Turbine engine having a 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, a rotor and a stator, a bracket assembly carried by the stator, and a seal assembly biased toward the rotor.

Description

Technical Field

[0001] The present disclosure relates generally to turbine engines and, more particularly, to rotor seal assemblies for gas turbine engines. Background Art

[0002] A turbine engine, particularly a gas turbine engine, is a rotary engine that extracts energy from a flow of working air that passes serially 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 provides thrust in an aircraft embodiment. The compressor stage and the turbine stage include axially arranged pairs of rotating blades and stationary blades. The gas turbine engine can be arranged as an engine core that includes at least a compressor section, a combustor section, and a turbine section arranged in an axial flow, and defines at least one rotating element or rotor and at least one stationary component or stator. A sealing assembly, particularly a labyrinth seal assembly, may be located between the stator and the rotor to reduce fluid leakage between the rotor and the stator. In a bypass turbofan embodiment, an annular bypass airflow passage is formed around the core, wherein the fan section is located axially upstream of the compressor section. Summary of the invention

[0003] In one aspect, the present disclosure relates to a turbine engine comprising: an engine core, the engine core comprising 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, the bracket assembly being carried by the stator and having a sealing seat defining a sealing cavity; and a sealing assembly, the sealing assembly having a floating seal body and a biasing element, the floating seal body being at least partially located in the sealing cavity and having a first sealing surface facing the rotor, the biasing element being located in the sealing cavity and biasing the floating seal body so that the sealing surface is biased toward the rotor. BRIEF DESCRIPTION OF THE DRAWINGS

[0004] A full and enabling disclosure of the present specification, including the best mode thereof, to one of ordinary skill in the art is set forth in the specification with reference to the accompanying drawings, in which:

[0005] Figure 1 is a schematic cross-sectional view of a gas turbine engine for an aircraft.

[0006] Figure 2 yes Figure 1 A schematic cross-sectional view of a gas turbine engine further comprising a rotor and a stator with a rotor seal assembly disposed therebetween.

[0007] Figure 3A yes Figure 2 An enlarged schematic cross-sectional view of a rotor seal assembly further comprising a carrier assembly, a seal assembly, and a biasing element in a first position relative to the rotor.

[0008] Figure 3B yes Figure 2 An enlarged schematic cross-sectional view of a rotor seal assembly further comprising a carrier assembly, a seal assembly, and a biasing element in a second position relative to the rotor.

[0009] Figure 4 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising a radial fastener coupling the biasing element to the carrier assembly.

[0010] Figure 5 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising a circumferential pin coupling the biasing element to the carrier assembly.

[0011] Figure 6 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising a pin extending axially and coupling the biasing element to the carrier assembly.

[0012] Figure 7 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising an exemplary pin extending axially and coupling the biasing element to the carrier assembly.

[0013] Figure 8 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising an exemplary pin extending axially and coupling the biasing element to the carrier assembly.

[0014] Fig. 9 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising a biasing element integrally formed with the carrier assembly.

[0015] Fig.10 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising an exemplary pin extending axially and coupling the biasing element to the carrier assembly, and further comprising a fastener securing the biasing element to the seal assembly.

[0016] Fig.11 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising a carrier assembly including an internal passage fluidly coupled to an interior of a biasing element.

[0017] Fig.12 yes Figure 2 A schematic cross-sectional view of an exemplary rotor seal assembly further comprising a protrusion extending from the carrier assembly. DETAILED DESCRIPTION

[0018] Aspects of the disclosure described herein broadly relate to a rotor seal assembly having a seal having a floating portion facing a rotor of a gas turbine engine and a static 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, the floating seal body including a first sealing surface opposite to the rotor. In some cases, a biasing element can be positioned between the bracket assembly and the floating seal body so that the floating seal body can move between a first position and a second position, wherein the first position is radially displaced inward relative to the rotor compared to the second position. The floating seal body can further include an internal passageway that fluidly couples an inlet on the second sealing surface to an outlet disposed on a third sealing surface, the second sealing surface being defined as an upstream or axially forward face of the floating seal body, the third sealing surface being radially opposite to the first sealing surface. The outlet can be fluidly coupled to the interior of the biasing element.

[0019] The rotor seal assembly can provide a dynamic sealing environment by using a biasing element that can move between a first position and a second position. For the purpose of illustration, an exemplary environment in which the rotor seal assembly can be used will be described in the form of a turbine engine. In a non-limiting example, such a turbine engine can be in the form of a gas turbine engine, a turboprop engine, a turboshaft engine, or a turbofan engine with a power gearbox. However, it will be understood that the aspects of the present disclosure described herein are not limited thereto and can have general applicability in other sealing systems. For example, the present disclosure can be applied to rotor seal assemblies in other engines or carriers, and can be used to provide benefits in industrial, commercial, and residential applications.

[0020] As used herein, the term "upstream" refers to a direction opposite to the direction of fluid flow, while the term "downstream" refers to a direction in the same direction as the direction of fluid flow. The terms "front" or "frontward" mean in front of something, and "rear" or "rearward" mean behind something. For example, when used in relation to fluid flow, front / front may refer to upstream, and rear / rearward may refer to downstream.

[0021] Furthermore, as used herein, the terms "radial" or "radially" refer to directions away from a common center. For example, in the overall context of a turbine engine, radial refers to a direction along a ray extending between a central longitudinal axis of the engine and an outer engine circumference. Furthermore, as used herein, the terms "group" or a "group" of elements may be any number of elements, including only one element.

