Seal device for magnetic turbomachinery

Abstract

To provide a sealing arrangement for a turbomachine.SOLUTION: A sealing arrangement (201) and a turbomachine are provided. The sealing arrangement (201) for the turbomachine includes a transition duct (44) having an upstream end (46) and a downstream end (48). The transition duct (44) includes an aft frame (100) that circumferentially surrounds the downstream end (48) of the transition duct (44). A stage-one nozzle (700) is separated from the aft frame (100) and defines a gap (202) therebetween. A sealing assembly (400) extends across the gap (202). The sealing assembly (400) includes a first seal link (602) magnetically coupled to the aft frame (100). The sealing assembly (400) further includes a second seal link (604) magnetically coupled to the first seal link (602) and the stage-one nozzle (700).SELECTED DRAWING: Figure 4

Description

TECHNICAL FIELD

[0001] The present disclosure relates generally to seal devices for turbomachinery. In particular, the present disclosure relates to an improved seal device between a rear frame and a first stage turbine nozzle.

BACKGROUND ART

[0002] Turbomachinery is utilized in various industries and applications for the purpose of energy transfer. For example, gas turbine engines generally include a compressor section, a combustion section, a turbine section, and an exhaust section. The compressor section gradually increases the pressure of the working fluid entering the gas turbine engine and supplies this compressed working fluid to the combustion section. The compressed working fluid and fuel (e.g., natural gas) are mixed in the combustion section and combusted in a combustion chamber to generate high-pressure and high-temperature combustion gas. The combustion gas flows from the combustion section to the turbine section, where it expands to generate work. For example, expansion of the combustion gas in the turbine section can rotate a rotor shaft connected to, for example, a generator to generate electricity. The combustion gas then exits the gas turbine through the exhaust section.

[0003] The combustion section of a gas turbine typically includes a combustor coupled to the first-stage nozzle of the turbine section via a transition duct. Generally, each transition duct has a rear frame positioned close to the inlet side of the turbine section. The rear frame is usually referred to as the inner and outer portions and has two arched portions that are radially inward and outward with respect to the turbine's central axis. The inner and outer portions of the rear frame are interconnected by radially extending straight portions, often referred to as lateral portions. Seal assemblies are typically used to seal between the rear frame and the inlet of the turbine section. In particular, inner and outer circumferential seals are used to seal between the inner and outer portions of the rear frame and the corresponding inlets of the turbine section. Similarly, radially oriented side seals can be positioned between adjacent rear frames to substantially close and seal the circumferential gap between the lateral portion of one rear frame and the next rear frame.

[0004] A seal assembly positioned around the rear frame typically functions to prevent the hot combustion gases from being diluted by the pressurized air surrounding the combustor before they enter the turbine section. In this way, the seal assembly ensures that the hot combustion gases are fully utilized to generate work within the turbine section.

[0005] However, problems exist with the use of many known seal assemblies. For example, the high temperatures of combustion gases can cause damage to the seal assembly over time, potentially limiting its lifespan and reducing its durability. Furthermore, thermal expansion and vibration of the rear frame and first-stage nozzle during gas turbine operation can cause displacement and / or complete separation of the seal assembly, resulting in incomplete sealing between components.

[0006] Therefore, improved seal assemblies are desired in the art. In particular, improved seal assemblies for gas turbine engines are desired, which have improved durability and alignment, thereby extending the overall lifespan and durability of the assembly. [Overview of the Initiative]

[0007] The embodiments and advantages of the sealing devices and turbomachinery described herein are partially described in the following description, or become apparent from the description, or can be learned through the practice of the art.

[0008] According to one embodiment, a sealing device for turbomachinery is provided. The sealing device includes a transition duct having an upstream end and a downstream end. The transition duct includes a rear frame that circumferentially surrounds the downstream end of the transition duct. A first stage nozzle is spaced apart from the rear frame, defining a gap between them. A sealing assembly extends across the gap. The sealing assembly includes a first sealing link magnetically coupled to the rear frame. The sealing assembly further includes a second sealing link magnetically coupled to the first sealing link and the first stage nozzle.

[0009] According to another embodiment, a turbomachinery is provided. The turbomachinery includes a compressor section and a combustor section having a plurality of combustors. Each combustor comprises a transition duct having an upstream end and a downstream end. The transition duct includes a rear frame that circumferentially surrounds the downstream end of the transition duct. The turbomachinery further includes a turbine section having a first-stage nozzle spaced apart from the rear frame. A gap is defined between the first-stage nozzle and the rear frame. A seal assembly extends across the gap. The seal assembly includes a first seal link magnetically coupled to the rear frame. The seal assembly further includes a second seal link magnetically coupled to the first seal link and the first-stage nozzle.

