• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a seal assembly for a turbomachine, comprising: at least one arcuate plate (44) connected to an inner surface of a stationary housing; a circumferentially segmented seal ring (46) disposed between a rotor (20) and the plate (44); a biasing member (66, 68) disposed between the arcuate plate (44) and the seal ring (46) and coupled to both; and a plurality of arcuate sealing members (70, 72) disposed between the sealing ring (46) and the rotor (20), wherein a gap (82, 84) extends from an upstream side (34) to a downstream side (36). progressively decreases; wherein the progressive decrease in the pitch of the teeth produces positive feedback, such that as a tip gap decreases, outward directed net radial forces due to the generated hydrostatic forces cause the seal ring (46) to move away from the rotor (20), and As the tip gap increases, inward net radial forces caused by the generated hydrostatic forces cause the seal ring (46) to move toward the rotor (20).
    公开号:CH702606B1
    申请号:CH00096/11
    申请日:2011-01-20
    公开日:2016-04-15
    发明作者:Vishvas Deo Hrishikesh；Roy Binayak
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Background of the invention
    The subject matter disclosed herein relates to the field of seals used in turbomachinery. In particular, the subject matter disclosed herein relates to a labyrinth seal having a progressively decreasing gap for use at the interface between a rotating component, such as a rotor in a turbine or compressor, and a stationary component, such as a housing or stator.
    Labyrinth seals used in gas turbines, steam turbines, aircraft engines, compressors, or other turbomachinery systems are prone to excessive leakage currents because a rotor gap may be configured to be sufficiently large to help prevent the rotor from rubbing against the rotor Prevent gasket. If the rotor comes into contact with the seal, which is referred to as rubbing or rubbing the rotor, the seal may be damaged, creating an even greater gap. In particular, rotor rubbing in a gas turbine may occur during many rotor transients involving dynamic rotor energization, relative rotor and stator thermal distortion, or rotor center offset due to the formation of a hydrodynamic lubricant film in the journal bearings as the speed increases can. It can lead to a deflection when a gas turbine critical speeds, for example, during startup, goes through. Warpage can be caused by thermal differences between components within the gas turbine. A large gap is needed between the seal and the rotor because a labyrinth seal may not be able to adjust its gap during the rotor transition operations as it may be rigidly coupled to the stator. The gaps between rotating and stationary components of gas turbines can affect both the efficiency and the performance of the turbine. When designing gas turbines, tight tolerances between components can lead to greater efficiency. Similar rotor transients occur in other turbomachinery systems, such as steam turbines, aircraft engines, or compressors, and the transients can often be difficult to estimate.
    [0003] In addition, labyrinth seals may be configured with a Variable Clearance Positive Pressure Packing (VCPPP) ring that biases the labyrinth seal away from the rotor to a large gap by means of a spring. This helps to prevent rubbing of the rotor during startup rotor transients. As the differential pressure across the seal increases above a certain level, forces applied to the VCPPP ring cause it to close to a small rotor gap. There is a vapor seal connection in the VCPPP ring design where the VCPPP ring is in contact with the housing or stator. The friction at this juncture can introduce hysteresis into the opening and closing of the VCPPP ring. When rotor transients occur after the VCPPP ring closes, rotor rubbing and damage to the labyrinth seal teeth occurs. There is therefore a need for a sealing arrangement in which the likelihood of such rubbing is reduced and in which, even in the presence of larger rotor transients, a small gap is maintained, resulting in smaller leakage and higher efficiency.
    Brief description of the invention
    The invention provides a sealing arrangement according to claim 1 and a turbine or a compressor according to claim 10 before.
    A turbomachine includes a stationary housing and a rotor that rotates about an axis. The inventive turbomachine seal assembly includes at least one arcuate plate coupled to an inner surface of the stationary housing and disposed in a radial plane. In addition, the seal assembly includes a circumferentially segmented seal ring disposed between the rotor and the plate. The sealing ring is positioned to move along the plate in a radial direction. The seal assembly further includes a plurality of arcuate sealing elements, also referred to as teeth, which are arranged between the sealing ring and the rotor. The gap distance between each tooth and the rotor progressively decreases as it passes from an upstream side of the turbomachine to a downstream side of the turbomachine. The progressive reduction of the gap of the teeth causes a passive feedback of the hydrostatic forces generated by the differential pressure across the seal assembly, so that as the gap distances decrease, outward directed net radial forces due to the generated hydrostatic forces force the seal ring to move cause the rotor to move away, and as the gap distances increase, inward net radial forces caused by the generated hydrostatic forces cause the seal ring to move toward the rotor. Finally, the seal assembly further includes a biasing member disposed between the arcuate plate and the seal ring and coupled to both.
    According to the invention, a turbine or a compressor includes a rotor which rotates about an axis, a stationary housing surrounding the rotor, and a circumferentially segmented seal assembly disposed between the rotor and the stationary housing. Each segment of the seal assembly further includes at least one arcuate plate coupled to an inner surface of the stationary housing and positioned in a radial plane. Each segment of the seal assembly further includes an arcuate segment of a seal ring disposed between the rotor and the plate. The sealing ring is positioned to move along the plate in a radial direction. The arcuate segment does not contain a vapor-seal connection. Each segment of the seal assembly further includes a plurality of arcuate teeth disposed between the seal ring and the rotor. A gap of each tooth progressively decreases in the course from an upstream side of the turbine or compressor to a downstream side of the turbine or compressor. The progressive decrease in the gap of the teeth creates a passive feedback of the hydrostatic forces generated by the differential pressure across the seal assembly such that as a tip gap decreases, outward directed net radial forces due to the generated hydrostatic forces cause the seal ring to move away from the seal Rotor move away, and as the tip gap increases, caused by the hydrostatic forces generated inward net radial forces cause the sealing ring to move towards the rotor. Finally, each segment of the seal assembly includes a biasing member disposed between the arcuate plate and the arcuate segment of the seal ring. The biasing member is coupled to the arcuate plate and the sealing ring.
