Heat distribution-based redirecting of turbine system component coolant by targeted change of cooling channel outlet opening cross-sectional area

Abstract

A method (300) for redirecting a flow of coolant is provided. The method (300) comprises an identification step of identifying a hot spot on an outer surface (212) of a body (210) of a component (200) of the turbine system (200). A first parameter of the component (200) indicates that a temperature of an outer surface (212) in the hot spot exceeds a threshold. Another identifying step identifies a cold spot on the outer surface (212). A second parameter of the component (200) indicates that a temperature of the outer surface (212) in the cold spot is below a threshold. The reconfiguration step reconfigures a plurality of cooling channels (202) of the component (200) to direct a portion of the coolant from a cold point to a hot point.

Description

Technical Field

[0001] The present disclosure relates generally to turbine system components and, more particularly, to targeting coolant flow redirection based on component thermal profiles, such as cooling profiles, such as by reducing cross-sectional areas of cooling passages of components with excess cooling capabilities. Background Art

[0002] Turbine system components typically include cooling passages that transport a coolant through the body of the component to cool it during use in a hot environment, such as a gas or steam turbine.The cooling passages exit the outer surface of the body at outlet openings.

[0003] Turbine system components may have local hot or cold spots due to thermal loads and / or operation at parameters different from those used in the component design. This may result in repeatable damage patterns that can be visually observed, measured and / or predicted using thermal / mechanical modeling. Without changing the component (such as its cooling system), the damage pattern may recur and require additional repairs. This damage pattern may be exacerbated when the system in which the component is installed is operated away from the design parameters (so-called "overburn" or "peaking"), which may result in increased transients, cycles, temperatures and other more extreme parameter values. This may lead to further increases in repair costs, the need for more extensive repair capabilities, or even the scrapping of the component when repair is not feasible.

[0004] Even when the system is operating within design parameters, thermal and mechanical analysis occasionally underestimates damage modes, and repair processes must respond to new or more severe damage than expected. Modifications can be introduced to address this, but can be challenging to execute when it involves changing the distribution of cooling airflow. One method for redistributing cooling airflow is to adjust the size of the cooling channel outlet openings.

[0005] Adjusting the size of the outlet openings of the cooling channels can change the amount of coolant passing therethrough, and the amount of cooling provided by the cooling channels. Current processes for changing the size of the outlet openings include completely filling the outlet openings of the cooling channels and reopening the outlet openings with openings of different sizes. The process of individually reopening each outlet opening (e.g., using drilling) after filling each outlet opening is time consuming and tedious, and the quality results are poor. Summary of the invention

[0006] All aspects, examples and features mentioned below can be combined in any technically possible way.

[0007] One aspect of the present disclosure provides a method comprising: identifying a hot spot on an outer surface of a body of a component of a turbine system, wherein a first parameter of the component indicates that a temperature of the outer surface in the hot spot exceeds a first threshold; identifying a cold spot on the outer surface, wherein a second parameter of the component indicates that a temperature of the outer surface in the cold spot is below a second threshold; and reconfiguring a plurality of cooling channels to direct a portion of coolant from the cold spot to the hot spot.

[0008] Another aspect of the present disclosure includes any of the foregoing aspects, and the outer surface includes a plurality of cooling channels extending thereto, each cooling channel having a first cross-sectional area and having a first outlet opening in the outer surface, and wherein redirecting the coolant includes changing the cross-sectional area of ​​the cold spot cooling channel in the cold spot to have a second cross-sectional area that is less than the first cross-sectional area.

[0009] Another aspect of the disclosure includes any of the foregoing aspects, and changing the cross-sectional area of ​​the cold spot cooling channel includes inserting a hollow member into the cold spot cooling channel, the hollow member having a second cross-sectional area, and coupling the hollow member to the cold spot cooling channel.

[0010] Another aspect of the present disclosure includes any of the preceding aspects, and the hollow member defines a second outlet opening in the outer surface having a second cross-sectional area.

[0011] Another aspect of the disclosure includes any of the foregoing aspects, and the cold spot cooling channel includes a first group of multiple cooling channels, and changing the cross-sectional area of ​​the cold spot cooling channel includes changing the cross-sectional area of ​​each cold spot cooling channel of the first group according to the pattern.

[0012] Another aspect of the present disclosure includes any of the preceding aspects, and identifying the hotspot includes measuring a first parameter of the component after operation of the turbine system.

[0013] Another aspect of the present disclosure includes any of the preceding aspects, and identifying the cold spot includes using a cooling profile of the component.

