• 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 blade (10) is provided comprising: pressure and suction sides (11, 12) connected to define an interior space through which coolant can flow, and first and second projection assemblies (20, 30), wherein each of the first and second protrusion assemblies (20, 30) includes protrusions (21, 31) respectively connected to radially outer portions of respective inner surfaces (111) of the pressure or suction side (11, 12). The protrusions (21) of the first protrusion assembly (20) are separated from protrusions (31) of the second protrusion assembly (30) by gaps (40) each defined between them.
    公开号:CH708438B1
    申请号:CH01164/14
    申请日:2014-07-29
    公开日:2018-11-30
    发明作者:Andrew Jones Mark；Taylor Boyer Bradley；Alan Brittingham Robert；Thomas Foster Gregory；William Kester Christopher
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    description
    Background of the Invention The present description relates to turbine blades.
    A turbine blade may be disposed in a turbine section of a gas turbine engine. The turbine blade may be installed as part of a group of turbine blades in one of a plurality of axially disposed stages of the turbine section. As each group interacts aerodynamically with combustion gases, the group rotates with a rotor passing through the turbine section and causes a corresponding rotation of the rotor that can be used to drive a compressor and a consumer.
    If natural frequencies of a turbine blade are tuned, one can increase the frequency by increasing the rigidity of the blade and / or reducing the mass of the blade (conversely, if one wants to lower the frequency). Since the increase in stiffness is usually associated with an increase in mass, tuning may be difficult because of the competing nature of these factors.
    Brief Description of the Invention The invention is defined based on the independent claims.
    The protrusions of the first protrusion arrangement of the above-mentioned turbine blade may each be connected to portions of the inner surface of the pressure side along an entire span of the turbine blade, and the protrusions of the second protrusion assembly may be connected to portions of the inner surface of the suction side, respectively, along the entire span of the turbine blade be.
    The gaps of each of the above turbine blades may be about 0.76 mm (0.03 inches) wide.
    The gaps of each of the above turbine blades may be defined along a camber line of the turbine blade, respectively.
    The gaps of each of the above-mentioned turbine blades may each be defined on one side of a dome line of the turbine blade.
    The gaps of each of the above turbine blades may be defined on either side or along a curve of the turbine blade.
    Mutually adjacent gaps of each of the above turbine blades may be defined on opposite sides of the camber line, respectively.
    A distribution of gaps, each defined on the individual sides of the camber line of the above-mentioned turbine blades, may be random.
    The gaps of each of the above-mentioned turbine blades may each be defined parallel to a camber line of the turbine blade.
    The gaps of each of the above-mentioned turbine blades may each be aligned transversely to a curvature line of the turbine blade.
    The protrusions of the first protrusion arrangement of the above-mentioned turbine blade may each be connected to portions of the inner surface of the pressure side along the entire span of the turbine blade, and the protrusions of the second protrusion assembly may each be connected to portions of the inner surface of the suction side along the entire span of the turbine blade be.
    The gaps of each of the above-mentioned turbine blades may each be defined along a curve of curvature of the turbine blade.
    The gaps of each of the above-mentioned turbine blades may each be defined on one side of a dome line of the turbine blade.
    The gaps of each of the above-mentioned turbine blades may be defined on both sides along a curvature line of the turbine blade, respectively.
    The turbine blade of claim 14, wherein adjacent gaps are defined on opposite sides of the camber line, respectively.
    A distribution of gaps, each defined on each side of the camber line of the above-mentioned turbine blades, may be random.
    The gaps of each of the above-mentioned turbine blades may each be defined parallel to a curve of the turbine blade.
    The gaps of each of the above-mentioned turbine blades may each be defined transversely or non-parallel to a line of curvature of the turbine blade.
    According to yet another aspect of the invention, there is provided a method of forming a turbine blade, comprising: forming a cavity-forming ceramic core having an elongate member with protrusion-forming recesses separated by gap-forming core portions from protrusion-forming recesses; Suction sides of the turbine blade on each side of the elongate member such that the pressure and suction sides include projection assemblies having projections formed in the projection forming recesses and connected to inner surfaces of the pressure and suction sides, and assembling the pressure and suction sides of the turbine blade such that the pressure-side protrusions are separated from the suction-side protrusions by gaps having dimensions similar to the gap-forming core portions and connected so as to form an internal space through which a K COOLANT can flow.
    These and other advantages and features of the invention will become more apparent from the following description taken in conjunction with the drawings.
