schematic cross-sectional view of the rotor seal assembly of, further including a bracket assembly, a seal assembly, and a biasing element in a second position relative to the rotor.

[0010] Figure 4 is Figure 2 Schematic cross-sectional view of an exemplary rotor seal assembly of, further including a radial fastener coupling the biasing element to the bracket assembly.

[0011] Figure 5 is Figure 2 Schematic cross-sectional view of an exemplary rotor seal assembly of, further including a circumferential pin coupling the biasing element to the bracket assembly.

[0012] Figure 6 is Figure 2 Schematic cross-sectional view of an exemplary rotor seal assembly of, further including a pin that axially extends and couples the biasing element to the bracket assembly.

[0013] Figure 7 is Figure 2 Schematic cross-sectional view of an exemplary rotor seal assembly of, further including an exemplary pin that axially extends and couples the biasing element to the bracket assembly.

[0014] Figure 8 is Figure 2 Schematic cross-sectional view of an exemplary rotor seal assembly of, further including an exemplary pin that axially extends and couples the biasing element to the bracket assembly.

[0015] Figure 9 is Figure 2 Schematic cross-sectional view of an exemplary rotor seal assembly of, further including a biasing element integrally formed with the bracket assembly.

[0016] Figure 10 is Figure 2 Schematic cross-sectional view of an exemplary rotor seal assembly of, further including an exemplary pin that axially extends and couples the biasing element to the bracket assembly, and further including a fastener securing the biasing element to the seal assembly.

[0017] Figure 11Yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly, further including a bracket assembly that includes an internal passage fluidly connected to the interior of a biasing element.

[0018] Figure 12 Yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly, further including a protrusion extending from the bracket assembly. Detailed Description

[0019] Aspects of the present disclosure described herein broadly relate to a rotor seal assembly having a seal with a floating portion facing a rotor of a gas turbine engine and a stationary portion carried by a stator of the gas turbine engine. Specifically, the rotor seal assembly includes a bracket assembly carried by the gas turbine engine and having a seal seat defining a seal cavity, and a seal assembly having a floating seal body that includes a first sealing surface facing the rotor. In some cases, a biasing element may be positioned between the bracket assembly and the floating seal body such that the floating seal body can move between a first position and a second position, wherein the first position is radially inwardly displaced relative to the rotor compared to the second position. The floating seal body may further include an internal passage that fluidly couples an inlet on a second sealing surface to an outlet disposed on a third sealing surface, the second sealing surface being defined as the upstream or axially forward face of the floating seal body, the third sealing surface being radially opposed to the first sealing surface. The outlet may be fluidly connected to the interior of the biasing element.

[0020] The rotor seal assembly can provide a dynamic sealing environment by using a biasing element that is movable between a first position and a second position. For illustrative purposes, one exemplary environment in which the rotor seal assembly may be used will be described in the form of a turbine engine. In a non-limiting example, such a turbine engine may be in the form of a gas turbine engine, a turboprop engine, a turboshaft engine, or a turbofan engine having a power gearbox. However, it will be understood that the aspects of the present disclosure described herein are not limited thereto and may have general applicability in other sealing systems. For example, the present disclosure may be applicable to rotor seal assemblies in other engines or vehicles and may be used to provide benefits in industrial, commercial, and residential applications.

[0021] As used herein, the term "upstream" refers to the direction opposite to the fluid flow direction, while the term "downstream" refers to the direction the same as the fluid flow direction. The terms "front" or "forward" indicate in front of something, and "rear" or "backward" indicate behind something. For example, when used in relation to fluid flow, front / forward may indicate upstream and rear / backward may indicate downstream.

[0022] Further, as used herein, the term "radial" or "radially" refers to a direction away from a common center. For example, in the overall context of a turbine engine, radial refers to the direction along a ray extending between the central longitudinal axis of the engine and the outer engine circumference. Further, as used herein, the term "group" or "a group of" elements can be any number of elements, including only one element.

[0023] Further, as used herein, the term "fluid" or its iterations can refer to any suitable fluid within a gas turbine engine, at least a portion of which is exposed to, for example but not limited to, combustion gases, ambient air, pressurized airflows, working airflows, or any combination thereof. It is further contemplated that the gas turbine engine can be other suitable turbine engines, such as but not limited to, steam turbine engines or supercritical carbon dioxide turbine engines. As a non-limiting example, the term "fluid" can refer to steam in a steam turbine engine, or carbon dioxide in a supercritical carbon dioxide turbine engine.

[0024] All directional references (e.g., radial, axial, proximal, distal, up, down, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are for identification purposes only to assist the reader in understanding the present disclosure and do not create a limitation, particularly as to the position, orientation, or use of aspects of the present disclosure described herein. Unless otherwise specified, connection references (e.g., attached, coupled, fixed, fastened, connected, and joined) will be construed broadly and may include intermediate members between element assemblies and relative movement between elements. Thus, a connection reference does not necessarily infer that two elements are directly connected and have a fixed relationship to each other. Exemplary drawings are for illustrative purposes only, and the dimensions, positions, sequences, and relative sizes reflected in the attached drawings may vary.

[0025] Figure 1 is a schematic cross-sectional view of a turbine engine, particularly a gas turbine engine 10 for an aircraft. The gas turbine engine 10 has a generally longitudinally extending axis or engine centerline 12 that extends from a front portion 14 to a rear portion 16. The gas turbine engine 10 includes, in a downstream serial flow relationship: a fan section 18 that includes a fan 20; a compressor section 22 that includes a booster or low-pressure (LP) compressor 24 and a high-pressure (HP) compressor 26; a combustion section 28 that includes a burner 30; a turbine section 32 that includes an HP turbine 34 and an LP turbine 36; and an exhaust section 38. The gas turbine engine 10 as described herein is meant to be a non-limiting example, and other architectures are possible, such as but not limited to, steam turbine engines, supercritical carbon dioxide turbine engines, or any other suitable turbine engines.

[0026] The fan section 18 includes a fan casing 40 that surrounds a fan 20. The fan 20 includes a set of fan blades 42 that are radially disposed about an engine centerline 12. The HP compressor 26, the combustor 30, and the HP turbine 34 form an engine core 44 of a gas turbine engine 10 that generates combustion gases. The engine core 44 is surrounded by a core casing 46 that may be connected to the fan casing 40.

[0027] An HP shaft or spool 48 that is coaxially disposed about the engine centerline 12 of the gas turbine engine 10 drivingly connects the HP turbine 34 to the HP compressor 26. An LP shaft or spool 50 that is coaxially disposed within a larger diameter annular HP spool 48 about the engine centerline 12 of the gas turbine engine 10 drivingly connects the LP turbine 36 to the LP compressor 24 and the fan 20. The spools 48, 50 are rotatable about the engine centerline 12 and are connected to a set of rotatable elements that may collectively define a rotor 51.