[0014] Another aspect of the present disclosure includes any of the preceding aspects, and the cooling profile is based at least in part on a flow rate of the coolant through the plurality of cooling channels.

[0015] Another aspect of the present disclosure includes any of the preceding aspects, and identifying the cold spot includes identifying a cold spot cooling channel having excess cooling capacity.

[0016] Another aspect of the present disclosure provides a method comprising: identifying a first region of an outer surface of a body of a component of a turbine system, wherein the first region requires more cooling than the first region currently receives, the first region comprising a first cooling channel of a plurality of cooling channels defined in the body of the component and extending to the outer surface thereof, each of the plurality of cooling channels having a first cross-sectional area and a first outlet opening, and the first cooling channel requiring more cooling than the first cooling channel currently receives; identifying a second region of the outer surface comprising a second cooling channel of the plurality of cooling channels, the second cooling channel receiving more cooling than the second cooling channel currently requires; and reconfiguring one or more of the first cooling channel and the second cooling channel to direct a portion of coolant from the second cooling channel to the first cooling channel.

[0017] Another aspect of the present disclosure includes any of the preceding aspects, and identifying the first region includes using a cooling profile of the component.

[0018] Another aspect of the disclosure includes any of the preceding aspects, and using the cooling profile for the component includes creating the cooling profile for the component.

[0019] Another aspect of the present disclosure includes any of the preceding aspects, and the cooling profile is based on parameters of an exterior surface of the component after use in a turbine system.

[0020] Another aspect of the disclosure includes any of the preceding aspects, and the parameter is oxidation of the outer surface.

[0021] Another aspect of the present disclosure includes any of the preceding aspects, and the parameter is creep.

[0022] Another aspect of the present disclosure includes any of the preceding aspects, and measuring a parameter.

[0023] Another aspect of the present disclosure includes any of the preceding aspects and predicts a parameter based on a digital model of the component.

[0024] Another aspect of the present disclosure includes any of the preceding aspects, and the cooling profile is based on a flow rate of the coolant through the plurality of cooling channels.

[0025] Another aspect of the present disclosure includes any of the preceding aspects, and the redistributing includes reducing a cross-sectional area of ​​the cold cooling channel.

[0026] Another aspect of the present disclosure includes any of the aforementioned aspects, and reducing the cross-sectional area of ​​the cold cooling channel includes inserting a hollow member into the cold cooling channel, the hollow member extending to the outer surface of the body and defining a second outlet opening therein, the second outlet opening in the hollow member having a second cross-sectional area smaller than the first cross-sectional area.

[0027] Two or more aspects described in this disclosure (including those described in this summary) can be combined to form implementations not specifically described herein.

[0028] The details of one or more implementations are set forth in the drawings and description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] These and other features of the present disclosure will be more readily understood from the following detailed description of various aspects of the present disclosure taken in conjunction with the accompanying drawings which depict various embodiments of the present disclosure, wherein:

[0030] FIG1 shows a schematic diagram of an exemplary turbine in the form of a gas turbine system;

[0031] FIG2 illustrates a cross-sectional view of an exemplary gas turbine assembly that may be used with the gas turbine system of FIG1 ;

[0032] Figure 3 shows a perspective view of a turbine system component in the form of a rotating blade according to an embodiment of the present disclosure;

[0033] Figure 4 shows a perspective view of a turbine system component in the form of a nozzle according to an embodiment of the present disclosure;

[0034] Figure 5 shows a perspective view of a turbine system component in the form of a shroud according to an embodiment of the present disclosure;

[0035] Figure 6 shows a schematic longitudinal cross-sectional view of a cooling passage in an exemplary turbine system component according to an embodiment of the present disclosure;

[0036] Figure 7 shows a schematic transverse cross-sectional view of a cooling passage in an exemplary turbine system component according to an embodiment of the present disclosure;

[0037] Figure 8 shows a schematic transverse cross-sectional view of a cooling channel according to another embodiment of the present disclosure;

[0038] Fig. 9 shows a schematic transverse cross-sectional view of a hollow member and a cooling channel according to yet another embodiment of the present disclosure;

[0039] Fig.10 shows a schematic longitudinal cross-sectional view of a hollow member and a cooling channel according to another embodiment of the present disclosure;

[0040] Fig.11 An end view of an exterior surface of a body of a turbine system component is shown, wherein all cooling channels of a plurality of cooling channels have hollow members therein, according to an embodiment of the present disclosure;