    Brief description of the drawings
    These and other features of the present invention will become better understood when the following detailed description is read with reference to the accompanying drawings, in which like reference characters designate like parts throughout the drawings, in which:<Tb> FIG. 1 <SEP> is a cross-sectional view of a turbine system according to an embodiment of the present disclosure;<Tb> FIG. FIG. 2 is a perspective view of a sealing region of a turbine system as illustrated in FIG. 1 with a seal assembly according to an embodiment of the present technique; FIG.<Tb> FIG. 3 <SEP> is a cross-sectional view of a seal assembly with teeth on the seal ring according to an embodiment of the present technique;<Tb> FIG. Figure 4 is a cross-sectional view of a seal assembly with teeth on the seal ring and with raised lugs on the rotating member according to an embodiment of the present technique;<Tb> FIG. 5 <SEP> is a cross-sectional view of a toothed seal assembly on the rotating member according to an embodiment of the present technique;<Tb> FIG. Fig. 6 is a cross-sectional view of a seal assembly with teeth on the seal ring and a plurality of plates according to an embodiment of the present technique;<Tb> FIG. 7 is a cross-sectional view of a toothed seal assembly on both the seal ring and the orbiting member according to an embodiment of the present technique;<Tb> FIG. 8 is a graph illustrating the expected pressure distribution among the seal ring teeth as a function of the last tooth gap or tip gap, according to one embodiment of the present technique;<Tb> FIG. 9 is a graph illustrating the closing and opening forces acting on a seal ring according to one embodiment of the present technique;<Tb> FIG. 10 is a diagram illustrating the concept of an equilibrium gap according to an embodiment of the present technique; and<Tb> FIG. 11 is a graph illustrating how the equilibrium gap is dependent on the pressure ratio between the upstream and downstream pressures, according to an embodiment of the present technique.
    Detailed description of the invention
    Embodiments of the present invention are described below. In an effort to provide a concise and concise description of these embodiments, not all features of an actual implementation may be described in the description.
    When elements of various embodiments of the present invention are introduced, the articles "a," "an," "the," and "the" mean that one or more of the elements are present. The expressions "comprising", "containing" and "having" are to be understood in the inclusive sense and mean that there can be other elements besides the listed elements.
    Fig. 1 shows a cross-sectional view of one embodiment of a turbine system 10 which may include a variety of components, some of which are not illustrated for the sake of simplicity. In the illustrated embodiment, the gas turbine system 10 includes a compressor section 12, a combustor section 14, and a turbine section 16. The turbine section 16 includes a stationary housing 18 and a perimetric element 20 that revolves about an axis 22. Circumferential vanes 24 are attached to the orbiting member 20 while stationary vanes 26 are attached to the stationary housing 18. The blades 24 and the stationary blades 26 are alternately arranged in the axial direction. There are several possible locations where seal assemblies may be incorporated, such as location 28 between a shrouded blade 24 and a stationary housing 18, a location 30 between the orbiting member 20 and the stationary blade 26, and an end packing seal 32 the revolving element 20 and the stationary housing 18.
    FIG. 2 shows a perspective view of an embodiment of a seal arrangement 32 of the turbine system 10 according to FIG. 1. Air, fuel or other gases flow in the turbine system 10 from an upstream side 34 to a downstream side 36 of the seal assembly. In the illustrated embodiment, the axial direction is indicated by an axis 40, and the radial direction is indicated by an axis 42. With the arcuate surface of the stationary housing 18, which faces the rotating element 20, an arcuate plate 44 is connected. In certain embodiments, the plate may be made of steel or steel alloys. In addition, the cross-section of the plate, as indicated in Fig. 2, appear as T-shaped. The plate 44 may be rigidly connected to the housing 18. In addition, the plate 44 may be arranged as a complete 360 degree ring, as two 180 degree rings or as smaller arcs that together form a complete ring. Further, in some embodiments, the plate 44 may consist of multiple plates that are similarly configured.
    Between the plate 44 and the peripheral element 20, an arcuate sealing ring 46 is arranged. The ring 46 consists of several segments, which together form a complete ring. In some embodiments, the ring may be made of steel or steel alloys. In addition, the ring is configured to mate with the plate 44 with a gap 47. Between the stationary housing 18 and the sealing ring 46 biasing elements 48 are arranged. The biasing members 48 serve as flexure or flexion devices and provide high stiffness in the axial direction 40 and low stiffness in the radial direction 42. The high axial stiffness limits substantial movement in the axial direction. The low radial stiffness allows the seal ring 46 to move in the radial direction. In addition, the biasing member carries the weight of the sealing ring 46 and prevents it from touching the circulating element 20 under flow-free conditions. In certain embodiments, the biasing element 48 may consist of a plurality of biasing members, also referred to as diffractive devices. One end 50 of each diffracting device may be mechanically coupled to the sealing ring 46, while the other end 52 of each diffractive device may be mechanically coupled to the stationary housing 18 or to the plate 44, when T-shaped. In certain embodiments, examples of mechanical coupling may include a bolted joint, a welded joint, or other suitable methods for mechanically securing two structures. In other embodiments, the diffuser end 50 may form an integral part of the seal ring 46 and be mechanically secured to the housing 18. In yet another embodiment, the diffuser end 52 may form an integral part of the stationary housing 18 or plate 44, when T-shaped, and be mechanically secured to the seal ring. In this embodiment, each diffraction device is illustrated as a cantilever with a large aspect ratio of width to thickness. Other diffraction device designs are possible which also achieve high axial stiffness and low radial stiffness.
