• 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:
    There is disclosed a hot gas path component having a stacked structure and a method of manufacturing a hot gas path component having a stacked layout. The layer assembly (100) includes a substrate layer (102), a ceramic matrix composite layer (104), and a non-metallic spacer (106) between the substrate layer (102) and the ceramic matrix composite layer (104) configured to be one or more layers to train several pockets. The method includes securing a non-metallic spacer (106) between a substrate layer (102) and a ceramic matrix composite layer (104) of the hot gas path component having a layer arrangement.
    公开号:CH707023B1
    申请号:CH01633/13
    申请日:2013-09-24
    公开日:2017-10-13
    发明作者:James Zhang Xiuzhang；Wang Haiping
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Description Field of the Invention The present invention is directed to manufacturing components and methods of making manufacturing components. In particular, the present invention is directed to hot gas path components having a ceramic matrix composite layer in layered arrangements.
    Background of the Invention Ceramic matrix composite materials are known to have high temperature resistance. However, components using such ceramic matrix composites may have an undesirably low loading capacity. In contrast, metal components can have a high load capacity. However, metal components that are exposed to high temperatures, such as e.g. along a hot gas path of a turbine, such a load capacity when exposed to such high temperatures.
    Layered components with different materials are known to be challenges. Such challenges are greater for materials in direct contact that have different properties. For example, the difference in coefficients of thermal expansion, thermal conductivity, and other properties may cause the interface between these layers to separate and / or form undesirable features, thereby limiting the applications of such layered components.
    [0004] A hot gas path component having a layered structure and a method of making a hot gas pathway component having a layered arrangement that does not suffer from one or more of the foregoing disadvantages would be desirable in the art.
    Brief Description of the Invention In accordance with the invention, a hot gas path component for a stacked turbine turbine includes a substrate layer, a ceramic matrix composite layer, and a non-metallic spacer between the substrate layer and the ceramic matrix composite layer configured to contain one or more pockets define.
    Accordingly, a hot gas path component having a layer arrangement comprises: a substrate layer; a ceramic matrix composite layer; and a non-metallic spacer between the substrate layer and the ceramic matrix composite layer configured to define one or more pockets.
    The substrate layer and any aforementioned hot gas path component having a layer arrangement may be a nickel-based superalloy.
    The non-metallic spacer of any of the aforementioned hot gas path component having a layer structure may be made of ceramics.
    The non-metallic spacer of any of the above-mentioned hot gas path component having a stacked structure may include a thermal barrier coating.
    The non-metallic spacer of any of the above-mentioned hot gas path component having a layer structure may include yttria-stabilized zirconia.
    The non-metallic spacer of any of the aforementioned hot gas path component having a layer arrangement may at least partially enclose air in the layer arrangement.
    The hot gas path component having a layer arrangement of any type mentioned above may be a side wall of a turbine vane.
    The hot gas path component having a layer arrangement of any type mentioned above may be an airfoil surface.
    The hot gas path component having a layer arrangement of any type mentioned above may be a turbine shroud.
    The non-metallic spacer of any of the aforementioned hot gas path component having a layer arrangement may include a rib extending along the layer arrangement.
    The non-metallic spacer of any of the aforementioned hot gas path component having a layered arrangement may include intersecting ribs.
    The non-metallic spacer of any of the aforementioned hot gas path component having a layer arrangement defines the one or more pockets, wherein the one or more pockets are configured to contain air.
    The non-metallic spacer of any of the aforementioned hot gas path component having a layer arrangement defines the one or more pockets, the one or more pockets being filled with a heat-insulating substance.
    The non-metallic spacer of any of the aforementioned hot gas path component having a layer arrangement may be mechanically attached to either the substrate layer or the ceramic matrix composite layer, or both.
    The non-metallic spacer of any of the aforementioned hot gas path component having a layer arrangement may be bonded to the substrate layer or the ceramic matrix composite layer.
    The non-metallic spacer of any of the above-mentioned hot gas path component having a stacked structure may have a thermal conductivity that is at least one third of the thermal conductivity of the substrate layer.
    The substrate layer of any of the aforementioned hot gas path component having a layered arrangement may be at least 254 μm (10 mils) thick, with the ceramic matrix composite layer being at least 20 mils thick and the non-metallic spacer having a maximum thickness dimension of at least 762 pm (30 mils).
    [0023] In another exemplary embodiment, a hot gas path component having a layer arrangement of a turbine includes a nickel-based superalloy layer, a ceramic matrix composite layer, and a ceramic spacer between the nickel-based superalloy layer and the ceramic matrix composite layer. The ceramic spacer is mechanically attached to either the substrate layer or the ceramic matrix composite layer or both, and the ceramic spacer is bonded to the substrate layer or ceramic matrix composite layer.
