• 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 cooling system according to the invention includes: a serpentine cooling circuit (40), the serpentine cooling circuit having a first branch (42) extending in a first direction, a second branch (46) extending in a second direction, and a second branch (46) A bend (45) fluidly interconnecting the first branch (42) and the second branch (46); and an air supply cavity (44) for supplying cooling air to the serpentine cooling circuit (40); wherein the first branch (42) of the serpentine cooling circuit (40) extends radially outwardly from and at least partially covers at least one central plenum of a multi-walled blade (6) and wherein the second branch (46) of the serpentine cooling circuit (40) extends extends radially outward from a first set of near-wall cooling channels (18) of the multi-walled blade and this at least partially covered.
    公开号:CH711981A2
    申请号:CH01657/16
    申请日:2016-12-15
    公开日:2017-06-30
    发明作者:Ezekiel Smith Aaron；Thomas Foster Gregory；Wayne Weber David；Anthony Weber Joseph
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    Description [0001] This application is related to pending US applications numbers: _, GE reference 282 168-1,282 169-1,212 171-1,283 464-1,283 467-1,283 463-1 and 284 160-1, all of which have been filed are.
    BACKGROUND TO THE INVENTION
    The disclosure generally relates to turbine systems, and more particularly to a cooling circuit for a tip portion of a multi-walled blade.
    Gas turbine systems are an example of turbomachinery that are widely used in areas such as power generation. A conventional gas turbine system includes a compressor section, a combustor section and a turbine section. During operation of a gas turbine system, various components in the system, such as turbine blades, are exposed to high temperature flows that can cause component failure. Because higher temperature flows generally result in higher power, efficiency and power output of a gas turbine system, it is advantageous to cool the components exposed to the high temperature flows to allow the gas turbine system to operate at elevated temperatures to work.
    Turbine blades usually include a branched labyrinth of internal cooling channels. Cooling air, e.g. is fed to a compressor of a gas turbine system can be passed through the inner cooling channels to cool the turbine blades.
    Cooling systems for multi-walled turbine blades may include inner wall-mounted cooling circuits. Such near-wall cooling circuits may e.g. near-wall cooling channels adjacent to the outer walls of a multi-walled blade included. The near-wall cooling channels are usually small, requiring less cooling flow while still maintaining a sufficient velocity for effective cooling to take place. Other, usually larger, lower ductility internal channels of a multi-walled blade may be used as a source of cooling air and may be used in one or more reuse circuits to collect and redirect "spent" cooling flow to make it the lower heat load regions of the multiwall Redistribute shovel. At the top of a multi-walled blade, the near-wall cooling channels and the inner channels with lower cooling efficiency are exposed to very high heat loads.
    BRIEF DESCRIPTION OF THE INVENTION
    A first aspect of the disclosure provides a refrigeration system including: a serpentine refrigeration cycle, wherein the serpentine refrigeration cycle includes a first branch extending in a first direction, a second branch extending in a second direction, and a bend contains, which fluidly connects the first branch and the second branch; and an air supply cavity for supplying cooling air to the serpentine cooling circuit; wherein the first branch of the serpentine cooling circuit extends radially outwardly from at least one central plenum of a multi-walled blade and at least partially covers the at least one central plenum, and wherein the second branch of the serpentine cooling circuit extends radially outwardly from a first set of wall-proximate cooling channels of the multiwall Shovel extends and the first set of near-wall cooling channels at least partially covered.
    In the aforementioned cooling system, the first branch of the serpentine cooling circuit may extend from the air supply cavity toward a trailing edge of the multi-walled blade, and the second branch of the serpentine cooling circuit may extend from the bend toward a leading edge of the multi-walled blade ,
    In addition, or as an alternative, the first branch of the serpentine cooling circuit may extend from the air supply cavity toward a leading edge of the multi-walled blade, while the second branch of the serpentine cooling circuit may extend from the bend toward a trailing edge of the multi-walled blade ,
    [0009] In some embodiments of any of the aforementioned cooling systems, the first set of near-walled cooling channels may be located adjacent to a pressure side of the multi-walled blade.