[0010] These and other features, aspects, and advantages of the sealing device and turbomachinery should be better understood by referring to the following description and the appended claims. The appended drawings, which are incorporated herein and constitute part of this specification, illustrate embodiments of the art and, together with the description in the specification, help to illustrate the principles of the art.

[0011] A complete and implementable disclosure of the sealing device and turbomachinery, including the best modes of manufacture and use of the system and method, directed to those skilled in the art, is described herein with reference to the accompanying drawings. [Brief explanation of the drawing]

[0012] [Figure 1] This is a schematic diagram of a turbomachinery according to an embodiment of the present disclosure. [Figure 2] This is a cross-sectional view of a combustor according to the embodiment of the disclosure. [Figure 3] This is a perspective view of a circumferentially adjacent transition duct according to an embodiment of the present disclosure. [Figure 4] This is a cross-sectional perspective view of a sealing device according to an embodiment of the present disclosure. [Figure 5] This is a cross-sectional perspective view of a sealing device according to an embodiment of the present disclosure. [Figure 6] This is a cross-sectional perspective view of a sealing device according to an embodiment of the present disclosure. [Modes for carrying out the invention]

[0013] Embodiments of the sealing device and turbomachinery described herein are provided in detail here, with one or more examples shown in the drawings. Each example is provided for illustrative purposes of the present art and is not intended to limit the present art. In fact, it will be apparent to those skilled in the art that modifications and changes are possible in the present art without departing from the scope or spirit of the claimed art. For example, features illustrated or described as part of one embodiment can be used in another embodiment to bring about further embodiments. Accordingly, this disclosure is intended to encompass such modifications and changes within the scope of the appended claims and their equivalents.

[0014] Detailed descriptions use numerals and letters to refer to features in the drawings. Similar or identical reference numerals in the drawings and descriptions are used to refer to similar or identical parts of the present invention. As used herein, the terms “first,” “second,” and “third” may be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of any individual component.

[0015] As used herein, the terms “upstream” (or “forward”) and “downstream” (or “backward”) refer to relative directions of fluid flow in a fluid path. For example, “upstream” refers to the direction in which the fluid is flowing, and “downstream” refers to the direction in which the fluid is flowing. The term “radially” refers to a relative direction substantially perpendicular to the axial centerline of a particular component, the term “axially” refers to a relative direction substantially parallel and / or coaxial with the axial centerline of a particular component, and the term “circumferentially” refers to a relative direction extending around the axial centerline of a particular component. Approximate terms such as “approximately” or “about” include values ​​within plus or minus 10 percent of the stated value. When used in the context of angles or directions, such terms include a range of plus or minus 10 degrees of the stated angle or direction. For example, “generally perpendicular” includes any direction, e.g., within 10 degrees from perpendicular in a clockwise or counterclockwise direction.

[0016] Referring here to the drawings, Figure 1 shows a schematic diagram of one embodiment of a turbomachinery, which in the illustrated embodiment is a gas turbine 10. Although industrial and onshore gas turbines are shown and described herein, this disclosure is not limited to onshore and / or industrial gas turbines unless specifically stated in the claims. For example, the present invention as described herein can be used in any type of turbomachinery, including, but is not limited to, steam turbines, aircraft gas turbines, or marine gas turbines.

[0017] As shown in the figure, the gas turbine 10 generally includes an inlet section 12, a compressor section 14 located downstream of the inlet section 12, a number of combustors (not shown) in a combustor section 16 located downstream of the compressor section 14, a turbine section 18 located downstream of the combustor section 16, and an exhaust section 20 located downstream of the turbine section 18. In addition, the gas turbine 10 may include one or more shafts 22 coupled between the compressor section 14 and the turbine section 18.

[0018] The compressor section 14 may generally include a plurality of rotor disks 24 (one of which is illustrated) and a plurality of rotor blades 26 connected to each rotor disk 24 and extending radially outward from each rotor disk 24. Each rotor disk 24 may then be coupled to a portion of a shaft 22 extending through the compressor section 14, or each rotor disk 24 may form such a portion.

[0019] The turbine section 18 may generally include a plurality of rotor disks 28 (one of which is illustrated) and a plurality of rotor blades 30 extending radially outward from each rotor disk 28 and interconnected with each rotor disk 28. Each rotor disk 28 may then be coupled to or form part of a shaft 22 extending through the turbine section 18. The turbine section 18 further includes an outer casing 31 that circumferentially surrounds part of the shaft 22 and the rotor blades 30, thereby at least partially defining a hot gas path 32 through the turbine section 18.

