• 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:
    A multi-stage turbine sealing system includes a plurality of first interstage seal subsystems (42) circumferentially disposed about a multi-stage turbine rotor shaft and extending axially between a first turbine stage (44) and a second turbine stage (46) of the multi-stage turbine. Each of the interstage seal subsystems (42) includes a plurality of near flow path seal segments (48). The first interstage seal subsystem (42) also includes a front cover plate (54) disposed axially between a first turbine wheel (56) of the first turbine stage (44) and the near flow path seal segment (48) and a rear cover plate (58) disposed axially between the Nahströmungspfaddichtungssegment (48) and a second turbine wheel (60) of the second turbine stage (46) is arranged on. In addition, each of the front cover plate (54) and the rear cover plate (58) extends radially to a first stage bucket or second stage bucket (64).
    公开号:CH710475A2
    申请号:CH01708/15
    申请日:2015-11-23
    公开日:2016-06-15
    发明作者:Samudrala Omprakash；Sevincer Edip；Michael Webster Jonathan；Jorge Casanova Fernando
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    BACKGROUND
    The present application relates generally to gas turbines, and more particularly to interstage gaskets within gas turbines.
    Generally, gas turbines burn a mixture of compressed air and fuel to produce hot combustion gases. The combustion gases may flow through one or more turbine stages to produce power for a load and / or a compressor. A pressure loss may occur between the stages, allowing leakage of a fluid, such as the combustion gases, through unintended paths. It is desirable to confine the combustion gases within a defined annular flow path to shield certain rotor parts and maximize power draw. In addition, turbine rotor wheels that carry the blades (blades) are exposed to considerable thermal stresses during their service life and therefore must be cooled. Therefore, seals, e.g. mechanical seals are placed between the stages to reduce fluid leakage between the stages and to prevent the turbine rotor wheels from being directly exposed to hot gases. Unfortunately, the seals in the field may not be serviceable, or a considerable amount of work is required to replace the seals in the field. In addition, the shape of the seals can make access to internal components of the turbine more difficult. In addition, the seals may require additional components, such as spacer wheels between two turbine wheels, to ensure correct axial and radial alignment of the seals. Static seals can also be used that require axial extensions of the two turbine wheels that meet in the middle to accommodate the static seal. However, this does not isolate the turbine wheel edges from the hot gas path, thereby requiring high performance alloys for the rotor parts at a high cost to withstand the harsh temperatures in the case of hot gas pickup. In addition, the static seals can not be applied to bolted rotor architectures where access to the wheel flange bolts is required during assembly / disassembly.
    There is therefore a need for improved gas turbine interstage seal systems. Such gaskets should improve overall system efficiency and be inexpensive to assemble and manufacture and provide increased life for the associated parts.
    SHORT DESCRIPTION
    In accordance with an example of the present technology, a seal system for a multistage turbine includes a plurality of first interstage seal subsystems circumferentially disposed about a rotor wheel shaft of the multistage turbine and extending axially between a first turbine stage and a second turbine stage of the multistage turbine. Each of the first interstage seal subsystems includes multiple near flow path seal segments. The first interstage seal subsystem also includes a front cover plate disposed axially between a first turbine stage first turbine wheel and the near flow path seal segment and a rear cover plate disposed axially between the near flow path seal segment and a second turbine stage second turbine wheel. In addition, both the front cover plate and the rear cover plate extend radially to a first stage blade and a second stage blade, respectively.
    [0005] In any embodiment of the sealing system, it may be advantageous for both the first and second turbine wheels to have a plurality of dovetail slots configured to mount a plurality of blades or blades.
    In any embodiment of the sealing system, it may be advantageous for a side of the first turbine wheel facing the front cover plate to have a wheel rim with a plurality of tab projections on an inner diameter of the wheel rim in a radially inward direction.
    [0007] In any embodiment of the sealing system, it may be advantageous for the front cover plate to have a plurality of curved L-shaped seats at an inner end to permit radial and circumferential retention when in the first turbine wheel side with the plurality of tab projections attached to the inner diameter of the wheel rim.
    In any embodiment of the sealing system, it may be advantageous that the sealing system further comprises a first sealing wire disposed in a sealing wire groove of the front cover plate and placed axially between the front cover plate and the first stage blade to the rim of the first Turbine wheel from a flow to isolate from the hot gas path.
