• 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 turbine shroud assembly (100) includes a plurality of arcuate shroud block assemblies (102) annularly arranged to form a shroud segment. The plurality of shroud block assemblies (102) include a first shroud block assembly (202) having a shroud block (206) and a second shroud block assembly (302) having a shroud block (306). The first shroud block assembly (202) includes a seal interface element (218) and a shroud seal (208). The seal interface element (228) has a side portion (234) adjacent a radial side surface (220) of the first shroud block (206). The second shroud block assembly (300) includes a seal interface element (328) and a shroud seal (308). The seal interface member (328) has a side portion adjacent to a radial side surface of the second shroud block (306).
    公开号:CH710620A2
    申请号:CH00022/16
    申请日:2016-01-07
    公开日:2016-07-15
    发明作者:Troy Hafner Matthew；Woodrow Roberts Frederic Jr；John Morgan Victor
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    The present invention generally relates to a turbine shroud assembly for a turbomachine. More particularly, this invention relates to a turbine shroud assembly having a seal interface element.
    BACKGROUND OF THE INVENTION
    A turbomachine, such as a gas turbine or a steam turbine, generally includes a turbine and a rotor shaft that extends axially through the turbine section. In certain arrangements, the turbine includes a plurality of turbine blades that extend radially outwardly from the rotor shaft. An inner shell encloses the turbine blades circumferentially and encloses a turbine shroud assembly. The turbine shroud assembly generally includes a plurality of shroud blocks annularly disposed along an inner surface of the inner housing. The shroud block assembly includes one or more shroud seals coupled thereto and each shroud seal encloses a seal side or surface. A radial gap is defined between a tip portion of the turbine blades and the sealing surfaces of the shroud seals.
    Typically, gaskets are provided with a joint formed between radial sides and surfaces of adjacent shroud blocks. The seals suppress and / or reduce the escape of combustion gases, steam and / or cooling air through the radial connection. During assembly, the seals may become pinched and / or misaligned. When this occurs, the shroud seals of adjacent shroud blocks may build up an unintentional load against each other. In certain instances, such as where the ceramic composite shroud gaskets are formed, this inadvertent loading can result in undesirable stresses on the shroud gaskets. Therefore, an improved turbine shroud assembly would be useful.
    BRIEF DESCRIPTION OF THE INVENTION
    Aspects and advantages of the invention will be set forth below in the description which follows, or may be obvious from the description, or may be learned by practice of the invention.
    One embodiment of the present invention is a turbine shroud assembly. The turbine shroud assembly includes a plurality of arcuate shroud block assemblies annularly arranged to form a shroud segment. The plurality of shroud block assemblies include a first shroud block assembly having a shroud block defining a radial side surface and a second shroud block assembly having a shroud block defining a radial side surface. The first shroud block assembly further includes a seal interface element and a shroud seal coupled to the first shroud block such that a side portion of the seal interface element is adjacent to the radial side surface of the first shroud block. The second shroud block assembly further includes a seal interface member and a shroud seal coupled to a second shroud block such that a side portion of the seal shim member is adjacent to the radial side surface of the second shroud block.
    In either embodiment of the turbine shroud assembly, it may be advantageous for the seal shroud member of the first shroud block assembly to include a sealing surface.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the seal shroud member of the first shroud block assembly is at least partially coated with a thermal barrier coating and / or a wear resistant coating.
    In any embodiment of the turbine shroud assembly, it may be advantageous for the seal shroud member of the second shroud block assembly to include a sealing surface.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the seal shroud member of the second shroud block assembly is at least partially coated with a thermal barrier coating and / or a wear resistant coating.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the radial side portion of the seal shim member of the first shroud block assembly defines a seal gap.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the radial side portion of the connecting shim member of the second shroud block assembly defines a sealing gap.
    [0012] In any embodiment of the turbine shroud assembly, it may be advantageous if the seal shim member of the first shroud block assembly and the second shroud block assembly of the first shroud block assembly of the first shroud block assembly and the shroud seal of the second shroud block assembly of a second material are formed differently from the first material.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the first material comprises a high temperature alloy and the second material comprises a ceramic matrix composite material.
    [0014] In any embodiment of the turbine shroud assembly, it may be advantageous if the plurality of shroud shroud block assemblies further include one or more shroud block assemblies disposed between the first shroud block assembly and the second shroud block assembly.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the seal shim member and the shroud block of the first shroud block assembly and / or the shim member and the shroud block of the second shroud block assembly are formed in one piece.