[0028] The LP compressor 24 and the HP compressor 26 each include a set of compressor stages 52, 54, where a set of compressor blades 56, 58 rotate relative to a corresponding set of stationary compressor vanes 60, 62 (also referred to as nozzles) to compress or pressurize a fluid flow passing through the stage. In a single compressor stage 52, 54, multiple compressor blades 56, 58 may be arranged in a ring and may extend radially outward from a blade platform to a blade tip relative to the engine centerline 12, while the corresponding stationary compressor vanes 60, 62 are positioned upstream of and adjacent to the rotating blades 56, 58. It should be noted that Figure 1 the number of blades, vanes, and compressor stages shown is chosen for illustrative purposes only, and other numbers are possible.

[0029] The blades 56, 58 for a stage of the compressor may be mounted to a disk 61 that is mounted to a corresponding one of the HP spool 48 and the LP spool 50, where each stage has its own disk 61. The vanes 60, 62 for a stage of the compressor may be mounted to the core casing 46 in a circumferential arrangement.

[0030] The HP turbine 34 and the LP turbine 36 each include a set of turbine stages 64, 66, where a set of turbine blades 68, 70 rotate relative to a corresponding set of stationary turbine vanes 72, 74 (also referred to as nozzles) to extract energy from a fluid flow passing through the stage. In a single turbine stage 64, 66, multiple turbine blades 68, 70 may be arranged in a ring and may extend radially outward from a blade platform to a blade tip relative to the engine centerline 12, while the corresponding stationary turbine vanes 72, 74 are positioned upstream of and adjacent to the rotating blades 68, 70. It should be noted that Figure 1The number of blades, vanes, and turbine stages shown is chosen for illustrative purposes only, and other numbers are possible.

[0031] The blades 68, 70 for one stage of the turbine can be mounted to a disk 71, which is mounted to a corresponding one of the HP spool 48 and the LP spool 50, with each stage having a dedicated disk 71. The vanes 72, 74 for one stage of the compressor can be mounted circumferentially to the core housing 46.

[0032] As a complement to the rotor portion, the stationary parts of the gas turbine engine 10 (such as the static vanes 60, 62, 72, 74 in the compressor section 22 and the turbine section 32) are also referred to individually or collectively as the stator 63. Thus, the stator 63 can refer to the combination of non-rotating elements in the entire gas turbine engine 10.

[0033] In operation, the airflow leaving the fan section 18 is split such that a portion of the airflow is directed into the LP compressor 24, which then supplies the pressurized airflow 76 to the HP compressor 26, which further pressurizes the air. The pressurized airflow 76 from the HP compressor 26 is mixed with fuel in the combustor 30 and ignited, thereby generating combustion gases. The HP turbine 34 extracts some work from these gases, and the HP turbine 34 drives the HP compressor 26. The combustion gases are discharged into the LP turbine 36, which extracts additional work to drive the LP compressor 24, and the exhaust is finally discharged from the gas turbine engine 10 via the exhaust section 38. The driving of the LP turbine 36 drives the LP spool 50 to rotate the fan 20 and the LP compressor 24. The pressurized airflow 76 and the combustion gases can together define a working airflow that flows through the fan section 18, the compressor section 22, the combustor section 28, and the turbine section 32 of the gas turbine engine 10.

[0034] A portion of the pressurized airflow 76 can be extracted as bleed air 77 from the compressor section 22. The bleed air 77 can be extracted from the pressurized airflow 76 and supplied to engine components that require cooling. The temperature of the pressurized airflow 76 entering the combustor 30 increases significantly. Therefore, the cooling provided by the bleed air 77 is necessary for operating such engine components in an elevated temperature environment.

[0035] The remaining portion of the airflow 78 bypasses the LP compressor 24 and the engine core 44 and exits the gas turbine engine 10 at the fan exhaust side 84 through a row of stationary vanes (and more specifically, an exit guide vane assembly 80 including a set of airfoil guide vanes 82). More specifically, a circumferential row of radially extending airfoil guide vanes 82 is used adjacent to the fan section 18 to exert some directional control on the airflow 78.

[0036] Some of the air supplied by fan 20 can bypass the engine core 44 and be used to cool portions (particularly the hot portions) of the gas turbine engine 10, and / or to cool or power other aspects of the aircraft. In the context of a turbine engine, the hot portions of the engine are typically downstream of the combustor 30, particularly in the turbine section 32, where the HP turbine 34 is the hottest portion as it is directly downstream of the combustion section 28. Other sources of cooling fluid can be, but are not limited to, fluid discharged from the LP compressor 24 or the HP compressor 26.

[0037] Figure 2 Further shown is the rotor 51, stator 63, and rotor seal assembly 100 for the gas turbine engine 10 as seen in cross-section II taken from Figure 1 In the example shown, at least a portion of the rotor seal assembly 100 can be disposed within the HP turbine 32 and depend from a portion of the stator 63, particularly from a turbine vane 72 that extends from an outer portion of the stator 63 and is located between two adjacent turbine blades 68. However, it should be understood that the rotor seal assembly 100 can be positioned within any portion of the gas turbine engine 10 (e.g., in the fan section 18, compressor section 22, or turbine section 32), between any suitable rotating and stationary components of the gas turbine engine 10. Thus, the rotor seal assembly 100 can depend from any suitable stationary component (such as, but not limited to, compressor vanes 60, 62, or turbine vanes 72, 74). For the purposes of this disclosure, the turbine vane 72 or any other vane (e.g., static vanes 60, 62, 72, 74) that depends from the stator 63 can be collectively referred to as the stator 63.

[0038] The rotor seal assembly 100 can include a carrier assembly 102 carried by the stator 63 and having a seal seat 106 that defines a seal cavity 108, and a seal assembly 104 that is at least partially located within the seal cavity 108 and has a segmented floating seal body 110. A biasing element 112 is located within the seal cavity 108, between the floating seal body 110 and the carrier assembly 102.

[0039] During operation of the gas turbine engine 10, the working fluid 88 may flow through the turbine blades 68 and the turbine vanes 72. In a particular example, the working fluid 88 may be defined by the pressurized air stream 76. However, it should be understood that the working fluid 88 may be any suitable working fluid or air stream, such as but not limited to the pressurized air stream 76, combustion gases, ambient air streams, any combination thereof, or any other suitable fluid as described herein. Most of the working fluid 88 may flow through the turbine vanes 72 and the turbine blades 68 to define a working fluid path. The leakage fluid 90 diverges from the working fluid 88 and enters the space between the compressor blades 58 and the compressor vanes 62, and flows between the radially inner portion of the stator 63 (e.g., the radially inner portion of the turbine vane 72) and the rotor 51. By establishing a labyrinth between the stator 63 and the rotor 51, the rotor seal assembly 100 may reduce or otherwise eliminate the amount of the leakage fluid 90 flowing from the upstream portion of the turbine vane 68 to the downstream portion of the turbine vane 68. In other words, the rotor seal assembly 100 may create a tortuous path for the leakage fluid 90, thereby reducing or eliminating the amount of the leakage fluid 90 that can flow around the radially inner portion of the stator 63.

[0040] Figures 3A - 3B is from Figure 2 the enlarged region III seen in the first position ( Figure 3A ) and the second position ( Figure 3B ) of the rotor seal assembly 100. As shown, the difference between the first position and the second position of the rotor seal assembly is that the seal assembly 104 is more radially close to the rotor 51 when in the first position than when in the second position. In addition, the biasing element 112 in the first position may expand in the radial direction compared to the biasing element 112 in the second position. Thus, Figures 3A - 3B comparisons of the rotor seal assembly 100 between the first position and the second position are respectively shown.