[0020] During operation, a working fluid such as air 36 flows through the inlet section 12 into the compressor section 14, where the air 36 is gradually compressed, and thus pressurized or compressed air 38 is delivered to the combustors 17 (Figure 2) of the combustor section 16. The compressed air 38 is mixed with fuel 40 and combusted in each combustor 17 (Figure 2) to produce combustion gases 34. The combustion gases 34 flow from the combustor section 16 to the turbine section 18 through the high-temperature gas path 32, where energy (kinetic energy and / or thermal energy) is transferred from the combustion gases 34 to the rotor blades 30, causing the shaft 22 to rotate. The mechanical rotational energy can then be used to supply power to the compressor section 14 and / or generate electricity. The combustion gases 34 discharged from the turbine section 18 can then be exhausted from the gas turbine 10 via the exhaust section 20.

[0021] As shown in Figure 2, the combustor 17 may be at least partially surrounded by an outer casing 31, such as a compressor discharge casing. The outer casing 31 can at least partially define a high-pressure plenum 42 that at least partially surrounds various components of the combustor 17, such as a transition duct 44. The high-pressure plenum 42 is in fluid communication with the compressor 14 (Figure 1) and can receive compressed air 38 from there. As shown in Figure 2, the combustor 17 may be connected to the first-stage nozzle 700 of the turbine 18 via a transition duct 44, which includes a rear frame 100. The transition duct 44 defines a flow path P. Also shown in Figure 2 is the central axis A of the turbine 18, which defines an axial direction substantially parallel to and / or along axis A, a radial direction R (Figure 3) perpendicular to axis A, and a circumferential direction C (Figure 3) extending around axis A.

[0022] Referring now to FIG. 3, a pair of transition ducts 44 arranged in the circumferential direction, each having an upstream end 46 and a downstream end 48, are shown. As illustrated, the aft frame 100 surrounds the respective downstream end 48 of each transition duct 44. As shown in FIG. 3, in some embodiments, the aft frame 100 may have an inner portion 102 and an outer portion 104, and may have a pair of opposing side portions 106 and 108 extending radially between the inner portion 102 and the outer portion 104. FIG. 3 also shows an inner seal 200 and an outer seal 300 disposed on the inner portion 102 and the outer portion 104 of each aft frame 100, respectively. The aft frame 100 may include a notch or slot 101 (shown in FIG. 4) for partially receiving the inner seal 200 and / or the outer seal 300. In some embodiments, the notch 101 may extend around the entire circumference of the aft frame 100 to receive both the inner seal 200 and the outer seal 300, as well as a radially oriented side seal (not shown) that may be provided between adjacent aft frames 100 (for example, the notch 101 may be continuous through the side portions 106 and 108 and the inner portion 102 and outer portion 104). In some embodiments, it is also possible to provide separate slots or notches for each of the seals 200 and 300.

[0023] As shown in FIG. 3, the inner seal 200 and the outer seal 300 may be oriented in the circumferential direction relative to the circumferential direction C of the gas turbine 10. For example, each inner seal 200 is circumferentially aligned with the other inner seal 200 of the adjacent aft frame 100, and each outer seal 300 is circumferentially aligned with the other outer seal 300 of the adjacent aft frame 100. Accordingly, the inner seal 200 and the outer seal 300 may collectively be referred to as circumferentially oriented seals.

[0024] In the description of the present specification, certain features of the aft frame 100, the first stage nozzle 700, and the seals 200, 300 are described with reference to one or the other of the inner portion 102 / inner seal 200 and the outer portion 104 / outer seal 300, nevertheless, those skilled in the art will appreciate that such features may be associated with either or both of the inner portion 102 and / or the outer portion 104.

[0025] Figures 4 to 6 show cross-sectional views of a seal device 201 according to embodiments of the present disclosure. For example, Figure 4 shows a cross-sectional view of the seal device 201 having a seal assembly 400, Figure 5 shows a cross-sectional view of the seal device 201 having a seal assembly 500, and Figure 6 shows a cross-sectional view of the seal device 201 having a seal assembly 600. The seal assemblies 400, 500, and 600 described herein may represent the inner seal 200, the outer seal 300, or both. As shown in Figures 4 to 6, the seal device 201 includes a transition duct 44 having an upstream end 46 and a downstream end 48 (shown in Figure 3). In many embodiments, the aft frame 100 circumferentially surrounds the downstream end 48 of the transition duct 44. The first stage nozzle 700 of the turbine 18 may be spaced apart from the aft frame 100, and may define a gap 202 between the first stage nozzle 700 and the aft frame 100. Specifically, the first stage nozzle 700 and the aft frame 100 may be axially spaced apart to allow movement and / or thermal expansion of the first stage nozzle 700 and / or the aft frame 100 during operation of the gas turbine 10. The gap 202 may be axially defined between the aft face 204 of the aft frame 100 and the front face 206 of the first stage nozzle 700.