[0041] Fig.12 An end view of an exterior surface of a body of a turbine system component according to an embodiment of the present disclosure is shown, the body including a plurality of cooling passages, some of the plurality of cooling passages including hollow members therein;

[0042] Fig.13 An end view of an exterior surface of a body of a turbine system component according to an embodiment of the present disclosure is shown, the body including a plurality of cooling passages, some of the plurality of cooling passages including hollow members therein;

[0043] Fig.14 An end view of an exterior surface of a body of a turbine system component including a plurality of cooling passages is shown according to an embodiment of the present disclosure;

[0044] Fig.15 An end view of an exterior surface of a body of a turbine system component is shown, including coupling a hollow member into a selected cooling passage, according to an embodiment of the present disclosure; and

[0045] Fig.16 An end view of an outer surface of a body of a turbine system component is shown, including removal of a portion of a hollow member extending beyond the outer surface of the body, according to an embodiment of the present disclosure.

[0046] Fig.17 A schematic diagram is shown illustrating one example of a coolant redirection method in a turbine system component according to an embodiment of the present disclosure.

[0047] Fig.18 A schematic diagram is shown illustrating another example of a coolant redirection method in a turbine system component according to an embodiment of the present disclosure.

[0048] It should be noted that the drawings of the present disclosure are not necessarily drawn to scale. The drawings are intended to depict only typical aspects of the present disclosure and therefore should not be considered to limit the scope of the present disclosure. In the drawings, like numbers represent like elements between drawings. DETAILED DESCRIPTION

[0049] First, in order to clearly describe the subject matter of the present disclosure, it will be necessary to select specific terms when referring to and describing relevant machine components within an exemplary industrial machine in the form of a turbine. To the extent possible, common industry terms will be used and adopted in a manner consistent with the accepted meaning of the terms. Unless otherwise stated, such terms should be given a broad interpretation consistent with the context of the present application and the scope of the appended claims. A person of ordinary skill in the art will understand that several different or overlapping terms may be used to refer to a particular component. An object that may be described as a single part herein may include multiple components and be referenced as consisting of multiple components in another context. Alternatively, an object that may be described as comprising multiple components herein may be referred to as a single part elsewhere.

[0050] In addition, several descriptive terms may be used regularly in this article, and it should prove helpful to define these terms at the beginning of this section. Unless otherwise specified, these terms and their definitions are as follows. As used herein, "downstream" and "upstream" are terms that indicate the direction relative to the flow of a fluid, such as a working fluid through a turbine engine, or, for example, an air flow through a combustor or a coolant through one of the component systems of a turbine. The term "downstream" corresponds to the direction of the flow of the fluid, and the term "upstream" refers to the direction opposite to the flow (i.e., the direction in which the flow is emitted).

[0051] It is often necessary to describe parts that are disposed at different radial positions relative to a central axis. The term "radial" refers to movement or position perpendicular to the axis. For example, if a first component is closer to the axis than a second component, this document will describe the first component as being "radially inward" of the second component or "inside" the second component. On the other hand, if the first component resides farther away from the axis than the second component, this document may describe the first component as being "radially outward" or "outside" of the second component. The term "axial" refers to movement or position parallel to the axis. Finally, the term "circumferential" refers to movement or position around the axis. It should be understood that such terms may apply relative to the central axis of the turbine.

[0052] In addition, several descriptive terms may be used regularly herein, as described below. The terms "first," "second," and "third" may be used interchangeably to distinguish one component from another and are not intended to indicate the position or importance of individual components.

[0053] The terms used herein are only used for the purpose of describing specific embodiments and are not intended to limit the present disclosure. As used herein, the singular forms "one", "a kind of" and "the" are intended to also include plural forms, unless the context clearly states otherwise. It will be further understood that when used in the specification, the terms "include" and / or "comprising" specify the presence of stated features, integers, steps, operations, elements and / or parts, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, parts and / or their groups. "Optional" or "optionally" means that the event or situation described subsequently may or may not occur, or the parts or elements described subsequently may or may not exist, and the description includes the situation where the event occurs or the parts exist and the situation where the event does not occur or the parts do not exist.

[0054] Where an element or layer is referred to as being "on," "engaged to," "connected to," or "coupled to," it may be directly on, engaged to, connected to, or coupled to, or there may be intervening elements or layers. In contrast, when an element is referred to as being "directly on," "directly engaged to," "directly connected to," or "directly coupled to," there may be no intervening elements or layers. Other words used to describe relationships between elements should be interpreted in a similar manner (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.