[0022] Furthermore, as used herein, the term "fluid" or iterations thereof may 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, a pressurized gas stream, a working gas stream, or any combination thereof. It is further contemplated that the gas turbine engine may be other suitable turbine engines, such as, but not limited to, a steam turbine engine or a supercritical carbon dioxide turbine engine. As non-limiting examples, the term "fluid" may refer to steam in a steam turbine engine, or to carbon dioxide in a supercritical carbon dioxide turbine engine.

[0023] All directional references (e.g., radial, axial, proximal, distal, upper, lower, upward, downward, left, right, lateral, front, rear, top, bottom, above, below, vertical, horizontal, clockwise, counterclockwise, upstream, downstream, forward, backward, etc.) are used only for identification purposes to help the reader understand the present disclosure, and do not create limitations, especially limitations on the position, orientation or use of the aspects of the present disclosure described herein. Unless otherwise stated, connection references (e.g., attachment, connection, fixing, fastening, connection and engagement) will be interpreted broadly and may include intermediate members between element sets and relative movement between elements. Therefore, connection references do not necessarily infer that two elements are directly connected and have a fixed relationship to each other. The exemplary drawings are only for illustrative purposes, and the dimensions, positions, orders and relative sizes reflected in the attached drawings may vary.

[0024] 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 extending from a front portion 14 to an aft portion 16. The gas turbine engine 10 includes, in downstream serial flow relationship: a fan section 18 including a fan 20; a compressor section 22 including a boost or low pressure (LP) compressor 24 and a high pressure (HP) compressor 26; a combustion section 28 including a combustor 30; a turbine section 32 including an HP turbine 34 and an LP turbine 36; and an exhaust section 38. The gas turbine engine 10 as described herein is intended to be a non-limiting example, and other architectures are possible, such as, but not limited to, a steam turbine engine, a supercritical carbon dioxide turbine engine, or any other suitable turbine engine.

[0025] The fan section 18 includes a fan case 40 surrounding the fan 20. The fan 20 includes a set of fan blades 42 radially arranged around the engine centerline 12. The HP compressor 26, the combustor 30, and the HP turbine 34 form an engine core 44 of the gas turbine engine 10, which produces combustion gases. The engine core 44 is surrounded by a core case 46, which can be connected to the fan case 40.

[0026] An HP shaft or spool 48 disposed coaxially 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 disposed coaxially about the engine centerline 12 of the gas turbine engine 10 within the larger diameter annular HP spool 48 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 coupled to a set of rotatable elements that may collectively define a rotor 51.

[0027] The LP compressor 24 and the HP compressor 26 each include a set of compressor stages 52, 54 in which a set of compressor blades 56, 58 rotate relative to a corresponding set of static compressor vanes 60, 62 (also referred to as nozzles) to compress or pressurize a fluid flow through the stage. In a single compressor stage 52, 54, a plurality of 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, with the corresponding static compressor vanes 60, 62 positioned upstream of and adjacent to the rotating blades 56, 58. It should be noted that Figure 1 The numbers of blades, buckets, and compressor stages shown in FIG. 5 are selected for illustrative purposes only, and other numbers are possible.

[0028] Blades 56, 58 for one stage of the compressor may be mounted to disks 61 mounted to respective ones of the HP spool 48 and the LP spool 50, with each stage having its own disk 61. Buckets 60, 62 for one stage of the compressor may be mounted to the core housing 46 in a circumferential arrangement.

[0029] The HP turbine 34 and the LP turbine 36 each include a set of turbine stages 64, 66 in which a set of turbine blades 68, 70 rotate relative to a corresponding set of static turbine vanes 72, 74 (also referred to as nozzles) to extract energy from the fluid flow through the stage. In a single turbine stage 64, 66, a plurality of 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, with the corresponding static turbine vanes 72, 74 positioned upstream of and adjacent to the rotating blades 68, 70. It should be noted that Figure 1The numbers of blades, buckets, and turbine stages shown in FIG. 5 are selected for illustrative purposes only, and other numbers are possible.

[0030] Blades 68, 70 for one stage of the turbine may be mounted to disks 71 mounted to respective ones of HP spool 48 and LP spool 50, with each stage having a dedicated disk 71. Buckets 72, 74 for one stage of the compressor may be mounted to core housing 46 in a circumferential arrangement.

[0031] In addition to the rotor portion, the stationary portion of the gas turbine engine 10 (such as the static blades 60, 62, 72, 74 in the compressor section 22 and the turbine section 32) is also individually or collectively referred to as a stator 63. Therefore, the stator 63 can refer to the combination of non-rotating elements in the entire gas turbine engine 10.

[0032] In operation, the airflow exiting the fan section 18 is split so that a portion of the airflow is directed into the LP compressor 24, which then supplies a 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 producing combustion gases. The HP turbine 34 extracts some work from these gases, which 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 gas is ultimately discharged from the gas turbine engine 10 via the exhaust section 38. The drive 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 may 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.

[0033] A portion of the pressurized air flow 76 may be extracted from the compressor section 22 as bleed air 77. The bleed air 77 may be extracted from the pressurized air flow 76 and provided to engine components that require cooling. The temperature of the pressurized air flow 76 entering the combustor 30 is significantly increased. Therefore, the cooling provided by the bleed air 77 is necessary for operating such engine components in an elevated temperature environment.

[0034] 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 stationary vane row (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 the fan section 18 to exert some directional control on the airflow 78.

[0035] Some of the air supplied by the fan 20 may bypass the engine core 44 and be used to cool portions of the gas turbine engine 10, particularly the hot portions, 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 the turbine section 32, with the HP turbine 34 being the hottest portion as it is located directly downstream of the combustion section 28. Other sources of cooling fluid may be, but are not limited to, fluid exhausted from the LP compressor 24 or the HP compressor 26.

