Suction face seal assembly for a rotary machine

Abstract

A suction face seal assembly includes a stationary component and a seal body defining a seal face. The seal body defines a fluid supply passage within the seal body. The fluid supply passage includes an inlet and one or more supply ports defined along the seal face. The seal body is movably coupled to the stationary component via an elastomeric member. A first pressure plenum is defined radially outward from the seal body, and a second pressure plenum is defined radially inward from the seal body. The seal assembly further includes a plenum seal forming a seal between a portion of the seal body and the stationary component and at least partially defining a third pressure plenum in fluid communication with a source of high pressure fluid and the inlet of the fluid supply passage. The third pressure plenum is pressurized at a higher pressure than both the first pressure plenum and the second pressure plenum.

Description

Technical Field

[0001] This disclosure generally relates to rotating machines. More specifically, the subject matter herein relates to a suction sealing assembly between rotating and stationary parts in a rotating machine. Background Technology

[0002] A turbine engine, particularly a gas or combustion turbine engine, is a rotating machine that extracts energy from a stream of combustion gases passing through the engine and transfers it to multiple rotating turbine blades. A turbine engine comprises multiple rotating parts forming a rotor assembly and multiple stationary parts forming a stator assembly.

[0003] Suction face seals are used to minimize leakage through gaps between two components, such as between a rotor assembly and a stator assembly, by restricting fluid flow from a higher-pressure area to a lower-pressure area. Furthermore, suction face seals can compensate for transient changes that may occur in the gaps between these components. Fluid leakage through suction seal assemblies can significantly increase fuel consumption and adversely affect engine efficiency and the overall efficiency of gas turbine engines. Attached Figure Description

[0004] The complete and feasible disclosure of this disclosure, including its best mode, is set forth in the specification with reference to the accompanying drawings, for those skilled in the art, wherein:

[0005] Figure 1 This is a cross-sectional view of a gas turbine engine according to an exemplary aspect of this disclosure.

[0006] Figure 2 An embodiment of a suction face sealing assembly according to at least one embodiment of the present disclosure is shown. Figure 1 The image shows a cross-sectional view of a portion of the core engine of a gas turbine engine.

[0007] Figure 3 At least one embodiment according to the present disclosure is shown. Figure 2 A cross-sectional view of another embodiment of the suction surface sealing assembly shown.

[0008] Figure 4 At least one embodiment of the present disclosure is shown as follows Figure 3 A cross-sectional view of an alternative embodiment of the suction surface sealing assembly shown.

[0009] Figure 5 At least one embodiment according to the present disclosure is shown. Figure 2 A cross-sectional view of another embodiment of the suction surface sealing assembly shown.

[0010] Figure 6 At least one embodiment according to the present disclosure is shown. Figure 2 A cross-sectional view of another embodiment of the suction surface sealing assembly shown.

[0011] Figure 7 At least one embodiment according to the present disclosure is shown. Figure 2 A cross-sectional view of another embodiment of the suction surface sealing assembly shown. Detailed Implementation

[0012] Reference will now be made in detail to the present embodiments of this disclosure, one or more examples of which are illustrated in the accompanying drawings. The detailed description uses numerals and letter reference numerals to denote features in the drawings. Similar or analogous reference numerals in the drawings and description have been used to denote similar or analogous portions of this disclosure.

[0013] The term "exemplary" is used herein to mean "used as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as superior or better than other implementations. Furthermore, unless explicitly stated otherwise, all embodiments described herein should be considered exemplary.

[0014] For the purposes described below, the terms “upper,” “lower,” “right,” “left,” “vertical,” “horizontal,” “top,” “bottom,” “lateral,” “longitudinal,” and their derivatives shall be used in relation to the implementation, for example, its orientation in the accompanying drawings. However, it should be understood that various alternative variations may be assumed in the embodiments unless explicitly stated otherwise. It should also be understood that the specific devices shown in the drawings and described in the following description are merely exemplary embodiments of this disclosure. Therefore, the specific dimensions and other physical characteristics associated with the embodiments disclosed herein should not be considered limiting.

[0015] Unless the context clearly indicates otherwise, the singular forms “a,” “a,” and “the” include plural references.

[0016] As used herein, the terms “first,” “second,” and “third” are used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.

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

[0018] The terms "front" and "rear" refer to relative positions within a gas turbine engine or vehicle. For example, in the context of a gas turbine engine, "front" refers to the position closer to the engine inlet, while "rear" refers to the position closer to the engine nozzle or exhaust port.

[0019] The terms "upstream" and "downstream" refer to the relative directions of fluid flow within a fluid path. For example, "upstream" refers to the direction from which the fluid flows, and "downstream" refers to the direction from which the fluid flows.

[0020] Unless otherwise stated herein, the terms “connection,” “fixed,” “attached to,” etc., refer to both direct connection, fixation, or attachment, and indirect connection, fixation, or attachment via one or more intermediate components or features.

[0021] The term “turbine” or “turbomachinery” refers to a machine that includes one or more compressors, a heating section (e.g., a combustion section), and one or more turbines that together generate torque output.

[0022] The term "gas turbine engine" refers to an engine that has a turbine as its power source, in whole or in part. Examples of gas turbine engines include turbofan engines, turboprop engines, turbojet engines, turboshaft engines, and hybrid electric versions of one or more of these engines.

[0023] The term "plenum" refers to an air-filled space, such as a defined cavity or volume within the core engine of a gas turbine engine or other rotating machine.

[0024] When used with compressors, turbines, shafts, or spools, unless otherwise specified, the terms “low” and “high,” or their respective comparatives (e.g., “lower” and “higher,” where applicable), refer to relative speeds within the engine. For example, “low-speed turbine” or “low-turbine” defines a component configured to operate at a rotational speed (e.g., the maximum permissible rotational speed) lower than that of a “high-speed turbine” or “high-speed turbine” at the engine.

[0025] Advanced air membrane seals operate with very low axial clearance, at least in part due to the air bearing stiffness generated by the high-pressure air forming a curtain between the slider and rotating hardware (the slider / seal has a feed port that "draws in" air and provides this stiffness to the air membrane). The pressure required to achieve this increased stiffness exceeds that of existing sealing systems.

[0026] This disclosure generally relates to a suction face sealing assembly in fluid communication with a high-pressure air source that supplies a high-pressure airflow to a sealing cavity defined between one or more sealing ports defined along the sealing face of a sealing body and the sealing face of a rotating component, to generate an air bearing seal at increased pressure above existing systems. The proposed design has several embodiments in which high-pressure air from a high-pressure source (e.g., but not limited to, a TV (turbine blade) hubbox) supplies high-pressure air to the air bearing, and a second sealing unit (piston ring seal, etc.) is used to separate pressure cavities around the sealing assembly, the pressure of which is maintained below the pressure of the air supplied by the high-pressure air source.

[0027] Referring now to the accompanying drawings, the same numbers throughout the drawings denote the same elements. Figure 1 An exemplary rotating machine configured as a gas turbine engine 10 is shown, which can be combined with various embodiments of this disclosure. In some embodiments, the gas turbine engine 10 can be mounted to an aircraft, such as in an underwing configuration or a tail-mounted configuration. Figure 1 The gas turbine engine 10 shown is provided as an example and is not intended to be limiting. The subject matter of this disclosure can be implemented with other types of turbine engines and other types of rotating machines.

[0028] Typically, the gas turbine engine 10 may include a fan section 12 and a core engine 14 disposed downstream of the fan section 12. The fan section 12 may include a fan 16 with any suitable configuration, such as a variable-pitch, single-stage configuration. The fan 16 may include a plurality of fan blades 18 spaced apart and coupled to a fan disk 20. The plurality of fan blades 18 may extend outward from the fan disk 20 generally along a radial direction (R) relative to the longitudinal centerline 22 of the gas turbine engine 10. The core engine 14 may be directly or indirectly coupled to the fan section 12 to provide torque for driving the fan section 12.