    Brief Description of the Invention The subject matter contemplated as the invention is pointed out and specifically claimed in the claims at the end of this specification. The above and other features and advantages of the invention will be apparent from the following detailed description taken in conjunction with the accompanying drawings, in which:
    Fig. 1 is a schematic perspective view of a turbine blade;
    FIG. 2 is an enlarged perspective view of a trailing edge cavity of a turbine blade having rows of split protrusions according to embodiments; FIG.
    Fig. 3 is a schematic illustration of gaps formed between rows of split protrusions according to embodiments;
    Fig. 4 is a schematic representation of offset gaps formed between rows of split protrusions according to embodiments;
    Fig. 5 is a schematic illustration of non-parallel gaps formed between rows of split protrusions according to embodiments;
    Fig. 6 is a perspective view of a ceramic core according to embodiments.
    The detailed description explains embodiments of the invention together with advantages and features by way of example with reference to the drawings.
    Detailed Description of the Invention Referring to Figures 1 and 2, a turbine blade 10 is shown, e.g. for use in a gas turbine in which the turbine blade 10 is installed in a turbine section where combustion gases expand to produce work. The turbine blade 10 may be installed as part of a group of turbine blades in one of a plurality of axially disposed stages of the turbine section. As each group interacts aerodynamically with the combustion gases, the group rotates with a rotor extending through the turbine section. The rotation of the group causes a corresponding rotation of the rotor, which can be used to drive a compressor and a consumer rotating.
    The turbine blade 10 has a pressure side 11 and a suction side 12, which are arranged opposite to each other. The pressure side 11 and the suction side 12 both have a similar span extending along a radial dimension of the rotor. The pressure side 11 and the suction side 12 may be connected to each other at a leading edge 13 and a trailing edge 14, so that they define an interior space 15. The turbine blade 10 may further include baffles 16 (see FIG. 2) extending along portions of the spans of the pressure side 11 and the suction side 12 through the interior space 15. The baffles 16 define channels 17 or cavities 18 with which coolant through the interior 15 can be directed and directed. The cavity 18 near the trailing edge 14 is referred to herein as the "trailing edge cavity" 180.
    The turbine blade 10 further includes a first protrusion assembly 20 and a second protrusion assembly 30. The first projection arrangement 20 has a projection 21 which is connected at least to a radially outer portion of an inner surface 111 of the pressure side 11 in the trailing edge cavity 180. The second projection arrangement 30 has a projection 31 which is connected at least to a radially outer portion of an inner surface 121 of the suction side 12 in the discharge edge cavity 180. It should be understood that the protrusions 21 and 31 as shown in FIG. 2 may be provided as a first plurality of protrusions 21 and a second plurality of protrusions 31. For the sake of clarity and brevity, the case where the protrusions 21 and 31 are provided as the first plurality of protrusions 21 and the second plurality of protrusions 31 will be described below. It should also be understood that the projections 21 and 31 may not only be disposed in the trailing edge cavity 180.
    The radially outer portion of the inner surface 111 and the radially outer portion of the inner surface 121 are defined at a radially outer portion Rops the span. Thus, according to embodiments, the first group of projections 21 and the second group of projections 31 are provided at least in the radially outer portion Rops of the span (see FIG. 6). However, according to other embodiments, the first group of protrusions 21 and the second group of protrusions 31 may be provided along the entire span.
    Each individual protrusion 22 of the first group of protrusions 21 of the first protrusion assembly 20 may, but need not, correspond in position to a corresponding single protrusion 32 of the second group of protrusions 31 of the second protrusion assembly 30. That is, according to alternative embodiments, the individual projections 22 may be offset with respect to the individual projections 32. In addition, each projection 22 is separated by a gap 40 from one or more of the individual projections 32. It should be understood that FIG. 2 illustrates a gap 40 at least for pairs of individual protrusions 22 and 32, and therefore, the turbine blade 10 is provided with a plurality of gaps 40.
    According to embodiments, the gap 40 may be about 0.76 mm (0.03 inches) wide, but this is not mandatory and there are embodiments in which the gap 40 is wider or narrower and where the size of the gap 40 varied. More generally, the gap 40 is larger than any gap normally found in a conventional turbine blade due to manufacturing tolerances due to the shape and size of the conventional ceramic core and the injection molding or casting of the conventional pressure and suction sides.