[0036] Figure 2 It is further shown that Figure 1 FIG. 1 is a diagram showing a rotor 51, a stator 63, and a rotor seal assembly 100 for a gas turbine engine 10 as seen in section II of FIG. 1. In the example shown, at least a portion of the rotor seal assembly 100 may be disposed in the HP turbine 32 and depend from a portion of the stator 63, in particular, from a turbine bucket 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 may be positioned within any portion of the gas turbine engine 10 (e.g., in the fan section 18, the compressor section 22, or the turbine section 32), between any suitable rotating component and a stationary component of the gas turbine engine 10. Thus, the rotor seal assembly 100 may depend from any suitable stationary component (e.g., but not limited to, the compressor buckets 60, 62 or the turbine buckets 72, 74). For purposes of this disclosure, the turbine buckets 72 or any other buckets (e.g., the static buckets 60, 62, 72, 74) that depend from the stator 63 may be collectively referred to as the stator 63.

[0037] The rotor seal assembly 100 may include a carrier assembly 102 carried by the stator 63 and having a seal seat 106 defining a seal cavity 108, and a seal assembly 104 at least partially located within the seal cavity 108 and having 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.

[0038] During operation of the gas turbine engine 10, a 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 airflow 76, however, it should be understood that the working fluid 88 may be any suitable working fluid or airflow, such as, but not limited to, the pressurized airflow 76, combustion gases, ambient airflow, any combination thereof, or any other suitable fluid as described herein. A majority of the working fluid 88 may flow through the turbine vanes 72 and the turbine blades 68 to define a working fluid path. A leakage fluid 90 is diverted 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 vanes 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 leakage fluid 90 flowing from the upstream portion of the turbine vanes 68 to the downstream portion of the turbine vanes 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 leakage fluid 90 that can flow around the radially inner portion of the stator 63 .

[0039] Figure 3A-3B is from Figure 2 The first position ( Figure 3A ) and the second position ( Figure 3B ) is a schematic cross-sectional view of a 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 closer to the rotor 51 in the first position than in the second position. In addition, the biasing element 112 in the first position can be expanded in the radial direction compared to the biasing element 112 in the second position. Therefore, Figure 3A-3B A comparison of the rotor seal assembly 100 between a first position and a second position is shown, respectively.

[0040] At least one of the carrier 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 carrier 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 segmented into two or more segments around the engine centerline 12. The number of segments of the carrier assembly 102 may correspond to the number of segments of the seal assembly 104.

[0041] The biasing element 112 may extend within the seal cavity 108 between the carrier assembly 102 and the seal assembly 104 and be operably coupled to at least one of the floating seal body 110 or the carrier assembly 104 by any suitable method (e.g., but not limited to bonding, fastening, welding, etc.). The biasing element 112 may include a head 115 defined as a radially outer portion of the biasing element 112 that faces at least a portion of the carrier assembly 102.

[0042] As shown, the biasing element 112 is a pneumatic bellows defining an interior 113 (particularly a hollow interior). Thus, a fluid may be introduced into the interior of the biasing element 112 to move the biasing element 112 from a retracted position ( Figure 3B ) to the extended position ( Figure 3A ), which results in a corresponding movement of the floating seal body 110. It is contemplated that the biasing element 112 may be biased to a retracted position. The size of the biasing element 112 may be designed based on the location 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 may be increased or decreased based on the desired extended or retracted length of the biasing element 112. Although illustrated as a pneumatic bellows, it should be understood that the biasing element may be any other suitable biasing element, such as, but not limited to, a leaf spring, a garter spring, a flexure, etc.

[0043] The carrier assembly 102 of the rotor seal assembly 100 can define a seal seat 106, which defines a seal 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. The first wall 114 and the second wall 116 can both extend radially inward from the stator 63 (particularly the turbine bucket 72), wherein the second wall 116 is upstream or axially forward of the first wall 114. The third wall 118 can extend in an 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 therefore define the seal cavity 108. It should be understood that the dimensions of the first wall 114, the second wall 116, and the third wall 118, and therefore the dimensions of the seal seat 106, can be designed so that the seal assembly 104 (and more specifically, the floating seal body 110) can be at least partially received within the seal 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 freely move in the radial direction within the seal cavity 108 divided by the first wall 114 and the second wall 116.

[0044] The second wall 116 may include teeth 120 facing at least a portion of the floating seal body 110. The teeth 120 may be used to limit, restrict, or prevent leakage fluid 90 from passing between the second wall 116 and the floating seal body 110 and entering the seal cavity 108. It is contemplated that the teeth 120 may be designed to provide a minimal radial friction load on the seal assembly 104 while still ensuring that the leakage fluid 90 is limited or otherwise prevented from flowing around the seal assembly 104 and entering the seal cavity 108.

[0045] The seal seat 106 may also include a flange 122 extending from a portion of the seal seat 106 and into the seal cavity 108. As a non-limiting example, the flange 122 may extend from a radially inner portion of the third wall 118 and into the seal cavity 108. In other words, the flange 122 may extend radially inward from a portion of the bracket assembly 102 and into the seal cavity 108. However, it should be understood that the flange 122 may extend from any other suitable portion of the bracket assembly 102 and into the seal cavity 108. For example, the flange 122 may extend axially inward from the second wall 116 and axially into the seal cavity 108. The distal end of the flange 122 may face the floating seal body 110. As a non-limiting example, the floating seal body 110 may 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 may be coupled to the seat 124 by any suitable coupling method, such as, but not limited to, welding, bonding, fastening, magnetism, friction, or any combination thereof. Since the carrier assembly 102 is static and the flange 122 is coupled to or otherwise part of the carrier assembly 102, the flange 122 may be further defined as a static portion of the rotor seal assembly 100. Thus, the flange 122 and the seat 124 may limit at least one of axial, circumferential, or radial movement of the floating seal body 110.