    In another embodiment of the present invention is a turbine shroud assembly. The turbine shroud assembly includes a plurality of arcuate shroud block assemblies arranged annularly to form a continuous shroud ring. The plurality of shroud block assembly includes a first shroud block assembly having a first shroud block defining a first radial side surface and a second shroud block assembly adjacent to the first shroud block assembly. The second shroud block assembly includes a second shroud block. The second shroud block defines a second radial side surface. A connection is defined between the first and second radial side surfaces. The first shroud block assembly further includes a seal interface member and a shroud seal coupled to an inner surface of the first shroud block. The seal interface element has a side portion that is adjacent to the radial side surface of the first shroud block. The second shroud block assembly further includes a seal interface member and a shroud seal coupled to an inner surface of the second shroud block. The seal interface member also has a side portion that is adjacent to the radial side surface of the second shroud block. The side portion of the seal interface element of the first shroud block assembly and the side portion of the seal shim member of the second shroud block assembly are adjacent.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the connection between the first shroud block assembly and the second shroud block assembly coincides with a horizontal connection of a turbomachine.
    [0018] In any embodiment of the turbine shroud block assembly, it may be advantageous if the first shroud block assembly is coupled to an inner surface of a first arcuate portion of a turbine housing and the second shroud block assembly is coupled to an inner surface of a second arcuate portion of the turbine housing.
    [0019] In any embodiment of the turbine shroud assembly, it may be advantageous for the seal shroud member of the first shroud block assembly and / or the seal shroud member of the second shroud block assembly to include a sealing surface.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the seal surface is at least partially coated with a thermal barrier coating and / or a wear resistant coating.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the side surface of the seal shim member of the first shroud block assembly and / or the side surface of the shim block of the second shroud block assembly define a seal gap.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the radial side surface of the first shroud block and / or the radial side surface of the second shroud block defines a sealing gap.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the turbine shroud assembly further includes a seal extending between the radial side surfaces of the first and second shroud blocks.
    In any embodiment of the turbine shroud assembly, it may be advantageous if the seal shroud element of the first shroud block assembly and the seal shroud element of the second shroud block assembly are formed of a metal and the first shroud seal is formed of a ceramic matrix composite material.
    Those skilled in the art will better appreciate the features and aspects of such embodiments and others upon review of the specification.
    BRIEF DESCRIPTION OF THE DRAWINGS
    A full and enabling disclosure of the present invention, including the best mode thereof, to a person skilled in the art, is more particularly set forth in the remainder of the specification, including the reference to the accompanying drawings, in which:<Tb> FIG. 1 <SEP> is a cross-sectional view of an exemplary turbomachine, especially a gas turbine turbomachine, as may include various embodiments of the present invention;<Tb> FIG. FIG. 2 is a perspective view of an exemplary inner and outer casing of a turbomachine as may be incorporated in various embodiments of the present invention; FIG.<Tb> FIG. 3 is a perspective view of a portion of the inner housing as shown in FIG. 2, according to one or more embodiments of the present invention;<Tb> FIG. FIG. 4 is a front perspective view of a portion of an exemplary turbine shroud assembly according to an embodiment of the present invention; FIG.<Tb> FIG. 5 is a side perspective view of an exemplary shroud block of the turbine shroud assembly as shown in FIG. 4, according to at least one embodiment of the present invention;<Tb> FIG. FIG. 6 is a perspective view of an opposite side of a shroud block of a shroud block assembly of the turbine shroud block assembly as shown in FIG. 5 in accordance with at least one embodiment of the present invention; FIG.<Tb> FIG. FIG. 7 is a side view of an exemplary seal interface element according to various embodiments; FIG.<Tb> FIG. FIG. 8 is a front perspective view of a portion of a turbine shroud assembly as shown in FIG. 4, according to an embodiment of the present invention; FIG.<Tb> FIG. 9 is a side perspective view of a portion of an exemplary shroud block assembly according to one embodiment of the present invention; and<Tb> FIG. Figure 10 provides a simplified cross-sectional side view of a portion of a turbine shroud assembly according to one embodiment of the present invention.