    Accordingly, a hot gas path component of a turbine may include: a ceramic spacer mechanically attached to either the substrate layer or the ceramic matrix composite layer, or both; wherein the ceramic spacer is bonded to the substrate layer or the ceramic matrix composite layer.
    In accordance with another aspect of the invention, a method of making a hot gas path component having a layer arrangement of the type described above includes attaching a non-metallic spacer between a substrate layer and a ceramic matrix composite layer of the layer assembly.
    Further features and advantages of the present invention will become apparent from the following more detailed description of the preferred embodiment, taken in conjunction with the accompanying drawings which illustrate, by way of example, the principles of the invention.
    Brief description of the drawings [0027]
    FIG. 1 illustrates a side view of an exemplary hot gas path component with a layer assembly according to an embodiment of the disclosure. FIG.
    FIG. 2 illustrates a perspective view of an exemplary hot gas path component with a layer assembly according to an embodiment of the disclosure. FIG.
    3 illustrates a perspective view of an exemplary turbine vane with a layer assembly according to an embodiment of the disclosure.
    4 illustrates a cross-sectional view of an exemplary airfoil having a layer arrangement according to an embodiment of the disclosure.
    5 illustrates a side view of an exemplary turbine shroud having a layer arrangement according to an embodiment of the disclosure.
    FIG. 6 is a sectional view taken along line A-A of the exemplary turbine shroud shown in FIG. 5. FIG.
    FIG. 7 illustrates a perspective sectional view of an exemplary turbine shroud having a layer arrangement according to an embodiment of the disclosure. FIG.
    FIG. 8 illustrates a perspective view of an exemplary non-metallic multi-fin spacer according to the disclosure. FIG.
    FIG. 9 illustrates a perspective view of an exemplary non-metallic multi-fin spacer according to the disclosure. FIG.
    FIG. 10 illustrates a perspective view of an exemplary non-metallic spacer having a plurality of intersecting ribs according to the disclosure. FIG.
    As far as possible, the same reference numerals are used throughout the drawings to illustrate the like parts.
    DETAILED DESCRIPTION OF THE INVENTION An exemplary hot gas path component having a layered structure and a method of making a hot gas pathway component having a layered structure in accordance with the disclosure are provided. Embodiments of the present disclosure enable use of hot gas pathway components at elevated temperatures and / or for extended periods of time, allowing the use of positive ceramic matrix composite and metal or metallic substrate properties in a layer component, enabling higher turbine efficiency, enabling extended utilization / durability of hot gas path components a turbine, allow for higher turbine quality, allow for higher firing temperatures in turbines, allow for a higher temperature gradient between layers of a hot gas path component or combinations thereof, for example compared to using layer components with a matrix ceramic composite and metal layers in direct contact.
    Figures 1 and 2 illustrate a layer assembly 100 having a substrate layer 102, a ceramic matrix composite layer 104, and one or more non-metallic spacers 106 between the substrate layer 102 and the ceramic matrix composite layer 104. In one embodiment, a portion of a Hot gas path component 101, the layer assembly 100 and defines a surface 111 of the hot gas path components 101, such as a hot gas path 109 (see FIG. 1), a sidewall 302 (see FIG. 3) of a turbine nozzle 300 (see FIG. 3), an airfoil surface 402 (see FIG. 4) of an airfoil 400 (see FIG. 4), a turbine shroud 500 (see FIG. 5) or a combination thereof. Additionally or alternatively, the hot gas path component (101) may be provided with a layer assembly 100 for components that are subject to stress, such as, e.g. a turbine housing, are used.
    Referring to FIGS. 1 and 2, the substrate layer 102, the ceramic matrix composite layer 104, and the non-metallic spacer (s) 106 may have any suitable dimensions based on the desired properties. For example, a suitable substrate thickness 103 for the substrate layer 102 is at least about 10 mils, at least about 15 mils, at least about 20 mils, between about 10 mils, and about 762 microns. 30 mils), between about 15 mils and about 25 mils, between about 25 mils (10 mils) and about 20 mils, between about 50 mils (20 mils) and about 762 microns (30 mils), about 508 pm (20 mils) or any suitable combination, subcombination, region or subset therein. A suitable ceramic matrix composite thickness 105 for the ceramic matrix composite layer 104 is at least about 508 μm (20 mils), at least about 762 μm (30 mils), at least about 1016 μm (40 mils), between about 762 μm (30 mils), and about 50 mils, between about 30 mils and 40 mils, between about 10 mils (40 mils) and about 50 mils, between about 35 mils (35 mils) and about 45 mils, about 10 mils or any suitable combination, subcombination, region or subset therein. As described in more detail below, the dimensions of the non-metallic spacer (s) 106 depend on the geometry of the non-metallic spacer (s) 106.