    The sealing ring 46 further includes a plurality of arcuate teeth 54, which are coupled to the surface of the ring which faces the peripheral element 20. The segments of each tooth disposed on each segment of the ring 46 together form a complete ring around the orbiting member 20. In some embodiments, the teeth 54 may be made of a steel alloy. In addition, the gaps between the teeth and the orbiting member 20 from the upstream side 34 of the turbine or compressor to the downstream side 36 become progressively smaller. This can be accomplished as the tooth heights progressively increase in the course from the upstream side 34 to the downstream side 36. The reduction of the column may be linear, square, parabolic or arbitrary. In addition, the spacing between adjacent teeth may be the same or vary as discussed below.
    3 shows a cross-sectional view of one embodiment of a seal assembly 60 with teeth on the seal ring 46. In the illustrated embodiment, the seal ring 46 is connected to the plate 44 by two sets of diffractors, a set of diffractors 66 on the upstream side, and one Set of diffraction devices 68 on the downstream side, coupled. The radial compliances of the upstream set 66 and the downstream set 68 of diffractive devices are indicated schematically as springs. In the particular embodiment illustrated, upstream and downstream arrays of diffractive ring diffraction devices 46 associated with the upstream and downstream portions of the ring surrounding the plate 44 are used. A front gap 74 is present between the upstream portion of the seal ring 46 and the plate 44, and similarly, there is a rear gap 76 between the downstream portion of the seal ring and the plate. These gaps provide flow resistance to the leakage current and should be minimized to reduce leakage current. In some embodiments, the front gap 74 and the rear gap 76 may be between about 50 microns and 250 microns. The high axial stiffness of the diffracting devices maintains the front and rear gaps at approximately the same value during operation. There is a pocket 78 between the seal ring 46 and the plate 44. The height 79 of the pocket 78 is designed to allow sufficient radial movement to avoid reaming of the rotor during rotor transition operations. Gases escape through a leakage path 80 that passes through the front gap 74, the pocket 78 and the rear gap 76. Thus, the front gap 74 and the rear gap 76 are configured to reduce the amount of gases that escape through the path 80. In addition, the seal ring 46 does not include a vapor seal connection to eliminate friction, allowing the seal ring to radially move in response to passive feedback forces, as described below.
    The seal ring 46 further includes a plurality of arcuate teeth including a tooth 70 on the upstream side and a tooth 72 on the downstream side, which are arranged on the surface facing the rotating element 20. The distance between the tip of the downstream tooth 72 and the orbiting member 20 is defined as the downstream tip clearance 84. In some embodiments, the downstream tip gap 84 may be in operation between about 125 microns and 380 microns. The distance between the tip of the upstream tooth 70 and the orbiting member 20 is defined as the upstream tip clearance 82. The difference between the upstream tip gap 82 and the downstream tip gap 84 is defined as the gap progression 83, which in some embodiments may be between about 400 microns and 1400 microns. The upstream tip gap 82 is larger than the downstream tip gap 84. In addition, the gap spacing of the teeth progressively decreases from the upstream side 34 to the downstream side 36. This progression of the tooth gap distances creates passive feedback forces, which are discussed hereinafter, that act on the seal ring 46. Referring to FIG. 4, there is illustrated a cross-sectional view of an alternative embodiment of a raised lance seal assembly 100 which also illustrates the progressive decrease in tooth gap distances from the upstream side 34 to the downstream side 36. Such "up-down" features may be useful in generating multiple tortuous paths for the leakage current. As illustrated in FIGS. 3 and 4, the distance 86 between adjacent teeth may be uniform or uneven. For example, For example, in one embodiment, the distance 86 may increase in the course from the upstream side 34 to the downstream side 46. Furthermore, the width of the labyrinth seal 88 depends on the differential pressure across it. Finally, gases escape through the leakage path 90 existing between the tip of each tooth and the orbiting member 20, and finally through the downstream tip gap 84. Thus, the downstream tip gap 84 is configured to reduce the amount of gases that escape through the path 90. to reduce.
    Other dimensions illustrated in Figures 3 and 4 include the distance 92 between the sealing ring 46 and the plate 44. The minimum value of the distance 92 should allow for expected radial transitions. The maximum value of the distance 92 is determined by space constraints. The width 94 depends on the differential pressure across the seal, as the plate 44 should not significantly flex due to the differential pressure.