[0029] The core engine 14 may include an engine housing 24 that surrounds one or more portions of the core engine 14, including a compressor section 26, a combustor section 28, and a turbine section 30. The engine housing 24 may at least partially define a core engine inlet 32, an exhaust nozzle 34, and a core airflow path 36 therebetween. The core airflow path 36 may pass through the compressor section 26, the combustor section 28, and the turbine section 30. The compressor section 26 may include a turbocharger or a low-pressure compressor 38 and a high-pressure compressor 40 disposed downstream of the low-pressure compressor 38. The turbine section 30 may include a high-pressure turbine 42 and a low-pressure turbine 44. The compressor section 26, the combustor section 28, the turbine section 30, and the exhaust nozzle 34 may be arranged in a series flow relationship along a longitudinal centerline 22 and may each define a portion of the core airflow path 36 passing through the core engine 14.

[0030] The core motor 14 and fan section 12 can be coupled to a shaft driven by the core motor 14. As an example, such as... Figure 1 As shown, the core engine 14 may include a high-pressure shaft 46 and a low-pressure shaft 48. The high-pressure shaft 46 can drive the high-pressure turbine 42 to the high-pressure compressor 40. The low-pressure shaft 48 can drive the low-pressure turbine 44 to the low-pressure compressor 38. In other embodiments, the turbine engine may have three shafts, for example in the case of a turbine engine including an intermediate-pressure turbine. The shafts of the core engine 14, together with the rotating portions of the core engine 14, may sometimes be referred to as "spools". The high-pressure shaft 46, the rotating portions of the high-pressure compressor 40 connected to the high-pressure shaft 46, and the rotating portions of the high-pressure turbine 42 connected to the high-pressure shaft 46 may be collectively referred to as high-pressure spool 50. The low-pressure shaft 48, the rotating portions of the low-pressure compressor 38 connected to the low-pressure shaft 48, and the rotating portions of the low-pressure turbine 44 connected to the low-pressure shaft 48 may be collectively referred to as low-pressure spool 52.

[0031] In some embodiments, fan section 12 may be directly coupled to the shaft of core engine 14, for example, directly coupled to low-pressure shaft 48. Alternatively, as Figure 1 As shown, fan section 12 and core engine 14 can be interconnected via a power gearbox 54, such as a planetary reduction gearbox or a rotary gearbox. For example, power gearbox 54 can connect low-pressure shaft 48 to fan 16, such as fan disc 20 connected to fan section 12. Power gearbox 54 may include multiple gears for reducing the rotational speed of low-pressure shaft 48 to a more efficient rotational speed of fan section 12.

[0032] Still referencing Figure 1The fan section 12 of the gas turbine engine 10 may include a fan housing 56 that at least partially surrounds a fan 16 and / or a plurality of fan blades 18. The fan housing 56 may be supported by a core engine 14, for example, by a plurality of circumferentially spaced and substantially radially extending outlet guide vanes 58. The gas turbine engine 10 may include a nacelle 60. The nacelle 60 may be fixed to the fan housing 56. The nacelle 60 may include one or more sections that at least partially surround the fan section 12, the fan housing 56, and / or the core engine 14. For example, the nacelle 60 may include a front shroud, a fan shroud, an engine shroud, a thrust reverser, etc. The inward portion of the fan housing 56 and / or the nacelle 60 may circumferentially surround the outer portion of the core engine 14. The inward portion of the fan housing 56 and / or the nacelle 60 may define a bypass passage 62. The bypass passage 62 may be arranged in a ring between the outer portion of the core engine 14 and the inward portion of the fan casing 56 and / or the nacelle 60 surrounding the outer portion of the core engine 14.

[0033] During operation of the gas turbine engine 10, inlet airflow 64 enters the gas turbine engine 10 through inlet 66 defined by nacelle 60 (such as by the front shroud of nacelle 60). Inlet airflow 64 passes through multiple fan blades 18. Inlet airflow 64 is split into core airflow 68, which flows into and passes through core airflow path 36 of core engine 14, and bypass airflow 70, which flows through bypass passage 62. Core airflow 68 is compressed by compressor section 26. The pressurized air from compressor section 26 flows downstream to combustor section 28, where fuel is introduced to produce combustion gases 72. Combustion gases 72 exit combustor section 28 and flow through turbine section 30, generating torque that rotates compressor section 26 to support combustion and also rotates fan section 12. Rotation of fan section 12 causes bypass airflow 70 to flow through bypass passage 62, thereby generating propulsive thrust. Combustion gases 72 exiting from exhaust nozzle 34 generate additional thrust.

[0034] refer to Figure 1 The various features and properties of the gas turbine engine 10 described herein are provided by way of example only and are not intended to be limiting. In fact, this disclosure can be implemented for any turbine engine, including those turbine engines that have properties or features that differ from the gas turbine engine 10 described herein in one or more respects.

[0035] Still referencing Figure 1The gas turbine engine 10 includes sealing assemblies at multiple locations throughout the gas turbine engine 10, any one or more of which can be constructed according to this disclosure. The sealing assemblies of this disclosure can be located at any location within the gas turbine engine 10, including interfaces with rotating portions of the gas turbine engine 10, such as interfaces with rotating portions of the core engine 14 or spools. For example, the sealing assembly can be included at an interface with a portion of the low-pressure spool 52 and / or with an interface with the high-pressure spool 50. In some embodiments, the sealing assembly can be included at an interface between a spool (such as the low-pressure spool 52 or the high-pressure spool 50) and a stationary portion of the core engine 14.

[0036] Alternatively or additionally, a sealing assembly may be included at the interface between the low-pressure spool 52 and the high-pressure spool 50. Alternatively or additionally, a sealing assembly may be included at the interface between the stationary portion of the core engine 14 and the low-pressure spool 48 or the high-pressure spool 46, and / or at the interface between the low-pressure spool 48 and the high-pressure spool 46.

[0037] As an example, Figure 1 Some exemplary locations of the sealing assembly are shown. As an example, the sealing assembly may be located at or near the bearing chamber 74. A sealing assembly located at or near the bearing chamber 74 may sometimes be referred to as a bearing chamber seal. Such a bearing chamber seal may be configured to prevent airflow, such as core airflow 68, from entering the bearing chamber 74 of the gas turbine engine 10, such as the bearing chamber 74 located at the interface between the low-pressure shaft 48 and the high-pressure shaft 46.

[0038] As another example, the sealing assembly may be located at or near the compressor section 26 of the gas turbine engine 10. In some embodiments, the sealing assembly may be located at or near, for example, the compressor discharge port 76 of the high-pressure compressor 40. A sealing assembly located at or near the compressor discharge port 76 may sometimes be referred to as a compressor discharge pressure seal. Such a compressor discharge pressure seal may be configured to maintain pressure downstream of the compressor section 26 and / or provide bearing thrust balance.

[0039] Alternatively or additionally, the sealing assembly may be located between adjacent compressor stages 78 of compressor section 26. The sealing assembly located between adjacent compressor stages 78 may sometimes be referred to as an interstage compressor seal. Such an interstage compressor seal may be configured to restrict air recirculation within compressor section 26.

[0040] As another example, the sealing assembly may be located at or near the turbine section 30 of the gas turbine engine 10. In some embodiments, the sealing assembly may be located near one or both inlets 80 of the high-pressure turbine 42. Additionally or alternatively, the sealing assembly may be located near one or both inlets 82 of the low-pressure turbine 44. The sealing assembly located at or near inlets 80 or 82 may sometimes be referred to as a front turbine seal. Such a front turbine seal may be configured to receive high-pressure cooling air for the high-pressure turbine 42 and / or the low-pressure turbine 44, such as for its turbine disk and turbine blades.

[0041] Additionally or alternatively, the sealing assembly may be located at or near one or more turbine disk edges 84. A sealing assembly located at or near turbine disk edges 84 may sometimes be referred to as a turbine disk edge seal. Such a turbine disk edge seal may be configured to inhibit the intake of hot gases into the disk edge region.

[0042] Alternatively or additionally, the sealing assembly may be located between adjacent turbine stages 86 of the turbine section 30. The sealing assembly located between adjacent turbine stages 86 may sometimes be referred to as an inter-stage seal. Such an inter-stage seal may be configured to restrict air recirculation within the turbine section 30.

[0043] According to this disclosure, sealing assemblies can be constructed at any one or more locations in these or other locations of the gas turbine engine 10. Additionally or alternatively, without departing from the scope of this disclosure, the gas turbine engine 10 may include the sealing assemblies of this disclosure at one or more other locations of the gas turbine engine 10. The sealing assemblies of this disclosure can also be used in other rotating machines. (See also...) Figure 1 The gas turbine engine 10 described herein is provided by way of example only and is not intended to be limiting. The sealing components disclosed herein may be included in any rotating machine, such as the gas turbine engine 10.