    In any embodiment of the sealing system, it may be advantageous that the sealing system further comprises a front axial retaining ring, which is arranged between the plurality of tab projections on the inner diameter of the wheel rim of the first turbine wheel and the front cover plate to the front cover plate with the lock first turbine wheel.
    In any embodiment of the sealing system, it may be advantageous for a side of the second turbine wheel facing the rear cover plate to have a wheel rim with a plurality of tab projections on an inner diameter of the wheel rim in a radially inward direction.
    In any embodiment of the sealing system, it may be advantageous for the rear cover plate to have a plurality of curved L-shaped seats at an inner end to allow retention in a radial and circumferential direction when on the side of the second Turbine wheel with the plurality of tab projections on the inner diameter of the wheel rim is mounted.
    In any embodiment of the sealing system, it may be advantageous that the sealing system further comprises a second sealing wire disposed in a sealing wire groove of the rear cover plate and placed axially between the rear cover plate and the second stage turbine blades around the wheel rim of the second Turbine wheel from a flow to isolate from the hot gas path.
    In any embodiment of the sealing system, it may be advantageous that the sealing system further comprises a rear axial retaining ring disposed between the plurality of tab projections on the inner diameter of the wheel rim of the second turbine wheel and the rear cover plate to the rear cover plate with the lock second turbine wheel.
    In any embodiment of the sealing system, it may be advantageous for the rear cover plate to have an angel wing structure at an outer end of the rear cover plate.
    [0015] In any embodiment of the sealing system, it may be advantageous for the rear cover plate to have a retaining hook portion disposed on a side facing the second turbine wheel for axial retention with each of a blade retaining hook of the second stage buckets.
    In any embodiment of the sealing system, it may be advantageous for the near flow path seal segment to have an angel wing structure at an outer end toward a front of the near flow path seal segment.
    In any embodiment of the sealing system, it may be advantageous for a portion of the front cover plate attached to the first turbine wheel to extend in part along a blade shank of the first stage bucket and form a hook, and the near flow path seal segment on the first turbine shroud Hook the front cover plate is mounted toward a front.
    In any embodiment of the sealing system, it may be advantageous for the rear cover plate to have a receiving structure between a plurality of angel wing lands to retain the near flow path sealing segment at the rear.
    [0019] In any embodiment of the sealing system, it may be advantageous for the receiving structure to have a plurality of recessed round recesses that enable locking with a plurality of protruding tabs disposed below the near flow path seal segment at the rear to circumferentially retain the near flow path seal segment ,
    In any embodiment of the sealing system, it may be advantageous for the sealing system to further include a plurality of intersegment key seals disposed on either side of each of the plurality of near flow path seal segments to avoid inter-segment gap leakage.
    In any embodiment of the sealing system, it may be advantageous for the rear cover plate to extend to a plurality of flange bolts disposed on a plurality of blades to facilitate cooling flow supply passages.
    In accordance with an example of the present technology, a method of assembling a sealing system of a multi-stage turbine is disclosed. The multistage turbine has a plurality of first stage buckets and a plurality of second stage buckets disposed on a first turbine wheel and on a second turbine wheel, respectively. The method includes installing each of the plurality of second stage buckets into each of a plurality of dovetail slots on the second turbine wheel. The method also includes placing a rear seal wire in a seal wire groove of each of the plurality of back cover plates. The method further includes attaching a corresponding portion of each of the plurality of back cover plates to the elongated plurality of second stage buckets by moving each of the plurality of back cover plates axially and then radially outwardly so that a plurality of blade retention hooks fully engage are with the corresponding portion of the rear cover plate, wherein the corresponding portion has a retaining hook structure. In addition, the method includes sliding the plurality of second stage buckets together with the rear cover plate into the plurality of dovetail slots. The method also includes placing a rear axial retaining ring between a plurality of tab projections on an inner diameter of the rim of the second turbine wheel and the rear cover plate to lock the rear cover plate to the second turbine wheel. The method also includes mounting a plurality of bent L-shaped seats at an inner end of each of the plurality of front cover plates with a plurality of tab projections on an inner diameter of a wheel rim of the first turbine wheel, such that the plurality of bent L-shaped ones Sitting fully engaged with the plurality of tab projections. In addition, the method includes placing a front axial retaining ring between a plurality of tab projections on an inner diameter of the wheel rim of the first turbine wheel and the front cover plate to lock the front cover plate to the first turbine wheel. The method includes attaching a front end and a rear end to each of the plurality of Nahströmungspfaddichtungssegmenten on a hook portion of the front cover plate and a receiving structure of the rear cover plate and installing each of the plurality of first stage buckets in each one of a plurality of Dovetail slots of the first turbine wheel.