[0055] As described above, the present disclosure provides a turbine system component. The turbine system component includes a body having an outer surface and a cooling channel defined in the body. The cooling channel may be a cooling channel of a gas turbine component and other flow metering channels, orifices or other similar elements, which reduce the flow through this part of the system when this process is applied. The cooling channel extends to the outer surface of the body and has a first cross-sectional area. The turbine system component also includes a hollow member, which is connected in the cooling channel and defines a first outlet opening at the outer surface of the body. The first outlet opening in the hollow member has a second cross-sectional area, which is smaller than the first cross-sectional area, thereby forming an outlet opening smaller in size than the original cooling channel. The connection of the hollow member in one or more cooling channels according to the embodiment of the method of the present disclosure allows the cross-sectional area of ​​the cooling channel to be reduced at the outer surface of the body, and reduces the cooling capacity of the cooling channel. A thermal distribution (such as a cooling distribution) of the turbine system component can be generated to identify those cooling channels with overcooling, so that these cooling channels can reduce the cross-sectional area of ​​their outlet openings, thereby allowing the saved cooling potential energy to be used more effectively elsewhere in the turbine or turbine system component.

[0056] FIG. 1 shows a schematic diagram of an exemplary industrial machine in the form of a turbine 100. Some turbine system components of the turbine 100 may include cooling passages according to the teachings of the present disclosure. In this example, the turbine 100 is in the form of a gas or gas turbine system. The turbine 100 includes a compressor 102 and a burner 104. The burner 104 includes a combustion area 106 and a fuel nozzle assembly 108. The turbine 100 also includes a turbine assembly 110 and a common compressor / turbine shaft 112 (sometimes referred to as a rotor 112). In one embodiment, the turbine 100 may be a 7FA.04 gas turbine (GT) system, which can be commercially available from GE Vernova. The present disclosure is not limited to any particular GT system, and can be implanted with other engines, including, for example, other HA, F, B, LM, GT, TM and E-class engine types of General Electric Energy, and engine types of other companies. The present disclosure is not limited to any particular turbine or turbine, and can be applied to, for example, steam turbines, jet engines, compressors, turbofans, etc. Furthermore, the present disclosure is not limited to any particular component and may be applied, for example, to any form of hot component that is exposed to hot combustion gases in a combustor or a hot gas path of a turbine and requires cooling. In addition to turbines, the present disclosure may also be applied to any industrial machine that requires reduced cooling of hot components.

[0057] Referring to FIG. 1 , air flows through a compressor 102, and the compressed air is supplied to a combustor 104. Specifically, the compressed air is supplied to a fuel nozzle assembly 108, which is integral with the combustor 104. Assembly 108 is in fluid communication with a combustion region 106. Fuel nozzle assembly 108 is also in fluid communication with a fuel source and guides fuel and air to the combustion region 106. The combustor 104 is ignited and the fuel is burned. The combustor 104 is in fluid communication with a turbine assembly 110 so that the gas stream thermal energy is converted into mechanical rotational energy. The turbine assembly 110 (also referred to as a turbine system) includes a turbine 111, which is rotatably coupled to a rotor 112 and drives the rotor. The compressor 102 is also rotatably coupled to the rotor 112. In an exemplary embodiment, there are a plurality of combustors 106 and fuel nozzle assemblies 108.

[0058] FIG2 shows a cross-sectional view of a portion of an exemplary turbine assembly 110 of the turbine 100 ( FIG1 ). The turbine 111 of the turbine assembly 110 includes a row or stage 1 of nozzles 120 coupled to a stationary housing 122 of the turbine 100 and an axially adjacent row or stage 1 of rotating blades 124. The stationary nozzles 126 (also referred to as vanes) may be retained in the turbine assembly 110 by radially outer platforms 128 and radially inner platforms 130. Each stage of blades 124 in the turbine assembly 110 includes a rotating blade 132 that is coupled to the rotor 112 and rotates with the rotor. The rotating blade 132 may include a radially inner platform 134 (at the root of the blade) coupled to the rotor 112 and a radially outer tip 136 (at the tip of the blade). A shroud 138 may separate the nozzles 126 and rotating blades 132 of adjacent stages. A working fluid 140 (including, for example, combustion gases in an exemplary gas turbine) passes through the turbine 111 along a path referred to as a hot gas path (hereinafter referred to as "HGP"). The HGP may be any area of ​​the turbine 111 that is exposed to combustion gases having a high temperature. Various components of the turbine 111 are directly or indirectly exposed to the HGP in the turbine 111 or the hot combustion gases in the combustor 104, and may include a hot gas turbine system component 200 (hereinafter referred to as a "turbine system component"). In the exemplary turbine 111, the nozzle 126, the blade 132, and the shroud 138 are all examples of turbine system components that may benefit from the teachings of the present disclosure. It should be understood that other parts of the turbine 111 that are directly or indirectly exposed to the HGP may also be considered turbine system components that can benefit from the teachings of the present disclosure.