    FIG. 5 shows a cross-sectional view of an alternative embodiment of a toothed seal assembly 110 on the orbiting member 20. In the illustrated embodiment, all aspects of the teeth, including height, pitch, and configuration, may be the same as those on the seal ring in FIG 3 arranged teeth. The sealing ring 46 is similar to the ring in FIG. 3, except that instead of teeth arranged on the surface facing the peripheral element 20, an abradable coating 112 is provided on the ring. In some embodiments, the abradable coating 112 may include nickel, chromium, aluminum, hexagonal boron nitride, iron, or a combination of these. Other abradable materials may be used. The composition of the abradable coating 112 is such that in the event that the tips of any of the teeth contact the coating, the coating preferably wears without damage to the teeth. In the particular embodiment illustrated, the downstream tip gap 84 and the upstream tip gap 82 represent the distances between the abradable coating 112 of the seal ring and the tips of the downstream tooth 72 and the upstream tooth 70, respectively. Further elements illustrated in FIG 3, are explained above.
    Fig. 6 shows a cross-sectional view of an alternative embodiment of a multi-plate seal assembly 120. In the illustrated embodiment, in addition to the intermediate plate 44, an upstream plate 122 and a downstream plate 124 are present. The addition of the upstream and downstream plates creates a more tortuous leakage path 80. Specifically, any gases that pass through the leakage path 80 can pass through the gap # 1 126 between the upstream plate 122 and the upstream portion of the seal ring 46, gap # 2 128 between the upstream portion of the ring and the intermediate plate 44, the gap # 3 130 between the plate 44 and the downstream portion of the ring, and the gap # 4 142 between the downstream portion of the ring and the downstream plate 124. These gaps provide flow resistance to the leakage current and should be minimized to reduce leakage current. Such a path 80 may reduce the gas leakage amount compared to the paths illustrated in FIGS. 3 and 5. Other elements illustrated in FIG. 6 which are similar to those illustrated in FIG. 3 are explained above.
    Fig. 7 shows a cross-sectional view of an alternative embodiment of a seal assembly 140 having teeth disposed on both the seal ring 46 and the orbiting member 20. In the illustrated embodiment, the seal ring 46 may include a plurality of arcuate teeth, including an upstream tooth 142 and a downstream tooth 144, disposed on the surface facing the orbiting member 20. Further, the peripheral member 20 may include a plurality of arcuate teeth, including an upstream tooth 146 and a downstream tooth 148, disposed on the surface facing the seal ring 46. The spacing 86 between adjacent teeth on the sealing ring 46 may be different as compared to the spacing 87 between adjacent teeth on the rotating element 20. As with the seal assembly 60 illustrated in FIG. 3, the distances 86 and 87 between all teeth may be uniform or uneven. The width of the labyrinth seal 150 depends on the differential pressure across it and may be smaller than that of other labyrinth seals due to the smaller gap. The use of interdigitated teeth may be advantageous in that the leakage path 90 is more tortuous than in an embodiment with only a single set of teeth, resulting in less leakage. In some embodiments, an abradable coating, similar to that illustrated in FIG. 5, may be provided on the seal ring 46. Other elements illustrated in FIG. 7 similar to those illustrated in FIGS. 3-6 are discussed above.
    Fig. 8 is a graph illustrating simulation results of the pressure distribution among the seal ring teeth as a function of the last tooth gap or tip gap. In the graph, the abscissa (x-axis) 162 represents the axial position of a tooth in centimeters, and the ordinate (y-axis) 164 represents the pressure under the tooth in megapascals for an upstream pressure of 12.8 MPa and a downstream one Pressure of 10.3 MPa. The curves on this graph are referred to as the axial pressure profile. Three cases are illustrated: The first case 166 shows the pressure distribution when the last gap distance is 125 micrometers, the second case 168 represents a gap of 380 micrometers, and the last case 169 shows the results at a gap of 635 micrometers. These three cases are used in the simulation to indicate the change in pressure profile (and the resulting force on the seal ring) as the seal ring moves radially inward or outward. In any case, there are five teeth arranged at the same positions along the axial direction, and the width of the gasket is the same. The distance between all teeth increases in the course from left to right along the abscissa 162, which makes the distance uneven. In addition, the tooth splitting progression is the same for each case, approximately equal to 760 microns, and the progression occurs linearly. In other words, and using Case 166 as an example, the gaps in the course from the upstream tooth to the downstream tooth 890, 690, 508, 318 and 125 would be microns. Similarly, for the 168 case, the gap of the upstream tooth would be 1140 microns, and in the case 169 would be 1395 microns. In the illustrated graph, the pressure under each respective tooth is higher in the case 166 than in the cases 168 and 169. Thus, the pressure profile changes as the gap under the last tooth changes due to the change in the tip gap, as shown in FIG. 8 is illustrated.