    [0023] In accordance with another example of the present technology, a gas turbine system includes a plurality of first stage buckets attached to a first turbine wheel and a plurality of second stage buckets attached to a second turbine wheel. The gas turbine system also includes a plurality of first interstage seal subsystems circumferentially disposed about a rotor wheel shaft of the gas turbine and extending axially between a first turbine stage and a second turbine stage of the gas turbine. Each of the plurality of first interstage seal subsystems has a plurality of near flow path seal segments. The first interstage seal subsystem also includes a front cover plate disposed axially between a first turbine stage first turbine and the near flow path seal segment and a rear cover plate disposed axially between the near flow path seal segment and a second turbine stage second turbine each extending from the front cover plate each extending radially to a blade of the first stage and a blade of the second stage.
    DRAWINGS
    These and other features, aspects, and advantages 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 represent like parts throughout the drawings, wherein:<Tb> FIG. 1 <SEP> is a schematic flowchart of a gas turbine that may utilize a turbine gasket in accordance with an example of the present technology;<Tb> FIG. 2 <SEP> is a cross-sectional side view of a gas turbine along a longitudinal axis in accordance with an example of the present technology;<Tb> FIG. 3 is a partial perspective view of an interstage seal subsystem of a gas turbine in accordance with an example of the present technology;<Tb> FIG. 4 is a perspective view of the first turbine wheel of the gas turbine in accordance with an example of the present technology;<Tb> FIG. Fig. 5 is a perspective view of the front cover plate of the interstage seal subsystem in accordance with an example of the present technology;<Tb> FIG. FIG. 6 is a perspective view of a second turbine wheel of the gas turbine in accordance with an example of the present technology; FIG.<Tb> FIG. Fig. 7 is a perspective view of a back cover plate of the intermediate stage subsystem 42 in accordance with an example of the present technology;<Tb> FIG. 8 is a perspective view of a sealing system having the interstage seal subsystem in accordance with an example of the present technology;<Tb> FIG. 9A <SEP> is a flowchart illustrating the involved steps in a method of assembling a sealing system of a multi-stage turbine in accordance with one embodiment of the present technology; and<Tb> FIG. FIG. 9B is a flowchart illustrating the involved steps in a method of mounting a sealing system of a multi-stage turbine in accordance with an embodiment of FIG. 9A. FIG.
    DETAILED DESCRIPTION
    When elements of various embodiments of the present invention are introduced, the articles "a," "an," "the," and "this," are intended to mean that one or more of These elements may be present. The terms "having", "containing" and "having" are intended to be inclusive and to imply that there may be additional elements other than the specified elements. Any examples of operating parameters are not exclusive of other parameters of the disclosed embodiments.
    FIG. 1 is a block diagram of an exemplary system 10 including a gas turbine 12 that may utilize interstage seals as described in greater detail below. In certain embodiments, the system 10 may include an aircraft, hydropower, locomotive, power generation system, or combinations thereof. The illustrated gas turbine engine 12 includes an air inlet section 16, a compressor 18, a combustor section 20, a turbine 22, and an outlet section 24. The turbine 22 is connected to the compressor 18 via a shaft 26.
    As indicated by the arrows, air may enter the gas turbine 12 through the inlet section 16 and flow into the compressor 18, which compresses the air prior to entering the combustor section 20. The illustrated combustor section 20 includes a combustor shell 28 that is concentrically or annularly disposed about the shaft 26 between the compressor 18 and the turbine 22. The compressed air from the compressor 18 enters combustion chambers 30 where the compressed air may be mixed with fuel and combusted within the combustion chambers 30 to drive the turbine 22. From the combustion chamber section 20, the hot combustion gases flow through the turbine 22, driving the compressor 18 by means of the shaft 26. For example, the combustion gases may exert drive forces on turbine rotor blades within the turbine 22 to drive the shaft 26. After flowing through the turbine 22, the hot combustion gases may exit the gas turbine 12 through the outlet section 24. As discussed below, the turbine 22 may include a plurality of interstage seal subsystems that reduce the leakage of hot combustion gases between the stages of the turbine 22 and reduce the clearances between rotating components of the turbine 22, such as rotor wheels. Throughout the discussion provided herein, reference is made to a set of axes. These axes are based on a cylindrical coordinate system and show a radial direction 13 and a circumferential direction 15 in an axial direction 11 (eg longitudinal direction). In addition, the terms "first" and "second" can be applied to elements of the system 10 to distinguish between recurring instances of a system To distinguish elements. These terms are not intended to imply any order or time limitation on the elements in question.