[0044] Figure 2 An embodiment of a suction surface sealing assembly (hereinafter referred to as "sealing assembly 100") according to at least one embodiment of the present disclosure is shown. Figure 1 A cross-sectional view of a portion of the core engine 14 is shown. The sealing assembly 100 is a film-riding face seal that forms a seal between a first pressure chamber 102 (also referred to as the outer side or outer volume) and a second pressure chamber 104 (also referred to as the inner side or inner volume) via high-pressure fluid. Figure 2In some embodiments, the first pressure chamber 102 is pressurized with a higher fluid pressure than the second pressure chamber 104. While the description herein focuses on the first pressure chamber 102 having a higher pressure than the second pressure chamber 104, not all embodiments are limited in this manner. For example, one or more embodiments may have a higher fluid pressure in the second pressure chamber 104 and a lower fluid pressure in the first pressure chamber 102. The fluid may be from the gas turbine engine 10 ( Figure 1 The core engine 14 contains compressed air or other gases, such as, but not limited to, combustion gases.

[0045] exist Figure 2 In the illustrated embodiment, the sealing assembly 100 is located on the rotating component 106 (e.g., but not limited to the high-pressure shaft 46 or the low-pressure shaft 48, such as...) Figure 1 A fluid seal is formed between the stationary component 108 of the core engine 14 and the component shown. The stationary component 108 is in Figure 2 The shapes shown are schematic and may differ from those shown. It should be understood that... Figure 2 A portion of the rotating component 106 and a portion of the stationary component 108 can be seen. The rotating component 106 rotates about or around a rotation axis 110, such as the longitudinal centerline 22 of the gas turbine engine 10. Figure 1 The rotating component 106 rotates in and out of the page plane along a rotational or circumferential direction “C”. The component shown in the cross-sectional view herein may extend entirely around the axis of rotation 110, or it may be a curved segment of several segments that, when combined, extend around the axis of rotation 110.

[0046] In an exemplary embodiment, the sealing assembly 100 includes a stationary arm 112 coupled to the stationary member 108. Optionally, the stationary arm 112 may be part of the stationary member 108 (e.g., an extension of the stationary member 108), such that the stationary arm 112 also represents the stationary member 108.

[0047] like Figure 2 As shown, the sealing assembly 100 includes a sealing body 114. The sealing body 114 includes or defines a crossbar portion 116 and a sealing arm portion 118. The sealing arm portion 118 at least partially defines a sealing surface 120. A stationary arm 112 engages with the crossbar portion 116 such that the sealing arm portion 118 and the sealing surface 120 are axially movable relative to an axial direction (A) toward or away from the rotating component 106. The axial direction A is along or parallel to the axis of rotation 110.

[0048] The elastic member 122 is connected to both the stationary arm 112 and the sealing body 114. Figure 2In the exemplary embodiment shown, one end of the elastic member 122 is connected to the stationary arm 112, and the second end is connected to the crossbar portion 116. The elastic member 122 may include a spring or a bellows. The elastic member 122 applies a force to the seal 114 to hold or bias the sealing surface 120 toward the stationary arm 112 or the stationary member 108 and away from the sealing surface 124 of the rotating member 106. The stationary arm 112 and the seal 114 may be formed as loops extending about the axis of rotation 110. Each of the stationary arm 112 and the seal 114 may be a continuous loop or may be formed of segmented portions, each segment extending partially about the axis of rotation 110.

[0049] The seal 114 includes or defines a fluid supply passage 126 that extends and passes through at least a portion of the seal 114. Figure 2 In the exemplary embodiment shown, the fluid supply passage 126 includes an inlet 128 oriented radially inward toward the stationary arm 112 relative to the radial direction R. A first radial portion 130 of the fluid supply passage 126 extends from the inlet 128 in the radial direction R within the crossbar portion 116 to a first axial portion 132 of the fluid supply passage 126. The first axial portion 132 extends in the axial direction A within the crossbar portion 116 toward the sealing arm portion 118 of the seal body 114. A second radial portion 134 of the fluid supply passage 126 extends radially inward from the first axial portion 132 in the radial direction R within the sealing arm portion 118. The second axial portion 136 of the fluid supply passage 126 extends in the axial direction A from the second radial portion to one or more supply ports 138 or outlets defined along the sealing surface 120. The fluid supply passage 126 provides or defines a continuous flow path through the seal body 114 between the inlet 128 and one or more supply ports 138.

[0050] In an exemplary embodiment, the sealing assembly 100 may further include a gas chamber seal 140. Figure 2 In the illustrated embodiment, the chamber seal 140 may be disposed between a portion of the sealing body 114 and a portion of the stationary member 108, thereby forming a seal between them. The chamber seal 140 may be a piston seal. Figure 2In the illustrated embodiment, the outer surface 142 of the chamber seal 140, the stationary component 108, and the stationary arm 112 at least partially define a third pressure chamber 144 therebetween. The third pressure chamber 144 receives high-pressure fluid 146 from a high-pressure fluid source 148 of the core engine 14. For example, the high-pressure fluid source 148 may include one or more of a high-pressure compressor 40 and a high-pressure turbine 42. The fluid 146 is supplied to the third pressure chamber at a pressure greater than that of both the first and second pressure chambers 102 and 104. The third pressure chamber 144 is in fluid communication with the inlet 128 of a fluid supply passage 126. In this configuration, the fluid supply passage 126 defines a continuous flow path from the third pressure chamber 144 to one or more supply ports 138.

[0051] In operation, the resilient member 122 pulls or otherwise biases the seal 114, particularly the sealing surface 120, toward the stationary member 108 and away from the sealing surface 124 of the rotating member 106. Fluid pressure from the first pressure chamber 102 can push or force the seal 114, particularly the sealing surface 120, toward the sealing surface 124 of the rotating member 106 (e.g., in the axial direction A, opposite to the direction in which the resilient member 122 pulls the seal 114), because an increased fluid pressure is created in the first pressure chamber 102, which is higher than the fluid pressure in the second pressure chamber 104.

[0052] As the sealing body 114 moves toward the rotating component 106, the main teeth 150 of the rotating component 106 move closer to the secondary sealing surface 152 of the sealing body 114, thereby reducing the axial clearance 154 through which fluid can move from the first pressure chamber 102 to the second pressure chamber 104. The fluid allowed to pass through the axial clearance forms a diaphragm bearing or seal between the main teeth 150 and the secondary sealing surface 152 of the sealing body 114. This bearing or seal can prevent or reduce fluid leakage from the first pressure chamber 102, which operates at a higher fluid pressure, to the second pressure chamber 104, which operates at a lower pressure than the first pressure chamber.

[0053] Fluid 146 flows from the third pressure chamber 144 into the fluid supply passage 126 via inlet 128, passes through the fluid supply passage 126, and flows out through one or more supply ports 138, entering the fluid cavity 156 defined between the sealing surface 120 of the sealing body 114 and the sealing surface 124 of the rotating component 106. The fluid 146 forms an axial fluid film bearing 158 between the sealing surface 120 of the sealing body 114 and the sealing surface 124 of the rotating component 106. The axial thickness of this axial fluid film bearing 158 is... Figure 1The figures are shown in enlarged dimensions. In one embodiment, the axial thickness can be approximately three to six mils. Alternatively, the thickness can be less than three mils or greater than six mils. The axial separation between the secondary sealing surface 152 of the seal body 114 and the main teeth 150 can be reduced, thereby forming a seal between the seal body 114 and the rotating component 106 at the interface between the secondary sealing surface 152 and the main teeth 150.

[0054] Figure 3 A cross-sectional view of another embodiment of the suction surface sealing assembly according to at least one embodiment of the present disclosure is shown, hereinafter referred to as "sealing assembly 200". Figure 3 As shown, the suction surface sealing assembly 200 has a... Figure 2 The sealing assembly 100 shown is similar to other components, and these components have similar markings. Figure 2 The sealing component 100 is the same as that in the middle. Figure 3 The sealing assembly 200 shown is a membrane bonding surface seal that forms a seal between the first pressure chamber 102 and the second pressure chamber 104 via a high-pressure fluid.