[0026] As shown in Figures 4 to 6, the rear frame 100 may define a first slot 101 that extends axially and circumferentially within the rear frame 100 with respect to the axial centerline of the gas turbine 10. Similarly, the first stage nozzle 700 may define a second slot 701 that extends axially and circumferentially within the first stage nozzle 700 with respect to the axial centerline of the gas turbine 10. The seal assemblies 400, 500, and 600 may be partially located within the first slot 101 and the second slot 701, respectively, to advantageously shield the seal assemblies 400, 500, and 600 from the hot combustion gas 34.

[0027] As shown in Figure 4, the sealing device 201 may include a sealing assembly 400 extending across the gap 202 to prevent the combustion gas 34 exiting the transition duct 44 from being diluted by the pressurized air 38 from the high-pressure plenum 42. As shown, the sealing assembly 400 may include a sealing link 402 extending across the gap 202. The sealing link 402 may be magnetically coupled to the rear frame 100 at its upstream end 406 and magnetically coupled to the first stage nozzle 700 at its downstream end 408. For example, the sealing link 402 may include a first magnetic end 403 at the upstream end 406 that is magnetically coupled to the rear frame 100, and a second magnetic end 404 that is magnetically coupled to the first stage nozzle 700. In various embodiments, the magnetic ends 403, 404 may be in the form of metallic material pieces whose constituent atoms are aligned so that the material exhibits magnetic properties, such as attracting other iron-containing objects or self-aligning in an external magnetic field. In exemplary embodiments, the magnet ends 403 and 404 are permanent magnets mainly composed of a combination of aluminum, nickel, and cobalt, but may also be Alnico magnets which may include copper, iron, and titanium. Alnico magnets can enable operation at extremely high temperatures, such as above 1000°F.

[0028] In some embodiments, the rear frame 100 and / or the first stage nozzle 700 may be formed from an iron (or iron-containing) metal such that the rear frame 100 and / or the first stage nozzle 700 are attracted to and coupled to the magnetic ends 403, 404. In other embodiments, the rear frame 100 and / or the first stage nozzle 700 may be formed from a non-ferrous metal. In such embodiments, one or more magnets 410 may be embedded within the rear frame 100 and the first stage nozzle 700 to generate an attractive magnetic force between the magnets 410 and the magnetic ends 403, 404 of the seal link 402. In the embodiment shown in Figure 4, the seal link 402 may be sealed against the rear frame 100 and the first stage nozzle 700 via a pressure load applied by pressurized air 38. Furthermore, the seal link 402 may be sealed against the rear frame 100 and the first stage nozzle 700 via an attractive magnetic force.

[0029] As shown in Figure 4, the seal link 402 may include a flexible seal element 424 extending between the upstream end 406 and the downstream end 408. The flexible seal element 424 may be composed mainly of a cloth material, which may be a woven mesh cloth of a suitable metal material, such as alloy L605. The material of the flexible seal element 424 can be laminated, for example, as shown in Figure 4, a single sheet of cloth material can be folded on top of itself, and / or multiple layers of cloth material can be welded to each other.

[0030] As shown in Figure 5, the sealing device 201 may include a sealing assembly 500 extending across the gap 202 to prevent the combustion gas 34 exiting the transition duct 44 from being diluted by the pressurized air 38 from the high-pressure plenum 42. As shown, the sealing assembly 500 may include a sealing link 502 extending across the gap 202. The sealing link 502 may be magnetically coupled to the rear frame 100 at its upstream end 506 and to the first stage nozzle 700 at its downstream end 508. As shown, the upstream end 506 of the sealing link 502 may include either a convex magnetic end 512 or a concave magnetic end 510. Similarly, the downstream end 508 of the sealing link 502 may include either a convex magnetic end 512 or a concave magnetic end 510. The convex magnet end 512 may be in the form of a projection, ball, or substantially circular axially outward-facing surface configured to be rotatably and magnetically coupled to either the rear frame 100 or the first stage nozzle 700. Similarly, the concave magnet end 510 may be in the form of a recess, socket, or substantially circular axially inward-facing surface configured to be rotatably and magnetically coupled to either the rear frame 100 or the first stage nozzle 700. For example, as shown in Figure 5, the convex magnet end 512 of the seal link 502 is rotatably and magnetically coupled to the first stage nozzle 700, and the concave magnet end 510 is rotatably and magnetically coupled to the rear frame 100.