    FIG. 2 is a cross-sectional side view of one embodiment of the gas turbine 12 of FIG. 1 taken along a longitudinal axis 32. As illustrated, the gas turbine engine 22 has three separate stages 34; however, the gas turbine 22 may include any number of stages 34. Each stage 34 includes a set of airfoils 36 connected to a rotor wheel 38 which may be rotatably connected to the shaft 26 (FIG. 1). The airfoils 36 extend radially outward from the rotor wheels 38 and are partially disposed within the path of the hot combustion gases through the turbine 22. As will be described in more detail below, interstage seal subsystems 42 extend between the stages 34 and are supported by adjacent rotor wheels 38. The interstage seal subsystems 32 may include a plurality of axial components that wed against each other. Accordingly, the interstage seal subsystems 42 may be configured to be maintainable in the field and interchangeable in the field. In addition, the interstage seal subsystems 42 may provide improved cooling of the stages 34. Although the gas turbine illustrated in FIG. 2 is illustrated as a three-stage turbine, the interstage seal subsystems 42 described herein may be used in any suitable turbine type having any number of stages and shafts. For example, the interstage seal subsystems may be included in a single turbine system, a dual turbine system including a low pressure turbine and a high pressure turbine, or in a steam turbine. In addition, the interstage seal subsystems 42 described herein may also be used in a rotary compressor such as the compressor 18 illustrated in FIG. 1. The interstage seal subsystems 42 may be fabricated from various high temperature alloys, such as but not limited to nickel based alloys. The interstage seal subsystems 42 may span one or a plurality of airfoils.
    In certain embodiments, the interstage volume may be cooled by output air tapped from the compressor 18 or provided by another source. However, a flow of hot combustion gases into the interstage volume can reduce the cooling effects. Thus, the interstage seal subsystems 42 may be disposed between adjacent rotor wheels 38 to seal and enclose the interstage volume of the hot combustion gases. Additionally, the interstage seal subsystems 42 may be configured to direct a cooling fluid to the interstage volume or from the interstage volume to the airfoils 36.
    FIG. 3 is a partial perspective view of a first interstage seal subsystem 42 of a gas turbine engine 12 (shown in FIG. 1) in accordance with an example of the present technology. It should be noted that a plurality of such first interstage seal subsystems 42 may be circumferentially disposed about a rotor wheel shaft (shown as shaft 26 in FIG. 1) of a multi-stage gas turbine (shown as 12 in FIG. 1) and located axially between a first turbine stage 44 and a second turbine stage 46 of the multi-stage gas turbine 12 (as shown in Fig. 1) extend. Each of the first interstage seal subsystems 42 includes a plurality of near flow path seal segments 48. As shown, an optimal geometry of the near flow path seal segments 48 includes a curved bottom end portion 50 and a horizontal straight top end portion 52. In other embodiments, the optimum geometry may vary depending on the application. The first interstage seal subsystem 42 also includes a front cover plate 54 disposed axially between a first turbine wheel 56 of the first turbine stage 44 and the near flow path seal segment 48. The first interstage seal subsystem 42 also includes a rear cover plate 58 disposed axially between the near flow path seal segment 48 and a second turbine 60 of the second turbine stage 46. In addition, each of the front cover plate 54 and the rear cover plate 58 extends radially toward a first turbine stage rotor blade 62 and second turbine stage rotor blade 64, respectively.
    As shown in Fig. 3, the first interstage seal subsystem 42 includes a first seal wire 66 disposed in a seal wire groove 68 of the front cover plate 54 and disposed axially between the front cover plate 54 and the first turbine stage rotor blade 62 to isolate a wheel rim of the first turbine wheel 56 from a flow from the hot gas path 69. The first interstate seal subsystem 42 may also include a second seal wire 70 disposed in a seal wire groove 72 of the rear cover plate 58 and disposed axially between the rear cover plate 58 and the second turbine stage rotor 64 to deflect the wheel rim of the second turbine wheel 60 from the flow from the hot gas path 69 to isolate. In addition, the interstage seal subsystem 42 may include a front axial retainer ring 74 disposed between a plurality of tab projections 76 on the inner diameter of the rim of the first turbine 56 and the front cover plate 54 to lock the front cover plate 54 to the first turbine 56. Likewise, the first interstage seal subsystem 42 includes a rearward axial retaining ring 78 disposed between a plurality of tab projections 80 on the inner diameter of the rim of the second turbine wheel 60 and the rear cover plate 58 for locking the rear cover plate 58 to the second turbine wheel 60. Both the front axial retainer ring 74 and the rear axial retainer ring 78 have a 360 degree ring with a single portion. In certain other embodiments, the retaining rings 74, 78 may also be made of a plurality of segments interconnected by mechanical fasteners, such as bolts.