[0055] exist Figure 3 In the illustrated embodiment, the first pressure chamber 102 is pressurized with a higher fluid pressure than the second pressure chamber 104. While the description herein focuses on the first pressure chamber 102 having a higher pressure than the second pressure chamber 104, not all embodiments are limited in this manner. For example, one or more embodiments may have a higher fluid pressure in the second pressure chamber 104 and a lower fluid pressure in the first pressure chamber 102. The fluid may be compressed air or from the core engine 14 of the gas turbine engine 10. Figure 1 Other gases.

[0056] like Figure 3 As shown, the sealing assembly 200 is located in the rotating component 106 (e.g., but not limited to the high-pressure shaft 46 or the low-pressure shaft 48). Figure 1 A fluid seal is formed between the stationary component 108 of the core engine 14 and the sealing assembly 200. The sealing assembly 200 includes a stationary arm 112 coupled to the stationary component 108. Optionally, the stationary arm 112 may be part of the stationary component 108 (e.g., an extension of the stationary component 108), such that the stationary arm 112 also represents the stationary component 108.

[0057] like Figure 3As shown, the sealing assembly 200 includes a sealing body 114. The sealing body 114 includes or defines a crossbar portion 116 and a sealing arm portion 118. The sealing arm portion 118 at least partially defines a sealing surface 120. A stationary arm 112 engages with the crossbar portion 116 such that the sealing arm portion 118 and the sealing surface 120 are axially movable relative to an axial direction A toward or away from the rotating component 106. The axial direction A is along or parallel to the axis of rotation 110.

[0058] The elastic member 122 can be connected to both the stationary arm 112 and the sealing body 114. Figure 3 In the exemplary embodiment shown, one end of the elastic member 122 is connected to the stationary arm 112, and the second end is connected to the crossbar portion 116. The elastic member 122 may include a spring or a bellows. The elastic member 122 applies a force to the seal 114 to hold or bias the sealing surface 120 toward the stationary arm 112 or the stationary member 108 and away from the sealing surface 124 of the rotating member 106. The stationary arm 112 and the seal 114 may be formed as loops extending about the axis of rotation 110. Each of the stationary arm 112 and the seal 114 may be a continuous loop or may be formed of segmented portions, each segment extending partially about the axis of rotation 110.

[0059] like Figure 3 As shown, the seal 114 includes or defines a fluid supply passage 126 that extends and passes through at least a portion of the seal 114. Figure 3 In the exemplary embodiment shown, inlet 128 is disposed along the radially outer surface 160 of seal 114 and oriented radially outward relative to the radial direction R away from stationary arm 112. For example, inlet 128 may be disposed at or near a portion of sealing arm portion 118 of seal 114. Fluid supply passage 126 extends radially inward from inlet 128 toward axis of rotation 110 to one or more supply ports 138 defined along sealing surface 120. Fluid supply passage 126 provides or defines a continuous flow path through seal 114 to sealing surface 120 between inlet 128 and one or more supply ports 138.

[0060] like Figure 3 As shown, the sealing assembly 200 also includes a chamber seal 140. The chamber seal 140 may be disposed between the radially outer surface 160 of the sealing body 114, oriented radially outward from the axis of rotation 110, and a portion of the stationary member 108, thereby forming a seal between them. This portion of the stationary member 108 may include a stationary extension arm 162 coupled to or integrally formed (e.g., formed as a single body) with the stationary member 108. The stationary extension arm 162 is disposed radially outside the radially outer surface 160 of the sealing body 114. The chamber seal 140 may slidably engage with the stationary extension arm 162. Figure 3 In the illustrated configuration, the chamber seal 140 may be disposed near the end portion 164 of the seal body 114. The end portion 164 is located away from the stationary component 108. In an exemplary embodiment, the chamber seal 140 may be a piston seal. Figure 3 In the illustrated embodiment, the air chamber seal 140, the radial outer surface 160 of the seal body 114, the stationary arm 112, and the stationary extension arm 162 at least partially define the third pressure air chamber 144.

[0061] In operation, the third pressure chamber 144 receives high-pressure fluid 146 from the high-pressure fluid source 148 of the core engine 14. For example, the high-pressure fluid source 148 may include... Figure 1 One or more of the high-pressure compressor 40 and high-pressure turbine 42 shown. Fluid 146 is supplied to the third pressure chamber 144 at a pressure greater than that of the first pressure chamber 102 and the second pressure chamber 104. The third pressure chamber 144 is in fluid communication with the inlet 128 of the fluid supply passage 126.

[0062] The resilient member 122 pulls or otherwise biases the seal 114, particularly the sealing surface 120, toward the stationary member 108 and away from the sealing surface 124 of the rotating member 106. Fluid pressure from the third pressure chamber 144 can push or force the seal 114, particularly the sealing surface 120, toward the sealing surface 124 of the rotating member 106 (e.g., in the axial direction A, opposite to the direction in which the resilient member 122 pulls the seal 114), because an increased fluid pressure is formed in the third pressure chamber 144, which is higher than the fluid pressure in the second pressure chamber 104 and the first pressure chamber 102.

[0063] As the sealing body 114 moves toward the rotating component 106, the main teeth 150 of the rotating component 106 move closer to the secondary sealing surface 152 of the sealing body 114, thereby reducing the axial clearance 154 through which fluid can move from the first pressure chamber 102 to the second pressure chamber 104. The fluid allowed to pass through the axial clearance 154 forms a diaphragm bearing or seal between the main teeth 150 and the secondary sealing surface 152 of the sealing body 114. This bearing or seal can prevent or reduce fluid leakage from the first pressure chamber 102, which operates at a higher fluid pressure, to the second pressure chamber 104, which operates at a lower pressure than the first pressure chamber.

[0064] Fluid 146 flows from the third pressure chamber 144 into the fluid supply passage 126 via inlet 128, passes through the fluid supply passage 26, and exits through one or more supply ports 138, entering the fluid cavity 156 defined between the sealing surface 120 of the seal body 114 and the sealing surface 124 of the rotating component 106. The fluid 146 forms an axial fluid film bearing 158 between the sealing surface 120 of the seal body 114 and the sealing surface 124 of the rotating component 106. In one embodiment, the axial thickness of the axial fluid film bearing 158 can be about three to six mils. Alternatively, the thickness can be less than three mils or greater than six mils. The axial separation between the secondary sealing surface 152 of the seal body 114 and the main tooth 150 can be reduced, thereby forming a seal between the seal body 114 and the rotating component 106 at the interface between the secondary sealing surface 152 and the main tooth 150.

[0065] Figure 4 A cross-sectional view of another embodiment of the suction surface sealing assembly according to at least one embodiment of the present disclosure is shown, hereinafter referred to as "sealing assembly 300". Figure 4 The embodiments have the same Figure 2 The sealing assembly 100 shown contains similar components, which are similarly labeled. Furthermore, embodiments of the sealing assembly 300 are similar to... Figure 3 The embodiment of the sealing assembly 200 shown differs from the location of the air chamber seal 140 and the inlet 128 of the fluid supply channel 126.

[0066] like Figure 4 As shown, the seal 114 includes or defines a fluid supply passage 126 that extends and passes through at least a portion of the seal 114. For example, the fluid supply passage 126 extends in the axial direction A through the crossbar portion 116 and in the radial direction R within the sealing arm portion 118 of the seal 114. An inlet 128 is defined along a radial extension of a portion of the crossbar portion 116 of the seal 114 or by a radial sidewall 165. The fluid supply passage 126 provides or defines a continuous flow path through the seal 114 to the sealing surface 120 between the inlet 128 and one or more supply ports 138.

[0067] A gas chamber seal 140 is disposed between the radially outer surface 160 of a seal body 114 oriented radially outward from the axis of rotation 110 and a portion of a stationary member 108, thereby forming a seal therebetween. Figure 4 In the illustrated embodiment, this portion of the stationary component 108 includes a stationary extension arm 162 that is coupled to or integrally formed with the stationary component 108 (e.g., formed as a single body). The stationary extension arm 162 is disposed radially outside the radially outer surface 160 of the seal 114. The air chamber seal 140 can slidably engage with the stationary extension arm 162. Figure 4In the illustrated configuration, the chamber seal 140 is disposed along the crossbar portion 116 of the seal body 114. The chamber seal 140 may be a piston seal. Figure 4 In the illustrated embodiment, the air chamber seal 140, the radial outer surface 160 of the seal body 114, the stationary arm 112, and the stationary extension arm 162 at least partially define the third pressure air chamber 144.