[0041] At least one of the bracket assembly 102 or the seal assembly 104 may extend around the entire periphery of the rotor 51, or otherwise be circumferentially continuous around the engine centerline 12. Additionally or alternatively, at least one of the seal assembly 104 or the bracket assembly 102 may be segmented around the engine centerline 12. For example, the seal assembly 104 may be a segmented seal assembly 104 that is divided into two or more segments around the engine centerline 12. The number of segments of the bracket assembly 102 may correspond to the number of segments of the seal assembly 104.

[0042] The biasing element 112 can extend between the carriage assembly 102 and the seal assembly 104 within the sealed cavity 108 and be operatively coupled to at least one of the floating seal body 110 or the carriage assembly 102 by any suitable means, such as, but not limited to, adhesion, fastening, welding, etc. The biasing element 112 can include a head 115 that is defined as the radially outer portion of the biasing element 112 and faces at least a portion of the carriage assembly 102.

[0043] As shown, the biasing element 112 is a pneumatic bellows that defines an interior 113 (specifically, a hollow interior). Thus, a fluid can be introduced into the interior of the biasing element 112 to move the biasing element 112 from a contracted position ( Figure 3B ) to an extended position ( Figure 3A ), which results in a corresponding movement of the floating seal body 110. It is contemplated that the biasing element 112 can be biased to the contracted position. The size of the biasing element 112 can be designed based on the position of the rotor seal assembly 100 within the gas turbine engine 10. For example, in the case of a pneumatic bellows, the number of folds or layers and the thickness of the pneumatic bellows can be increased or decreased based on the desired extended or contracted length of the biasing element 112. Although illustrated as a pneumatic bellows, it should be understood that the biasing element can be any other suitable biasing element, such as, but not limited to, a leaf spring, a tightening spring, a flexure, etc.

[0044] The carriage assembly 102 of the rotor seal assembly 100 can define a seal seat 106 that defines the sealed cavity 108. The seal seat 106 can take many forms, but, as shown, the seal seat 106 includes a first wall 114, a second wall 116, and a third wall 118. Both the first wall 114 and the second wall 116 can extend radially inwardly from the stator 63 (specifically, the turbine blade 72), where the second wall 116 is upstream or axially forward of the first wall 114. The third wall 118 can extend in the axial direction and interconnect the first wall 114 and the second wall 116. The first wall 114, the second wall 116, and the third wall 118 together can define the seal seat 106 and, thus, define the sealed cavity 108. It should be understood that the sizes of the first wall 114, the second wall 116, and the third wall 118, and thus the size of the seal seat 106, can be designed such that the seal assembly 104 (and more specifically, the floating seal body 110) can be at least partially received within the sealed cavity 108. The first wall 114 and the second wall 116 together define a radial seal guide for the floating seal body 110. In other words, the floating seal body 110 can move freely in the radial direction within the sealed cavity 108 defined by the first wall 114 and the second wall 116.

[0045] The second wall 116 may include teeth 120 that face at least a portion of the floating seal 110. The teeth 120 can be used to restrict, confine, or prevent the leakage fluid 90 from passing between the second wall 116 and the floating seal 110 and into the seal cavity 108. It is contemplated that the teeth 120 can be designed to provide a minimum radial frictional load on the seal assembly 104 while still ensuring that the leakage fluid 90 is restricted or otherwise prevented from flowing around the seal assembly 104 and into the seal cavity 108.

[0046] The seal seat 106 may further include a flange 122 that extends from a portion of the seal seat 106 and into the seal cavity 108. As a non-limiting example, the flange 122 can extend from the radially inner portion of the third wall 118 and into the seal cavity 108. In other words, the flange 122 can extend radially inward from a portion of the carrier assembly 102 and into the seal cavity 108. However, it should be understood that the flange 122 can extend from any other suitable portion of the carrier assembly 102 and into the seal cavity 108. For example, the flange 122 can extend axially inward from the second wall 116 and axially into the seal cavity 108. The distal end of the flange 122 can face the floating seal 110. As a non-limiting example, the floating seal 110 can include a seat 124, and the distal end of the flange 122 faces, physically contacts, or is coupled to the seat 124. As a non-limiting example, the flange 122 can be coupled to the seat 124 by any suitable coupling method (such as but not limited to welding, bonding, fastening, magnetic, friction, or any combination thereof). Since the carrier assembly 102 is static and the flange 122 is coupled to the carrier assembly 102 or otherwise forms part of the carrier assembly 102, the flange 122 can be further defined as a static part of the rotor seal assembly 100. Thus, the flange 122 and the seat 124 can restrict at least one of the axial, circumferential, or radial movement of the floating seal 110.

[0047] The carrier assembly 102 may further include a tab 128 extending from the seal seat 106, particularly extending between the third wall 118 and the stator 63. The tab 128 can be used to physically couple the carrier assembly 102 to the stator 63. As shown, the tab 128 extends from the upstream or front portion of the third wall 118 to the turbine blade 72 or the stator 63. However, it should be understood that the tab 128 can extend from any part of the carrier assembly 102 and be coupled to any part of the stator 63. The coupling between the tab 128 and the stator 63 can be accomplished by any suitable method (such as but not limited to welding, bonding, fastening, frictional contact (e.g., facing each other without physical coupling), etc.). As shown, the carrier assembly 102 is a separate discrete component coupled to the stator by the tab 128. However, it should be understood that the carrier assembly 102 can be integrally formed with the stator 63. Specifically, the carrier assembly can be integrally formed with the turbine blade 72 or any other suitable component of the stator 63 by additive manufacturing, casting, etc., such that at least a portion of the carrier assembly 102 and the stator 63 form a monolithic structure.

[0048] A retainer groove 130 can be formed in a portion of the seal seat 106, specifically in the third wall 118, where the retainer 132 corresponds to the retainer groove 130. As shown, the retainer groove 130 can be formed on the axially downward or downstream portion of the third wall 118. It is contemplated that the retainer groove 130 and the retainer 132 can be positioned along the radially outer portion of the third wall, which is axially opposite to the position from which the tab 128 extends. The retainer 132 can be any suitable retainer, such as but not limited to a snap ring, a cover plate, a cover plate with bolts, a bayonet-retained cover plate, etc.

[0049] It is contemplated that the seal seat 106 can include any number of one or more walls, including any components described herein (such as the flange 122). At least one of the first wall 114, the second wall 116, or the third wall 118 can be excluded from the carrier assembly 102. As a non-limiting example, the rotor seal assembly 100 can be defined as a compressor discharge pressure (CDP) seal assembly. In this case, the second wall 116 can be excluded, such that the seal seat 106 is defined at least by the first wall 114 that extends radially inwardly towards the rotor 51 at the downstream portion of the seal assembly 104 and the third wall 118 that extends upstream or in front of the second wall 116.