    DETAILED DESCRIPTION OF THE INVENTION
    [0027] Reference will be made in detail to present embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. This description uses numeric and letter designations to refer to features in the drawings. Like or similar terms in the drawings and the description have been used to refer to the same or similar parts of the invention. As used herein, the terms "first", "second" and "third" may be used interchangeably to distinguish one component from another, and it is not intended that the location or importance of the individual To designate components. In addition, the terms "upstream" and "downstream" refer to the relative location of the components in a fluid path. For example, component A is upstream of component B when fluid flows from component A to component B. Conversely, component B is downstream of component A when component B receives fluid flow from component A.
    Each example is provided by way of illustration of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that the modifications and variations can be made in the present invention without departing from its scope or spirit. For example, features that are illustrated or described as part of one embodiment may be used in one embodiment to obtain a still further embodiment. Therefore, it is intended that the present invention cover such modifications and variations as come within the scope of the appended claims and their equivalents.
    Referring now to the drawings, FIG. 1 illustrates a cross-sectional side view of an exemplary turbomachine, particularly a turbomachine with a gas turbine engine 10, as may include various embodiments of the present invention. As shown, the gas turbine engine 10 generally includes a compressor section 12 having an inlet 14 disposed at an upstream end of the axial compressor 16. The gas turbine engine 10 further includes a combustion section 18 having one or more combustion chambers 20 positioned downstream of the compressor 16 and a turbine section 22 downstream of the combustion section 18. A rotor shaft 24 extends generally axially through the gas turbine engine 10. The turbine section 22 generally includes alternating stages of stationary nozzles 26 and turbine rotor blades 28 disposed within the turbine section 22 along an axial centerline 30 of the shaft 24. An inner housing or shell 32 circumferentially surrounds the alternating stages of the stationary nozzles 26 and the turbine rotor blades 28. An outer housing or shell 34 surrounds the inner housing 32 circumferentially.
    FIG. 2 provides a perspective view of the inner and outer housings 32, 34. Typically, as shown in FIG. 3, the inner housing 32 and the outer housing 34 are split along a horizontal plane 40 that extends parallel to a common axial centerline 42 of the inner and outer housings 32, 34. The outer housing 34 is divided into a lid part (removed for clarity) and a bottom part 44. The lid part may be separated from the bottom part, for example by a crane or other lifting device, to access the other housing 32.
    The inner housing 32 is typically divided into an upper portion 46 and a lower portion 48 along a horizontal plane 40. A horizontal joint 50 is defined between the upper and lower parts 46,48. The upper portion 46 may be separated from and / or lowered onto the lower portion 48 by a crane and / or other lifting device to access the lower portion 48 of the inner housing 32 during assembly and / or disassembly. The upper and lower parts 46, 48 may be further divided into a plurality of bent portions.
    FIG. 3 provides a perspective view of a portion of the inner housing 32 according to one or more embodiments. As shown in FIGS. 2 and 3, an upper surface 60 of the inner housing 32 is typically fixed to channels and / or includes channels, slot hooks, or other coupling or attachment features 62. As shown in FIG. 3, the attachment features 62 may be used. to attach shroud blocks 64 of a turbine shroud assembly thereto.
    FIG. 4 provides a front perspective view of a portion of an exemplary turbine shroud assembly 100 according to an embodiment of the present invention. In one embodiment, as shown in FIG. 4, the turbine shroud assembly 100 includes a plurality of arcuately shaped shroud block assemblies 102 that are annularly arranged to form a shroud segment 104. The turbine shroud assembly 100 may be formed from a single shroud segment 104 or a plurality of shroud segments 104 coupled together to at least partially form a shroud ring. Each shroud block assembly 102 includes a shroud block 106 and a shroud seal 108 that is coupled to and / or secured to the shroud block 106.
    FIG. 5 provides a side perspective view of an exemplary shroud block 106 of the turbine shroud assembly 100 as shown in FIG. 4, in accordance with at least one embodiment of the present invention. FIG. 6 provides a perspective view of an opposite side of the shroud block 106 of the turbine shroud assembly 100 as shown in FIG. 5 in at least one embodiment of the present invention. As shown in FIGS. 5 and 6, the shroud block 106 generally includes an arcuate inner surface 110 that is radially spaced from an arcuate outer surface 112. The outer surface 112 is configured to couple to or attach to the attachment feature 62 of the inner surface 60 of the inner housing 32. The inner surface 110 is configured to receive and / or connect the shroud seal 108 (FIG. 4). For example, as shown in FIG. 6, inner surface 110 may include and / or define arcuate gaps or slots 114, 116.