    As shown in FIG. 3, a portion of the front cover plate 54 mounted on the first turbine wheel 56 extends partially along a blade shaft 82 of the first stage blade 62, forming a hook 84, the one the near flow path seal segment 48 is attached to a front side 86. In addition, the near flow path seal segment 48 has an angel wing structure 88 at an outer end toward the front side 86, while the rear cover plate 58 has another angel wing structure 90 at an outer end at the rear side 92. In addition, the rear cover plate 58 has a retaining hook portion 94 disposed on a side facing the second turbine wheel 60 for axial retention with each of a blade retention hook 96 of the second turbine stage buckets 64. As shown in FIG. 3, the rear cover panel has a receiving structure 98 between angel wing lands to retain the Nahströmungspfaddichtungssegmente 48 on the rear side 92. When assembled, both ends of the near flow path sealing segment 48 are in intimate contact with a first retaining ridge 100 within the hook 84 of the front cover plate 54 on the front side 86 and with a second retaining ridge 102 within the receiving structure 98 of the rear cover plate 58 on the rear side 92 First interstage seal subsystem 42 also includes inter-segment wedge gaskets 99 disposed on either side of the near flow path seal segment to avoid inter-segment gap leakage.
    FIG. 4 is a perspective view of the first turbine wheel 56 of the gas turbine in accordance with an example of the present technology. FIG. As shown, the turbine wheel 56 has a plurality of dovetail slots 104 configured to mount a plurality of blades or blades (not shown). The first turbine wheel 56 also shows the plurality of tab projections 76 on the inner diameter of the wheel rim 106 in a radially inward direction. As shown, each of the plurality of tab protrusions 76 circumferentially span along a dovetail slot width and are spaced from each other by a dovetail slot width. In other embodiments, the span may be a fraction of the dovetail width or a plurality of dovetail widths.
    Fig. 5 is a perspective view of the front cover plate 54 of the interstage seal subsystem 42 in accordance with an example of the present technology. As shown, the front cover plate 54 has a plurality of bent L-shaped seats 108 at an inner end to allow radial and circumferential retention when on the side of the first turbine wheel 56 having the plurality of tab projections 76 is attached to the inner diameter of the wheel rim (as shown in Fig. 4). Each of the plurality of bent L-shaped seats 108 has a land surface 110 that is fully engaged with the first turbine 56 in the assembled state. The front cover plate 54 also has a plurality of radial retaining means 112, which also allow retention of the front cover plate 54 in the radial and circumferential directions. The front cover plate 54 also shows the seal wire groove 68 and a first retaining ridge structure 100 for holding the near flow path seal segment 48 in the assembled state.
    Fig. 6 is a perspective view of a second turbine wheel 60 of the gas turbine in accordance with an example of the present technology. As shown, the second turbine wheel 60 has a plurality of dovetail slots 120 configured to mount a plurality of blades or paddles (not shown). The second turbine wheel 60 also shows the plurality of tab protrusions 122 on the inner diameter of the wheel rim 124 in a radially inward direction. As shown, each of the plurality of tab protrusions 122 circumferentially span along a dovetail slot width and are spaced from each other by a dovetail slot width. It should be noted that the outer diameter of the wheel rim 126 has no hooks.