    In some embodiments of any of the aforementioned cooling systems, the first branch of the serpentine cooling circuit may extend above a second set of near-wall cooling channels in the multi-walled vane and at least partially cover the second set of near-walled cooling channels.
    In particular, the second set of near-wall cooling channels can be arranged adjacent to a suction side of the multi-walled blade.
    [0012] In any of the aforementioned cooling systems, at least one of the first branch or the second branch of the serpentine cooling circuit may include at least one tip film channel for directing the cooling air to a tip of the multi-walled blade to provide a tip film.
    In some embodiments of any of the aforementioned cooling systems, the second branch of the serpentine cooling circuit may include at least one pressure side film channel for directing the cooling air to a pressure side of the multi-walled blade to provide a pressure side film.
    Additionally or as an alternative, the cooling air may be delivered to the air supply cavity from a central plenum or near-wall cooling channel of the multi-walled blade.
    A second aspect of the disclosure provides a multi-wall turbine bucket comprising: a cooling system disposed inside the multi-wall turbine bucket, the cooling system including: a serpentine cooling circuit, the serpentine cooling circuit defining a first branch forming a first branch Direction extends, a second branch, which extends in a second direction, and includes a bend, which connects the first branch and the second branch in fluid communication with each other; and an air supply cavity for supplying cooling air to the serpentine cooling circuit; wherein the first branch of the serpentine cooling circuit extends radially outwardly from and at least partially covers at least one plenum of the multi-wall turbine blade, and wherein the second branch of the serpentine cooling circuit extends radially outwardly from and to a first set of near-wall cooling channels of the multi-walled turbine blade at least partially covered.
    In the aforementioned multi-wall turbine blade, the first branch of the serpentine cooling circuit may extend from the air supply cavity toward a trailing edge of the multi-walled blade, and the second branch of the serpentine cooling circuit may extend from the bend toward a leading edge of the multi-walled turbine blade extend multi-walled blade.
    In addition or as an alternative, the first branch of the serpentine cooling circuit may extend from the air supply cavity toward a leading edge of the multi-walled blade, and the second branch of the serpentine cooling circuit may extend from the bend towards a trailing edge of the multi-walled Shovel extend.
    In some embodiments of any of the aforementioned multi-wall turbine blades, the first set of near-walled cooling channels may be located adjacent to a pressure side of the multi-walled blade.
    In some embodiments of any of the aforementioned multi-wall turbine blades, the first branch of the serpentine cooling circuit may extend over and at least partially cover a second set of near-walled cooling channels in the multi-walled blade.
    In particular, the second set of near-wall cooling channels can be arranged adjacent to a suction side of the multi-walled blade.
    In some embodiments of any of the aforementioned multi-wall turbine blades, at least one of the first branch or the second branch of the serpentine cooling circuit may include at least one tip film channel for directing the cooling air to a tip of the multi-walled blade to provide a tip film.
    In some embodiments of any of the aforementioned multi-wall turbine blades, the second branch of the serpentine cooling circuit may include at least one pressure side film channel for directing the cooling air to a pressure side of the multi-walled blade to provide a pressure side film.
    In some embodiments of any of the aforementioned multi-wall turbine blades, the cooling air may be delivered to the air supply cavity from a central plenum or near-wall cooling channel of the multi-walled blade.
    In preferred applications, the multi-wall turbine bucket of any kind mentioned above may form a portion of a turbine bucket, wherein the turbine bucket may include a shank connected to the multi-walled turbine bucket.
    A third aspect of the disclosure provides a turbomachine including: a gas turbine system including a compressor component, a combustor component, and a turbine component, the turbine component including a plurality of turbine buckets, and wherein at least one of the turbine buckets includes a multi-walled bucket; and a cooling system disposed within the multi-walled vane, the cooling system including: a serpentine cooling circuit, the serpentine cooling circuit including a first branch extending in a first direction and a second branch extending in a second direction extends; and an air supply cavity for supplying cooling air to the serpentine cooling circuit; wherein the first branch of the serpentine cooling circuit extends radially outwardly from and at least partially covers at least one central plenum of the multi-walled blade, and wherein the second branch of the serpentine cooling circuit extends radially outwardly from a first set of near-wall cooling channels of the multi-walled blade; this at least partially covered.