[0068] In operation, the third pressure chamber 144 receives high-pressure fluid 146 from the high-pressure fluid source 148 of the core engine 14. For example, the high-pressure fluid source 148 may include... Figure 1 One or more of the high-pressure compressor 40 and high-pressure turbine 42 shown. Fluid 146 is supplied to the third pressure chamber 144 at a pressure greater than that of the first pressure chamber 102 and the second pressure chamber 104. The third pressure chamber 144 is in fluid communication with the inlet 128 of the fluid supply passage 126.

[0069] The resilient member 122 pulls or otherwise biases the seal 114, particularly the sealing surface 120, toward the stationary member 108 and away from the sealing surface 124 of the rotating member 106. Fluid pressure from the third pressure chamber 144 can push or force the seal 114, particularly the sealing surface 120, toward the sealing surface 124 of the rotating member 106 (e.g., in the axial direction A, opposite to the direction in which the resilient member 122 pulls the seal 114), because an increased fluid pressure is formed in the third pressure chamber 144, which is higher than the fluid pressure in the second pressure chamber 104 and the first pressure chamber 102.

[0070] As the sealing body 114 moves toward the rotating component 106, the main teeth 150 of the rotating component 106 move closer to the secondary sealing surface 152 of the sealing body 114, thereby reducing the axial clearance 154 through which fluid can move from the first pressure chamber 102 to the second pressure chamber 104. The fluid allowed to pass through the axial clearance 154 forms a diaphragm bearing or seal between the main teeth 150 and the secondary sealing surface 152 of the sealing body 114. This bearing or seal can prevent or reduce fluid leakage from the first pressure chamber 102, which operates at a higher fluid pressure, to the second pressure chamber 104, which operates at a lower pressure than the first pressure chamber.

[0071] Fluid 146 flows from the third pressure chamber 144 into the fluid supply passage 126 via inlet 128, passes through the fluid supply passage 26, and exits through one or more supply ports 138, entering the fluid cavity 156 defined between the sealing surface 120 of the seal body 114 and the sealing surface 124 of the rotating component 106. The fluid 146 forms an axial fluid film bearing 158 between the sealing surface 120 of the seal body 114 and the sealing surface 124 of the rotating component 106. In one embodiment, the axial thickness of the axial fluid film bearing 158 can be about three to six mils. Alternatively, the thickness can be less than three mils or greater than six mils. The axial separation between the secondary sealing surface 152 of the seal body 114 and the main tooth 150 can be reduced, thereby forming a seal between the seal body 114 and the rotating component 106 at the interface between the secondary sealing surface 152 and the main tooth 150.

[0072] Figure 5 A cross-sectional view of another embodiment of the suction surface sealing assembly according to at least one embodiment of the present disclosure is shown, hereinafter referred to as "sealing assembly 400". Figure 5 The sealing assembly 400 shown has a connection with Figure 2 Similar components to the sealing assembly 100 shown are similarly labeled. Like the sealing assembly 100, the sealing assembly 400 is a membrane-bonded seal that forms a seal between a first pressure chamber 102 (also referred to as the outer side or volume) and a second pressure chamber 104 (also referred to as the inner side or volume) via high-pressure fluid.

[0073] exist Figure 5 In some embodiments, the first pressure chamber 102 is pressurized with a higher fluid pressure than the second pressure chamber 104. While the description herein focuses on the first pressure chamber 102 having a higher pressure than the second pressure chamber 104, not all embodiments are limited in this manner. For example, one or more embodiments may have a higher fluid pressure in the second pressure chamber 104 and a lower fluid pressure in the first pressure chamber 102. The fluid may be compressed air or fluid from the gas turbine engine 10 ( Figure 1 Other gases in the core engine 14.

[0074] like Figure 5 As shown, the sealing assembly 400 is located in the rotating component 106 (e.g., but not limited to the high-pressure shaft 46 or the low-pressure shaft 48, such as...). Figure 1 A fluid seal is formed between the stationary component 108 of the core engine 14 and the component shown. The stationary component 108 is in Figure 5 The diagram is schematic and may have a different shape or appearance than shown. A portion of the rotating component 106 and a portion of the stationary component 108 are shown. Figure 5As can be seen, the rotating component 106 rotates about or around a rotation axis 110, such as the longitudinal centerline 22 of the gas turbine engine 10. Figure 1 The rotating component 106 rotates in and out of the page plane along a rotational or circumferential direction “C”. The component shown in the cross-sectional view herein may extend entirely around the axis of rotation 110, or it may be a curved segment of several segments that, when combined, extend around the axis of rotation 110.

[0075] The sealing assembly 400 includes a stationary arm 112 coupled to the stationary member 108. Optionally, the stationary arm 112 may be part of the stationary member 108 (e.g., an extension of the stationary member 108), such that the stationary arm 112 also represents the stationary member 108. Figure 5 As shown, the sealing assembly 400 includes a sealing body 114. The sealing body 114 includes or defines a crossbar portion 116 and a sealing arm portion 118. The sealing arm portion 118 at least partially defines a sealing surface 120. A stationary arm 112 engages with the crossbar portion 116 such that the sealing arm portion 118 and the sealing surface 120 are axially movable relative to an axial direction A toward or away from the rotating component 106. The axial direction A is along or parallel to the axis of rotation 110.

[0076] The elastic member 122 can be connected to both the stationary arm 112 and the sealing body 114. Figure 5 In the exemplary embodiment shown, one end of the elastic member 122 is connected to the stationary arm 112, and the second end is connected to the crossbar portion 116. The elastic member 122 may include a spring or a bellows. The elastic member 122 applies a force to the seal 114 to hold or bias the sealing surface 120 toward the stationary arm 112 or the stationary member 108 and away from the sealing surface 124 of the rotating member 106. The stationary arm 112 and the seal 114 may be formed as loops extending about the axis of rotation 110. Each of the stationary arm 112 and the seal 114 may be a continuous loop or may be formed of segmented portions, each segment extending partially about the axis of rotation 110.

[0077] like Figure 5 As shown, the seal 114 includes or defines a fluid supply passage 126 that extends and passes through at least a portion of the seal 114. Figure 5In the illustrated embodiment, the fluid supply passage 126 is at least partially defined by a pipe 166 extending from the seal 114 and into a high-pressure fluid source 148, or at least partially defined by a stationary component 108 and in fluid communication with the high-pressure fluid source 48, a chamber 168. The pipe 166 defines an inlet 128 for the fluid supply passage 126. The fluid supply passage 126, including the pipe 166, provides or defines a continuous flow path from the high-pressure fluid source 148, through the seal 114 to one or more supply ports 138, and to the sealing surface 120.

[0078] like Figure 5 As shown, the tube 166 can be slidably engaged with one or more chamber seals 170, which provide a seal between the outer surface of the tube 166 and the high-pressure fluid source 148, the stationary component 108, or the chamber 168. In an exemplary embodiment, the one or more chamber seals 170 may be piston seals. In the illustrated embodiment, a third pressure chamber 144 is at least partially defined by the chamber 168.

[0079] During operation, the third pressure chamber 144 or chamber 168 receives high-pressure fluid 146 from the high-pressure fluid source 148 of the core engine 14. For example, the high-pressure fluid source 148 may include... Figure 1 One or more of the high-pressure compressor 40 and high-pressure turbine 42 shown. Fluid 146 is supplied to a third pressure chamber 144 or chamber 168 at a pressure greater than that of the first pressure chamber 102 and the second pressure chamber 104. The third pressure chamber 144 or chamber 168 is in fluid communication with pipe 166 and fluid supply passage 126 via inlet 128.