    As shown in FIGS. 5 and 6 together, the shroud block 106 may also include circumferentially opposed radial side surfaces 118, 120 and / or set. The radial sides or surfaces 118, 120 may be configured generally in the same manner. For example, in one embodiment, at least one of the radial side surfaces 118, 120 includes a sealing gap 122, 124 and / or defines a sealing gap 122, 124. The radial side surfaces 118, 120 may be substantially flatter. As shown in FIG. 4, joints 126 are formed between the radial side surfaces 118, 120 of adjacent shroud blocks 106.
    In various embodiments, as shown in FIGS. 4, 5 and 6, at least one shroud block assembly 106 includes a seal interface element 128. The seal spacer 128 may be used to retain shroud seals 108 in situ during assembly and disassembly of the turbine shroud assembly 100 and / or the inner housing 32.
    As shown in Figures 5 and 6, an exemplary seal interface member 128 includes a portion having a leading edge 130, a trailing edge portion 132, a radial side portion 134 (Figure 5), an opposing radial side portion 136 (Figures 6) and a sealing surface 138. In certain embodiments, as shown in FIG. 4, the radial side portion 134 is adjacent to and / or with the radial side surface 120.
    In one embodiment, as illustrated in FIG. 5, the radial side portion 134 is adjacent to and / or with the radial side surface 118. The radial side portion 134 may be contiguous with, flush with or flush with the corresponding radial side surface 118, 120 In other embodiments, the radial side member 134 may extend outwardly from outer radial side surfaces 118, 120. In other embodiments, the seal spacer 128 is formed of a first material and the shroud seal 108 is formed of a second material that is different from the first material. For example, in one embodiment, the first material comprises a high temperature alloy and the second material comprises a ceramic matrix composite material. In certain embodiments, the seal interface element 128 may be molded or cast as an integral component or feature of the shroud block 106.
    FIG. 7 provides a side view of the seal interface element 128 in accordance with various embodiments. In certain embodiments, as shown in FIG. 7, the joint interface member 128 may include one or more gaps 140 for attaching or coupling the seal interface member 128 to the shroud block 106. Additionally or alternatively, the seal interface member 128 may include connection or mounting holes 142 for securing the seal interface member 128 to the shroud block 106.
    In certain embodiments, the sealing surface 138 of the seal interface element 128 may include a coating 144, such as a thermal barrier layer and / or a wear layer. The coating 144 may extend over the leading edge 130 and / or the trailing edge 132. In one embodiment, the seal interface element 128 includes a plurality of holes or passageways 146 that may provide for cooling the seal interface element 128 during operation of the turbine. In certain embodiments, as shown in FIGS. 5 and 7, the radial side portion 134 of the seal interface element 128 defines at least one sealing gap 148. The sealing gap 148 may be continuous and / or in alignment with the sealing gap 122, 124 and the shroud block 106.
    Turbine shroud assembly 100 may include a plurality of shroud block assemblies 102 including shroud blocks 106, shim members 128, shroud seals 108 and various other components and features as previously described herein and as illustrated in FIGS. 4, 5, 6 and 7 , FIG. 8 provides a front perspective view of a portion of the turbine shroud assembly 100 as shown in FIG. 4, and FIG. 9 provides a side perspective view of a portion of the shroud block assembly according to an embodiment of the present invention.
    In one embodiment, as shown in FIG. 8, the plurality of arcuate shroud block assemblies 102 include a first shroud block assembly 202 having a shroud block 206 defining a radial side surface 220 and a second shroud block assembly 302 having a shroud block 306 defining a radial side surface 318 (Figure 9). The first shroud block assembly 202 further includes a seal interface element 228 and a shroud seal 208 coupled to the first shroud block 206. The radial side portion 234 of the seal interface element 228 is adjacent to the radial side surface 220 of the first shroud block 206. The second shroud block assembly 302 further includes a seal interface element 328 and a shroud seal 308 coupled to the second shroud block 306. As shown in FIG. 9, the radial side portion 334 of the seal interface element 328 is substantially adjacent to the radial side surface 318 of the second shroud block 306.