    Fig. 9 is a graph illustrating the balance of forces in the radial direction for the seal ring 46, wherein closing and opening forces acting on the seal ring are indicated at 190 and 192, respectively. There are two different forces acting on a sealing ring. First, hydrodynamic forces are lifting forces generated by the rotation of the rotor on the sealing ring. Second, hydrostatic forces are forces generated due to the differential pressure across the seal assembly or any resulting leakage current on the seal ring. The hydrodynamic forces are insignificant compared to the hydrostatic forces. The passive feedback of the disclosed embodiments is configured to affect hydrostatic forces resulting in a more robust design. Returning to FIG. 9, longer arrows represent greater pressure. In one embodiment, the distance 182 from the upstream side 34 to the beginning of the gap for the plate may be between about 2.5 cm and 5 cm. Similarly, the distance 186 from the gap to the downstream side 36 may also be between about 2.5 cm and 5 cm. The width of the gap 184 may be between about 1.2 cm and 4.0 cm. The distances 182, 184 and 186 may all be configured to vary the closing force 190. The distance 188 between all teeth may be uniform or uneven. The arrows illustrated as pointing down and acting on the top of the seal ring represent the closing force 190. Accordingly, the upwardly directed arrows acting on the underside of the seal ring represent the opening force 192. In the illustrated graph, three different amounts of pressure are used exercised as closing forces. First, a high pressure 194 is applied to the upstream portions of the seal ring corresponding to the upstream distance 182. Second, a mean pressure 196 is applied to the gap portion of the seal ring corresponding to the gap distance 184. Finally, a slight pressure 198 is exerted on the downstream portions of the seal ring corresponding to the downstream distance 186. The pressure and thus the closing force in each section are unaffected by the radial movement of the sealing ring, as shown by the arrows having the same height.
    When the opening forces 192 are considered, the pressure on the upstream side 194 corresponds to the high pressure closing force, and the pressure on the downstream side 198 corresponds to the low pressure closing force. The opening forces 192 progressively decrease in the course from the upstream to the downstream side depending on the reduction of the tooth gap. The area under the pressure profile in Figure 8 corresponds to the opening force 192 on the sealing ring 46. For a small tip gap, as in Case 166, the area under the pressure profile is greater than the area under the pressure profile for a large tip gap, as in Case 169 Thus, the opening force is greater for a small nip and smaller for a large nip. Large nicks result in negative or inward net radial forces, while small nicks result in positive or outward net radial forces. The gap where the closing and opening forces are equal represents the equilibrium gap. The equilibrium gap is affected by a number of variables, including the gap progression profile (eg, linear, square, parabolic, and the like), the spacing between the teeth, the widths 182, 184, and 186 of the gasket sections, and the ratio of the front gap to the rear gap belong. These variables can be manipulated to achieve a desired equilibrium gap where the leakage is reduced.
    Fig. 10 is a graph showing simulation results illustrating the concept of an equilibrium gap. In the graph, the abscissa 172 represents the last tooth gap in microns, while the ordinate 174 represents the net radial force in Newtons. Here, a positive radial force corresponds to an outward radial force that causes the seal ring to open, and a negative radial force corresponds to an inward radial force that causes the seal ring to close. Curve 176 shows the change in net radial force as a function of the last tooth gap. The equilibrium gap 178 is when the net radial force is zero, resulting in no movement of the seal ring. In this simulation, the equilibrium gap 178 occurs at approximately 340 microns. The relationship between the equilibrium gap and the pressure ratio will be explained hereinafter with reference to FIG. 11.
    Fig. 11 is a graph showing simulation results illustrating how the equilibrium gap depends on the pressure ratio between the upstream and downstream pressures. In the graph, the abscissa 202 represents the last tooth pitch in microns, while the ordinate 204 represents the net radial force in Newtons. There are three cases illustrated. The first case 206 shows the radial forces when the upstream pressure is high, the second case 208 represents the radial forces when the pressure is near an intermediate value, and the last case 209 shows the results at a low pressure. In all three cases, the ratio of the upstream pressure to the downstream pressure is the same; the only difference for each case is the pressure difference. Thus, the simulation results of these three cases show that for a given value of the ratio between the upstream and downstream pressures, the seal assembly will have approximately the same value of equilibrium gap regardless of the value of the pressures.
    Therefore, an advantage of the proposed seal is that even in the presence of larger rotor transition events, a small gap is maintained, resulting in smaller leakage and higher efficiency. This is because passive feedback causes radially outward forces on the seal ring when the gap is small and radially inward forces when the gap is large. This shows the passive feedback phenomenon exhibited by the progressive gap seal assemblies described in the previous embodiments. Such passive feedback functions without any additional sensors or actuators that may fail or operate unreliably in the harsh environment of a turbine or compressor. As pressure conditions change, the equilibrium gap adapts in such a way as to reduce the risk of turbine or compressor damage and leakage paths.