[0031] As shown in Figure 5, the sealing device may include a first magnetic ball socket joint 514 and a second magnetic ball socket joint 516. As shown, the upstream end 506 of the seal link 502 may be coupled to the rear frame 100 via the first magnetic ball socket joint 514. In certain embodiments, as shown, the downstream end 608 of the seal link 502 may be coupled to the first stage nozzle 700 via the second magnetic ball socket joint 516.

[0032] In various embodiments, the rear frame may include either a ball magnet 520 or a socket magnet 522 configured to be rotatably and magnetically coupled to the upstream end 506 of the seal link 502. For example, in the embodiment shown in Figure 5, the rear frame 100 includes a ball magnet 520 fixedly coupled to the rear frame 100, and the seal link 502 includes a corresponding concave magnet end 510 to couple with the ball magnet 520 of the rear frame 100 and to form a first magnetic ball socket joint 514. However, in other embodiments (not shown), the rear frame 100 may include a socket magnet. In such embodiments, the seal link 502 may include a corresponding convex seal end to couple with the socket magnet of the rear frame 100.

[0033] Similarly, the first stage nozzle 700 may include either a ball magnet 520 or a socket magnet 522 configured to be rotatably and magnetically coupled to the downstream end 508 of the seal link 502. For example, in the embodiment shown in Figure 5, the first stage nozzle 700 includes a socket magnet 522 fixedly coupled to the first stage nozzle 700, and the seal link 502 includes a corresponding convex magnet end 512 to couple with the socket magnet 522 of the first stage nozzle 700 and form a second magnetic ball socket joint 516. However, in other embodiments (not shown), the first stage nozzle 700 may include a ball magnet. In such embodiments, the seal link 502 may include a corresponding concave seal end to couple with the ball magnet of the first stage nozzle 700.

[0034] The ball socket joints 514 and 516 depicted in Figure 5 show a socket or concave magnet end 510 located at the upstream end 506 of the seal link 502, and a ball or convex magnet end 512 located at the downstream end 508 of the seal link 502. However, it is assumed that one or more of the ball or convex magnet ends are located at the upstream end 506 and the corresponding socket or concave magnet end is located at the downstream end 508, which is within the scope of this disclosure.

[0035] In many embodiments, the seal link 502 may include a flexible seal element 524 extending between the upstream end 506 and the downstream end 508. The flexible seal element 524 may be composed mainly of a cloth material, which may be a woven mesh cloth of a suitable metal material, such as alloy L605. The material of the flexible seal element 524 can be laminated, for example, as shown in Figure 5, a single sheet of cloth material can be folded on top of itself, and / or multiple layers of cloth material can be welded to each other.

[0036] As shown in Figure 6, the seal assembly 600 may include a first seal link 602 and a second seal link 604. The first seal link 602 may be magnetically coupled to the rear frame 100 and may extend substantially axially toward the first stage nozzle 700. Similarly, the second seal link 604 may be magnetically coupled to the first stage nozzle 700 and may extend substantially axially toward the rear frame 100. In an exemplary embodiment, the first seal link 602 and the second seal link 604 may be magnetically coupled to each other between the rear frame 100 and the first stage nozzle 700, for example, within a gap 202. In this way, the first seal link 602 and the second seal link may extend toward each other and be magnetically coupled together at a position within the gap 202.

[0037] In many embodiments, the first seal link 602 may be rotatable relative to the rear frame 100. Similarly, the second seal link 604 may be rotatable relative to the first stage nozzle 700. In various embodiments, the first seal link 602 and the second seal link 604 are each rotatable relative to each other. For example, the first seal link 602 and the second seal link 604 may be rotatable at their respective mounting points, which is advantageous in that it allows thermal expansion and relative movement between the rear frame 100 and the first stage nozzle 700 without causing displacement and / or complete separation of the seal assembly 600.