    Substrate layer 102 is any suitable material. Suitable materials include, but are not limited to, nickel-based alloys and superalloys, chromium-based alloys and superalloys, cobalt-based alloys and superalloys, iron-based alloys and superalloys, or combinations thereof. In one embodiment, the substrate layer 102 has stress resistant properties that overhang those of the ceramic matrix composite layer 104 and / or other similar ceramic matrix composite materials.
    The ceramic matrix composite layer 104 is any suitable material that has properties for the desired application, e.g. Temperature resistances at the hot gas path 109, where the temperatures of the hot gas path component (101) exceeds about 1000 ° C, provides. Suitable materials for the ceramic matrix composite layer 104 include, but are not limited to, carbon, silicon carbide (SiC), silicon nitride (Si 3 N 4), aluminum oxide (Al 2 O 3), mullite (Al 2 O 3 -SiO 4), or a combination thereof. Fiber reinforcement of the ceramic matrix composite layer 104 is with carbon, silicon carbide (SiC), silicon nitride (Si 3 N 4), alumina (Al 2 O 3), mullite (Al 2 O 3 -SiO 4), or a combination thereof.
    The non-metallic spacer 106 separates any suitable portion or ceramic matrix composite layer 104 from the substrate layer 102. In one embodiment, the non-metallic spacer 106 is attached to either the substrate layer 102 or the ceramic matrix composite layer 104 both, as illustrated, for example, in FIG. 6, by interlocking between a protruding means 602 (on the ceramic matrix composite layer 104 and / or the substrate layer 102) and a groove 604 (on the ceramic matrix composite layer 104 and / or the substrate layer 102) ) mechanically fastened. Additionally or alternatively, the non-metallic spacer 106 is adhesively bonded to the substrate layer 102 or the ceramic matrix composite layer 104.
    The dimensions and geometry of the non-metallic spacer 106 depend on the configuration of the substrate layer 102 and the ceramic matrix composite layer 104. As shown in FIG. 5, in one embodiment, a plurality of the non-metallic spacers 106 do not have uneven dimensions based on location. In other embodiments, as illustrated in FIG. 3, the non-metallic spacers 106 have substantially uniform dimensions. Additionally or alternatively, in some embodiments, the non-metallic spacers 106 are arranged as discrete spacer bodies 108 extending from a spacer coating 110, as shown in FIG. 2, extending from the substrate layer 102, as shown in FIG. and / or extending from the ceramic matrix composite layer 104.
    As shown in FIGS. 8-10, in some embodiments, the non-metallic spacers 106 are configured as one or more ribs or ridges 108 that extend along the assembly 100 (see FIG. 1). The ribs 802 include a plateau 804 (see FIG. 8), a tip 902 (see FIG. 9), intersecting ribs 1002 (see FIG. 10), or a combination thereof. As shown in Figure 1, in one embodiment, a spacer thickness 107 (a thickness of the spacer body 108 and spacer coating 110, if present) is at least about 359 mils (35 mils), at least about 40 mils, at least about 1143 microns (45 mils), between about 35 mils and about 55 mils, between about 35 mils and about 45 mils, between about 45 mils and about 1397 pm (55 mils), between about 1016 pm (40 mils) and about 1270 pm (50 mils), about 1143 pm (45 mils), or any suitable combination, subcombination, region, or subregion therein.
    Referring again to Figs. 8-10, in one embodiment, the non-metallic spacer 106 defines pockets 806. The pockets 806 may comprise a substance 112 (see Fig. 1), such as e.g. Air and / or any other suitable substance capable of better thermal insulation than the substrate layer 102 and / or the ceramic matrix composite layer 104. Suitable substances include, but are not limited to, stagnant air, flowing air, fibers, fuel, cooling fluid (stagnant and / or flowing), liquid, gel, vapor or combinations thereof. In one embodiment, the non-metallic spacers 106 and the pockets 806 are completely enclosed by the substrate layer 102 and the ceramic matrix composite layer 104, thereby preventing flow into the pockets 806. Alternatively, the non-metallic spacers 106 and pockets 806 are not completely enclosed, thereby allowing flow into and out of the one or more pockets 806.
    The non-metallic spacer 106 is made of any suitable material or materials capable of reducing the heat transfer between the ceramic matrix composite layer 104 and the substrate layer 102, and are long in the, To reduce the influence of the load from the substrate layer 102 on the ceramic matrix composite layer. Suitable materials for the non-metallic spacer 106 include, but are not limited to, ceramics, yttria stabilized zirconia, gadolinium zirconate, rare earth zirconates, thermal barrier coatings, or combinations thereof. For example, suitable materials have a thermal conductivity that is less than that of the substrate layer 102 by at least a predetermined amount, such as, e.g. between about one tenth and about one third of the thermal conductivity of the substrate layer 102, between about one third and about half of the thermal conductivity of the substrate layer 102 is between about one quarter and about half of the thermal conductivity of the substrate layer 102 between about one quarter and about one third of the thermal conductivity of the substrate layer 102 is between about one tenth and about one third of the thermal conductivity of the substrate layer 102, about half, about a quarter, about one third, is about one tenth or any suitable combination, subcombination, range or subset thereof.