[0059] Figures 3 to 5 A perspective view of an example of a turbine system component 200 is shown in which the teachings of the present disclosure may be employed. Figure 3A perspective view of a turbine system component 200 in the form of a rotating blade 132 is shown. The rotating blade 132 includes a root 142 through which the rotating blade 132 is attached to the rotor 112 (FIG. 2). The root 142 may include a dovetail 144 configured to be mounted in a corresponding dovetail slot in the periphery of a rotor wheel 146 (FIG. 2) of the rotor 112 (FIG. 2). The root 142 may also include a shank 148 extending between the dovetail 142 and a platform 134, which is disposed at the connection of an airfoil 152 and the root 142 and defines a portion of the inner boundary of the HGP through the turbine assembly 110. It should be understood that the airfoil 152 is a moving part of the rotating blade 132 that intercepts the flow of the working fluid and causes the rotor disk to rotate. As can be seen, the airfoil 152 of the rotating blade 132 includes a concave pressure side (PS) outer wall 154 and a circumferentially or laterally opposite convex suction side (SS) outer wall 156, which extend axially between opposite leading edges 158 and trailing edges 160, respectively. The sidewalls 154 and 156 also extend in a radial direction from the platform 150 to the radially outer tip 136. The tip 136 may include any now known or later developed tip shroud (not shown). The cooling passage 202 ( Figures 6 to 16 ) may be used, for example, within an airfoil 152 , a platform 134 , or other parts of a rotating blade 132 .

[0060] Figure 4 A perspective view of a turbine system component 200 in the form of a stationary nozzle 126 is shown. The nozzle 126 includes a radially outer platform 128 by which the nozzle 126 is indirectly attached to the stationary casing 122 (FIG. 2) of the turbine. The outer platform 128 may include any now known or later developed mounting configuration for mounting in a corresponding mount in the casing. The nozzle 126 may also include a radially inner platform 130 for positioning between adjacent turbine rotating blades 132 ( Figure 3 ) and Platform 134( Figure 3 ). Platforms 128, 130 define respective portions of the outer and inner boundaries of the HGP through turbine assembly 110. It should be understood that airfoil 176 is a movable component of nozzle 126 that intercepts the flow of working fluid and directs the flow of working fluid toward turbine rotating blades 132 ( Figure 3 ). It can be seen that the airfoil 176 of the nozzle 126 includes a concave pressure side (PS) outer wall 178 and a circumferentially or laterally opposite convex suction side (SS) outer wall 180, which extend axially between opposite leading edges 182 and trailing edges 184, respectively. The sidewalls 178 and 180 also extend in a radial direction from the platform 130 to the platform 128. The cooling passage 202 ( Figures 6 to 16) may be used, for example, within the airfoil 176 , the platform 128 , the platform 130 , or other parts of the nozzle 126 .

[0061] Figure 5 A perspective view of a turbine system component 200 in the form of a shroud 138 is shown. The shroud 138 may include a platform 190 for positioning over the turbine rotating blades 132 ( FIGS. 2 to 3 ). Figure 3 ) of the tip 136 (FIG. 2 to Figure 3 ) and the nozzle 126 (FIG. 2 and Figure 4 ) of the radially outer platform 128 (FIG. 2 and Figure 4 ). The shield 138 may be secured to the housing 122 ( FIG. 2 ) in any manner. The cooling passage 202 ( Figures 6 to 16 ) may be used, for example, within face 192 or interior surface 194 or other parts of shield 138.