[0050] A set of tertiary seals 134 may be located between the carrier assembly 102 and the stator 63. Specifically, the set of tertiary seals 134 may be located between the radially inner portion of the stator 63 and the radially outer portion of the third wall 118. As shown, there may be two serially arranged tertiary seals 134. The set of tertiary seals 134 may include any suitable seals, such as but not limited to piston rings, E-seals, W-seals, C-seals, vane seals, bellows, braided / rope seals, contact seals, or any combination thereof. It should be understood that the tertiary seals may be 360-degree seals (e.g., they may circumferentially extend around the entire rotor 51), two segments of 180 degrees each, or more than two segments.

[0051] The seal assembly 104 may include a floating seal body 110 defined by a first seal face 136 facing the rotor 51, a second seal face 138 facing the second wall 116 of the carrier assembly 102, a third seal face 140 opposite the first seal face 136 and facing at least a portion of the seal cavity 108 and / or the biasing element 112, and a fourth seal face 142 opposite the second seal face 138 and facing the first wall 114. In other words, the first seal face 136 may define the radially inner face of the floating seal body 110, the second seal face 138 may define the axially forward or upstream face of the floating seal body 110 (e.g., the face facing at least a portion of the leakage fluid 90), the third seal face 140 may define the radially outer face of the floating seal body, and the fourth seal face 142 may define the axially downward or downstream face of the floating seal body 110.

[0052] The internal passage 144 may fluidly couple the leakage fluid 90 upstream of the rotor seal assembly 100 to various interfaces between portions of the seal assembly 104. The internal passage 144 may be formed within the floating seal body 110 and fluidly couple an inlet 146 on the second seal face 138 to a set of outlets 148 located on a portion of the third seal face 140 and facing at least one of the seal cavity 108 or the interior 113 of the biasing element 112. It is contemplated that at least one of the outlets 148 in the set of outlets 148 may be fluidly coupled to the interior 113 of the biasing element 112 and be radially or otherwise opposed to the head 115 of the biasing element 112.

[0053] During operation of the gas turbine engine 10, at least a portion of the leakage fluid 90 may flow into the internal passage 144 through the inlet 146. The leakage fluid 90 may then flow through the internal passage and ultimately out of at least one of the outlets 148 in the set of outlets 148. When the turbine engine 10 is started, the biasing element 112 may be in a contracted second position ( Figure 3B)。Once the working fluid 88 is generated, at least a portion of the leakage fluid 90 exiting the set of outlets 148 can be discharged into the interior 113 of the biasing element 112 or otherwise discharged into the interior of the seal cavity 108. This, in turn, can move the biasing element 112 from the contracted position ( Figure 3B ) to the extended position ( Figure 3A ). When the floating seal 110 is coupled to the biasing element 112, the floating seal 110 and thus the seal assembly 104 can move with the biasing element 112 between a first position ( Figure 3A ) and a second position ( Figure 3B ). In other words, the contraction or extension of the biasing element 112 can move the rotor seal assembly 100 between the first position and the second position. The movement of the biasing element 112 can depend on the operating state of the gas turbine engine 10. For example, when there is working fluid 88 or an air flow (e.g., the pressurized air flow 76 or the combustion gas) flowing through the gas turbine engine 10, the leakage fluid 90 will only be present in the gas turbine engine 10. In other words, the leakage fluid 90 will only be present when the gas turbine engine 10 is operating. Thus, at least a portion of the leakage fluid 90 will enter the interior 113 of the biasing element 112 and cause the biasing element 112 to expand or move into its expanded position. This will cause the rotor seal assembly 100 to be in the first position. However, when the gas turbine engine 10 is not operating, the pressurized working fluid and the leakage fluid 90 will not actively flow through the gas turbine engine 10. Thus, no leakage fluid 90 will flow into the interior 113 of the biasing element 112. This will cause the biasing element 112 to return to its biased position (e.g., the contracted position) and the rotor seal assembly 100 to be in the second position. The axial, circumferential, or radial position of the floating seal 110 can be further defined by the flange 122. For example, during operation of the gas turbine engine 10, the rotor 51 can apply an axial, radial, or circumferential force on the floating seal 110 such that the floating seal 110 will want to move in the direction of the force. Since the flange 122 is static and faces the seat 124, is received within the seat 124, or otherwise coupled to the seat 124, the flange 122 and the seat 124 can limit at least a portion of the circumferential, axial, or radial movement of the floating seal 110. In other words, the flange 122 can circumferentially, axially, or radially position the floating seal 110 within the seal cavity 108 and limit or otherwise prevent the floating seal 110 from moving in at least one of the axial, radial, or circumferential directions.

[0054] Leakage fluid 90 flowing into the interior 113 of the bias member 112 can cause the bias member 112 to expand, such that the bias member applies a closing force on the seal assembly 104. As used herein, the term "closing force" can refer to the radial force applied by the bias member 112, which pushes the seal assembly 104 towards the rotor 51, on the seal assembly 104, particularly on the floating seal body 110. The closing force can be based on the position of the rotor seal assembly 100 within the gas turbine engine 10 and on one or more operating characteristics of the gas turbine engine 10. As used herein, the term "operating characteristics" can refer to the operating state of the gas turbine engine 10 (e.g., the gas turbine engine 10 is operating, or the gas turbine engine 10 is not operating), or other characteristics of the gas turbine engine 10, such as but not limited to the pressure difference between the upstream side and the downstream side of the portion of the stator 63 from which the rotor seal assembly 100 hangs. Compared to a situation with a smaller pressure difference, if the pressure difference is larger (e.g., the upstream side has a higher pressure than the downstream side), the leakage fluid 90 will be at a higher pressure within the interior 113 of the bias member 112. The greater the pressure within the interior 113 of the bias member 112, or the greater the amount of leakage fluid 90 within the bias member 112, the greater the closing force. This in turn results in a closing force that is proportional to the pressure difference across the rotor seal assembly 100. Thus, the closing force will depend on the pressure difference or the operating state of the gas turbine engine 10. During operation of the gas turbine engine 10, the rotor 51 can translate radially. The closing force allows the rotor seal assembly 100 to accurately and faithfully follow the radial movement of the rotor 51 without displacing the rotor seal assembly 100 radially, axially, or circumferentially in an undesired manner.

[0055] Figure 4 Is Figure 2 Schematic diagram of a cross-sectional view of an exemplary rotor seal assembly 200. The exemplary rotor seal assembly 200 is similar to the rotor seal assembly 100; thus, similar components will be identified with similar numbers in the 200 series, and it should be understood that the description of the similar components of the rotor seal assembly 100 applies to the exemplary rotor seal assembly 200 unless otherwise specified.

[0056] The rotor seal assembly 200 can include a bias member 212, and the bias member 212 can include a first hole 260 that extends radially through a portion of the bias member 212. Specifically, the first hole 260 can extend through the radially distal portion of the bias member 112 (e.g., the head 215 of the bias member 212).