    The illustrative aspects of the present disclosure solve the problems described herein and / or other problems that are not discussed.
    BRIEF DESCRIPTION OF THE DRAWINGS
    These and other features of this disclosure will become more readily apparent from the following detailed description of various aspects of the disclosure, taken in conjunction with the accompanying drawings, which illustrate various embodiments of the disclosure.
    FIG. 1 is a perspective view of a turbine blade incorporating a multiwall blade according to embodiments. FIG.
    FIG. 2 shows a cross-sectional view of the multi-walled blade of FIG. 1, taken along the line A-A in FIG. 1, according to various embodiments.
    FIG. 3 shows a cross-sectional view of a tip portion of the multi-walled blade of FIG. 1, taken along line B-B in FIG. 1, according to various embodiments.
    4 shows a cross-sectional view of a tip portion of the multi-walled blade of FIG. 1, taken along line B-B in FIG. 1, according to various embodiments.
    FIG. 5 shows a cross-sectional view of a tip portion of the multi-walled blade of FIG. 1, taken along line B-B of FIG. 1, according to various embodiments.
    FIGS. 6-8 illustrate an illustrative method of forming a portion of a two-pass serpentine cooling circuit according to various embodiments.
    9 shows a schematic representation of a gas turbine system according to various embodiments.
    It should be noted that the drawing of the disclosure is not to scale. The drawing is intended to show only typical aspects of the disclosure, and thus should not be considered as limiting the scope of the disclosure. In the drawing, like reference characters designate like elements between the drawings.
    DETAILED DESCRIPTION OF THE INVENTION
    In the figures, e.g. in Fig. 9, the «A» axis represents an axial orientation. As used herein, the terms "axial" and / or "axial" refer to the relative position / direction of objects along axis A that is substantially parallel to the axis of rotation of the turbomachine (particularly the rotor section). As used herein, the terms "radial" and / or "radially" refer to the relative position / direction of objects along an axis (r) that is substantially perpendicular to axis A and axis A at only one single point cuts. In addition, the terms "circumferential" or "circumferential" refer to the relative position / direction of objects along a circumference (c) that surrounds the axis A but does not intersect the axis A at any point.
    As mentioned above, the disclosure relates generally to turbine systems and, more particularly, to a refrigeration cycle for cooling a tip portion of a multi-walled blade.
    According to embodiments, the refrigeration cycle is configured to cool the tip portion of a multi-walled blade of a gas turbine while providing a shield for inner channels of low cooling efficiency and providing a cooling film. The shield can also be created for near-wall cooling channels high cooling efficiency or performance. The refrigeration cycle may include a two-pass serpentine cooling circuit that may be fed with cooling air from a low cooling efficiency inner channel or a near-wall cooling channel. Air passes through the cooling circuit, achieving convection cooling, and is ejected as a cooling film to cool the tip portion of the multi-walled blade.
    Referring to Figure 1, a perspective view of a turbine blade 2 is illustrated. The turbine blade 2 includes a shank 4 and a multi-walled blade 6 which is connected to the shaft 4 and extends radially outwardly therefrom. The multi-walled blade 6 includes a pressure side 8, an opposite suction side 10 and a tip portion 12. The multi-walled blade 6 further includes a leading edge 14 between the pressure side 8 and the suction side 10 and a trailing edge 16 between the pressure side 8 and the suction side 10 on one of Leading edge 14 opposite side.
    The shank 4 and the multi-walled blade 6 may each be made of one or more metals (e.g., steel, steel alloys, etc.) and may be produced (e.g., cast, forged, or otherwise machined) by conventional methods. The shank 4 and the multi-walled blade 6 may be integrally formed (e.g., cast, forged, three-dimensionally printed, etc.) or may be formed as separate components that are subsequently joined together (e.g., by welding, soldering, gluing, or other bonding mechanisms).