[0046] The bracket assembly 102 may also include a tab 128 extending from the seal seat 106, particularly between the third wall 118 and the stator 63. The tab 128 may be used to physically couple the bracket assembly 102 to the stator 63. As shown, the tab 128 extends from the upstream or axial forward portion of the third wall 118 to the turbine bucket 72 or the stator 63, however, it should be understood that the tab 128 may extend from any portion of the bracket assembly 102 and be coupled to any portion of the stator 63. The coupling between the tab 128 and the stator 63 may 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 bracket assembly 102 is a separate discrete component coupled to the stator by the tab 128, however, it should be understood that the bracket assembly 102 may be integrally formed with the stator 63. Specifically, the bracket assembly may be integrally formed with the turbine bucket 72 or any other suitable component of the stator 63 by additive manufacturing, casting, etc., such that the bracket assembly 102 and at least a portion of the stator 63 form a unitary structure.

[0047] The retainer groove 130 can be formed in a portion of the seal seat 106, specifically in the third wall 118, wherein the retainer 132 corresponds to the retainer groove 130. As shown, the retainer groove 130 can be formed on an axially downward or downstream portion of the third wall 118. It is contemplated that the retainer groove 130 and the retainer 132 can be located along a radially outer portion of the third wall that is axially opposite to the location 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 cover plate retained by a bayonet, etc.

[0048] It is contemplated that the seal seat 106 may include any number of one or more walls, including any of the components described herein (e.g., flange 122). At least one of the first wall 114, the second wall 116, or the third wall 118 may be excluded from the bracket assembly 102. As a non-limiting example, the rotor seal assembly 100 may be defined as a compressor discharge pressure (CDP) seal assembly. In this case, the second wall 116 may be excluded so that the seal seat 106 is defined by at least the first wall 114 extending radially inwardly toward the rotor 51 at the downstream portion of the seal assembly 104 and the third wall 118 extending upstream or forward of the second wall 116.

[0049] A set of tertiary seals 134 may be located between the bracket 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 tertiary seals 134 arranged in series. The set of tertiary seals 134 may include any suitable seals, such as but not limited to piston rings, E-type seals, W-type seals, C-type seals, blade 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 extend circumferentially around the entire rotor 51), two sections of 180 degrees each, or more than two sections.

[0050] The seal assembly 104 may include a floating seal body 110 defined by a first sealing surface 136 facing the rotor 51, a second sealing surface 138 facing the second wall 116 of the carrier assembly 102, a third sealing surface 140 opposite the first sealing surface 136 and facing at least a portion of the seal cavity 108 and / or the biasing element 112, and a fourth sealing surface 142 opposite the second sealing surface 138 and facing the first wall 114. In other words, the first sealing surface 136 may define a radially inner face of the floating seal body 110, the second sealing surface 138 may define an axially forward or upstream face of the floating seal body 110 (e.g., a face facing at least a portion of the leakage fluid 90), the third sealing surface 140 may define a radially outer face of the floating seal body, and the fourth sealing surface 142 may define an axially downward or downstream face of the floating seal body 110.

[0051] The internal passage 144 can 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 can 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 outlet 148 in the set of outlets 148 can be fluidly coupled to the interior 113 of the biasing element 112 and diametrically or otherwise opposed to the head 115 of the biasing element 112.

[0052] During operation of gas turbine engine 10, at least a portion of leakage fluid 90 may flow into internal passage 144 through inlet 146. Leakage fluid 90 may then flow through the internal passage and ultimately out of at least one outlet 148 in set of outlets 148. When turbine engine 10 is started, biasing element 112 may be in a retracted second position ( Figure 3BOnce the working fluid 88 is generated, at least a portion of the leakage fluid 90 exiting the set of outlets 148 may be expelled into the interior 113 of the biasing element 112 or otherwise expelled into the interior of the sealed cavity 108. This in turn may cause the biasing element 112 to be moved from the retracted position ( Figure 3B ) to the extended position ( Figure 3A When the floating seal body 110 is coupled to the biasing element 112, the floating seal body 110 and thus the seal assembly 104 may be positioned together with the biasing element 112 in the first position ( Figure 3A ) and the second position ( Figure 3B ) between the first position and the second position. In other words, the contraction or extension of the biasing element 112 can cause the rotor seal assembly 100 to move 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 a working fluid 88 or a gas flow (e.g., a pressurized gas flow 76 or combustion gases) flowing through the gas turbine engine 10, the leakage fluid 90 will only exist in the gas turbine engine 10. In other words, the leakage fluid 90 will only exist when the gas turbine engine 10 is operating. Therefore, 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 enter its extended 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. Therefore, 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 biasing position (e.g., retracted position) and the rotor seal assembly 100 to be in the second position. The axial, circumferential, or radial position of the floating seal body 110 may be further defined by the flange 122. For example, during operation of the gas turbine engine 10, the rotor 51 may exert an axial, radial, or circumferential force on the floating seal body 110, such that the floating seal body 110 will want to move in the direction of the force. Since the flange 122 is static and faces the seat 124, is received in the seat 124, or is otherwise coupled to the seat 124, the flange 122 and the seat 124 may limit at least a portion of the circumferential, axial, or radial movement of the floating seal body 110. In other words, the flange 122 may position the floating seal body 110 circumferentially, axially, or radially within the seal cavity 108 and limit or otherwise prevent the floating seal body 110 from moving in at least one of the axial, radial, or circumferential directions.