    According to other embodiments, the interior space 15 of the turbine blade 10 need not have a pin which extends over the entire distance between the inner surface 111 of the pressure side 11 and the inner surface 121 of the suction sides 12 (ie, the turbine blade 10 may be configured to no pins or pins "full length" has). However, where the turbine blade 10 has full-length pins, the baffles may differ from full-length pins in that the baffles 16 extend substantially along the entire length of the spans of the pressure and suction sides 11 and 12 and thereby overall the sizes and Forming the channels 17, the cavities 18 in general and the trailing edge cavity 180 in particular define.
    Various embodiments will now be described with reference to Figs. 3-5. As illustrated in FIG. 3, the voids 40 may be defined in their entirety or in part along a center line of curvature 50 of the turbine bucket 10, the mean curvature line 50 being determined jointly by the respective shapes of the pressure and suction sides 11 and 12. Although not shown in FIG. 3, it should be understood that, alternatively, all gaps 40 or a portion thereof may be defined on one side of the middle camber line 50. As illustrated in FIG. 4, all or part of the gaps 40 may be defined on either or both sides of the center camber line 50. In these embodiments, all gaps 40 or a portion thereof may be defined on opposite sides of the centerline 50. Alternatively, a distribution of all the gaps 40 or a part thereof may be randomly defined on either side of the middle camber line 50. As shown in FIGS. 3 and 4, all the gaps 40 or a part thereof may be defined parallel to the middle warp line 50. Alternatively, as shown in FIG. 5, all gaps 40 or a portion thereof may be oriented transversely or non-parallel with respect to the centerline 50.
    In addition, as shown in Figs. 3 and 4, individual elongated protrusions 220, 320 may be connected to the respective inner surfaces 111, 121 of the pressure and suction sides 11 and 12, respectively. The individual elongated protrusions 220, 230 differ from the individual protrusions 22 and 32 in that the individual elongated protrusions 220 extend from the inner surface 111 and are separated from the inner surface 121 by corresponding gaps 40, while the individual elongated protrusions 320 extend from the inner surface 212 and are separated from the inner surface 111 by respective gaps 40.
    In any case, the embodiments of Fig. 3-5 may be provided alone or in various combinations with each other. In general, the size, shape and orientation of the individual projections 22 and 32 and the gaps 40 may be provided in accordance with various turbine engine 10 design considerations. For example, tuning natural frequencies of a turbine blade may increase the frequency by increasing the rigidity of the blade and / or reducing the mass of the blade (conversely, if you want to lower the frequency). However, because the increase in stiffness can cause an increase in mass, tuning may be difficult because of the competing nature of these tuning effects. That is, the frequency of a bucket with trailing edge movement can be changed if the stiffness could be affected without significantly affecting the mass. This can be achieved according to the embodiments described herein. By providing the gaps 40 between the individual protrusions 22 and 32 (that is, by separating the individual protrusions 22 and 32 from each other), the pressure side of the turbine blade 10 can be decoupled from the suction side, and the rigidity can be reduced. However, by maintaining the individual projections 22 and 32 and keeping the gaps 40 relatively small, the mass of the turbine blade 10 is not appreciably affected.
    According to further aspects of the invention, the size, shape and orientation of the individual projections 22 and 32 and the gaps 40 may be provided according to various design considerations for the turbine blade 10. For example, more efficient cooling of relatively warmer regions on the pressure side 11 or the suction side 12 can be achieved by providing longer individual protrusions 22 near the warmer region, thereby enhancing the rib effect in this region.
    Referring to Fig. 6, a method of forming the turbine blade 10 will now be described. The method includes creating a ceramic core 60 that may be used to form the trailing edge cavity 180. As shown in Fig. 6, the ceramic core 60 has an elongate member 61 having pin-forming recesses 62 and gap-forming core portions 63 at least at the radially outer portion Rüps of the span. The gap-forming core portions 63 are arranged between the projection-forming recesses 62 so that the individual projections 21 and 31 are spaced from each other. The elongate member 61 further includes trailing edge hole forming portions 64 disposed along one side of the elongated member 61 and used to form trailing edge holes 640 in the turbine blade 10 (see FIG. 2).
    Further, after the ceramic core 60 has been produced, the method includes casting (or other similar manufacturing process or other similar manufacturing process) the pressure and suction sides of the turbine blade 10 on each side of the elongate member 61 so that the pressure and pressure Suction sides include the above-described individual projections 22 and 32 formed in the projection-forming recesses 62, and the assembly of the pressure and suction sides of the turbine blade 10, so that the individual projections 22 on the pressure side through the gaps 40 having similar dimensions how the gap-forming core portions 63 are separated from the individual protrusions 32 on the suction side.