    Fig. 2 shows a cross-sectional view of the multi-walled blade 6 taken along the line A-A of Fig. 1. As illustrated, the multi-walled blade 6 may be e.g. include an array 30 of cooling passages including a plurality of high cooling efficiency near-the-wall cooling channels 18 and one or more low cooling efficiency inner passages 20, hereinafter referred to as "central plenums". Various cooling circuits can be created using various combinations of the near-wall cooling channels 18 and the central plenums 20.
    An embodiment incorporating a two-pass serpentine cooling circuit 40 is shown in FIG. 3, which is a cross-sectional view of the multi-walled blade 6 cut along the line B-B of FIG. The two-pass serpentine cooling circuit 40 is disposed radially outward along the multi-walled blade 6 (e.g., closer to the tip portion 12 of the multi-walled blade 6) relative to the arrangement 30 of cooling channels illustrated in FIG. Thus, comparing FIG. 2 with FIG. 3, the two-pass serpentine cooling circuit 40 effectively "shields" the central plenums 20 and at least some of the near-wall cooling channels 18 from the very high heat loads encountered during one rotation of the multi-walled blade 6 (eg in a gas turbine) usually occur at the tip portion 12 of the multi-walled blade 6.
    The two-pass serpentine cooling circuit includes a first branch 42 that extends above and at least partially covers the central plenums 20. The first branch 42 extends rearwardly from a front air supply cavity 44 toward the trailing edge 16 of the multi-walled blade 6. Although shown in FIG. 3 as extending above all of the central plenums 20, the first branch 42 may extend of the serpentine cooling circuit 40 having two passages generally extend over one or more of the central plenums 20.
    The two-pass serpentine cooling circuit 40 further includes a second branch 46 extending over a set (eg, one or more) of the near-wall cooling channels 18 adjacent to the pressure side 8 of the multi-walled blade 6 and the set the near-wall cooling channels 18 at least partially covered. A bend 45 disposed adjacent the trailing edge 16 of the multi-walled vane 6 fluidly interconnects the first and second branches 42, 46 of the serpentine cooling circuit 40 with two passages. The second branch 46 extends from the bend 45 towards the leading edge 14 of the multi-walled vane 6. Comparing Figure 2 with Figure 3, it can be seen that in this embodiment the second branch 46 extends over all the near-wall cooling channels 18 extends, which are arranged adjacent to the pressure side 8 of the multi-walled blade 6. In general, however, the second branch 46 of the dual-passage serpentine cooling circuit 40 may extend over one or more of the near-wall cooling channels 18 located adjacent the pressure side 8 of the multi-walled blade 6.
    Cooling air is supplied to the first branch 42 of the two-pass serpentine cooling circuit 40 via the air supply cavity 44. The air supply cavity 44 may be fluidly connected to at least one of the central plenums 20 and receive cooling air therefrom. In other embodiments, the air supply cavity 44 may be fluidly connected to at least one of the near-wall cooling channels 18 and receive cooling air therefrom. In any case, the air supply cavity 44 in this embodiment is located near the leading edge 14 of the multi-walled blade 6.
    In Fig. 3, taken in conjunction with Figs. 1 and 2, cooling air flows from the air supply cavity 44 (eg, out of the side in Fig. 3) into the first branch 42 through the bend 45 and into the second Branch 46 into it. In the first and second branches 42, 46 and the bend 45 of the two-pass serpentine cooling circuit 40, the cooling air absorbs heat (eg, via convection) from adjacent portions of the tip portion 12 of the multi-walled blade 6, with the underlying near-wall cooling channels 18 and the central plenums 20 are shielded against excessive heat. The cooling air flows out of the first and second branches 42, 46 via at least one tip film channel 48 (e.g., from the side in Fig. 3). The cooling air is directed through the tip film channels 48 to the tip 22 of the multi-walled blade 6. The cooling air is expelled from the tip 22 of the multi-walled blade 6 in the form of a tip film 24 to achieve peak film cooling. In addition, the cooling air is expelled from the second branch 46 to the pressure side 8 of the multi-walled blade 6 through at least one pressure side film channel 50 to provide a film 52 for pressure side film cooling.