[0057] The rotor seal assembly may further include a bracket assembly 202 carried by at least a portion of the stator 63. The bracket assembly 202 may include a first wall 114, a second wall 116, and a third wall 218 interconnecting the first wall 114 and the second wall 116. The third wall 218 may include a second hole 254 extending radially through a portion of the third wall 218. Specifically, the second hole 254 may extend from a radially distal portion of the third wall 218 and through at least a portion of the third wall 218. As shown, the second hole 254 may include a radially outer portion and a radially inner portion, wherein the radially outer portion has a larger diameter than the radially inner portion. Thus, the second hole 254 may be defined by a step such that the cross-sectional area of the hole decreases from the radially outer portion of the hole to the radially inner portion of the hole. Alternatively, the second hole 254 may be defined by a constant cross-sectional area.

[0058] The third wall 218 may further include a protrusion 256 extending radially inward from a radially inner portion of the third wall 218 facing the seal cavity 108. As shown, the protrusion 256 may include a seat 258 corresponding to the head 215 of the biasing element 212.

[0059] The biasing element 212 may be axially positioned such that the head 215 of the biasing element 212 corresponds to the seat 258 of the third wall 218. Thus, the first hole 260 may correspond to the second hole 254, specifically, to the radially inner portion of the second hole 254. A fastener 262 may extend through at least a portion of the second hole 254 and the first hole 260 to operably couple the biasing element 212 to the bracket assembly 202. It is contemplated that the fastener 262 and the seat 258 may restrict at least one of axial movement, circumferential movement, or radial movement of the biasing element 212. The fastener 262 may be any suitable fastener, such as but not limited to a screw, tab, pin, weld, bolt and nut (wherein the bolt is integrally formed with the top of the biasing element 212), a retaining snap ring, or any combination thereof.

[0060] Figure 5 is Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly 300. The exemplary rotor seal assembly 300 is similar to the rotor seal assemblies 100, 200; thus, like parts will be identified with like numbers in the 300 series, and it should be understood that the description of like parts of the rotor seal assemblies 100, 200 applies to the exemplary rotor seal assembly 300 unless otherwise noted.

[0061] The rotor seal assembly 300 may include a bracket assembly 302 carried by at least a portion of the stator 63. The bracket assembly 302 may include a first wall 114, a second wall 116, and a third wall 318 interconnecting the first wall 114 and the second wall 116. The third wall 318 may include a protrusion 356 extending radially inwardly from a radially inner portion of the third wall 318 facing the seal cavity 108. As shown, the protrusion 356 may include a seat 358 that extends radially through at least a portion of the protrusion 356 and into at least a portion of the third wall 318.

[0062] The biasing element 312 may include a head 315 that corresponds to and fits within the seat 358. The biasing element 312 may further include a circumferentially extending first hole 360. A pin 366 corresponding to the first hole 360 may extend circumferentially through at least a portion of the biasing element 312, particularly the head 315 of the biasing element 312. The pin 366 and the seat 358 may limit at least one of circumferential movement, axial movement, or radial movement of the biasing element 312.

[0063] Figure 6 is Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly 400. The exemplary rotor seal assembly 400 is similar to the rotor seal assemblies 100, 200, 300; thus, like components will be identified by like numbers in the 400 series, and it should be understood that the description of like components of the rotor seal assemblies 100, 200, 300 applies to the exemplary rotor seal assembly 400 unless otherwise noted.

[0064] The rotor seal assembly 400 may include a biasing element 412, and the biasing element 412 may include a head 415. The biasing element 412, particularly the head 415, may include a first hole 260 extending axially through the head 415 of the biasing element 412.

[0065] The rotor seal assembly 400 may include a bracket assembly 402 carried by at least a portion of the stator 63. The bracket assembly 402 may include a first wall 114, a second wall 116, and a third wall 418 interconnecting the first wall 114 and the second wall 116. The third wall 418 may include a protrusion 456 extending radially inwardly from a radially inner portion of the third wall 418 facing the seal cavity 108. As shown, the protrusion 456 may include a seat 358 that extends radially through at least a portion of the protrusion 456 and into at least a portion of the third wall 418. The protrusion 456 may extend along at least a portion of the entire downstream half and upstream half of the third wall 418 and include a second hole 254 extending axially within at least a portion of the protrusion 456 or the third wall 418. As shown, the second hole 254 may have a constant cross-sectional area and be discontinuous in the axial direction.

[0066] The head 415 can be adapted within the seat 458 such that the first hole 460 corresponds to the second hole 454, such that the pin 466 can axially extend through at least a portion of the first hole 260 and the second hole 254 to couple the biasing element 412 to the bracket assembly 402. The pin 466 and the seat 458 can couple the biasing element 412 to the bracket assembly 402 and restrict at least one of axial movement, radial movement, or circumferential movement or axial movement of the biasing element 412.

[0067] Figure 7 is Figure 2 FIG. is a schematic cross-sectional view of an exemplary rotor seal assembly 500. The exemplary rotor seal assembly 500 is similar to the rotor seal assemblies 100, 200, 300, 400; thus, like parts will be identified by like numbers in the 500 series, and it should be understood that the description of like parts of the rotor seal assemblies 100, 200, 300, 400 applies to the exemplary rotor seal assembly 500 unless otherwise stated.

[0068] The rotor seal assembly 500 can include a biasing element 512, and the biasing element 512 can include a head 515, and the head 515 includes a first hole 460 that axially extends through the head 515. The rotor seal assembly 500 can further include a bracket assembly 502 carried by at least a portion of the stator 63. The bracket assembly 502 can include a first wall 114, a second wall 116, and a third wall 520 that interconnects the first wall 114 and the second wall 116. The third wall 520 can include a second hole 554 that radially extends through a portion of the third wall 518, specifically, a radially outer portion of the third wall 518. The third wall 520 can further include a protrusion 556 that radially extends inwardly from a radially inner portion of the third wall 520 facing the seal cavity 108. The protrusion 556 can include a seat 558 that radially extends through at least a portion of the protrusion 556 and corresponds to the second hole 554 of the third wall 520.

[0069] As shown, the head 515 can be sized to have different diameters to fit through the seat 558 and the second hole 554. The head 515 can radially extend beyond the third wall 520. The pin 566 can axially extend through the first hole 560 of the biasing element 512. The seat 558, the second hole 554, and the pin 566 can couple the biasing element 512 to the bracket assembly 502 and restrict at least one of axial movement, radial movement, or circumferential neutral movement of the biasing element 512.

[0070] Figure 8 is Figure 2Schematic diagram of a cross-sectional view of an exemplary rotor seal assembly 600. The exemplary rotor seal assembly 600 is similar to the rotor seal assemblies 100, 200, 300, 400, 500; thus, similar components will be identified with similar numbers in the 600 series. It should be understood that, unless otherwise specified, the description of the similar components of the rotor seal assemblies 100, 200, 300, 400, 500 applies to the exemplary rotor seal assembly 600.

[0071] The rotor seal assembly 600 may include a biasing element 612, and the biasing element 612 may include a head 615 facing the bracket assembly 602. The head 615 may include a first hole 660 axially extending through the head 615.

[0072] The rotor seal assembly 600 may further include a bracket assembly 602 carried by at least a portion of the stator 63. The bracket assembly 602 may include a first wall 114, a second wall 116, and a third wall 618 interconnecting the first wall 114 and the second wall 116. The third wall 618 may include a set of protrusions 656 radially inwardly extending from a radially inner portion of the third wall 618 facing the seal cavity 108. Specifically, two protrusions 656 may extend from separate radially inner portions of the third wall 618. As shown, the set of protrusions 656 may each include a second hole 654 radially extending through at least a portion of the corresponding protrusion 656.