    Although the method described above relates to molded components, it should be understood that this is not necessary and that other manufacturing methods and processes may be used for other types of components. For example, the individual protrusions 22 and 32 may be formed in a part that is assembled or manufactured. Such a part may be provided in the form of paddles, blades, vanes, or any other gas turbine components.
    As described herein, a manufacturing method of the ceramic core 60 can be simplified as compared with conventional methods. According to the embodiments described herein, the ceramic core 60 is created so that the gaps 40 are formed and maintained directly. The core yield can be improved.
    Although the invention has been described in detail in connection with only a limited number of embodiments, it should be understood that the invention is not limited to the disclosed embodiments. While various embodiments of the invention have been described, it should be understood that aspects of the invention may include only a few of the described embodiments. Thus, the invention should not be understood as being limited to the above description, as it is limited only by the scope of the appended claims.
    [0042] 10 turbine blade 11 pressure side 111 inner surface 12 suction side 121 inner surface 13 leading edge 14 trailing edge 15 interior 16 impact elements 17 channels 18 cavities 180 trailing edge cavity 20 first projection arrangement 21 projection (first plurality of projections) 22 single projection
    权利要求:
    Claims (10)
    [1]
    claims
    A turbine blade comprising: pressure and suction sides connected to form an internal space through which a coolant can flow; and first and second protrusion assemblies, the first and second protrusion assemblies including protrusions respectively connected to inner surfaces of the pressure or suction sides, the protrusions of the first protrusion assembly being separated by protrusions of the second protrusion assembly defined by gaps between them ,
    [2]
    2. The turbine blade of claim 1, wherein the protrusions of the first protrusion assembly are each connected to portions of the inner surface of the pressure side along an entire span of the turbine blade, and the protrusions of the second protrusion assembly are connected to portions of the inner surface of the suction side, respectively, along the entire span of the turbine blade.
    [3]
    The turbine blade of claim 1, wherein the voids are about 0.76 mm (0.03 inches) wide.
    [4]
    4. The turbine blade of claim 1, wherein the gaps are each defined along a line of curvature of the turbine blade; and / or wherein the gaps are each defined on one side of a dome line of the turbine blade.
    [5]
    5. The turbine blade according to claim 1, wherein the gaps are respectively defined on both sides along a curvature line of the turbine blade; and wherein adjacent gaps are respectively defined on opposite sides of the camber line.
    [6]
    A turbine blade according to claim 5, wherein a distribution of gaps defined on each side of the camber line is random.
    [7]
    7. The turbine blade according to claim 1, wherein the gaps are each defined parallel to a curvature line of the turbine blade.
    [8]
    A turbine blade according to claim 1, wherein the gaps are each defined non-parallel with respect to a line of curvature of the turbine blade.
    [9]
    A turbine blade according to any one of the preceding claims, wherein each of the first and second projection arrays has extended projections, the elongated protrusions differing from the other protrusions in that they extend from one inner surface and from the other inner surface through respective gaps are separated.
    [10]
    10. A method of forming a turbine blade, comprising: creating a void-forming ceramic core having an elongate member having first protrusion-forming recesses separated from second protrusion-forming recesses by gap-forming core portions; Forming pressure and suction sides of the turbine blade on each side of the elongate member so that the pressure and suction sides include projection assemblies having projections formed in the projection forming recesses and connected to inner surfaces of the pressure and suction sides; and assembling the pressure and suction sides of the turbine blade so that the pressure-side protrusions are separated from the suction-side protrusions by gaps having dimensions similar to the gap-forming core portions and connected to form an internal space through which a coolant flows can.
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    同族专利:
    公开号 | 公开日
    JP2015031284A|2015-02-16|
    CH708438A8|2015-06-15|
    US20150037165A1|2015-02-05|
    US9695696B2|2017-07-04|
    DE102014110331A1|2015-02-05|
    CH708438A2|2015-02-13|
    JP6506512B2|2019-04-24|
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    法律状态:
    2015-04-30| PK| Correction|Free format text: BERICHTIGUNG ERFINDER |
    2015-06-15| PK| Correction|Free format text: ERFINDER BERICHTIGT. |
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2018-08-31| PK| Correction|Free format text: BERICHTIGUNG ERFINDER |
    2021-02-26| PL| Patent ceased|
    优先权:
    申请号 | 申请日 | 专利标题
    US13/955,679|US9695696B2|2013-07-31|2013-07-31|Turbine blade with sectioned pins|
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