    The cooling air may also be discharged from at least one of the near-wall cooling channels 18 to the tip 22 in order to achieve a tip film cooling. For example, For example, as illustrated in FIG. 3, at least one of the near-wall cooling channels 18 adjacent the suction side 10 of the multi-walled blade 6 may be fluidly connected to the tip 22 of the multi-walled blade 6 through at least one tip film channel 54. Cooling air is expelled from the tip film channels 54 (out of the page in Figure 3) to provide a tip film 24 for tip film cooling.
    In another embodiment, a rear air supply cavity 144 located adjacent to the trailing edge 16 of the multi-walled blade 6 may be used to deliver cooling air to the two-pass serpentine cooling circuit 140. Such a configuration is shown in Fig. 4, wherein it is considered in conjunction with Figs. 1 and 2.
    The two-pass serpentine cooling circuit 140 illustrated in FIG. 4 includes a first branch 142 that extends over and at least partially covers the central plenums 20. The first branch 142 extends forward from a rear air supply cavity 144, toward the leading edge 14 of the multi-walled blade 6. A second branch 146 of the two-pass serpentine cooling circuit 140 extends over a set (eg, one or more) of the near-wall cooling channels 18, which are arranged adjacent to the pressure side 8 of the multi-walled blade 6, and covers the set of wall-near cooling channels 18 at least partially. A bend 145 disposed adjacent the leading edge 14 of the multi-walled blade 6 fluidly interconnects the first and second branches 142, 146 of the serpentine cooling circuit 140 with two passages. The second branch 145 extends from the bend 145 towards the trailing edge 16 of the multi-walled blade 6.
    The air supply cavity 144 may be fluidly connected to at least one of the central plenums 20 or at least one of the near-wall cooling channels 18 and receive cooling air therefrom. As with the embodiment illustrated in FIG. 3, the two-pass serpentine cooling circuit 140 illustrated in FIG. 4 is configured to shield the central plenums 20 and at least some of the pressure-side near-wall cooling channels 18 from the very high heat loads that are commonly experienced occur at the tip portion 12 of the multi-walled blade 6. Further, the two-pass serpentine cooling circuit 140 shown in FIG. 4 is configured to provide a tip film 24 and a pressure side film 22 for tip film cooling.
    In yet another embodiment, as shown in Fig. 5, considered in conjunction with Figs. 1 and 2, a first branch 242 of a serpentine cooling circuit 240 may be enlarged with two passes in order not only on the 3) but also a set (eg, one or more) of the near-wall cooling channels 18, which are arranged adjacent to the suction side 10 of the multi-walled blade 6 to extend and at least partially cover them. The first branch 242 extends from an air supply cavity 244 toward the trailing edge 16 of the multi-walled blade 6. As in the embodiment illustrated in FIG. 3, the second branch 246 of the serpentine cooling circuit 240 extends with two passes over a set (eg, one or more sets) multiple) of the near-wall cooling channels 18, which are arranged adjacent to the pressure side 8 of the multi-walled blade 6, and covers the set of near-wall cooling channels 18 at least partially. A bend 245 disposed adjacent the trailing edge 16 of the multi-walled vane 6 fluidly interconnects the first and second branches 242, 246 of the serpentine cooling circuit 240 with two passages. The second branch 246 extends from the bend 245 toward the leading edge 14 of the multi-walled blade 6.
    The air supply cavity 244 may be fluidly connected to at least one of the near-wall cooling channels 18 or at least one of the central collecting chambers 20 and receive cooling air therefrom. The two-pass serpentine cooling circuit 240 illustrated in FIG. 5 is configured to shield the central plenums 20, at least some of the suction-side near-wall cooling channels 18, and at least some of the pressure-side near-wall cooling channels 18 against the very high heat loads that commonly occur the tip portion 12 of the multi-walled blade 6 occur. Further, similar to the embodiment illustrated in FIG. 3, the two-pass serpentine cooling circuit 240 illustrated in FIG. 5 is configured to provide a tip film 24 and a pressure side film 52 for tip film cooling.