    In one embodiment, as shown in FIG. 8, the seal interface element 228 includes a sealing surface 238 that is coated with a thermal barrier layer and / or a wear resistant layer. In one embodiment, as shown in FIG. 8, the seal interface element 328 includes a sealing surface 338 that is coated with a thermal barrier layer and / or a wear resistant layer. In one embodiment, the radial side portion 234 of the seal interface element 228 defines a sealing gap 224. In one embodiment, the radial side portion 234 of the seal interface element 228 defines a seal gap 248. In one embodiment, the radial side portion 334 of the seal interface element of the second shroud block assembly defines a sealing gap 348. In one embodiment, seal interface element 228 and seal interface element 328 are formed of a first material, and shroud seal 208 and shroud seal 308 are formed of a second material that is different than the first material. In one embodiment, the first material comprises a high temperature alloy and the second material comprises a ceramic matrix composite material. In one embodiment, the plurality of arcuate shroud block assemblies 102 further include one or more shroud block assemblies 102 circumferentially disposed between the first shroud block assembly 202 and the second shroud block assembly 302.
    Fig. 10 provides a simplified cross-sectional side view of a portion of the turbine shroud assembly 100 according to an embodiment of the present invention. As shown in FIG. 10, a first shroud block assembly 402 includes a first shroud block 406 defining a first radial side surface 418 and a second shroud block assembly 502 adjacent to a first shroud block assembly 502. The second shroud block assembly 502 includes a second shroud block 506 defining a second radial side surface 520. A joint 426 is defined between the first and second radial side surfaces 418, 520. The first shroud block assembly 402 further includes a seal interface element 428 and a shroud seal 408 that is coupled to or formed integrally with the interior surface 412 of the first shroud block 406. The seal interface element 428 has a radial side portion 434 that is adjacent to the radial side surface 418 of the first shroud block 406. Second shroud block assembly 502 further includes seal interface element 528 and shroud seal 508 coupled to inner surface 512 of the second shroud block. Seal spacer element 528 has a side portion 534 that is adjacent to the radial side surface 520 of the second shroud block 506. Lateral portion 434 of seal interface element 428 and side portion 534 of seal interface element 528 are adjacent and / or circumferentially aligned.
    In one embodiment, the connection 426 coincides with a horizontal connection 50 of the inner housing 32 of the turbomachine 10. In one embodiment, the first shroud block assembly 402 is coupled to the inner surface 60 of a first arcuate portion 52 of the inner housing 32 of the turbine and the second shroud block assembly 502 is coupled to an inner surface 60 of a second arcuate portion 54 of the inner housing 32.
    In an embodiment, the seal interface element 428 and / or 528 includes a sealing surface 438, 438. In one embodiment, the sealing surface 438 and / or the sealing surface 538 is at least partially coated with a thermal barrier coating and / or a wear resistant coating. In one embodiment, the side surface 434 of the seal interface element 428 and / or the side surface 534 of the seal interface element 528 defines a sealing gap 522. In one embodiment, the radial side surface 418 and / or the radial side surface 518 defines a sealing gap 448,. 548 firmly. In one embodiment, seal 66 extends between radial side surfaces 418 and 520. In one embodiment, seal interface element 428 and seal interface element 528 are formed of a metal and first shroud seal 408 and / or the second shroud seal are formed of a ceramic matrix composite material.
    The turbine shroud assembly 100, as described and illustrated herein, provides several technical advantages over known turbine shroud assemblies. For example, seal interface element 128 may reduce undesirable stresses between adjacent shroud seals. This is particularly advantageous in cases where at least one of the shroud seals is formed of a ceramic matrix composite material. In addition, the seal interface element 128 may be used to retain the shroud seals 108 in place during assembly and / or disassembly of the inner turbine housing 32. Additionally, the seal interface member 128 may allow various types of shroud seals to be used in conventional turbine shroud assemblies during testing and / or detection by exiting different shroud seal types from each other, and therefore isolating possible faults from new or developing shroud seals from non-imminent Development stage coverband seals. The spacer element (s) 128 may provide for the adaptation of a seal configuration or type in a shroud segment and the adaptation of another seal configuration or type to a spaced or adjacent shroud segment. Additionally or alternatively, the interface element (s) 128 may provide post-impact pressure and / or temperature separation across the interface element, and thus act as a flow dam or barrier to prevent cooling flow from escaping or escaping between adjacent shroud segments.