    Fig. 7 is a perspective view of the rear cover plate 58 of the interstage seal subsystem 42 in accordance with an example of the present technology. As shown, the rear cover plate 58 has a plurality of bent L-shaped seats 130 at an inner end to allow radial and circumferential retention when projecting on the side of the second turbine wheel 60 with the plurality of tabs 122 is attached to the inner diameter of the wheel rim (as shown in Fig. 6). Each of the plurality of curved L-shaped seats 130 has a land surface 132 which, when assembled, fully engages the second turbine wheel 60. The rear cover plate 58 also includes a plurality of radial retention means 134 which also permit retention of the front cover plate 54 in the radial and circumferential directions. As shown, there is a region 36 that provides space for the rear axial retaining ring 78. The rear cover plate 58 also shows the seal wire groove 72 and a second retaining ridge structure 102 for holding the near flow path seal segment 48 in the assembled state. The rear cover plate 58 also shows a retaining hook portion 94 disposed on the side facing the second turbine wheel 60 for axial retention with each of a blade retention hook 96 (shown in FIG. 3) of the second stage buckets 64 (shown in FIG Fig. 3). In addition, the rear cover plate 58 shows the angel wing structure 90 at the radially outer end.
    Fig. 8 is a perspective view of a sealing system 200 having an interstage seal subsystem 42 in accordance with an embodiment of the present technology. As shown in an enlarged view, the receiving structure 98 is in a locking position with the rear end of the near flow path seal segment 48 at the rear end 92. The receiving structure 98 has a plurality of recessed round recesses 202 that engage the locking with a plurality of protruding tabs 204 disposed on the underside of the near flow path seal segment 48 on the rear side 92 to circumferentially hold the near flow path seal segment 48. It should be noted that the plurality of near-flow path sealing segments 48 disposed on the interstage seal subsystem 42 may be present in lesser numbers as compared to the blades disposed on the first stage or the second stage of the multi-stage turbine. In one embodiment, the sealing system 200 has a wear-resistant coating, e.g. a hard coating on all contact surfaces between the front cover plate 54, the rear cover plate 58 and the Nahströmungspfad seal segment for wear reduction. In another embodiment, the rear cover plate 58 extends to a plurality of flange bolts (not shown) disposed on a plurality of blades 206 to facilitate cooling flow supply passages for the blades. The system 200 may also include a plurality of second interstage seal subsystems (not shown) and a plurality of third interstage seal subsystems (not shown) located axially between the second turbine stage and the third turbine stage (not shown) of the multistage turbine and between the third turbine stage and the fourth turbine stage extend.
    FIG. 9A is a flowchart illustrating the steps involved in a method of assembling a sealing system of a multi-stage turbine in accordance with one embodiment of the present technology. FIG. In step 302, the method includes installing each of the plurality of second stage buckets into each of a plurality of dovetail slots of the second turbine wheel. In one embodiment, approximately one fifth of the axial width of a dovetail of each of the plurality of second stage buckets is extended axially to a forward side. In another embodiment, the span of the axial width of the dovetail may vary from each of the plurality of second stage blades that extend axially toward the front side. In step 304, the method includes disposing a rear seal wire in a seal wire groove of each of the plurality of back seal plates. In step 306, the method includes attaching a corresponding portion of each of the plurality of back seal plates to the elongated plurality of second stage buckets by moving each of the plurality of back seal plates axially and then radially outward so that a plurality of blade retention hooks is fully engaged with the corresponding portion of the rear cover plate, wherein the corresponding portion has a retaining hook structure. Prior to attaching the plurality of back cover plates to the elongated plurality of second stage buckets, the method includes aligning the plurality of bucket retention hooks of the extended plurality of second stage buckets with the corresponding portion of each of the plurality of back cover plates.
    The method further includes, in step 308, translating the plurality of second stage buckets together with the rear cover plate to the plurality of dovetail slots. In addition, in step 310, the method includes placing a rear axial retaining ring between a plurality of tab projections on an inner diameter of the second turbine wheel rim and the rear cover plate to lock the rear cover plate to the second turbine wheel. In step 312, the method includes attaching a plurality of bent L-shaped seats to an inner end of each of the plurality of front cover plates having a plurality of tab protrusions on the inner diameter of a wheel rim of the first turbine wheel, so that the plurality of bent L-shaped Sitting fully engaged with the plurality of tab projections. The method also includes placing a front seal wire in a seal wire groove of each of the plurality of front cover plates prior to attaching the plurality of front cover plates to the first turbine wheel.
    Fig. 9B is a flowchart showing the steps involved in a method of assembling a sealing system of a multi-stage turbine in accordance with an embodiment of Fig. 9A. The method further includes, in step 314, disposing a front axial retaining ring between the plurality of tab projections on an inner diameter of the wheel rim of the first turbine wheel and the front cover plate to lock the front cover plate to the first turbine wheel. In step 316, the method includes attaching a front end and a rear end of each of the plurality of near-flow path seal segments to a hook portion of the front cover plate and a receiving structure of the rear cover plate, and finally installing each of the plurality of first-stage buckets to each one from a plurality of dovetail slots of the first turbine wheel in step 318. In addition, the method may also include locating inter-segment wedge seals between adjacent near-flow path seal segments.