    In Fig. 5, the air supply cavity 244 is located near the leading edge 14 of the multi-walled blade 6 with the first branch 242 of the serpentine cooling circuit 240 extending in two directions toward the trailing edge 16 of the multi-walled blade 6. Similar to the embodiment illustrated in FIG. 4, however, the air supply cavity 244 may be located near the trailing edge 16 of the multi-walled blade 6, with the first branch 242 of the serpentine cooling circuit 240 having two passages towards the trailing edge 16 of the multi-walled blade 6 extends.
    FIGS. 6-8 illustrate an illustrative method of producing a portion 60 of the dual pass serpentine cooling circuit 40 according to one embodiment. A cross-sectional view of a core 62 (e.g., a ceramic core) for use in a process for casting the portion 60 of the two-pass serpentine cooling circuit 40 is illustrated in FIG.
    The core 62 includes a squealer core portion 64, a tip core portion 66, and at least one body core portion 68. Handrails 70 secure and separate the various core portions 64, 66, and 68 from one another. The squealer core portion 64 forms a cavity at the tip 22 of the multi-walled blade 6 after casting, which is open radially towards the outside. The tip core portion 66 forms after casting one of the branches 42, 46 of the serpentine cooling circuit 40 with two passages. The body core portion 68 forms after casting at least one of the near-wall cooling channels 18 or the central plenums 20.
    An example of a metal casting 80 produced using the core 62 (e.g., by known casting techniques) is shown in FIG. The casting 80 includes a plurality of openings 82 corresponding to the locations of the support rods 70 in the core 62. In one embodiment, as illustrated in Fig. 8, each aperture 82 may be sealingly closed using a plug 84 of metal (e.g., a braze material). The plug 84 may e.g. are inserted into an aperture 82, press fit or otherwise inserted into a cavity-internal rib 86 of the casting 80 and secured (e.g., by brazing) to the bottom 88 of the scraper cavity 90 and the cavity-internal rib 86. As such, the plugs 84 extend completely through the aperture 92 between the in-cavity rib 86 and the bottom 88 of the scraper cavity 90, thereby preventing cooling air from escaping out of the aperture 92 through the apertures 82.
    The opening 92 between the cavity-internal rib 86 and the bottom 88 of the scraper cavity 90 may be e.g. be used to provide one of the branches 42, 46 of the serpentine cooling circuit 40 with two passages, the plugs 84 substantially perpendicular to the flow of cooling air (eg into or out of the side in FIG. 8) through the opening 92 are aligned therethrough. In this position, the plugs 84 not only seal the openings 82 on opposite sides of the opening 92, but also serve as cooling pins that increase the cooling efficiency of the two-pass serpentine cooling circuit 40 by improving convective heat flow and promoting turbulent airflow , Possible locations for the plugs 84 in the first and second branches 42, 46 of the two-pass serpentine cooling circuit 40 are illustrated in Figs. 3-5. The illustrated locations for plugs 84 in Figs. 3-5 are illustrative only and are not intended to be limiting.
    FIG. 9 shows a schematic view of a gas turbine engine 102 as may be used herein. The gas turbine engine 102 may include a compressor 104. The compressor 104 compresses an incoming airflow 106. The compressor 104 provides a flow of compressed air 108 to a combustor 110. The combustor 110 mixes the flow of compressed air 108 with a pressurized fuel flow 112 and ignites the mixture to produce a flow of combustion gases 114 to produce. Although only a single combustor 110 is illustrated, the gas turbine engine 102 may include any number of combustors 110. The flow of combustion gases 114 is in turn supplied to a turbine 116, which typically includes a plurality of turbine blades 2 (FIG. 1). The flow of the combustion gases 114 drives the turbine 116 to perform mechanical work. do. The mechanical work performed in the turbine 116 drives the compressor 104 via a shaft 118 and may be used to drive an external load 120, such as an electric generator and / or the like.
    In various embodiments, components described as being "connected" together may be interconnected along one or more junctions. In some embodiments, these junctions may include interconnections between various components, and in other instances these junctions may include a solid and / or integral interconnect. That is, components that are "connected" to each other can in some cases be designed simultaneously to define a single continuous element. However, in other embodiments, these bonded components may be fabricated as separate elements and subsequently joined together by known processes (e.g., attachment, ultrasonic welding, bonding).