    This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, to do so, and to use any apparatus or system and to carry out any method involved. The patentable scope of the invention is defined by the claims, and may include other examples that appear to those skilled in the art. Such other and examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal language of the claims.
    A turbine shroud assembly includes a plurality of arcuate shroud block assemblies arranged annularly to form a shroud segment. The plurality of shroud block assemblies include a first shroud block assembly having a shroud block and a second shroud block assembly having a shroud block. The first shroud block assembly includes a seal interface element and a shroud seal. The seal interface element has a side portion that is adjacent to a radial side surface of the first shroud block. The second shroud block assembly includes a seal interface element and a shroud seal. The seal interface element has a side portion that is adjacent to a radial side surface of the second shroud block.
    component list
    [0050]<Tb> 10 <September> Gas Turbine<Tb> 12 <September> compressor section<Tb> 14 <September> inlet<Tb> 16 <September> Compressor<Tb> 18 <September> combustion section<Tb> 20 <September> combustion chamber<Tb> 22 <September> turbine section<Tb> 24 <September> rotor shaft<Tb> 26 <September> nozzle<Tb> 28 <September> turbine rotor blade<tb> 30 <SEP> axial centerline<tb> 32 <SEP> inner case<tb> 34 <SEP> outer case<tb> 35-39 <SEP> not used<Tb> <September><tb> 40 <SEP> horizontal plane<tb> 42 <SEP> axial centerline<Tb> 44 <September> cover part<tb> 46 <SEP> upper part<tb> 48 <SEP> lower part<tb> 50 <SEP> horizontal connection<tb> 52 <SEP> arcuate section<tb> 54 <SEP> arcuate section<tb> 56 <SEP> arcuate section<tb> 58 <SEP> arcuate section<tb> 60 <SEP> inner surface<Tb> 62 <September> attachment feature<Tb> 64 <September> shroud block<Tb> 66 <September> seal<Tb> <September><Tb> 100 <September> turbine shroud assembly<Tb> 102 <September> shroud Power Pack<Tb> 104 <September> shroud segment<Tb> 106 <September> shroud block<Tb> 108 <September> shroud seal<tb> 110 <SEP> inner surface<tb> 112 <SEP> outer surface<tb> 114 <SEP> arcuate gap / slot<tb> 116 <SEP> arcuate gap / slot<Tb> 118 <September> radial side / surface<Tb> 120 <September> radial side / surface<Tb> 122 <September> sealing gap<Tb> 124 <September> sealing gap<Tb> 126 <September> Connection<Tb> 128 <September> seal spacer element<Tb> 130 <September> leading edge<Tb> 132 <September> trailing edge<tb> 134 <SEP> radial side panel<tb> 136 <SEP> radial side panel<Tb> 138 <September> sealing surface<Tb> 140 <September> gap<Tb> 142 <September> mounting hole<Tb> 144 <September> Coating<Tb> 146 <September> hole / passage<Tb> 148 <September> sealing gap<Tb> 150 <September><Tb> <September><tb> 202 <SEP> first shroud block assembly<Tb> 206 <September> shroud block<Tb> 208 <September> shroud seal<tb> 220 <SEP> radial surface<Tb> 228 <September> spacer element<tb> 234 <SEP> radial side panel<Tb> 238 <September> sealing surface<Tb> 248 <September> sealing gap<Tb> <September><tb> 302 <SEP> second shroud block assembly<Tb> 306 <September> shroud block<Tb> 308 <September> shroud seal<tb> 318 <SEP> radial surface<Tb> 328 <September> spacer element<tb> 334 <SEP> radial side panel<Tb> 338 <September> sealing surface<Tb> 348 <September> sealing gap<Tb> <September><tb> 402 <SEP> first shroud block assembly<tb> 406 <SEP> first shroud block<Tb> 408 <September> shroud seal<tb> 418 <SEP> first radial surface<Tb> 428 <September> spacer element<tb> 434 <SEP> radial side panel<Tb> 438 <September> sealing surface<Tb> 448 <September> sealing gap<Tb> <September><tb> 502 <SEP> second shroud block assembly<tb> 506 <SEP> second shroud block<Tb> 508 <September> shroud seal<tb> 520 <SEP> second radial surface<Tb> 528 <September> spacer element<tb> 534 <SEP> radial side panel<Tb> 538 <September> sealing surface<Tb> 548 <September> sealing gap
    权利要求:
    Claims (10)
    [1]
    A turbine shroud assembly comprising:a plurality of arcuate shroud block assemblies disposed annularly to form a shroud segment, the plurality of shroud block assemblies including a first shroud block group having a shroud block defining a radial side surface and including a second shroud block assembly having a shroud block comprising a shroud block specifies radial side surface;wherein the first shroud block assembly further comprises a seal interface element and a shroud seal coupled to the first shroud block, wherein a radial side portion of the seal interface element is adjacent to the radial side surface of the first shroud block; andwherein the second shroud block assembly further comprises a seal interface element and a shroud seal coupled to the second shroud block, wherein a radial side portion of the seal interface element is adjacent to the radial side surface of the second shroud block.