[0038] In certain embodiments, the first seal link 602 and the second seal link 604 may each extend between their respective upstream ends 606 and their respective downstream ends 608. In various embodiments, the respective upstream ends 606 of the seal links 602, 604 may include either a convex magnet end 612 or a concave magnet end 610. Similarly, the downstream ends 608 of the seal links 602, 604 may include either a convex magnet end 612 or a concave magnet end 610. The convex magnet end 612 may be in the form of a projection, ball, or substantially circular axially outward-facing surface configured to rotatably and magnetically couple to the corresponding concave magnet end 610 of an adjacent seal link. Similarly, the concave magnet end 610 may be in the form of a recess, socket, or substantially circular axially inward-facing surface configured to rotatably and magnetically couple to the corresponding convex magnet end 612 of an adjacent seal link. For example, as shown in Figure 6, the convex magnet end 612 of the first seal link 602 may be rotatably and magnetically coupled to the concave magnet end 610 of the second seal link 604.

[0039] As shown in Figure 6, the sealing device may include a first magnetic ball socket joint 614, a second magnetic ball socket joint 616, and a third magnetic ball socket joint 618. As shown, the upstream end 606 of the first seal link 602 may be coupled to the rear frame 100 via the first magnetic ball socket joint 614. In many embodiments, the downstream end 608 of the first seal link 602 may be coupled to the upstream end 606 of the second seal link 604 via the second magnetic ball socket joint 616. In certain embodiments, as shown, the downstream end 608 of the second seal link 604 may be coupled to the first stage nozzle 700 via the third magnetic ball socket joint 618.

[0040] In various embodiments, the rear frame may include either a ball magnet 620 or a socket magnet 622 configured to be rotatably and magnetically coupled to the upstream end 606 of the first seal link 602. For example, in the embodiment shown in Figure 6, the rear frame 100 includes a ball magnet 620 fixedly coupled to the rear frame 100, and the first seal link 602 includes a corresponding concave magnet end 610 to couple with the ball magnet 620 of the rear frame 100 and to form a first magnetic ball socket joint 614. However, in other embodiments (not shown), the rear frame 100 may include a socket magnet. In such embodiments, the first seal link 602 may include a corresponding convex seal end to couple with the socket magnet of the rear frame 100.

[0041] Similarly, the first stage nozzle 700 may include either a ball magnet 620 or a socket magnet 622 configured to be rotatably and magnetically coupled to the downstream end 608 of the second seal link 604. For example, in the embodiment shown in Figure 6, the first stage nozzle 700 includes a socket magnet 622 fixedly coupled to the first stage nozzle 700, and the second seal link 604 includes a corresponding concave magnet end 610 to couple with the socket magnet 622 of the first stage nozzle and form a third magnetic ball socket joint 618. However, in other embodiments (not shown), the first stage nozzle 700 may include a ball magnet. In such embodiments, the second seal link 604 may include a corresponding concave seal end to couple with the ball magnet of the first stage nozzle 700.

[0042] The ball-socket joints 614, 616, and 618 depicted in Figure 6 show socket or concave magnet end 610 located at the upstream end 606 of the first seal link 602 and the second seal link 604, and ball or convex magnet end 612 located at the downstream end 608 of the first seal link 602 and the second seal link 604. However, it is assumed that one or more of the ball or convex magnet ends are located at the upstream end 606 and the corresponding socket or concave magnet end is located at the downstream end 608, which is within the scope of this disclosure.

[0043] In many embodiments, each of the first seal link 602 and the second seal link 604 may include a flexible seal element 624 extending between their respective upstream end 606 and their respective downstream end 608. The flexible seal element 624 may be composed mainly of a cloth material, which may be a woven mesh cloth of a suitable metal material, such as alloy L605. The material of the flexible seal element 624 can be laminated, for example, as shown in Figure 6, by folding a single sheet of cloth material on itself and / or welding multiple layers of cloth material to each other.

[0044] As shown in Figures 4 to 6, the rear frame 100 may define a first slot 101 that extends axially and circumferentially within the rear frame 100 with respect to the axial centerline of the gas turbine 10. Similarly, the first stage nozzle 700 may define a second slot 701 that extends axially and circumferentially within the first stage nozzle 700 with respect to the axial centerline of the gas turbine 10. In many embodiments, at least a portion of the first seal link 602 extends into the first slot 101 defined by the rear frame 100, thereby advantageously shielding the first seal link 602 from the hot combustion gas 34. Similarly, at least a portion of the second seal link 604 may extend into the second slot 701 defined by the first stage nozzle 700, thereby advantageously shielding the second seal link 604 from the hot combustion gas 34.