    When an element or layer is referred to as being "on" another element, "engaged," "connected," or "coupled," it may or may not be directly on the other element, or be directly in engagement, connected or coupled, or there may be intermediate elements. In contrast, there are no intervening elements or layers when referring to an element as being "directly on" the other element, being "directly engaged," "directly connected," or "directly coupled is ". Other words used to describe the relationship between elements should be interpreted in the same way (e.g., "between" versus "directly between," "adjacent" versus "directly adjacent," etc.). As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.
    The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the disclosure. As used herein, the singular forms "a," "an," "the," "the," and "the" are also intended to encompass plurals unless the context clearly dictates otherwise. It is further understood that the terms "having" and / or "having" when used in this specification specify the presence of the specified features, integers, steps, operations, elements, and / or components, but the presence or inclusion one or more characteristics, integers, steps, operations, elements, components and / or their groups are not mutually exclusive.
    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, including the creation and use of any apparatus and systems and practice belong to any included method. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have 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 languages of the claims.
    REFERENCE SIGNS LIST 2 turbine blade 4 shank 6 multi-walled blade 8 pressure side 10 suction side 12 tip region 14 leading edge 16 trailing edge 18 near-wall cooling channel 20 central plenum 22 tip 24 tip film 30 cooling channels 40 serpentine cooling circuit with two passages 42 first branch 44 forward air supply cavity 45 bend 46 second branch 48 tip film channel 50 pressure side film channel 52 film 54 tip film channel 60 portion of the two pass cooling circuit 62 core 64 squealer core portion 66 tip core portion 68 body core portion 70 support rod 80 metal casting 82 aperture 84 plug 86 internal cavity rib 88 bottom 90 squealer cavity
    权利要求:
    Claims (10)
    [1]
    92 Orifice 102 Gas turbine engine 104 Compressor 106 Air 108 Compressed air 110 Combustion chamber 112 Fuel 114 Combustion gases 116 Turbine 118 Shaft 120 Load 140 Two-pass serpentine cooling circuit 142 First branch 144 Air supply cavity 145 Bend 146 Second branch 240 Two-pass serpentine refrigeration cycle 242 First branch 244 Air supply cavity 245 bend 246 second branch claims
    A cooling system comprising: a serpentine cooling circuit (40, 140, 240), the serpentine cooling circuit having a first branch (42, 142, 242) extending in a first direction, a second branch (46, 146, 246) ) extending in a second direction and having a bend (45, 145, 245) fluidly interconnecting the first branch (42, 142, 242) and the second branch (46, 146, 246); and an air supply cavity (44, 144, 244) for supplying cooling air to said serpentine cooling circuit (40, 140, 240), said first branch (42, 142, 242) of said serpentine cooling circuit (40, 140, 240) being radial extends outwardly from at least one central plenum (20) of a multi-walled blade (6) and at least partially covers it, and wherein the second branch (46, 146, 246) of the serpentine cooling circuit (40, 140, 240) extends radially outwardly from a first set of wall-near cooling channels (18) of the multi-walled blade extends from and at least partially covered.
    [2]
    The cooling system of claim 1, wherein the first branch (42, 242) of the serpentine cooling circuit (40, 240) extends from the air supply cavity (44, 244) toward a trailing edge (16) of the multi-walled blade and wherein the second branch (46, 246) of the serpentine cooling circuit (40, 240) extends from the bend (45, 245) towards a leading edge (14) of the multi-walled blade.
    [3]
    The cooling system of claim 1 or 2, wherein the first branch (142) of the serpentine cooling circuit (140) extends from the air supply cavity (144) toward a leading edge (14) of the multi-walled blade and wherein the second branch (145) of the multi-walled blade serpentine cooling circuit (140) extends from the bend (145) towards a trailing edge (16) of the multi-walled blade.
    [4]
    A cooling system according to any one of the preceding claims, wherein the first set of wall-near cooling channels (18) is located adjacent to a pressure side (8) of the multi-walled blade.