    [2]
    2. The turbine shroud assembly of claim 1, wherein the seal shim member of the first shroud block assembly and / or the second shroud block assembly comprises a sealing surface.
    [3]
    The turbine shroud assembly of claim 1 or 2, wherein the seal shim member of the first shroud block assembly and / or the second shroud block assembly is at least partially coated with a thermal barrier coating and / or a wear resistant coating.
    [4]
    4. The turbine shroud assembly of claim 1, wherein the radial side portion of the seal interface element of the first shroud block assembly and / or the second shroud block assembly defines a sealing gap.
    [5]
    5. The turbine shroud assembly of claim 1, wherein the seal shim member of the first shroud block assembly and the second shroud block assembly of the first shroud block assembly of a first material and the shroud seal of the first shroud block assembly and the shroud seal of the second shroud block assembly are formed of a second material different from the first material is.
    [6]
    6. The turbine shroud assembly of claim 5, wherein the first material comprises a high temperature alloy and the second material comprises a ceramic matrix composite material.
    [7]
    7. The turbine shroud assembly of claim 1, wherein the plurality of shroud shroud block assemblies further include one or more shroud block assemblies disposed between the first shroud block assembly and the second shroud block assembly.
    [8]
    8. turbine shroud assembly comprising:a plurality of arcuate shroud block assemblies arranged annularly to form a continuous shroud ring, the plurality of shroud block assemblies including a first shroud block assembly including a first shroud block defining a first radial side surface, a second shroud block assembly adjacent to the first shroud block assembly, wherein the second shroud block assembly includes a second shroud block defining a second radial side surface and wherein a connection between the first and second radial side surfaces is defined;wherein the first shroud block assembly further comprises a shroud interface element and a shroud seal coupled to an inner surface of the first shroud block, the seal interface element having a radial side portion adjacent to the radial side surface of the first shroud block;wherein the second shroud block assembly further comprises a seal interface element and a shroud seal coupled to an inner surface of the second shroud block, the seal interface element having a side portion adjacent to the radial side surface of the second shroud block; andwherein the side portion of the seal interface element of the first shroud block assembly and the side portion of the seal interface element of the second shroud block assembly are adjacent.
    [9]
    9. The turbine shroud assembly of claim 8, wherein the connection between the first shroud block assembly and the second shroud block assembly coincides with a horizontal connection of a turbomachine; and / or wherein the first shroud block assembly is coupled to an inner surface of a first arcuate portion of a turbine housing and the second shroud block assembly is coupled to an inner surface of a second arcuate portion of the turbine housing.
    [10]
    10. The turbine shroud assembly of claim 8 or 9, further comprising a seal extending between the radial side surfaces of the first and second shroud blocks.