[0080] The resilient member 122 pulls or otherwise biases the seal 114, particularly the sealing surface 120, toward the stationary member 108 and away from the sealing surface 124 of the rotating member 106. Fluid pressure from the third pressure chamber 144 or chamber 168 can push or force the seal 114, particularly the sealing surface 120, toward the sealing surface 124 of the rotating member 106 (e.g., in the axial direction A, opposite to the direction in which the resilient member 122 pulls or otherwise biases the seal 114), because an increased fluid pressure is formed in the third pressure chamber 144 or chamber 168, which is higher than the fluid pressure in the second pressure chamber 104 and the first pressure chamber 102.

[0081] As the sealing body 114 moves toward the rotating component 106, the main teeth 150 of the rotating component 106 move closer to the secondary sealing surface 152 of the sealing body 114, thereby reducing the axial clearance 154 through which fluid can move from the first pressure chamber 102 to the second pressure chamber 104. The fluid allowed to pass through the axial clearance forms a diaphragm bearing or seal between the main teeth 150 and the secondary sealing surface 152 of the sealing body 114. This bearing or seal can prevent or reduce fluid leakage from the first pressure chamber 102, which operates at a higher fluid pressure, to the second pressure chamber 104, which operates at a lower pressure than the first pressure chamber.

[0082] The fluid pressure of fluid 146 from high-pressure fluid source 148 is higher than the fluid pressure in the first pressure chamber 102 and the second pressure chamber 104. Fluid 146 flows from the third pressure chamber 144 into the fluid supply passage 126 via inlet 128 and pipe 166, passes through the fluid supply passage 26, and exits through one or more supply ports 138, entering a fluid cavity 156 defined between the sealing surface 120 of the seal body 114 and the sealing surface 124 of the rotating component 106. Fluid 146 forms an axial fluid film bearing 158 between the sealing surface 120 of the seal body 114 and the sealing surface 124 of the rotating component 106. In one embodiment, the axial thickness of the axial fluid film bearing 158 can be about three to six mils. Alternatively, the thickness can be less than three mils or greater than six mils. The axial separation between the secondary sealing surface 152 and the main tooth 150 of the sealing body 114 can be reduced, thereby forming a seal between the sealing body 114 and the rotating component 106 at the interface between the secondary sealing surface 152 and the main tooth 150.

[0083] Figure 6 A cross-sectional view of another embodiment of a suction surface sealing assembly according to at least one embodiment of the present disclosure is shown, hereinafter referred to as "sealing assembly 500". Figure 6 The sealing assembly 500 shown has a similar Figure 2 Similar components to the shown sealing assembly 100 are similarly labeled. Like sealing assembly 100, sealing assembly 500 is a membrane-bonded seal that forms a seal between a first pressure chamber 102 and a second pressure chamber 104 via high-pressure fluid. Figure 6 In some embodiments, the first pressure chamber 102 is pressurized with a higher fluid pressure than the second pressure chamber 104. While the description herein focuses on the first pressure chamber 102 having a higher pressure than the second pressure chamber 104, not all embodiments are limited in this manner. For example, one or more embodiments may have a higher fluid pressure in the second pressure chamber 104 and a lower fluid pressure in the first pressure chamber 102. The fluid may be compressed air or from the core engine 14 of the gas turbine engine 10. Figure 1Other gases.

[0084] like Figure 6 As shown, the sealing assembly 500 is located in the rotating component 106 (e.g., but not limited to the high-pressure shaft 46 or the low-pressure shaft 48). Figure 1 A fluid seal is formed between the stationary component 108 of the core engine 14 and the component shown. The stationary component 108 is in Figure 6 The diagram is shown schematically, and may have a different shape or appearance than that shown. Figure 6 Only a portion of the rotating component 106 and a portion of the stationary component 108 are visible. The rotating component 106 rotates about or around a rotation axis 110, such as the longitudinal centerline 22 of the gas turbine engine 10. Figure 1 The rotating component 106 rotates in and out of the page plane along a rotational or circumferential direction “C”. The component shown in the cross-sectional view herein may extend entirely around the axis of rotation 110, or it may be a curved segment of several segments that, when combined, extend around the axis of rotation 110.

[0085] like Figure 6 As shown, the sealing assembly 500 includes a stationary arm 112 coupled to the stationary member 108. Optionally, the stationary arm 112 may be part of the stationary member 108 (e.g., an extension of the stationary member 108), such that the stationary arm 112 also represents the stationary member 108.

[0086] The sealing assembly 500 includes a sealing body 114. The sealing body 114 includes or defines a crossbar portion 116 and a sealing arm portion 118. The sealing arm portion 118 at least partially defines a sealing surface 120. A stationary arm 112 engages with the crossbar portion 116 such that the sealing arm portion 118 and the sealing surface 120 are axially movable relative to an axial direction A toward or away from the rotating component 106. The axial direction A is along or parallel to the axis of rotation 110.

[0087] The elastic member 122 is connected to the stationary arm 112 and the sealing body 114. Figure 6 In the exemplary embodiment shown, one end of the elastic member 122 is connected to the stationary arm 112, and the second end is connected to the crossbar portion 116. The elastic member 122 may include a spring or a bellows. Figure 6 In the illustrated embodiment, the elastic member 122 is at least partially disposed within or surrounded by the inner pocket 172 defined at least partially by the seal 114.

[0088] The elastic member 122 applies force to the seal 114 to hold or bias the sealing surface 120 toward the stationary arm 112 or stationary member 108 and away from the sealing surface 124 of the rotating member 106. The stationary arm 112 and the seal 114 may be formed as loops extending about the axis of rotation 110. Each of the stationary arm 112 and the seal 114 may be a continuous loop or may be formed of segmented portions, each segment extending partially about the axis of rotation 110.

[0089] like Figure 6 As shown, the sealing body 114 includes or defines a fluid supply passage 126 that extends and passes through at least a portion of the sealing body 114. The fluid supply passage 126 includes an inlet 128 axially oriented relative to an axial direction A toward the resilient member 122. A first radial portion 130 of the fluid supply passage 126 extends radially in the crossbar portion 116 from the inlet 128 to a first axial portion 132 of the fluid supply passage 126. The first axial portion 132 extends radially in the crossbar portion 116 toward a sealing arm portion 118. A second radial portion 134 of the fluid supply passage 126 extends radially in the sealing arm portion 118 from the first axial portion 132 toward the rotating member 106. The second axial portion 136 of the fluid supply passage 126 extends radially in the second radial portion in the axial direction A to one or more supply ports 138 or outlets defined along the sealing surface 120. The fluid supply passage 126 provides or defines a continuous flow path through the seal 114 between the inlet 128 and one or more supply ports 138.

[0090] like Figure 6 As shown, the sealing assembly 500 may further include a chamber seal 140. In the illustrated embodiment, the chamber seal 140 is disposed between a portion of the sealing body 114 and a portion of the stationary arm 112, thereby forming a seal therebetween. In an exemplary embodiment, the chamber seal 140 may be a piston seal. In this embodiment, the chamber seal 140, the inner pocket 172 of the sealing body 114, and the stationary arm 112 at least partially define a third pressure chamber 144.

[0091] The third pressure chamber 144 receives high-pressure fluid 146 from a high-pressure fluid source 148 of the core engine 14 via a channel 174 defined within or at least partially by the stationary arm 112. The high-pressure fluid source 148 may include one or more of a high-pressure compressor 40 and a high-pressure turbine 42. The fluid 146 is supplied to the third pressure chamber at a pressure greater than that of both the first and second pressure chambers 102 and 104. The third pressure chamber 144 is in fluid communication with the inlet 128 of a fluid supply passage 126. In this configuration, the fluid supply passage 126 defines a continuous flow path from the third pressure chamber 144 to one or more supply ports 138.

[0092] In operation, the resilient member 122 pulls or otherwise biases the seal 114, particularly the sealing surface 120, toward the stationary member 108 and away from the sealing surface 124 of the rotating member 106. Fluid pressure from the first pressure chamber 102 can push or force the seal 114, particularly the sealing surface 120, toward the sealing surface 124 of the rotating member 106 (e.g., in the axial direction A, opposite to the direction in which the resilient member 122 pulls the seal 114), because an increased fluid pressure is created in the first pressure chamber 102, which is higher than the fluid pressure in the second pressure chamber 104.