[0053] The leakage fluid 90 flowing into the interior 113 of the biasing element 112 may expand the biasing element 112 such that the biasing element applies a closing force on the seal assembly 104. As used herein, the term "closing force" may refer to a radial force applied by the biasing element 112 on the seal assembly 104, particularly the floating seal body 110, that pushes the seal assembly 104 toward the rotor 51. The closing force may be based on the position of the rotor seal assembly 100 within the gas turbine engine 10, and based on one or more operating characteristics of the gas turbine engine 10. As used herein, the term "operating characteristic" may refer to an 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, a pressure differential between an upstream side and a downstream side of a portion of the stator 63 from which the rotor seal assembly 100 is suspended. If the pressure differential is large (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 biasing element 112 than if the pressure differential is small. The greater the pressure within the interior 113 of the biasing element 112, or the greater the amount of leakage fluid 90 within the biasing element 112, the greater the closing force. This in turn results in a closing force that is proportional to the pressure differential across the rotor seal assembly 100. Therefore, the closing force will depend on the pressure differential or the operating state of the gas turbine engine 10. During operation of the gas turbine engine 10, the rotor 51 may 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 undesirable manner.

[0054] Figure 4 yes Figure 2 FIG. 2 is a 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; therefore, like parts will be identified with like numbers in the 200 series, and it should be understood that the description of like parts of the rotor seal assembly 100 applies to the exemplary rotor seal assembly 200 unless otherwise specified.

[0055] The rotor seal assembly 200 may include a biasing element 212 that may include a first bore 260 extending radially through a portion of the biasing element 212. Specifically, the first bore 260 may extend through a radially distal portion of the biasing element 112 (eg, a head 215 of the biasing element 212).

[0056] The rotor seal assembly may also 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 upper portion and a radially inner portion, wherein the radially upper portion has a larger diameter than the radially inner portion. In this way, the second hole 254 may be defined by a step so 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.

[0057] The third wall 218 may also include a protrusion 256 extending radially inwardly 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.

[0058] The biasing element 212 can 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 can correspond to the second hole 254, specifically, to the radially inner portion of the second hole 254. The fastener 262 can 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 can limit at least one of axial movement, circumferential movement, or radial movement of the biasing element 212. The fastener 262 can be any suitable fastener, such as, but not limited to, a screw, a tab, a pin, a weld, a bolt and a nut (where the bolt is integrally formed with the top of the biasing element 212), a retaining snap ring, or any combination thereof.

[0059] Figure 5 yes Figure 2 FIG. 3 is a schematic diagram of a 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; therefore, 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 specified.

[0060] The rotor seal assembly 300 may include a carrier assembly 302 carried by at least a portion of the stator 63. The carrier 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 inward 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.

[0061] The biasing element 312 may include a head 315 that corresponds to the seat 358 and fits within the seat 358. The biasing element 312 may also 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 the circumferential movement, axial movement, or radial movement of the biasing element 312.

[0062] Figure 6 yes Figure 2 Schematic diagram of a 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; therefore, like parts will be identified with like numbers in the 400 series, and it should be understood that the description of like parts of the rotor seal assemblies 100, 200, 300 applies to the exemplary rotor seal assembly 400 unless otherwise specified.

[0063] The rotor seal assembly 400 may include a biasing element 412, which may include a head 415. The biasing element 412, and in particular the head 415, may include a first aperture 260 extending axially through the head 415 of the biasing element 412.

[0064] 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 inward 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 the upstream half of the third wall 418, and include a second hole 254 extending axially within the protrusion 456 or at least a portion of the third wall 418. As shown, the second hole 254 may have a constant cross-sectional area and be discontinuous in the axial direction.

[0065] The head 415 can be fitted within the seat 458 so that the first hole 460 corresponds to the second hole 454, so that the pin 466 can extend axially 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 limit at least one of axial movement, radial movement, or circumferential movement or axial movement of the biasing element 412.

[0066] Figure 7 yes Figure 2 Schematic diagram of a 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; therefore, like parts will be identified with 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 specified.

[0067] The rotor seal assembly 500 may include a biasing element 512, which may include a head 515, and the head 515 includes a first hole 460 extending axially through the head 515. The rotor seal assembly 500 may also include a bracket assembly 502 carried by at least a portion of the stator 63. The bracket assembly 502 may include a first wall 114, a second wall 116, and a third wall 520 interconnecting the first wall 114 and the second wall 116. The third wall 520 may include a second hole 554 extending radially through a portion of the third wall 518, specifically, extending radially through a radially outer portion of the third wall 518. The third wall 520 may also include a protrusion 556 extending radially inward from a radially inner portion of the third wall 520 facing the seal cavity 108. The protrusion 556 may include a seat 558 extending radially through at least a portion of the protrusion 556 and corresponding to the second hole 554 of the third wall 520.

[0068] 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 extend radially beyond the third wall 520. The pin 566 can extend axially 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 limit at least one of axial movement, radial movement, or circumferential neutral movement of the biasing element 512.

[0069] Figure 8 yes Figure 2Schematic diagram of a cross-sectional view of an exemplary rotor seal assembly 600. Exemplary rotor seal assembly 600 is similar to rotor seal assemblies 100, 200, 300, 400, 500; therefore, like parts will be identified with like numbers in the 600 series, and it should be understood that the description of like parts of rotor seal assemblies 100, 200, 300, 400, 500 applies to exemplary rotor seal assembly 600 unless otherwise specified.

[0070] The rotor seal assembly 600 may include a biasing element 612 that may include a head 615 facing the carrier assembly 602. The head 615 may include a first bore 660 extending axially therethrough.

[0071] The rotor seal assembly 600 may also 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 extending radially inward 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 extending radially through at least a portion of the corresponding protrusion 656.

[0072] The biasing element 612 can be positioned such that the head 615 is axially positioned between the set of protrusions 656. Specifically, the biasing element 612 can 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 can extend axially 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 limit at least one of axial movement, radial movement, or circumferential neutral movement of the biasing element 612.