    parts list
    [0026]<Tb> 10 <September> Turbine System<Tb> 12 <September> compressor section<Tb> 14 <September> combustor section<Tb> 16 <September> turbine section<tb> 18 <SEP> stationary housing<tb> 20 <SEP> revolving element<Tb> 22 <September> axis<Tb> 24 <September> blades<tb> 26 <SEP> stationary blades<tb> 28 <SEP> Location of the seal assembly between blade and stationary housing<tb> 30 <SEP> Location of the sealing arrangement between the rotating element and the stationary blade<tb> 32 <SEP> Location of the sealing arrangement between the rotating element and the stationary housing<tb> 34 <SEP> upstream side<tb> 36 <SEP> downstream page<tb> 40 <SEP> axial axis<tb> 42 <SEP> radial axis<tb> 44 <SEP> arcuate plate<tb> 46 <SEP> Arcuate Sealing Ring<Tb> 47 <September> gap<Tb> 48 <September> biasing members<tb> 50 <SEP> with the seal ring coupled end of the biasing member<tb> 52 <SEP> with the stationary housing or the arcuate plate coupled end of the biasing member<tb> 54 <SEP> arcuate teeth<tb> 60 <SEP> Sealing arrangement with teeth on the sealing ring<tb> 66 <SEP> upstream diffraction devices<tb> 68 <SEP> downstream diffraction devices<tb> 70 <SEP> tooth on the upstream side<tb> 72 <SEP> tooth on the downstream side<tb> 74 <SEP> front gap<tb> 76 <SEP> rear gap<Tb> 78 <September> Pocket<Tb> 79 <September> pocket height<tb> 80 <SEP> Leakage path between the arcuate plate and the arcuate seal ring<tb> 82 <SEP> upstream nip<Tb> 83 <September> gap progression<tb> 84 <SEP> downstream tip gap<tb> 86 <SEP> Distance between adjacent teeth<tb> 87 <SEP> Distance between adjacent teeth on the rotating element<tb> 88 <SEP> Width of the labyrinth seal<tb> 90 <SEP> Leakage path between the teeth and the revolving element<tb> 92 <SEP> Distance between the arcuate seal ring and the arcuate plate<tb> 94 <SEP> Width of the vertical element of the arcuate plate<tb> 100 <SEP> Sealing arrangement with raised lugs<tb> 102 <SEP> sublime approaches<tb> 110 <SEP> Sealing arrangement with teeth on the rotating element<tb> 112 <SEP> abradable coating<tb> 120 <SEP> Sealing arrangement with multiple arcuate plates<tb> 122 <SEP> upstream arcuate plate<tb> 124 <SEP> downstream arcuate plate<tb> 126 <SEP> The gap between the upstream arcuate plate and the upstream portion of the arcuate seal ring<tb> 128 <SEP> gap between the upstream portion of the arc-shaped seal ring and the arc-shaped intermediate plate<tb> 130 <SEP> The gap between the arcuate intermediate plate and the downstream portion of the arcuate seal ring<tb> 132 <SEP> gap between the downstream portion of the arcuate seal ring and the downstream arcuate plate<tb> 140 <SEP> Sealing arrangement with teeth on the arcuate sealing ring and peripheral element<tb> 142 <SEP> Upstream arcuate seal ring tooth<tb> 144 <SEP> downstream arcuate seal ring tooth<tb> 146 <SEP> Upstream tooth of the orbiting member<tb> 148 <SEP> downstream tooth of the revolving element<tb> 150 <SEP> Width of the labyrinth seal<tb> 160 <SEP> Graphic of the pressure distribution under the sealing ring as a function of the last tooth gap<tb> 162 <SEP> axial position of the tooth (abscissa)<tb> 164 <SEP> Pressure under the tooth (ordinate)<tb> 166 <SEP> Case when the last tooth gap is 125 microns<tb> 168 <SEP> Case when the last tooth gap is 380 microns<tb> 169 <SEP> Case when the last tooth gap is 635 microns<tb> 170 <SEP> Graphic illustrating the equilibrium gap<tb> 172 <SEP> last tooth gap (abscissa)<tb> 174 <SEP> Net Radial Force (ordinate)<tb> 176 <SEP> Graph illustrating the change in net radial force as a function of the last tooth gap<Tb> 178 <September> equilibrium gap<tb> 180 <SEP> Graph illustrating the balance of forces in the radial direction<tb> 182 <SEP> Distance from the upstream side to the beginning of the gap<tb> 184 <SEP> Width of the gap<tb> 186 <SEP> Distance from the gap to the downstream side<tb> 188 <SEP> Distance between adjacent teeth<Tb> 190 <September> closing forces<Tb> 192 <September> opening forces<tb> 194 <SEP> high pressure<Tb> 196 <September> intermediate pressure<tb> 198 <SEP> low pressure<tb> 200 <SEP> Graph showing how the equilibrium gap depends on the pressure ratio<tb> 202 <SEP> last tooth gap (abscissa)<tb> 204 <SEP> net radial force (ordinate)<tb> 206 <SEP> Case when the upstream pressure is high<tb> 208 <SEP> Case when the upstream pressure is an intermediate pressure<tb> 209 <SEP> Case when the upstream pressure is low
    权利要求:
    Claims (10)
    [1]
    A sealing arrangement for a turbomachine, the turbomachine comprising a stationary housing (18) and a stationary housing (18) penetrating rotor (20) which rotates about an axis (22), wherein the sealing arrangement between the rotor (20) and stationary Housing (18) is arranged sealingly and comprises:at least one arcuate plate (44) coupled to an inner surface of the stationary housing (18) and disposed in a radial plane of the rotor (20);a sealing ring (46) segmented in a circumferential direction of the rotor (20) and disposed between the rotor (20) and the plate (44), the sealing ring (46) being positioned to rotate relative to the plate (44) a radial direction (42) perpendicular to the axis (22) of the rotor (20) to move;a biasing member (48) disposed between the arcuate plate (44) and the seal ring (46) is coupled to both and configured to radially bias the segmented seal ring (46) toward the rotor (20) between arcuate plate (44) and sealing ring (46) forms a radial gap in the idle state; anda plurality of arcuate, circumferentially extending sealing elements (54) disposed between the sealing ring (46) and the rotor (20) in an axial direction (40) of the rotor (20) offset from each other, wherein sealing gaps (82, 84) of the respective Sealing members (54) progressively decrease in the course of a first side (34) of the seal assembly to a second side (36) of the seal assembly such that passive feedback of the hydrostatic forces generated by the differential pressure across the seal assembly during operation of the Turbomachine is caused so that when the sealing gaps decrease, caused by the hydrostatic forces generated outward Nettoradialkräfte cause the sealing ring (46) to move away from the rotor (20), and as the sealing gaps increase, by the generated hydrostatic Forces induced inward net radial forces to cause the sealing ring (46) to join the Rotor (20) to move.