[0093] As the sealing body 114 moves toward the rotating component 106, the main teeth 150 of the rotating component 106 move closer to the secondary sealing surface 152 of the sealing body 114, thereby reducing the axial clearance 154 through which fluid can move from the first pressure chamber 102 to the second pressure chamber 104. The fluid allowed to pass through the axial clearance 154 forms a diaphragm bearing or seal between the main teeth 150 and the secondary sealing surface 152 of the sealing body 114. This bearing or seal can prevent or reduce fluid leakage from the first pressure chamber 102, which operates at a higher fluid pressure, to the second pressure chamber 104, which operates at a lower pressure than the first pressure chamber.

[0094] Fluid 146 from high-pressure fluid source 148 flows through channel 174 and into third pressure chamber 144 at a pressure higher than the fluid pressure in first pressure chamber 102 and second pressure chamber 104. Fluid 146 flows from third pressure chamber 144 into fluid supply channel 126 via inlet 128, passes through fluid supply channel 26, and exits through one or more supply ports 138, entering fluid cavity 156 defined between sealing surface 120 of seal body 114 and sealing surface 124 of rotating component 106. Fluid 146 forms axial fluid film bearing 158 between sealing surface 120 of seal body 114 and sealing surface 124 of rotating component 106. In one embodiment, the axial thickness of the axial fluid film bearing 158 can be about three to six mils. Alternatively, the thickness can be less than three mils or greater than six mils. The axial separation between the secondary sealing surface 152 and the main tooth 150 of the sealing body 114 can be reduced, thereby forming a seal between the sealing body 114 and the rotating component 106 at the interface between the secondary sealing surface 152 and the main tooth 150.

[0095] Figure 7 A cross-sectional view of another embodiment of a suction surface sealing assembly according to at least one embodiment of the present disclosure is shown, hereinafter referred to as "sealing assembly 600". Figure 7 The sealing assembly 600 shown has a connection with Figure 2 Similar components to the shown sealing assembly 100 are similarly labeled. Like sealing assembly 100, sealing assembly 600 is a membrane-bonded seal that forms a seal between a first pressure chamber 102 and a second pressure chamber 104 via high-pressure fluid. Figure 7 In some embodiments, the first pressure chamber 102 is pressurized with a higher fluid pressure than the second pressure chamber 104. While the description herein focuses on the first pressure chamber 102 having a higher pressure than the second pressure chamber 104, not all embodiments are limited in this manner. For example, one or more embodiments may have a higher fluid pressure in the second pressure chamber 104 and a lower fluid pressure in the first pressure chamber 102. The fluid may be compressed air or from the core engine 14 of the gas turbine engine 10. Figure 1 Other gases.

[0096] like Figure 7 As shown, the sealing assembly 600 is located in the rotating component 106 (e.g., but not limited to the high-pressure shaft 46 or the low-pressure shaft 48, such as...). Figure 1 A fluid seal is formed between the stationary component 108 of the core engine 14 and the component shown. The stationary component 108 is in Figure 7 The diagram is shown schematically, and may have a different shape or appearance than that shown. Figure 7Only a portion of the rotating component 106 and a portion of the stationary component 108 are visible. The rotating component 106 rotates about or around a rotation axis 110, such as the longitudinal centerline 22 of the gas turbine engine 10. Figure 1 The rotating component 106 rotates in and out of the page plane along a rotational or circumferential direction “C”. The component shown in the cross-sectional view of this document may extend entirely around the axis of rotation 110, or it may be a curved segment of several segments that, when combined, extend entirely around the axis of rotation 110.

[0097] like Figure 7 As shown, the sealing assembly 600 includes a stationary arm 112 coupled to the stationary member 108. Optionally, the stationary arm 112 may be part of the stationary member 108 (e.g., an extension of the stationary member 108), such that the stationary arm 112 also represents the stationary member 108.

[0098] The sealing assembly 600 includes a sealing body 114. The sealing body 114 includes or defines a crossbar portion 116 and a sealing arm portion 118. The sealing arm portion 118 at least partially defines a sealing surface 120. A stationary arm 112 engages with the crossbar portion 116 such that the sealing arm portion 118 and the sealing surface 120 are axially movable relative to an axial direction A toward or away from the rotating component 106. The axial direction A is along or parallel to the axis of rotation 110.

[0099] The elastic member 122 of the sealing assembly 600 is disposed between the radial outer surface 160 of the sealing body 114 and the stationary extension arm 162, and extends in the axial direction A. One end of the elastic member 122 of the sealing assembly 600 is connected to the stationary extension arm 162, and the other end is connected to the sealing body 114. The elastic member 122 may include a spring or a bellows.

[0100] The elastic member 122 applies force to the seal 114 to hold or bias the sealing surface 120 toward the stationary extension arm 162 or the stationary member 108 and away from the sealing surface 124 of the rotating member 106. The stationary arm 112, the stationary extension arm 162, and the seal 114 may be formed as a loop extending about the axis of rotation 110. Each of the stationary arm 112, the stationary extension arm 162, and the seal 114 may be a continuous loop or may be formed of segmented portions, each segment extending partially about the axis of rotation 110.

[0101] like Figure 7 As shown, the sealing body 114 of the sealing assembly 600 defines an inner pocket 172. More specifically, the inner pocket 172 is defined between the crossbar portion 116 and the radial inner arm portion 176 of the sealing body 114.

[0102] like Figure 7As shown, the sealing body 114 of the sealing assembly 600 includes or defines a fluid supply passage 126 that extends and passes through at least a portion of the sealing body 114. Figure 7 In the exemplary embodiment shown, the fluid supply passage 126 includes an inlet 128 defined along a radial sidewall 178 and in fluid communication with the third pressure chamber 144 and the inner pocket 172. The fluid supply passage 126 extends within the sealing arm portion 118 toward the rotating member 106 and extends to one or more supply ports 138 or outlets defined along the sealing surface 120. The fluid supply passage 126 provides or defines a continuous flow path through the seal 114 between the inlet 128 and the one or more supply ports 138.

[0103] like Figure 7 As shown, the sealing assembly 600 may further include a chamber seal 140. In the illustrated embodiment, the chamber seal 140 is disposed between a portion of the sealing body 114, particularly the inner arm portion 176, and a portion of the stationary arm 112, thereby forming a seal therebetween. In an exemplary embodiment, the chamber seal 140 may be a piston seal. In this embodiment, the chamber seal 140, the inner pocket 172 of the sealing body 114, the stationary arm 112, the inner arm portion 176, and the stationary extension arm 162 at least partially define a third pressure chamber 144.

[0104] The third pressure chamber 144 receives high-pressure fluid 146 from a high-pressure fluid source 148 of the core engine 14. The high-pressure fluid source 148 may include one or more of a high-pressure compressor 40 and a high-pressure turbine 42. The fluid 146 is supplied to the third pressure chamber 144 at a pressure greater than that of the first pressure chamber 102 and the second pressure chamber 104. The third pressure chamber 144 is in fluid communication with the inlet 128 of a fluid supply passage 126. In this configuration, the fluid supply passage 126 defines a continuous flow path from the third pressure chamber 144 to one or more supply ports 138.

[0105] In operation, the resilient member 122 pulls or otherwise biases the seal 114, particularly the sealing surface 120, toward the stationary member 108 and away from the sealing surface 124 of the rotating member 106. Fluid pressure from the first pressure chamber 102 can push or force the seal 114, particularly the sealing surface 120, toward the sealing surface 124 of the rotating member 106 (e.g., in the axial direction A, opposite to the direction in which the resilient member 122 pulls the seal 114), because an increased fluid pressure is created in the first pressure chamber 102, which is higher than the fluid pressure in the second pressure chamber 104.

[0106] As the sealing body 114 moves toward the rotating component 106, the main teeth 150 of the rotating component 106 move closer to the secondary sealing surface 152 of the sealing body 114, thereby reducing the axial clearance 154 through which fluid can move from the first pressure chamber 102 to the second pressure chamber 104. The fluid allowed to pass through the axial clearance 154 forms a diaphragm bearing or seal between the main teeth 150 and the secondary sealing surface 152 of the sealing body 114. This bearing or seal can prevent or reduce fluid leakage from the first pressure chamber 102, which operates at a higher fluid pressure, to the second pressure chamber 104, which operates at a lower pressure than the first pressure chamber.