[0045] As shown in Figures 4 to 6, the rear frame 100 may define a cooling channel 234 that functions to cool various components of the sealing device 201. As shown, the cooling channel 234 may extend along the rear frame 100. In many embodiments, the cooling channel 234 may extend radially inward with respect to the axial centerline A of the gas turbine 10 in the direction in which the combustion gas 34 flows through the rear frame 100 (from the upstream end to the downstream end). The cooling channel 234 may further include an outlet 236. The outlet 236 may be oriented substantially radially to guide a flow of cooling air 238 toward the sealing assemblies 400, 500, 600. The flow of cooling air 238 can provide impact cooling to the various components of the sealing assemblies 400, 500, 600. The flow of cooling air 238 can ensure that the various magnets within the sealing assemblies 400, 500, 600 maintain an operable temperature, i.e., the magnets do not overheat.

[0046] In many embodiments, the seal assemblies 400, 500, and 600 described herein may extend continuously in the circumferential direction C (inside and outside the pages of Figures 4 to 6). In this way, each of the ball socket joints described herein can extend continuously in the circumferential direction C. In other embodiments, the ball socket joints may be a plurality of ball socket joints spaced apart from each other in the circumferential direction.

[0047] During operation, combustion gases 34 may exit the combustor 17 via the rear frame 100 and must travel across the gap 202 before entering the turbine section 18 via the first-stage nozzle 700. The seal assemblies 400, 500, and 600 described herein can ensure that the combustion gases 34 are not diluted with pressurized air 38 before entering the turbine section. In this way, the seal assembly 400 ensures that all of the thermal energy from the combustion gases 34 is utilized by the turbine section 18, thereby maintaining the high operational efficiency of the turbomachine. The magnetic ball socket joints 614, 616, and 618 described herein can advantageously provide relative movement between seal links 602, 602 while maintaining proper alignment of the entire seal assembly 600. For example, during the operation of the turbomachine, the rear frame 100 and the first-stage nozzle 700 may move relative to each other due to thermal expansion and / or general operating vibrations. The seal assembly 600 described herein can move and rotate together with the rear frame 100 and the first stage nozzle 700, and magnets ensure that the seal assembly 600 maintains its alignment.

[0048] This specification uses examples to disclose the present invention, including its best mode, and to enable any person skilled in the art to practice the invention, including the fabrication and use of any device or system and the implementation of any incorporated method. The patentable scope of the present invention is defined by the claims and may include other examples that a person skilled in the art may conceive. Such other examples are included in the technical scope of the claims if they include structural elements that do not differ from the language of the claims, or equivalent structural elements that do not differ substantially from the language of the claims. [Explanation of Symbols]

[0049] 10 Gas Turbines 12 Entrance Section 14 Compressor section, compressor 16. Combustor Section 17 Combustor 18. Turbine section, turbine 20 Exhaust Section 22 shafts 24 Rotor Discs 26 rotor blades 28 Rotor Discs 30 rotor blades 31 Outer casing 32 High-temperature gas pathway 34 High-temperature combustion gases 36 Air 38 Compressed air, pressurized air 40 fuel 42 High-pressure plenum 44 Transition Duct 46 Upstream end 48 Downstream end 100 Rear frame 101 Notch, 1st Slot 102 Inner part 104 Outer part 106 Lateral part 200 Inner seal 201 Sealing device 202 Gap 204 Rear 206 Front 234 cooling channels 236 Exit 238 Cooling air 300 outer seal 400 seal assembly 402 Seal Link 403 First magnetic end, magnetic end 404 Second magnetic end, magnetic end 406 Upstream end 408 Downstream end 410 Magnets 424 Flexible sealing element 500 seal assembly 502 Seal Link 506 Upstream end 508 Downstream end 510 Concave magnet end 512 Convex magnet end 514 First Magnetic Ball Socket Joint 516 Second Magnetic Ball Socket Joint 520 Ball Magnets 522 Socket Magnet 524 Flexible sealing element 600 seal assembly 602 First seal link 604 Second seal link 606 Upstream end 608 Downstream end 610 Concave magnet end 612 Convex magnet end 614 First Magnetic Ball Socket Joint 616 Second Magnetic Ball Socket Joint 618 Third Magnetic Ball Socket Joint 620 Ball Magnets 622 Socket Magnet 624 Flexible sealing element 700 First stage nozzle 701 Second slot A Center axis, axial center line C circumferential direction P channel R Radial direction

Claims

1. A sealing device (201) for turbomachinery, wherein the sealing device (201) A transition duct (44) having an upstream end (46) and a downstream end (48), the transition duct (44) comprising a rear frame (100) surrounding the downstream end (48) of the transition duct (44) in the circumferential direction, A first-stage nozzle (700) spaced apart from the rear frame (100), the first-stage nozzle (700) defining a gap (202) between itself and the rear frame (100), A seal assembly (400) extending across the gap (202), comprising a seal link (402) which is magnetically coupled to the rear frame (100) at its upstream end (406) and to the first stage nozzle (700) at its downstream end (408), and It is equipped with, A sealing device (201) for turbomachinery, wherein the seal link (402) comprises flexible sealing elements (424, 524, 624) extending between the upstream end (406) and the downstream end (408).