[0073] The biasing element 612 may be positioned such that the head 615 is axially positioned between the set of protrusions 656. Specifically, the biasing element 612 may be positioned such that the first hole 660 of the head 615 corresponds to the second hole 654 of the protrusion 656. A pin 666 may axially extend through the first hole 660 and the second hole 654 such that the pin 666 can couple the biasing element 612 to the bracket assembly 602 and restrict at least one of axial movement, radial movement, or circumferential neutral movement of the biasing element 612.

[0074] Figure 9 is Figure 2 Schematic diagram of a cross-sectional view of an exemplary rotor seal assembly 700. The exemplary rotor seal assembly 700 is similar to the rotor seal assemblies 100, 200, 300, 400, 500, 600; thus, similar components will be identified with similar numbers in the 700 series. It should be understood that, unless otherwise specified, the description of the similar components of the rotor seal assemblies 100, 200, 300, 400, 500, 600 applies to the exemplary rotor seal assembly 700.

[0075] The rotor seal assembly 700 may include a bracket assembly 702 carried by at least a portion of the stator 63. The bracket assembly 702 may include a first wall 114, a second wall 116, and a third wall 718 interconnecting the first wall 114 and the second wall 116. The third wall 718 may include a protrusion 756 extending radially inwardly from a radially inner portion of the third wall 718 facing the seal cavity 108.

[0076] The biasing element 712 may include a head 715 facing the bracket assembly 702, wherein the head 715 is integrally formed with at least a portion of the bracket assembly 702. Specifically, the head 715 may be integrally formed within a portion of the protrusion 756 to couple the biasing element 712 to the bracket assembly 702. It is contemplated that the biasing element 712 or the head 715 of the biasing element 712 may be integrally formed with the protrusion 756 by any suitable method (such as but not limited to additive manufacturing or casting), or otherwise coupled to the protrusion 756 by any suitable method (such as but not limited to welding, bonding, etc.). The protrusion 756 may couple the biasing element 712 to the bracket assembly 602 and restrict at least one of axial movement, radial movement, or circumferential neutral movement of the biasing element 612.

[0077] Figure 10 is Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly 800. The exemplary rotor seal assembly 800 is similar to the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700; thus, like components will be identified with like numbers in the 800 series. It should be understood that unless otherwise stated, the description of like components of the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700 applies to the exemplary rotor seal assembly 800.

[0078] The rotor seal assembly 800 may include a bracket assembly 802, a rotor seal assembly 804, and a biasing element 812 disposed therebetween. The biasing element 812 may include a head 815 facing the bracket assembly 802. The head 815 may include a first hole 860 extending axially through the head 815.

[0079] The bracket assembly 802 may be carried by at least a portion of the stator 63 and include a first wall 114, a second wall 116, and a third wall 818 interconnecting the first wall 114 and the second wall 116. The third wall 818 may include a protrusion 856 extending radially inwardly from a radially inner portion of the third wall 818 facing the seal cavity 108. As shown, the protrusion 856 may include a second hole 854 extending radially through at least a portion of the protrusion 856 and into at least a portion of the third wall 818. The protrusion 856 may further include a seat 858 extending radially through at least a portion of the protrusion 856 or the third wall 818.

[0080] The seal assembly 804 can be at least partially located within the seal cavity 108 and includes a floating seal body 810 defined by a first seal face 836, a second seal face 138, a third seal face 140, and a fourth seal face 842. The third hole 870 can radially extend from the first seal face 836 through at least a portion of the seal body 810 to the fourth seal face 842.

[0081] The biasing element 812 can be axially positioned to cover the third hole 870 and align the head 815 with and fit within the seat 858 such that the first hole 860 aligns with the second hole 854. The pin 866 can axially extend through at least a portion of the first hole 860 and the second hole 854 to couple the biasing element 812 to the bracket assembly 402. The fastener 876 can radially extend through the third hole 870 of the seal assembly 804 and couple the biasing element 812 to the floating seal body 810. As shown, the fastener 876 can be a screw and nut assembly; however, it can be any other suitable fastener, such as but not limited to screws, tabs, pins, welds, dovetails, etc. The pin 866 and the seat 858 can couple the biasing element 812 to the bracket assembly 802, while the fastener 876 can couple the biasing element 812 to the seal assembly 804. The pin 866, the seat 858, and the fastener 876 restrict at least one of axial movement, radial movement, or circumferential movement of the biasing element 812.

[0082] The internal passage 844 can be formed within at least a portion of the floating seal body 810 and the fastener 876. The internal passage 844 can fluidly couple the inlet 146 on the third seal face 140 to at least the outlet 848, which is disposed along a portion of the fastener 876 that is exposed to the interior 113 of the biasing element 812. Thus, the internal passage 844 can be formed within the floating seal body 810 and the fastener 876 and fluidly couple the interior 113 to the inlet 146.

[0083] Figure 11 is Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly 900. The exemplary rotor seal assembly 900 is similar to the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800; thus, like components will be identified with like numbers in the 900 series, and it should be understood that the descriptions of like components of the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800 apply to the exemplary rotor seal assembly 900 unless otherwise specified.

[0084] The rotor seal assembly 900 may include a carrier assembly 902 carried by at least a portion of the stator 63. The carrier assembly 902 may include a first wall 114, a second wall 116, and a third wall 918 interconnecting the first wall 114 and the second wall 116. An internal passage 978 may be formed within the third wall 918 of the carrier assembly 902 and fluidly couple an inlet 980 formed on an upstream face 982 of the third wall 918 to an outlet 984 located on a radially inner face 986 of the third wall 918 facing the seal cavity 108.

[0085] The rotor seal assembly 900 may further include a seal assembly 904 that is at least partially located within the seal cavity 108 and includes a floating seal body 910 defined by a first sealing face 136, a second sealing face 938 similar to the first sealing face 136 but without an inlet 146, a third sealing face 140, and a fourth sealing face 942. A biasing element 912 may include a head 915 facing the seal assembly 804, particularly the fourth sealing face 942. An interior 113 of the biasing element 912 may correspond to the outlet 984 such that the interior 113 is fluidly coupled to the inlet 980 through the internal passage 978. The biasing element may be coupled to at least one of the carrier assembly 902 or the seal assembly 904 by any suitable coupling method (such as but not limited to welding, bonding, fastening, etc.).

[0086] An additional biasing element 912 shown as a set of lacing springs 990 may circumferentially extend around or otherwise coil around the entire floating seal body 910, or alternatively circumferentially extend or otherwise coil across one or more segments of a set of floating seal bodies 910. Similar to how the biasing element 912 pushes the floating seal body 910 toward the rotor 51, the set of lacing springs 990 may push the floating seal body 910 toward the rotor 51. Thus, the set of lacing springs 990 and the biasing element 912 may together be used as or otherwise defined as a biasing element configured to provide a closing force. The set of lacing springs 990 may engage the floating seal body 910 through corresponding slots or channels 992. As shown, the channels 992 may be formed within a protrusion extending from the fourth sealing face 942. Additionally or alternatively, the channels 992 may extend into the third sealing face 940 such that at least a portion of the set of lacing springs 990 extends into the floating seal body 910.