    Advantageously, the present sealing system is a reliable, robust seal for multiple locations in gas turbines with high pressure drops and large transients. The gasket assemblies are also economical to manufacture resulting in significant cost savings resulting from spacer wheel material savings. Therefore, the present sealing system also improves the power density and reduces secondary flows. The present sealing system also allows for rotor architectures with flange bolts, field renewal with only a reduced blade stage, and flow path variability. The present sealing system provides flexibility for radial positioning of a bolted flange and disassembly of airfoil rows is not required. The present sealing system may also use a reduced number of near-flow path sealing segments, resulting in lower inter-segment gaps and thereby lower leakage. The present sealing system also allows the cover plates to extend to a plurality of flange bolts disposed on a plurality of blades to allow cooling flow passageways for the blades. The sealing system also ensures that the direction of the load transferred from the near flow path seal segments to the blades or blade dovetails is changed so that the load is deterministic. In addition, the present sealing system does not require the use of blade dovetail seals and blade shank seals.
    In addition, those skilled in the art will recognize the interchangeability of various features of various embodiments. Likewise, the various method steps and features described, as well as other known equivalents for each such method and feature, may be mixed and matched by one of ordinary skill in the art to create additional systems and techniques in accordance with the principles of this disclosure. Of course, it should be understood that not necessarily all such objects and advantages as described above can be achieved in accordance with any particular embodiment. Thus, for example, those of ordinary skill in the art will recognize that the systems and techniques described herein may be embodied and embodied in a manner that achieves or optimizes an advantage or group of advantages as taught herein without necessarily other objects or advantages, as they are taught or suggested herein.
    While only certain features of the invention have been illustrated and described herein, many modifications and changes will become apparent to those skilled in the art. It is therefore to be understood that the appended claims are intended to embrace all such modifications and changes as fall within the true spirit of the invention.
    A sealing system for a multistage turbine includes a plurality of first interstage seal subsystems circumferentially disposed about a rotor wheel shaft of the multistage turbine and extending axially between a first turbine stage and a second turbine stage of the multistage turbine. Each of the interstage seal subsystems has multiple near flow path seal segments. The first interstage seal subsystem also includes a front cover plate disposed axially between a first turbine stage first turbine and the near flow path seal segment and a rear cover plate disposed axially between the near flow path seal segment and a second turbine stage second turbine. In addition, each of the front cover plate and the rear cover plate radially extend to a first stage blade and a second stage blade, respectively.
    权利要求:
    Claims (10)
    [1]
    A sealing system for a multi-stage turbine, the sealing system comprising:a plurality of first interstage seal subsystems circumferentially disposed about a rotor wheel shaft of the multistage turbine and extending axially between a first turbine stage and a second turbine stage of the multistage turbine, each of the plurality of first interstage seal subsystems comprising:a plurality of near-flow path sealing segments;a front cover plate disposed axially between a first turbine stage of the first turbine stage and the Nahströmungspfaddichtungssegment; anda rear cover plate disposed axially between the Nahströmungspfaddichtungssegment and a second turbine wheel of the second turbine stage, wherein each of the front cover plate and the rear cover plate extends radially to a first stage blade and a second stage blade.
    [2]
    2. Sealing system according to claim 1, wherein a side of the first turbine wheel, which faces the front cover plate having a wheel rim with a plurality of tab projections on the inner diameter of the wheel rim in a radially inward direction and / or wherein one side of the second turbine wheel, which faces the rear cover plate, has a wheel rim with a plurality of tab projections on an inner diameter of the wheel rim in a radially inward direction.
    [3]
    3. The sealing system of claim 2, wherein the front cover plate has a plurality of curved L-shaped seats at an inner end to allow retention in the radial and circumferential directions when on one side of the first turbine wheel with the plurality of tab projections on Inner diameter of the wheel rim is mounted and / or wherein the rear cover plate having a plurality of curved L-shaped seats at an inner end to allow retention in the radial and circumferential direction when they project on one side of the second turbine wheel with the plurality of tabs attached to the inner diameter of the wheel rim.