[0073] Fig. 9 yes Figure 2 Schematic diagram of a cross-sectional view of an exemplary rotor seal assembly 700. Exemplary rotor seal assembly 700 is similar to rotor seal assemblies 100, 200, 300, 400, 500, 600; therefore, like parts will be identified with like numbers in the 700 series, and it should be understood that the description of like parts of rotor seal assemblies 100, 200, 300, 400, 500, 600 applies to exemplary rotor seal assembly 700 unless otherwise specified.

[0074] 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 inward from a radially inner portion of the third wall 718 facing the seal cavity 108.

[0075] 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 (e.g., but not limited to additive manufacturing or casting), or otherwise coupled to the protrusion 756 by any suitable method (e.g., but not limited to welding, bonding, etc.). The protrusion 756 may couple the biasing element 712 to the bracket assembly 602 and limit at least one of axial movement, radial movement, or circumferential neutral movement of the biasing element 612.

[0076] Fig.10 yes Figure 2 Schematic diagram of a cross-sectional view of an exemplary rotor seal assembly 800. Exemplary rotor seal assembly 800 is similar to rotor seal assemblies 100, 200, 300, 400, 500, 600, 700; therefore, like parts will be identified with like numbers in the 800 series, and it should be understood that the description of like parts of rotor seal assemblies 100, 200, 300, 400, 500, 600, 700 applies to exemplary rotor seal assembly 800 unless otherwise specified.

[0077] The rotor seal assembly 800 may include a carrier 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 carrier assembly 802. The head 815 may include a first hole 860 extending axially therethrough.

[0078] The bracket assembly 802 can be carried by at least a portion of the stator 63 and includes 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 inward 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 that extends 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 also include a seat 858 that extends radially through at least a portion of the protrusion 856 or the third wall 818.

[0079] Seal assembly 804 may be at least partially located within seal cavity 108 and include a floating seal body 810 defined by first sealing surface 836, second sealing surface 138, third sealing surface 140, and fourth sealing surface 842. Third aperture 870 may extend radially through at least a portion of seal body 810 from first sealing surface 836 to fourth sealing surface 842.

[0080] The biasing element 812 can be axially positioned to cover the third hole 870 and have the head 815 correspond to and fit within the seat 858 so that the first hole 860 corresponds to the second hole 854. The pin 866 can extend axially 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 extend radially 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 a screw, a tab, a pin, a weld, a dovetail, etc. The pin 866 and the seat 858 can couple the biasing element 812 to the bracket assembly 802, and the fastener 876 can couple the biasing element 812 to the seal assembly 804. The pin 866 , seat 858 , and fastener 876 limit at least one of axial movement, radial movement, or circumferential movement or axial movement of the biasing element 812 .

[0081] An 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 sealing surface 140 to at least an outlet 848 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.

[0082] Fig.11 yes Figure 2 Schematic diagram of a cross-sectional view of an exemplary rotor seal assembly 900. Exemplary rotor seal assembly 900 is similar to rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800; therefore, like parts will be identified with like numbers in the 900 series, it being understood that the description of like parts of rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800 applies to exemplary rotor seal assembly 900 unless otherwise noted.

[0083] 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 in 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.

[0084] The rotor seal assembly 900 may also include a seal assembly 904 that is at least partially located within the seal cavity 108 and includes a floating seal body 910 that is defined by a first seal surface 136, a second seal surface 938 that is similar to the first seal surface 136 but lacks the inlet 146, a third seal surface 140, and a fourth seal surface 942. The biasing element 912 may include a head 915 that faces the seal assembly 804, and in particular, faces the fourth seal surface 942. The 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 bracket assembly 902 or the seal assembly 904 by any suitable coupling method, such as, but not limited to, welding, bonding, fastening, etc.

[0085] The additional biasing element 912, shown as a set of cinching springs 990, may extend circumferentially around the entire floating seal body 910 or otherwise be coiled on the entire floating seal body 910, or alternatively extend circumferentially across one or more segments of a set of floating seal bodies 910 or otherwise be coiled 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 cinching springs 990 can push the floating seal body 910 toward the rotor 51. Therefore, the set of cinching springs 990 and the biasing element 912 can be used together or otherwise defined as a biasing element configured to provide a closing force. The set of cinching springs 990 can engage with the floating seal body 910 through a corresponding groove or channel 992. As shown, the channel 992 can be formed in a protrusion extending from the fourth sealing surface 942. Additionally or alternatively, the passage 992 may extend into the third sealing surface 940 such that at least a portion of the set of tension springs 990 extends into the floating seal body 910 .

[0086] The set of cinching springs 990 may be used when the rotor seal assembly 900 is disposed within a portion of the gas turbine engine 10 having a high pressure differential. Thus, the set of cinching springs 990 may provide 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.

[0087] Fig.12 yes Figure 2 Schematic diagram of a cross-sectional view of an exemplary rotor seal assembly 1000. The exemplary rotor seal assembly 1000 is similar to rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800, 900; therefore, like parts will be identified with like numbers in the 1000 series, and it should be understood that the description of like parts of rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800, 900 applies to the exemplary rotor seal assembly 1000 unless otherwise stated. The rotor seal assembly 1000 is similar to 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 the rotor seal assemblies 100, 200, 300, 400, 500, 600, 700, 800, 900.

[0088] The rotor seal assembly 1000 may include a carrier assembly 1002 carried by at least a portion of the 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 inward from a radially inner portion of the third wall 1018 and facing the seal cavity 108. The 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 not circumferentially continuous around the rotor 51). The pin 1066 may be used as a method of physically coupling a segment of the carrier assembly 1002 (or any other portion 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 can be any suitable component to couple one segment to another segment, such as, but not limited to, a bolt, a pin, a fastener, etc.