[0107] Fluid 146 from high-pressure fluid source 148 flows into third pressure chamber 144 at a pressure higher than the fluid pressure in first pressure chamber 102 and second pressure chamber 104. Fluid 146 flows from third pressure chamber 144 into fluid supply passage 126 via inlet 128, passes through fluid supply passage 26, and exits through one or more supply ports 138, entering fluid cavity 156 defined between sealing surface 120 of seal body 114 and sealing surface 124 of rotating component 106. Fluid 146 forms axial fluid film bearing 158 between sealing surface 120 of seal body 114 and sealing surface 124 of rotating component 106. In one embodiment, the axial thickness of the axial fluid film bearing 158 can be about three to six mils. Alternatively, the thickness can be less than three mils or greater than six mils. The axial separation between the secondary sealing surface 152 and the main tooth 150 of the sealing body 114 can be reduced, thereby forming a seal between the sealing body 114 and the rotating component 106 at the interface between the secondary sealing surface 152 and the main tooth 150.

[0108] Further details are provided through the following topics:

[0109] A suction surface sealing assembly includes: a rotating member defining a sealing surface; a stationary member; a sealing body defining a sealing surface and defining a fluid supply passage within the sealing body, wherein the fluid supply passage includes an inlet and one or more supply ports defined along the sealing surface, wherein the sealing body is movably coupled to the stationary member via an elastic member; a first pressure chamber defined radially outward from the sealing body; a second pressure chamber defined radially inward from the sealing body; and a chamber seal forming a seal between a portion of the sealing body and the stationary member. The chamber seal, the stationary member, and the sealing body at least partially define a third pressure chamber in fluid communication with a high-pressure fluid source, wherein the third pressure chamber is in fluid communication with the inlet of the fluid supply passage, and wherein the third pressure chamber is pressurized at a pressure higher than both the first and second pressure chambers.

[0110] The suction face sealing assembly according to the preceding clause or any of the foregoing clauses, wherein an axial clearance is defined between the sealing face and the sealing surface.

[0111] The suction face sealing assembly according to any of the preceding or foregoing clauses, wherein the sealing body defines a crossbar portion and a sealing arm portion.

[0112] According to any of the preceding or foregoing clauses, the suction face sealing assembly wherein the fluid supply passage extends axially within the crossbar portion of the seal body between the inlet and the one or more supply ports, and extends radially within the sealing arm portion of the seal body.

[0113] According to any of the preceding or foregoing clauses of the suction face sealing assembly, the stationary component includes a stationary extension arm, wherein the air chamber seal extends from the stationary extension arm to the radially outer surface of the seal body, and wherein the stationary extension arm at least partially defines the third pressure air chamber.

[0114] According to any of the preceding or foregoing clauses, the suction face sealing assembly wherein the inlet is defined along the radial outer surface of the seal.

[0115] A suction face sealing assembly according to any of the preceding or foregoing clauses, wherein the sealing body defines a radial sidewall, and wherein the inlet is defined along the radial sidewall.

[0116] According to any of the preceding or foregoing clauses of the suction face sealing assembly, the stationary component includes a stationary arm, the chamber seal extends from the stationary arm to the outer surface of the seal body, and the stationary arm at least partially defines the third pressure chamber.

[0117] According to any of the preceding or foregoing clauses, the suction face sealing assembly, wherein the seal body defines an inner pocket, wherein the inner pocket at least partially defines the third pressure chamber.

[0118] The suction face sealing assembly according to any of the preceding or foregoing clauses, wherein the inlet is defined within the inner pocket.

[0119] According to any of the preceding or foregoing clauses, the suction face sealing assembly, wherein the stationary arm defines a channel extending therein, wherein the channel defines a fluid passage between the high-pressure fluid source and the third pressure chamber.

[0120] The suction face sealing assembly according to any of the preceding or foregoing clauses, wherein the resilient member is disposed outside the inner pocket.

[0121] The suction face sealing assembly according to any prior clause or any of the foregoing clauses further includes a tube, wherein the tube extends from the seal body into the stationary member, wherein the tube at least partially defines the fluid supply passage including the inlet, and wherein the tube is in fluid communication with the high-pressure fluid source and the fluid supply passage.

[0122] According to any of the preceding or foregoing clauses, the suction surface sealing assembly wherein the air chamber seal is slidably engaged with the outer surface of the tube.

[0123] According to any of the preceding or foregoing clauses, the suction face sealing assembly, wherein the stationary member defines an air chamber therein, wherein the air chamber defines the third pressure air chamber.

[0124] According to any of the preceding or foregoing clauses, the suction surface sealing assembly, wherein the rotating component includes a primary tooth, and the sealing body defines a secondary sealing surface adjacent to the primary tooth.

[0125] The suction face sealing assembly according to any of the preceding or foregoing clauses, wherein the rotating component is one of the high-pressure shaft and the low-pressure shaft of the gas turbine engine.

[0126] According to any of the preceding or foregoing clauses, the suction face sealing assembly, wherein the high-pressure fluid source is one of the high-pressure compressor, low-pressure compressor, compressor outlet, or high-pressure turbine of the gas turbine engine.

[0127] The suction face sealing assembly according to any of the preceding or foregoing clauses, wherein the elastic member is a spring or a bellows.

[0128] According to any preceding clause or any of the foregoing clauses, the suction surface sealing assembly, wherein the resilient member includes a first end coupled to the stationary member and a second end coupled to the sealing body, wherein the resilient member biases the sealing surface of the sealing body away from the sealing surface of the rotating member.

[0129] A gas turbine engine including a suction face sealing assembly as described in any of the preceding clauses.

[0130] This written description uses examples to disclose this disclosure, including best practices, and also enables any person skilled in the art to practice this disclosure, including making and using any device or system and methods of making any combination. The patentable scope of this disclosure is defined by the claims, but may include other examples that would occur to a person skilled in the art. Such other examples are intended to fall within the scope of the claims if they include structural elements that are not indistinguishable from the literal language of the claims, or if they include equivalent structural elements that are not substantially different from the literal language of the claims.

Claims

1. A suction surface sealing assembly, characterized in that, include: A rotating component that defines a sealing surface; stationary parts; A sealing body defining a sealing surface, the sealing body defining a fluid supply passage within the sealing body, wherein the fluid supply passage includes an inlet and one or more supply ports defined along the sealing surface, wherein the sealing body is movably coupled to the stationary member via an elastic member; A first pressure chamber is defined radially outward from the sealing body; A second pressure chamber is defined radially inward from the sealing body; and A chamber seal that forms a seal between a portion of the sealing body and the stationary component, wherein the chamber seal, the stationary component, and the sealing body at least partially define a third pressure chamber in fluid communication with a high-pressure fluid source, wherein the third pressure chamber is in fluid communication with the inlet of the fluid supply passage, and wherein the third pressure chamber is pressurized at a pressure higher than that of both the first and second pressure chambers.

2. The suction surface sealing assembly according to claim 1, characterized in that, An axial gap is defined between the sealing surface and the sealing surface.

3. The suction surface sealing assembly according to claim 1, characterized in that, The sealing body defines a crossbar portion and a sealing arm portion.

4. The suction surface sealing assembly according to claim 3, characterized in that, The fluid supply channel extends axially within the crossbar portion of the seal body between the inlet and the one or more supply ports, and extends radially within the sealing arm portion of the seal body.

5. The suction surface sealing assembly according to claim 1, characterized in that, The stationary component includes a stationary extension arm, wherein the air chamber seal extends from the stationary extension arm to the radial outer surface of the seal body, and wherein the stationary extension arm at least partially defines the third pressure air chamber.

6. The suction surface sealing assembly according to claim 5, characterized in that, The inlet is defined along the radial outer surface of the seal.

7. The suction surface sealing assembly according to claim 5, characterized in that, The sealing body defines a radial sidewall, and the inlet is defined along the radial sidewall.

8. The suction surface sealing assembly according to claim 1, characterized in that, The stationary component includes a stationary arm, wherein the air chamber seal extends from the stationary arm to the outer surface of the seal, and wherein the stationary arm at least partially defines the third pressure air chamber.

9. The suction surface sealing assembly according to claim 8, characterized in that, The sealing body defines an inner pocket, wherein the inner pocket at least partially defines the third pressure chamber.

10. The suction surface sealing assembly according to claim 9, characterized in that, The inlet is defined within the inner pocket.

Images