    [4]
    4. A sealing system according to claim 2 or 3, further comprising a front axial retaining ring, which is arranged between the plurality of tab projections on the inner diameter of the Radrandes the first turbine wheel and the front cover plate to lock the front cover plate with the first turbine and / or further comprising a rear axial retaining ring disposed between the plurality of tab projections on the inner diameter of the wheel rim of the second turbine wheel and the rear cover plate to lock the rear cover plate to the second turbine wheel.
    [5]
    5. Sealing system according to one of the preceding claims, further comprising a first sealing wire, which is arranged in a Dichtungsdrahtnut the front cover plate and disposed axially between the front cover plate and the first stage blade to the wheel rim of the first turbine wheel from flowing out of the To isolate hot gas path and / or further comprising a second sealing wire, which is arranged in a second sealing wire groove of the rear cover plate and disposed axially between the rear cover plate and the second stage blade to the Radrand the second turbine wheel of a flow from the hot gas path to isolate.
    [6]
    6. Sealing system according to one of the preceding claims, wherein the rear cover plate has an angel wing structure at an outer end of the rear cover plate and / or wherein the rear cover plate has a retaining hook portion which is disposed on a side facing the second turbine wheel to the axial Retaining with each of a blade retention hook of the second stage buckets.
    [7]
    7. The sealing system of claim 1, wherein the near flow path seal segment has an angel wing structure at an outer end to a front side of the Nahströmungspfaddichtungssegments.
    [8]
    8. A sealing system according to any one of the preceding claims, wherein a rear cover plate has a receiving structure between a plurality of angel wing webs to hold the Nahströmungspfaddichtungssegment on the rear side.
    [9]
    9. A method of assembling a sealing system of a multi-stage turbine having a plurality of first stage buckets and a plurality of second turbine stage buckets on a first turbine wheel and a second turbine wheel, respectively, the method comprising:Installing each of the plurality of second stage buckets on each of a plurality of dovetail slots of the second turbine wheel;Disposing a rear seal wire in a seal wire groove of each of the plurality of back cover plates;Attaching a corresponding portion of each of the plurality of rear cover plates on the extended plurality of second stage buckets by moving each of the plurality of rear cover plates axially and then radially outwardly, so that the plurality of blade retaining hook completely with the corresponding portion of the rear Cover plate engage, wherein the corresponding portion has a retaining hook structure;Shifting the plurality of second stage buckets together with the rear cover plate to the plurality of dovetail slots;Placing a rear axial retaining ring between a plurality of tab projections on an inner diameter of the rim of the second turbine wheel and the rear cover plate to lock the rear cover plate to the second turbine wheel;Mounting a plurality of curved L-shaped seats at an inner end of each of the plurality of front cover plates with a plurality of tab protrusions on the inner diameter of a wheel rim of the first turbine wheel so that the plurality of curved L-shaped seats is fully engaged with the first Plurality of tab projections;Arranging a front axial retaining ring between a plurality of tab projections on an inner diameter of the wheel rim of the first turbine wheel and the front cover plate for locking the front cover plate with the first turbine wheel;Attaching a front end and a rear end of each of the plurality of Nahströmungspfaddichtungssegmenten to a hook portion of the front cover plate and a receiving structure of the rear cover plate;Installing each of the plurality of first stage buckets on each of a plurality of dovetail slots of the first turbine wheel.
    [10]
    10. Gas turbine system comprising:a plurality of blades of a first turbine stage attached to a first turbine wheel;a plurality of second turbine stage blades attached to a second turbine wheel;a plurality of first interstage seal subsystems circumferentially disposed about a rotor wheel shaft of the gas turbine and extending axially between a first turbine stage and a second turbine stage of the gas turbine, each of the plurality of first interstage seal subsystems comprising:a plurality of near-flow path sealing segments,a front cover plate disposed axially between a first turbine stage of the first turbine stage and the Nahströmungspfaddichtungssegment; anda rear cover plate disposed axially between the Nahströmungspfaddichtungssegment and a second turbine wheel of the second turbine stage, wherein each of the front cover plate and the rear cover plate extends radially to a first stage blade and a second stage blade.
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    同族专利:
    公开号 | 公开日
    JP6866062B2|2021-04-28|
    US10662793B2|2020-05-26|
    DE102015120128A1|2016-06-02|
    JP2016109125A|2016-06-20|
    CN105649684A|2016-06-08|
    US20160153302A1|2016-06-02|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-08-15| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/556,305|US10662793B2|2014-12-01|2014-12-01|Turbine wheel cover-plate mounted gas turbine interstage seal|
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