[0089] The rotor seal assembly 1000 may also include a seal assembly 1004 that is at least partially located within the seal cavity 108 and includes a floating seal body 1010 that is defined by a first seal face 136, a second seal face 1038 that is similar to the first seal face 136 but lacks the inlet 146, a third seal face 1040, and a fourth seal face 142. A pair of biasing elements, shown as a set of cinch springs 1090, may be received within a set of circumferential channels 1092 formed within a portion of the seal assembly 1004. As a non-limiting example, the set of cinch springs 1090 may be received within a set of circumferential channels 1092 formed within a portion of the third seal face 1040. As shown, the floating seal body 1010 does not include an internal passageway.

[0090] Compared with conventional rotor seal assemblies, the benefits of the present disclosure include rotor seal assemblies with increased sealing capabilities without increasing manufacturing burdens. For example, conventional rotor seal assemblies can rely on forming a labyrinth between the stator and the rotor by extending components 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 limiting or preventing leakage fluid from passing 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 separately depending on its position within the turbine engine. Based on seal diameter, vibration response, and other factors, conventional labyrinth seals also have limited leakage control capabilities. The sealing gap or gap of the labyrinth seal teeth to the stator (usually honeycomb wearable) can only be kept so tight in gas turbine engine operation, typically with a physical gap of 4 to 100 mils, depending on seal size and position. However, as described herein, the rotor seal assembly, in particular the floating seal body, can be radially translated relative to the rotor by the biasing element based on the operating characteristics of the turbine engine. Specifically, the biasing element can move between a retracted position and an extended 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 retracted position to the extended 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 started, shut down or not in operation, the total time that the seal assembly is in contact with the rotor is reduced compared to the conventional rotor seal assembly, which reduces the total wear of the rotor seal assembly and ultimately extends the total life of the rotor seal assembly. In addition, 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 bracket assembly of the rotor seal assembly is suspended. Because the rotor seal assembly is scalable based on its location in the overall turbine engine, there is less manufacturing burden because the rotor seal assembly does not need to be tuned, designed, or otherwise manufactured separately based on its location within the turbine engine.The rotor seal assembly can be used throughout the turbine engine.

[0091] Yet another benefit of the present disclosure includes a rotor seal assembly that is dynamic based on the operating state of the turbine engine compared to a conventional turbine engine including a conventional rotor seal assembly. For example, during operation of a conventional turbine engine, a fluid film may be formed between a portion of the rotor seal assembly and the rotor. A radial opening force depending on the pressure differential at the location of the conventional rotor seal assembly may be formed by a fluid film that pushes or otherwise displaces the rotor seal assembly radially away from the rotor or radially outward from the rotor. In addition, 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 generated by the conventional rotor seal assembly may cause the conventional rotor seal assembly to translate axially, circumferentially or radially in an undesirable manner, ultimately reducing the sealing effect of the conventional rotor seal assembly. However, the rotor seal assembly as described herein uses a closing force, particularly a radial closing force, generated by a biasing element to offset the radial opening force. As discussed herein, a closing force similar to the radial 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 offset the radial opening force. This in turn ensures that the seal assembly is not displaced too far radially from the rotor, thereby ensuring reduced membrane stiffness compared to conventional rotor seal assemblies, and the floating seal body can faithfully or accurately track the radial movement of the rotor. In addition, the pressurized biasing element allows a method for increasing the closing force. This allows for dynamic force / torque balancing of the floating seal body. This ensures that the rotor seal assembly described herein allows for increased sealing effect compared to conventional rotor seal assemblies, which ultimately increases the overall efficiency of the turbine engine.

[0092] To the extent not yet described, the different features and structures of each aspect can be used in combination with each other as needed. A feature that cannot be shown in all aspects does not mean that it cannot be included, but is done so for the sake of brevity of description. Therefore, various features of different aspects can be mixed and matched as needed to form new aspects, whether or not the new aspects are explicitly described. The combination or arrangement of the features described herein is covered by the present disclosure.

[0093] This written description uses examples to describe the aspects of the disclosure described herein, including the best mode, and also to enable any person skilled in the art to practice aspects of the disclosure, including making and using any device or system and performing any combined methods. The patentable scope of aspects of the disclosure is defined by the claims, and may include other examples that occur to one 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 substantially from the literal language of the claims.

[0094] Further aspects of the invention are provided by the subject matter of the following clauses:

[0095] A turbine engine comprises: an engine core, the engine core comprising 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, the bracket assembly being carried by the stator and having a sealing seat defining a sealing cavity; and a sealing assembly, the sealing assembly having a floating seal body and a biasing element, the floating seal body being at least partially located in the sealing cavity and having a first sealing surface facing the rotor, the biasing element being located in the sealing cavity and biasing the floating seal body so that the first sealing surface is biased toward the rotor.

[0096] A turbine engine according to any preceding clause, further comprising an internal passage located within the floating seal body, the internal passage connecting 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 to the first sealing surface.

[0097] A turbine engine as recited in any preceding clause, wherein the biasing element includes a hollow interior and the outlet is fluidly coupled to the hollow interior.

[0098] A turbine engine according to any preceding clause, wherein the biasing element is a pneumatic bellows.

[0099] A turbine engine according to any preceding clause, wherein the seal seat further comprises: a first wall extending radially inward from the stator; a second wall extending radially inward 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.

[0100] A turbine engine according to any preceding clause, further comprising a protrusion extending radially inwardly from the third wall relative to the engine centreline, and a pin extending circumferentially through at least a portion of the protrusion.

[0101] The turbine engine according to any of the preceding clauses further comprises: a flange, which extends at least one of axially inward or radially inward from the second wall or the third wall respectively and enters the sealing cavity; and a seat, which extends from the floating seal body and enters the sealing cavity; wherein the flange faces the seat to limit at least one of axial or circumferential movement of the floating seal body relative to the centerline of the engine.