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    同族专利:
    公开号 | 公开日
    DE102016100043A1|2016-07-21|
    JP2016133117A|2016-07-25|
    CN105804812A|2016-07-27|
    US9784116B2|2017-10-10|
    CN105804812B|2020-01-10|
    US20160208633A1|2016-07-21|
    JP6931972B2|2021-09-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US1452602A|1921-05-10|1923-04-24|Westinghouse Electric & Mfg Co|Turbine-blade fastening|
    US3147952A|1963-01-28|1964-09-08|Westinghouse Electric Corp|Pin-block, adjustable diaphragm support|
    US3788767A|1971-12-01|1974-01-29|Westinghouse Electric Corp|Two-piece bladed diaphragm for an axial flow machine|
    US3825364A|1972-06-09|1974-07-23|Gen Electric|Porous abradable turbine shroud|
    US5474417A|1994-12-29|1995-12-12|United Technologies Corporation|Cast casing treatment for compressor blades|
    GB2310255B|1996-02-13|1999-06-16|Rolls Royce Plc|A turbomachine|
    US6758653B2|2002-09-09|2004-07-06|Siemens Westinghouse Power Corporation|Ceramic matrix composite component for a gas turbine engine|
    GB0308147D0|2003-04-09|2003-05-14|Rolls Royce Plc|A seal|
    US6984106B2|2004-01-08|2006-01-10|General Electric Company|Resilent seal on leading edge of turbine inner shroud|
    US7587818B2|2004-12-23|2009-09-15|General Electric Company|Repair of gas turbine blade tip without recoating the repaired blade tip|
    US7563071B2|2005-08-04|2009-07-21|Siemens Energy, Inc.|Pin-loaded mounting apparatus for a refractory component in a combustion turbine engine|
    RU2312993C1|2006-09-26|2007-12-20|Закрытое акционерное общество "ОРМА"|Method of restoring radial clearance between stator and rotor parts of turboset|
    GB0703827D0|2007-02-28|2007-04-11|Rolls Royce Plc|Rotor seal segment|
    US7819625B2|2007-05-07|2010-10-26|Siemens Energy, Inc.|Abradable CMC stacked laminate ring segment for a gas turbine|
    US8061977B2|2007-07-03|2011-11-22|Siemens Energy, Inc.|Ceramic matrix composite attachment apparatus and method|
    US8047773B2|2007-08-23|2011-11-01|General Electric Company|Gas turbine shroud support apparatus|
    US8365405B2|2008-08-27|2013-02-05|United Technologies Corp.|Preforms and related methods for repairing abradable seals of gas turbine engines|
    US8118548B2|2008-09-15|2012-02-21|General Electric Company|Shroud for a turbomachine|
    US8250756B2|2009-02-20|2012-08-28|General Electric Company|Method of manufacture of compliant plate seals|
    EP2295722B1|2009-09-09|2019-11-06|Ansaldo Energia IP UK Limited|Blade of a turbine|
    US8303245B2|2009-10-09|2012-11-06|General Electric Company|Shroud assembly with discourager|
    US8454303B2|2010-01-14|2013-06-04|General Electric Company|Turbine nozzle assembly|
    US8632300B2|2010-07-22|2014-01-21|Siemens Energy, Inc.|Energy absorbing apparatus in a gas turbine engine|
    US7997874B2|2010-08-19|2011-08-16|General Electric Company|Wind turbine rotor blade joint|
    JP5751950B2|2011-06-20|2015-07-22|三菱日立パワーシステムズ株式会社|Gas turbine and gas turbine repair method|
    US20150308276A1|2012-12-17|2015-10-29|General Electric Company|Robust turbine blades|US9759079B2|2015-05-28|2017-09-12|Rolls-Royce Corporation|Split line flow path seals|
    US20170276000A1|2016-03-24|2017-09-28|General Electric Company|Apparatus and method for forming apparatus|
    US10718226B2|2017-11-21|2020-07-21|Rolls-Royce Corporation|Ceramic matrix composite component assembly and seal|
    JPWO2019171495A1|2018-03-07|2021-02-25|川崎重工業株式会社|Gas turbine shroud mounting structure, shroud assembly and shroud elements|
    US20190284947A1|2018-03-14|2019-09-19|General Electric Company|Cmc shroud segment with interlocking mechanical joints and fabrication|
    CN109578091B|2018-11-23|2021-09-17|东方电气集团东方汽轮机有限公司|Gas turbine cuts apart ring fixed knot and constructs|
    US11015485B2|2019-04-17|2021-05-25|Rolls-Royce Corporation|Seal ring for turbine shroud in gas turbine engine with arch-style support|
    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-05-31| NV| New agent|Representative=s name: FREIGUTPARTNERS IP LAW FIRM DR. ROLF DITTMANN, CH |
    2019-11-29| AZW| Rejection (application)|
    2020-05-29| AEN| Modification of the scope of the patent|Free format text: :DIE PATENTANMELDUNG WURDE AUFGRUND DES WEITERBEHANDLUNGSANTRAGS VOM 24.01.2020 REAKTIVIERT. |
    2020-10-30| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/597,772|US9784116B2|2015-01-15|2015-01-15|Turbine shroud assembly|
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