[0087] In the case where the rotor seal assembly 900 is disposed within a portion of a gas turbine engine 10 having a high pressure differential, the set of lacing springs 990 may be used. Thus, the set of lacing springs 990 may provide an additional closing force to the closing force generated by the biasing element 912 based on the pressure differential to ensure that the total closing force is sufficient.

[0088] Figure 12 is Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly 1000. The exemplary rotor seal assembly 1000 is similar to the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800, 900; thus, like parts will be identified with like numbers in the 1000 series. It should be understood that, unless otherwise specified, the description of like parts of the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800, 900 applies to the exemplary rotor seal assembly 1000. The rotor seal assembly 1000 is similar to the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800, 900 except that the rotor seal assembly 1000 does not include a biasing element as do the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800, 900.

[0089] The rotor seal assembly 1000 may include a carrier assembly 1002 carried by at least a portion of a stator 63. The carrier assembly 1002 may include a first wall 114, a second wall 116, and a third wall 1018 interconnecting the first wall 114 and the second wall 116. The third wall 1018 may include a protrusion 1056 extending radially inwardly from a radially inner portion of the third wall 1018 and facing the seal cavity 108. A pin 1066 may extend circumferentially through the protrusion 1056. It is contemplated that the pin 1066 may be used in the case where the rotor seal assembly 1000 is defined as a segmented rotor seal assembly 100 (e.g., at least a portion of the rotor seal assembly 1000 is circumferentially discontinuous around the rotor 51). The pin 1066 may serve as a means for physically coupling a section of the carrier assembly 1002 (or any other part of the rotor seal assembly 1000) to a corresponding adjacent carrier assembly 1002. It should be understood that the pin 1066 extending through the protrusion 1056 may be any suitable component for coupling a section to another section, such as but not limited to a bolt, a pin, a fastener, etc.

[0090] The rotor seal assembly 1000 may further include a seal assembly 1004. The seal assembly 1004 is at least partially located within the seal cavity 108 and includes a floating seal body 1010. The floating seal body 1010 is defined by a first sealing surface 136, a second sealing surface 1038 that is similar to the first sealing surface 136 but without an inlet 146, a third sealing surface 1040, and a fourth sealing surface 142. A pair of biasing elements, shown as a set of tightening springs 1090, may be received within a set of circumferential channels 1092 that are formed within a portion of the seal assembly 1004. As a non-limiting example, the set of tightening springs 1090 may be received within a set of circumferential channels 1092 formed within a portion of the third sealing surface 1040. As shown, the floating seal body 1010 does not include an internal passageway.

[0091] Compared with traditional rotor seal assemblies, the benefits of the present disclosure include a rotor seal assembly with increased sealing capabilities without increasing the manufacturing burden. For example, traditional rotor seal assemblies can rely on forming a labyrinth between the stator and the rotor through components extending from the rotor (e.g., teeth extending from the rotor). The space between the components from the rotor and the stator ultimately determines the effectiveness of the rotor seal assembly in restricting or preventing leakage of fluid through the rotor-stator gap. This space can only be scaled by positioning the stationary components of the rotor seal assembly closer to the components extending from the rotor. This ultimately leads to an increased manufacturing burden because each rotor seal assembly needs to be tuned, designed, or otherwise manufactured individually depending on its position within the turbine engine. Based on seal diameter, vibration response, and other factors, traditional labyrinth seals also have limited leakage control capabilities. The seal clearance or gap between the labyrinth seal teeth and the stator (usually a honeycomb wear-resistant) can only be maintained so tight during gas turbine engine operation, typically a physical gap of 4 to 100 mils, depending on the seal size and location. However, a rotor seal assembly as described herein, particularly a floating seal body, can be radially translated relative to the rotor by a biasing element based on the operating characteristics of the turbine engine. Specifically, the biasing element can move between a contracted position and an expanded position based on the operating state of the turbine engine, thereby radially moving the seal assembly relative to the rotor based on the operating state of the turbine engine. For example, when the turbine engine is operating, the leakage fluid will enter the interior of the biasing element and move from the contracted position to the expanded position, causing the biasing element to apply a closing force on the seal assembly, and vice versa when the turbine engine is not operating. Since the seal assembly does not contact the rotor when the turbine engine is starting up, shutting down, or not operating, the total time of contact between the seal assembly and the rotor is reduced compared to traditional rotor seal assemblies, which reduces the total wear of the rotor seal assembly and ultimately extends the total life of the rotor seal assembly. Additionally, as discussed herein, the closing force is scaled based on the position of the rotor seal assembly within the turbine engine because the closing force is based on the pressure difference between the upstream and downstream sides of the portion of the stator from which the carriage assembly of the rotor seal assembly is suspended. Since the rotor seal assembly is scalable based on its position throughout the turbine engine, there is less manufacturing burden because the rotor seal assembly does not need to be tuned, designed, or otherwise manufactured individually based on its position within the turbine engine. The rotor seal assembly can be used throughout the turbine engine.

[0092] Another benefit of the present disclosure includes a rotor seal assembly that is dynamic based on the operating state of a turbine engine as compared to a conventional turbine engine that includes a conventional rotor seal assembly. For example, during operation of a conventional turbine engine, a fluid film may form between a portion of the rotor seal assembly and the rotor. A radially opening force depending on the pressure differential at the location of the conventional rotor seal assembly may be formed by the fluid film, which radially away from the rotor or radially outwardly from the rotor pushes or otherwise displaces the rotor seal assembly. Additionally, during operation of the turbine engine, the rotor may translate radially, and it is important that the rotor seal assembly accurately follows the radial translation of the rotor (e.g., the rotor seal assembly should not become axially or circumferentially displaced based on the radial movement of the rotor). The fluid film created by the conventional rotor seal assembly can cause the conventional rotor seal assembly to translate axially, circumferentially, or radially in an undesirable manner, ultimately reducing the sealing effectiveness of the conventional rotor seal assembly. However, the rotor seal assembly as described herein counteracts the radially opening force with a closing force, particularly a radially closing force, generated by a biasing element. As discussed herein, a closing force similar to the radially opening force depends on the pressure differential. Since the biasing element allows the closing force to be proportional to the pressure differential, this means that the closing force can be adjusted to counteract the radially opening force. This in turn ensures that the seal assembly does not displace too far radially from the rotor, and thus ensures a reduced film stiffness as compared to a conventional rotor seal assembly, and the floating seal body can faithfully or accurately track the radial movement of the rotor. Additionally, a pressurized biasing element allows for a method of increasing the closing force. This allows for dynamic force / moment balancing of the floating seal body. As compared to a conventional rotor seal assembly, this ensures that the rotor seal assembly as described herein allows for an increased sealing effectiveness, which ultimately increases the overall efficiency of the turbine engine.