[0102] A turbine engine according to any preceding clause, further comprising an internal passage formed within one of the bracket assembly or the floating seal body and coupling an inlet disposed on an upstream face of the bracket assembly or the floating seal body with an outlet fluid coupled to an interior of the biasing element.

[0103] A turbine engine according to any preceding clause, wherein the biasing element further comprises a head located on a radially opposite end of the biasing element relative to the outlet.

[0104] A turbine engine as claimed in any preceding clause, wherein the head is integrally formed with at least a portion of the cradle assembly.

[0105] A turbine engine as claimed in any preceding clause, wherein the head comprises a first bore extending axially, radially or circumferentially through the head.

[0106] A turbine engine as claimed in any preceding clause, wherein a pin extends through the first aperture.

[0107] The turbine engine of any preceding clause, further comprising 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.

[0108] A turbine engine according to any of the preceding clauses, further comprising: a third hole extending radially through at least a portion of the floating seal body; a fastener extending through the third hole and connected to a portion of the biasing element radially opposite the head; and an internal passage formed within the floating seal body and a portion of the fastener and connecting an inlet fluid located on the upstream face of the floating seal body to at least one outlet, the at least one outlet being positioned along a portion of the fastener facing the biasing element, wherein the outlet fluid is connected to the interior of the biasing element.

[0109] A turbine engine according to any preceding clause, further comprising a second hole, the 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.

[0110] A 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 connected 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.

[0111] A turbine engine according to any preceding clause, wherein the seal assembly further comprises a set of additional biasing elements extending circumferentially along a portion of the floating seal body.

[0112] A turbine engine as claimed in any preceding clause, wherein the bracket assembly is formed integrally with the stator.

[0113] A turbine engine as claimed in any preceding clause, wherein the bracket assembly and the seal assembly are located within the turbine section.

[0114] A turbine engine as claimed in any preceding clause, wherein the cradle assembly is segmented about the engine centreline.

Claims

1. A turbine engine, characterized in that: include: an engine core, the engine core comprising 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 engine core further having a rotor and a stator; a bracket assembly carried by the stator and having a sealing seat defining a sealing cavity; as well as a seal assembly having a floating seal body at least partially located within the seal cavity and having a first seal surface facing the rotor, and a biasing element located within the seal cavity and biasing the floating seal body such that the first seal surface is biased toward the rotor; An internal passage is formed in one of the bracket assembly or the floating seal body and fluidly couples an inlet disposed on an upstream face of the bracket assembly or the floating seal body with an outlet fluidly coupled to an interior of the biasing element.

2. The turbine engine according to claim 1, characterized in that in, The sealing seat further comprises: a first wall extending radially inwardly from the stator; a second wall extending radially inwardly from the stator and upstream of the first wall; and a third wall interconnecting the first wall and the second wall; The first wall, the second wall and the third wall at least partially define the sealing cavity and surround the floating seal body.

3. The turbine engine according to claim 2, characterized in that: Further comprising a protrusion extending radially inwardly from the third wall relative to the engine centerline and a pin extending circumferentially through at least a portion of the protrusion.

4. The turbine engine according to claim 2, characterized in that: Further including: a flange, the flange extending at least one of axially inwardly or radially inwardly from the second wall or the third wall, respectively, and entering the sealing cavity; as well as a seat extending from the floating seal body 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 body relative to the engine centerline.

5. The turbine engine according to claim 1, characterized in that: in, The biasing element further includes a head portion located on a radially opposite end of the biasing element relative to the outlet.

6. The turbine engine according to claim 5, characterized in that in, The head is integrally formed with at least a portion of the bracket assembly.

7. The turbine engine according to claim 5, characterized in that in, The head includes a first aperture extending axially, radially or circumferentially through the head.

8. The turbine engine according to claim 7, characterized in that in, A pin extends through the first hole.

9. The turbine engine according to claim 8, characterized in that Further comprising 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.

10. The turbine engine according to claim 9, characterized in that Further including: a third bore extending radially through at least a portion of the floating seal body; a fastener extending through the third aperture and coupled to a portion of the biasing element diametrically opposite the head; as well as an internal passage formed within the floating seal and a portion of the fastener and fluidly coupling an inlet located on an upstream face of the floating seal to at least one outlet located along a portion of the fastener facing the biasing element, wherein the outlet fluidly couples to an interior of the biasing element.

11. The turbine engine according to claim 7, characterized in that Further comprising 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.

12. The turbine engine according to claim 1, characterized in that in, The bracket assembly further comprises: 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 three seals disposed between a radially outer portion of the carrier 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.

13. The turbine engine according to any one of claims 1 to 12, characterized in that Further comprising an internal passage within the floating seal body, the internal passage connecting an inlet on a second sealing surface of the floating seal body to an outlet 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 to the first sealing surface.

14. The turbine engine according to claim 13, characterized in that in, The biasing element includes a hollow interior, and the outlet is fluidly coupled to the hollow interior.

15. The turbine engine according to any one of claims 1 to 12, characterized in that in, The biasing element is a pneumatic bellows.

16. The turbine engine according to any one of claims 1 to 12, characterized in that in, The seal assembly further includes a set of additional biasing elements extending circumferentially along a portion of the floating seal body.

17. The turbine engine according to any one of claims 1 to 12, characterized in that in, The bracket assembly is integrally formed with the stator.

18. The turbine engine according to any one of claims 1 to 12, characterized in that in, The carrier assembly and the seal assembly are located within the turbine section.

19. The turbine engine according to any one of claims 1 to 12, characterized in that in, The bracket assembly is segmented about the engine centerline.

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