    The non-metallic spacer 106, the individual spacer bodies 108, the spacer coating 110 or a combination thereof are allowed to grow and / or are applied to the substrate layer 102 and / or the ceramic matrix composite layer 104. In one embodiment, such application is by electron beam electron beam deposition (EBPVD), air plasma spray (APS), high velocity flame spraying (HVOF), electrostatic spray assisted vapor deposition (ESAVD), direct vapor deposition, other suitable spraying techniques, or a combination thereof. In another embodiment, the non-metallic spacer 106 is positioned after processing the substrate layer 102 and / or after the formation / stiffening of the ceramic matrix composite layer 104 to thereby complete geometric features of the substrate layer 102 and / or the ceramic matrix composite layer 104. For example, in these embodiments, the pockets 806 in the non-metallic spacers 106 are formed, at least in part, by non-planar features of the substrate layer 102 and / or the ceramic matrix composite layer 104. In another embodiment, the non-metallic spacer 106 is removed after stripping an existing layer, such as an adhesive. of the non-metallic spacer 106 after extended use, the substrate layer 102, the ceramic matrix composite layer 104, or a combination thereof.
    There is disclosed a hot gas path component and a method of manufacturing such. The hot gas path component includes a laminate having a substrate layer, a ceramic matrix composite layer, and a non-metallic spacer between the substrate layer and the ceramic matrix composite layer configured to form one or more pockets. The laminated hot gas path component includes a nickel-based superalloy layer, a ceramic matrix composite layer, and a ceramic spacer between the nickel-based superalloy layer and the ceramic matrix composite layer.
    The ceramic spacer is mechanically attached to either or both of the substrate layer or the ceramic matrix composite layer, and the ceramic spacer is adhesively bonded to the substrate layer or ceramic matrix composite layer. The method includes securing a non-metallic spacer
    权利要求:
    Claims (10)
    [1]
    between a substrate layer and a ceramic matrix compound layer of the hot gas path component having a layer arrangement. claims
    A hot gas path component (101) of a turbine comprising a layer assembly (100) comprising: a substrate layer (102); a ceramic matrix composite layer (104); and a non-metallic spacer (106) between the substrate layer (102) and the ceramic matrix composite layer (104) configured to define one or more pockets (806).
    [2]
    A hot gas path component (101) having a layer assembly (100) according to claim 1, wherein the substrate layer (102) consists of a nickel-based superalloy or a ceramic, wherein the non-metallic spacer (106) preferably includes a thermal barrier coating.
    [3]
    3. hot gas path component (101) having a layer arrangement (100) according to any one of the preceding claims, wherein the non-metallic spacer (106) at least partially enclosing air in the layer assembly (100).
    [4]
    A hot gas path component (101) having a layer assembly (100) according to any one of the preceding claims, wherein the hot gas path component (101) is a side wall (302) of a turbine vane (300) or airfoil surface (402) or turbine shroud (500).
    [5]
    A hot gas path component (101) comprising a layer assembly (100) according to any one of the preceding claims, wherein the non-metallic spacer (106) includes a rib (802) extending along the layer assembly (100) or intersecting ribs (1002 ) contains.
    [6]
    A hot gas path component (101) comprising a layer assembly (100) according to any one of the preceding claims, wherein the non-metallic spacer (106) defines the one or more pockets (806), the one or more pockets (806) being for the Inclusion of air are set up.
    [7]
    A hot gas path component (101) comprising a layer assembly (100) as claimed in any one of the preceding claims, wherein the non-metallic spacer (106) defines the one or more pockets (806), the one or more pockets (806) being connected to one heat-insulating substance (112) are filled.
    [8]
    8. hot gas path component (101) having a layer assembly (100) according to any one of the preceding claims, wherein the non-metallic spacer (106) has a thermal conductivity which is at least one third of the thermal conductivity of the substrate layer (102).
    [9]
    A hot gas path component (101) of a turbine according to any one of the preceding claims, wherein the ceramic spacer (106) is mechanically secured to either the substrate layer (102) or the ceramic matrix composite layer (104) or both; wherein the ceramic spacer (106) is bonded to the substrate layer (102) or ceramic matrix composite layer (104).
    [10]
    A method of making a hot gas path component (101) having a layer assembly (100) according to any one of the preceding claims, the method comprising attaching a non-metallic spacer (106) between a substrate layer (102) and a ceramic matrix composite layer (104) Layer arrangement (100).
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2021-04-30| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US13/630,708|US9527262B2|2012-09-28|2012-09-28|Layered arrangement, hot-gas path component, and process of producing a layered arrangement|
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