[0093] Within the scope not yet described, the different features and structures of the various aspects can be used in combination with each other as needed. The fact that a feature is not shown in all aspects does not mean that it is to be construed as not having it, but rather is done for the sake of brevity of description. Thus, the various features of the different aspects can be mixed and matched as needed to form new aspects, whether or not the new aspects are explicitly described. Combinations or permutations of the features described herein are covered by the present disclosure.

[0094] This written description uses examples to describe aspects of the present disclosure described herein, including the best mode, and also enables any person skilled in the art to practice aspects of the present disclosure, including making and using any device or system and performing any incorporated method. The patentable scope of the aspects of the present disclosure is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to fall within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements that do not differ in substance from the literal language of the claims.

[0095] A further aspect of the present invention is provided by the subject matter of the following clauses:

[0096] A turbine engine comprising: an engine core including at least a compressor section, a combustor section, and a turbine section in an axial flow arrangement, the engine core defining an axial direction and an engine centerline, and defining a rotor and a stator; a carrier assembly carried by the stator and having a seal seat defining a seal cavity; and a seal assembly having a floating seal body and a biasing element, the floating seal body being at least partially located within the seal cavity and having a first sealing surface facing the rotor, the biasing element being located within the seal cavity and biasing the floating seal body such that the first sealing surface is biased towards the rotor.

[0097] The turbine engine according to any of the preceding clauses, further comprising an internal passage located within the floating seal body, the internal passage coupling an inlet located on a second sealing surface of the floating seal body to an outlet located on a third sealing surface of the floating seal body, wherein the second sealing surface is upstream of the third sealing surface, and the third sealing surface is opposite the first sealing surface.

[0098] The turbine engine according to any of the preceding clauses, wherein the biasing element includes a hollow interior, and the outlet is fluidly coupled to the hollow interior.

[0099] The turbine engine according to any of the preceding clauses, wherein the biasing element is a pneumatic bellows.

[0100] The turbine engine according to any of the preceding clauses, wherein the seal seat further comprises: a first wall extending radially inwards from the stator; a second wall extending radially inwards from the stator and upstream of the first wall; and a third wall interconnecting the first wall and the second wall; wherein the first wall, the second wall, and the third wall at least partially define the seal cavity and surround the floating seal body.

[0101] The turbine engine according to any of the preceding clauses, further comprising a protrusion and a pin, the protrusion extending radially inwards from the third wall relative to the engine centerline, the pin extending circumferentially through at least a portion of the protrusion.

[0102] The turbine engine according to any of the preceding clauses further comprises: a flange that extends axially inwardly and / or radially inwardly from at least one of the second wall or the third wall and into the seal cavity; and a seat that extends from the floating seal and into the seal cavity; wherein the flange faces the seat to limit at least one of axial or circumferential movement of the floating seal relative to the engine centerline.

[0103] The turbine engine according to any of the preceding clauses further comprises an internal passage formed in one of the bracket assembly or the floating seal and fluidly coupling an inlet provided on an upstream face of the bracket assembly or the floating seal to an outlet, the outlet being fluidly coupled to the interior of the biasing element.

[0104] The turbine engine according to any of the preceding clauses, wherein the biasing element further comprises a head located at a radially opposite end of the biasing element relative to the outlet.

[0105] The turbine engine according to any of the preceding clauses, wherein the head is integrally formed with at least a portion of the bracket assembly.

[0106] The turbine engine according to any of the preceding clauses, wherein the head includes a first hole extending axially, radially, or circumferentially through the head.

[0107] The turbine engine according to any of the preceding clauses, wherein a pin extends through the first hole.

[0108] The turbine engine according to any of the preceding clauses further comprises a second hole corresponding to the first hole, the second hole extending through at least a portion of the bracket assembly, and wherein the pin extends through at least a portion of the second hole.

[0109] The turbine engine according to any of the preceding clauses further comprises: a third hole extending radially through at least a portion of the floating seal; a fastener extending through the third hole and coupled to a portion of the biasing element radially opposite the head; and an internal passage formed in a portion of the floating seal and the fastener and fluidly coupling an inlet located on an upstream face of the floating seal to at least one outlet positioned along a portion of the fastener facing the biasing element, wherein the outlet is fluidly coupled to the interior of the biasing element.

[0110] The turbine engine according to any of the preceding clauses further includes a second hole corresponding to the first hole, the second hole extending through at least a portion of the bracket assembly, wherein the first hole and the second hole each extend radially, and a fastener extends through at least a portion of the first hole and the second hole.

[0111] The turbine engine according to any of the preceding clauses, wherein the bracket assembly further includes: a retainer guide extending into a portion of the seal seat and shaped to receive a retainer; a tab extending from the seal seat and coupled to at least a portion of the stator; a flange extending from the seal seat and facing a corresponding portion of the floating seal body; and a set of tertiary seals disposed between a radially outer portion of the bracket assembly and a radially inner portion of the stator; wherein the tab, the retainer, and the flange limit at least one of axial or circumferential movement of the bracket assembly.

[0112] The turbine engine according to any of the preceding clauses, wherein the seal assembly further includes a set of additional biasing elements extending circumferentially along a portion of the floating seal body.

[0113] The turbine engine according to any of the preceding clauses, wherein the bracket assembly is integrally formed with the stator.

[0114] The turbine engine according to any of the preceding clauses, wherein the bracket assembly and the seal assembly are located within the turbine section.

[0115] The turbine engine according to any of the preceding clauses, wherein the bracket assembly is segmented about the engine centerline.

Claims

1. A turbine engine having an engine centerline, characterized in that, the turbine engine comprises: a core housing; a stator extending from the core housing; a rotor; and a seal assembly including: a carrier assembly carried by the stator and radially spaced from the core housing relative to a rotational axis, the carrier assembly having a seal seat defining a seal cavity, the carrier assembly being segmented, the carrier assembly having tabs extending between the stator and the carrier assembly, the tabs coupling the carrier assembly to the stator; a seal body disposed in the seal cavity and having a first sealing surface facing the rotor and a second sealing surface opposite the first sealing surface and facing the seal cavity; and a biasing element disposed in the seal cavity and biasing the seal body radially toward the rotor.

2. The turbine engine according to claim 1, characterized in that, wherein, the carrier assembly is segmented about the engine centerline.

3. The turbine engine according to claim 1, characterized in that, wherein, the seal assembly further includes a pin extending through at least a portion of the carrier assembly.

4. The turbine engine according to claim 3, characterized in that, wherein, the pin operatively couples adjacent segments of the plurality of segments to each other.

5. The turbine engine according to claim 3, characterized in that, wherein, the pin extends circumferentially through corresponding portions of the seal assembly.

6. The turbine engine according to claim 1, characterized in that, wherein, the carrier assembly extends around the entire outer periphery of the rotor.

7. The turbine engine according to claim 1, characterized in that, wherein, the seal assembly is disposed entirely axially within the seal cavity.

8. The turbine engine according to claim 1, characterized in that, further comprising an internal passage disposed within one of the carrier assembly or the seal body.

9. The turbine engine according to claim 8, characterized in that, wherein, the internal passage is in fluid communication with the biasing element.

10. The turbine engine according to claim 1, characterized in that, wherein, the biasing element is a garter spring.

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