    [2]
    The seal assembly of claim 1, wherein the biasing member (48) serves as a bearing and restricts movement of the seal ring (46) in the axial direction (40) and permits movement of the seal ring (46) in the radial direction (42).
    [3]
    3. A seal assembly according to claim 1, configured such that due to the passive feedback of the hydrostatic forces at a constant ratio of the pressure on the first side to the pressure on the second side, an equilibrium gap between the plurality of sealing elements (54) and the rotor (20 ) maintains the same value regardless of the value of the upstream and downstream pressures.
    [4]
    4. A seal assembly according to claim 1, wherein the plurality of arcuate sealing elements (54) are coupled to the sealing ring (46).
    [5]
    5. Sealing arrangement according to claim 1, wherein the plurality of arcuate sealing elements (54) are coupled to the rotor (20).
    [6]
    6. Sealing arrangement according to claim 1,wherein a first subset of the plurality of arcuate sealing elements (54) is coupled to the sealing ring (46);wherein a second subset of the plurality of arcuate sealing elements (54) is coupled to the rotor (20); andwherein the first subset of the plurality of arcuate sealing elements (54) and the second subset of the plurality of arcuate sealing elements (54) are arranged such that the sealing elements (54) in the axial direction (40) intermesh with each other.
    [7]
    7. A sealing arrangement according to claim 1, wherein an abradable coating (112) on the rotor (20) facing surface of the sealing ring (46) is arranged.
    [8]
    8. Sealing arrangement according to claim 1,the biasing member (48) having a plurality of biasing members mechanically coupled to the arcuate plate (44) and the sealing ring (46); andwherein the plurality of biasing members are arranged to allow the sealing ring (46) to move in the radial direction (42) but restrict movement in the axial direction.
    [9]
    9. Sealing arrangement according to claim 1, comprising:a first gap (74) formed between two radially extending opposed first surfaces of the plate (44) and the seal ring (46), and a second gap (76) disposed between two radially opposed opposing second surfaces Plate (44) and the sealing ring (46), wherein the first and the second gap (74, 76) for reducing leakage through the first and the second gap (74, 76) between the first and the second side (34 , 36) of the seal assembly are between 50 microns and 250 microns.
    [10]
    A turbine or compressor, comprising: a rotor (20) rotating about an axis (22), a stationary housing (18) surrounding the rotor (20), and a circumferentially segmented seal assembly according to claim 1, which is disposed between the rotor (20) and the stationary housing (18).
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    同族专利:
    公开号 | 公开日
    CH702606A2|2011-07-29|
    US8360712B2|2013-01-29|
    US20110182719A1|2011-07-28|
    CN102135019A|2011-07-27|
    JP5830247B2|2015-12-09|
    CN102135019B|2015-06-03|
    JP2011169460A|2011-09-01|
    DE102011000203A1|2011-07-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4351532A|1975-10-01|1982-09-28|United Technologies Corporation|Labyrinth seal|
    JPS57176960U|1981-05-06|1982-11-09|
    US4513975A|1984-04-27|1985-04-30|General Electric Company|Thermally responsive labyrinth seal|
    US5143383A|1984-06-04|1992-09-01|General Electric Company|Stepped tooth rotating labyrinth seal|
    US5002288A|1988-10-13|1991-03-26|General Electric Company|Positive variable clearance labyrinth seal|
    US5029876A|1988-12-14|1991-07-09|General Electric Company|Labyrinth seal system|
    US5603510A|1991-06-13|1997-02-18|Sanders; William P.|Variable clearance seal assembly|
    US5224713A|1991-08-28|1993-07-06|General Electric Company|Labyrinth seal with recirculating means for reducing or eliminating parasitic leakage through the seal|
    JPH06173609A|1992-12-08|1994-06-21|Fuji Electric Co Ltd|Gland part sealing mechanism for steam turbine|
    US5599026A|1995-09-06|1997-02-04|Innovative Technology, L.L.C.|Turbine seal with sealing strip and rubbing strip|
    US5890873A|1997-08-13|1999-04-06|General Electric Co.|Labyrinth seal for a turbine bucket cover|
    KR100569648B1|1999-02-11|2006-04-11|제너럴 일렉트릭 캄파니|Variable clearance packing ring with clips for preventing circumferential displacement|
    US6394459B1|2000-06-16|2002-05-28|General Electric Company|Multi-clearance labyrinth seal design and related process|
    US6547522B2|2001-06-18|2003-04-15|General Electric Company|Spring-backed abradable seal for turbomachinery|
    US6877952B2|2002-09-09|2005-04-12|Florida Turbine Technologies, Inc|Passive clearance control|
    US7419164B2|2006-08-15|2008-09-02|General Electric Company|Compliant plate seals for turbomachinery|
    US7717671B2|2006-10-16|2010-05-18|United Technologies Corporation|Passive air seal clearance control|