    [5]
    A cooling system according to any one of the preceding claims, wherein the first branch (42, 142, 242) of the serpentine cooling circuit (40, 140, 240) extends over and at least partially over a second set of near-wall cooling channels (18) in the multi-walled blade covered, wherein the second set of near-wall cooling channels (18) adjacent to a suction side (10) of the multi-walled blade is arranged.
    [6]
    A refrigeration system according to any one of the preceding claims, wherein at least one of the first branch (42, 142, 242) or the second branch (46, 146, 246) of the serpentine cooling circuit (40, 140, 240) comprises at least one tip film channel (48) for conducting the Cooling air to a tip (22) of the multi-walled blade to provide a tip film (24) contains.
    [7]
    A cooling system according to any one of the preceding claims, wherein the second branch (46, 146, 246) of the serpentine cooling circuit (40, 140, 240) comprises at least one pressure side film channel (50) for directing the cooling air to a pressure side (8) of the multi-walled blade to provide a printed side film (52).
    [8]
    A cooling system according to any one of the preceding claims, wherein the cooling air is supplied to the air supply cavity (44, 144, 244) from a central plenum (20) or a near-wall cooling channel (18) of the multi-walled scoop.
    [9]
    A multi-wall turbine blade (6) comprising: a cooling system disposed inside the multi-wall turbine blade, the cooling system including: a serpentine cooling circuit (40, 140, 240), the serpentine cooling circuit having a first branch (42, 142 , 242) extending in a first direction, a second branch (46, 146, 246) extending in a second direction, and a bend (45, 145, 245) connecting the first branch (42, 142, 242) and the second branch (46, 146, 246) in fluid communication with each other; and an air supply cavity (44, 144, 244) for supplying cooling air to the serpentine cooling circuit (40, 140, 240); wherein the first branch (42, 142, 242) of the serpentine cooling circuit (40, 140, 240) extends radially outwardly from and at least partially covers at least one central plenum (20) of the multi-wall turbine blade, and wherein the second branch (46, 146) , 246) of the serpentine cooling circuit (40, 140, 240) extends radially outwardly from and at least partially covers a first set of near-wall cooling channels (18) of the multi-walled turbine blade.
    [10]
    A turbomachine (102) comprising: a gas turbine system (102) including a compressor component (104), a combustor component (110) and a turbine component (116), wherein the turbine component (116) includes a plurality of turbine blades (2) and wherein at least one of the turbine blades includes a multi-walled blade (6); and a cooling system disposed inside the multi-walled vane, the cooling system including: a serpentine cooling circuit (40, 140, 240), the serpentine cooling circuit (40, 140, 240) having a first branch (42, 142, 242). extending in a first direction, a second branch (46, 146, 246) extending in a second direction, and a bend (45, 145, 245) forming the first branch (42, 142, 242) ) and the second branch (46, 146, 246) fluidly interconnects; and an air supply cavity (44, 144, 244) for supplying cooling air to the serpentine cooling circuit (40, 140, 240); wherein the first branch (42, 142, 242) of the serpentine cooling circuit (40, 140, 240) extends radially outwardly from and at least partially covers at least one central plenum (20) of the multi-walled blade, and wherein the second branch (46 , 146, 246) of the serpentine cooling circuit (40, 140, 240) extends radially outwardly from and at least partially covers a first set of near-wall cooling channels (18) of the multi-walled blade.
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    同族专利:
    公开号 | 公开日
    US20170175547A1|2017-06-22|
    DE102016124019A1|2017-06-22|
    US9926788B2|2018-03-27|
    JP2017122445A|2017-07-13|
    CN106894844B|2021-01-15|
    CN106894844A|2017-06-27|
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    法律状态:
    2019-05-31| NV| New agent|Representative=s name: FREIGUTPARTNERS IP LAW FIRM DR. ROLF DITTMANN, CH |
    2020-12-15| AZW| Rejection (application)|
    优先权:
    申请号 | 申请日 | 专利标题
    US14/977,247|US9926788B2|2015-12-21|2015-12-21|Cooling circuit for a multi-wall blade|
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