2. The sealing device (201) according to claim 1, wherein the upstream end (406) of the seal link (402) is connected to the rear frame (100) via a first magnetic ball socket joint (614), and the downstream end (408) of the seal link (402) is connected to the first stage nozzle (700) via a second magnetic ball socket joint (616).

3. The sealing device (201) according to claim 1, wherein the rear frame (100) includes either a ball magnet (620) or a socket magnet (622) configured to be rotatably and magnetically coupled to the upstream end (406) of the sealing link (402).

4. The sealing device (201) according to claim 1, wherein the first stage nozzle (700) includes either a ball magnet (620) or a socket magnet (622) configured to be rotatably and magnetically coupled to the downstream end (408) of the sealing link (402).

5. The sealing device (201) according to claim 2, wherein the upstream end (406) of the sealing link (402) includes either a convex magnet end (612) or a concave magnet end (610), and the downstream end (408) of the sealing link (402) includes either a convex magnet end (612) or a concave magnet end (610).

6. The sealing device (201) according to claim 1, wherein the seal link (402) is a first seal link (602), and the seal assembly (400) further comprises a second seal link (604) magnetically coupled to the first seal link (602), and the first seal link (602) and the second seal link (604) each extend between their respective upstream ends (606) having either a convex magnet end (612) or a concave magnet end (610) and their respective downstream ends (608) having either a convex magnet end (612) or a concave magnet end (610).

7. The sealing device (201) according to claim 6, wherein each of the upstream ends (606) of the first seal link (602) is magnetically coupled to the rear frame (100) via a first magnetic ball socket joint (614), each of the downstream ends (608) of the second seal link (604) is coupled to the first stage nozzle (700) via a second magnetic ball socket joint (616), and each of the downstream ends (608) of the first seal link (602) is coupled to each of the upstream ends (606) of the second seal link (604) via a third magnetic ball socket joint (618).

8. The sealing device (201) according to claim 6, wherein the first sealing link (602) is rotatable with respect to the rear frame (100), the second sealing link (604) is rotatable with respect to the first stage nozzle (700), and the first sealing link (602) and the second sealing link (604) are each rotatable with respect to each other.

9. The sealing device (201) according to claim 1, wherein a cooling flow channel is defined within the rear frame (100), and the cooling flow channel directs cooling air (238) exiting from the outlet toward the seal assembly (400) to provide impact cooling.

10. Compressor section (14) and A combustor section (16) having a plurality of combustors (17), wherein each combustor (17) is provided with a transition duct (44) having an upstream end (46) and a downstream end (48), and the transition duct (44) is provided with a rear frame (100) that surrounds the downstream end (48) of the transition duct (44) in the circumferential direction, A turbine section (18) having a first-stage nozzle (700) spaced apart from the rear frame (100), wherein a gap (202) is defined between the first-stage nozzle (700) and the rear frame (100), A seal assembly (400) extending across the gap (202), comprising a seal link (402) which is magnetically coupled to the rear frame (100) at its upstream end (406) and to the first stage nozzle (700) at its downstream end (408), and A turbomachinery comprising the seal link (402) having flexible seal elements (424, 524, 624) extending between the upstream end (406) and the downstream end (408).

11. The turbomachinery according to claim 10, wherein the upstream end (406) of the seal link (402) is coupled to the rear frame (100) via a first magnetic ball socket joint (614), and the downstream end (408) of the seal link (402) is coupled to the first stage nozzle (700) via a second magnetic ball socket joint (616).

12. The turbomachinery according to claim 10, wherein the rear frame (100) includes either a ball magnet (620) or a socket magnet (622) configured to be rotatably and magnetically coupled to the upstream end (406) of the seal link (402).

13. The turbomachinery according to claim 10, wherein the first stage nozzle (700) includes either a ball magnet (620) or a socket magnet (622) configured to be rotatably and magnetically coupled to the downstream end (408) of the seal link (402).

14. The turbomachinery according to claim 11, wherein the upstream end (406) of the seal link (402) includes either a convex magnet end (612) or a concave magnet end (610), and the downstream end (408) of the seal link (402) includes either a convex magnet end (612) or a concave magnet end (610).

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