    FR2915535B1|2007-04-30|2009-07-24|Snecma Sa|ROTATING MACHINE COMPRISING A PASSIVE AXIAL BALANCING SYSTEM|
    US20090304493A1|2008-06-09|2009-12-10|General Electric Company|Axially oriented shingle face seal for turbine rotor and related method|CA2905936C|2013-03-15|2021-05-04|Advanced Technologies Group, Inc.|Self-adjusting non-contact seal|
    US8919781B2|2003-05-01|2014-12-30|Advanced Technologies Group, Inc.|Self-adjusting non-contact seal|
    US8142141B2|2009-03-23|2012-03-27|General Electric Company|Apparatus for turbine engine cooling air management|
    US8277172B2|2009-03-23|2012-10-02|General Electric Company|Apparatus for turbine engine cooling air management|
    DE102009016803A1|2009-04-09|2010-10-14|Rolls-Royce Deutschland Ltd & Co Kg|Labyrinth rubbing seal for a turbomachine|
    US9181817B2|2010-06-30|2015-11-10|General Electric Company|Method and apparatus for labyrinth seal packing rings|
    US9074486B2|2011-01-31|2015-07-07|General Electric Company|Method and apparatus for labyrinth seal packing ring|
    US8932001B2|2011-09-06|2015-01-13|General Electric Company|Systems, methods, and apparatus for a labyrinth seal|
    JP5774963B2|2011-10-21|2015-09-09|三菱重工業株式会社|sealing device|
    US8985938B2|2011-12-13|2015-03-24|United Technologies Corporation|Fan blade tip clearance control via Z-bands|
    EP2642081A1|2012-03-21|2013-09-25|Alstom Technology Ltd|Labyrinth seal for turbines|
    US9567908B2|2012-04-27|2017-02-14|General Electric Company|Mitigating vortex pumping effect upstream of oil seal|
    US9322478B2|2012-07-31|2016-04-26|General Electric Company|Seal system and method for rotary machine|
    CN102797509B|2012-08-24|2014-09-17|中国南方航空工业有限公司|Shock absorption/lubrication structure of turbine blade|
    GB2531081B|2013-06-21|2018-03-14|United Technologies Corp|Seals for gas turbine engine|
    CN103410700B|2013-07-12|2016-07-06|沈阳理工大学|A kind of axial labyrinth seal toothing of parabola|
    EP3060763B1|2013-10-21|2020-04-15|United Technologies Corporation|Incident tolerant turbine vane gap flow discouragement|
    CN103982247B|2014-05-21|2016-04-06|南京博沃科技发展有限公司|A kind of self trim packing and Installation and Debugging method thereof|
    US10968917B2|2014-10-27|2021-04-06|Zhongshan Broad-Ocean Motor Manufacturing Co., Ltd.|Blower comprising a pressure measuring connector|
    JP6161208B2|2014-10-30|2017-07-12|三菱日立パワーシステムズ株式会社|Clearance control type seal structure|
    DE102014224283A1|2014-11-27|2016-06-02|Robert Bosch Gmbh|Compressor with a sealing channel|
    DE102014224285A1|2014-11-27|2016-06-02|Robert Bosch Gmbh|Compressor with a sealing channel|
    DE102014224757A1|2014-12-03|2016-06-09|Robert Bosch Gmbh|Compressor with a sealing channel|
    CN106640735A|2015-08-03|2017-05-10|北京航天动力研究所|Low temperature liquid hydrogen liquid oxygen pump labyrinth sealing device|
    WO2017072844A1|2015-10-27|2017-05-04|三菱重工業株式会社|Rotary machine|
    FR3050250B1|2016-04-15|2018-04-13|Safran Transmission Systems|NON-CONTACT SEAL OF LABYRINTH TYPE OBTAINED BY ADDITIVE MANUFACTURE|
    US10690251B2|2016-09-23|2020-06-23|General Electric Company|Labyrinth seal system and an associated method thereof|
    FR3059041B1|2016-11-21|2020-05-08|Safran Aircraft Engines|ROTOR / STATOR STEERING DEVICE WITH SPRING SLEEVE|
    EP3333372A1|2016-12-09|2018-06-13|General Electric Technology GmbH|Turbine, corresponding steam turbine and operating method|
    US10731500B2|2017-01-13|2020-08-04|Raytheon Technologies Corporation|Passive tip clearance control with variable temperature flow|
    JP6917162B2|2017-02-28|2021-08-11|三菱パワー株式会社|Blades, rotor units, and rotating machines|
    US10883373B2|2017-03-02|2021-01-05|Rolls-Royce Corporation|Blade tip seal|
    US11199104B2|2017-05-15|2021-12-14|Raytheon Technologies Corporation|Seal anti-rotation|
    US10598038B2|2017-11-21|2020-03-24|Honeywell International Inc.|Labyrinth seal with variable tooth heights|
    DE102017220880A1|2017-11-22|2019-05-23|Efficient Energy Gmbh|Electric motor, heat pump with the electric motor, method of manufacturing the electric motor and method of operating the electric motor using a labyrinth seal|
    DE102017221660A1|2017-12-01|2019-06-06|MTU Aero Engines AG|Module for a turbomachine|
    US11118469B2|2018-11-19|2021-09-14|General Electric Company|Seal assembly for a turbo machine|
    US20210254487A1|2020-02-17|2021-08-19|Pratt & Whitney Canada Corp.|Labyrinth seal with variable seal clearance|
    CN111878447A|2020-06-23|2020-11-03|珠海格力电器股份有限公司|Compressor with good sealing effect and fuel cell air compressor|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-08-31| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US12/692,369|US8360712B2|2010-01-22|2010-01-22|Method and apparatus for labyrinth seal packing rings|
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