[0062] Common Reference Figures 3 to 5 As described above, embodiments of the present disclosure described herein may be applied to any turbine system component 200 of the turbine 111 ( FIG. 2 ), such as, but not limited to, the turbine rotating blades 132 ( Figure 3 )、Nozzle 126( Figure 4 ) and / or shield 138 ( Figure 5 ). However, it is emphasized that the teachings of the present disclosure are also applicable to combustor 104 components such as fuel nozzles, liners, flow passages, head end components, etc. It should be understood that turbine system component 200 typically includes one or more cooling circuits therein, which include one or more cooling passages 202 to deliver a coolant (typically a gas such as air) to its parts exposed to the hot combustion gases of combustor 104 or the HGP of turbine 111, thereby cooling those parts. Figures 6 to 16 For descriptive purposes, cooling passages 202 according to embodiments of the present disclosure will be shown and described relative to a schematic body 210, which may include any portion of a turbine system component 200, such as, but not limited to, the trailing edges 160, 184 of airfoils 152, 176, respectively, for rotating blades 132 or nozzles 126. It is emphasized that the teachings of the present disclosure may be applied to any cooling passage 202 that exits an outer surface 212 of a body 200 in any turbine system component 200.

[0063] According to an embodiment of the present disclosure, Figure 6 A schematic longitudinal cross-sectional view of a cooling passage 202 in an exemplary turbine system component 200 is shown, and Figure 7A schematic transverse cross-sectional view of a cooling passage 202 of an exemplary turbine system component 200 is shown. The turbine system component 200 includes a body 210 having an outer surface 212. As noted, the body 210 may be part of a hot gas path component of the turbine 111 (FIG. 2). The turbine system component 200 also includes a cooling passage 202 defined in the body 210. The cooling passage 202 may be fluidically coupled to any cooling circuit within the body 210. The body 210 may be any structure capable of having a cooling passage 202 therein so that it extends to an (original) outlet opening 214 in its outer surface 212. The body 210 may include any material now known or later developed for hot components. In the setting of the turbine 111, the body 210 may include a nickel-based or cobalt-based superalloy. More specifically, it may include superalloys suitable for turbine system components, such as but not limited to: nickel-based superalloys such as R108, MarM 247 / CM-247, GTD-222 / 241 / 262 / 111 / 141 / 444, Rene N5 / N4 / N400 / N500, Inco 738; or cobalt superalloys of similar structure.

[0064] The cooling channel 202 has a cross-sectional area in the body 210, referred to herein as the "channel cross-sectional area". The cross-sectional area of ​​the cooling channel 202 may vary along its length. The channel cross-sectional area may be calculated as the average cross-sectional area over the length of the cooling channel 202, excluding the use of a hollow member 220 as described herein. Figure 7 2, the cooling channel 202 has a generally circular transverse cross-section such that the channel cross-sectional area is circular. However, the cooling channel 202 may have a variety of non-circular cross-sectional shapes. Although the cooling channel 202 has a generally linear or rectilinear layout, it may have some curvature. The length of the cooling channel 202 may be the portion thereof that is generally linear and in fluid communication with the outer surface 212 of the body 210.

[0065] Figure 6 and Figure 7Also shown is a turbine system component 200, which includes a hollow member 220 that is coupled to the cooling channel 202 and defines a (new) outlet opening 222 at the outer surface 212 of the body 210. The cross-sectional area of ​​the hollow member 220 at the outlet opening 222 is smaller than the channel cross-sectional area. For reference purposes, the cross-sectional area of ​​the hollow member 220 is referred to as the "member cross-sectional area" in this article. In this way, compared with the original outlet opening 214, the hollow member 220 reduces the dosage of the coolant that passes through the cooling channel 202 and leaves the outlet opening 222, thereby reducing the cooling capacity of the cooling channel 202. The reduction in the cross-sectional area of ​​the outlet opening 222 can be defined by the user. In one example, the member cross-sectional area is about 30% to 50% of the channel cross-sectional area. Alternatively, the channel cross-sectional area is about 2 to 3 times the member cross-sectional area. It should be understood that the cross-sectional area can vary according to many factors, such as but not limited to the size of the turbine system component 200, the location of the turbine system component to be cooled, the desired cooling amount and / or the specific cooling channel. The hollow member 220 has an outer cross-section shaped to allow coupling to the inner cross-section of the cooling channel 202 .

[0066] The hollow member 220 may be coupled to the cooling channel 202 in the body 210 by any number of joining techniques, including brazing, soldering, resistance welding, and other techniques. Figure 7 As shown, the hollow member 220 can be connected to the cooling channel 202 in the body 210 by a brazing material 226. In another embodiment, the brazing material 26 may have a maximum thickness of 300 μm. The brazing material 226 may include any suitable material for brazing the materials of the body 210 and the hollow member 220, such as, but not limited to, a nickel-based, low melting point brazing material such as AMS4782, 103, D15, DF4B or B1P brazing material. The hollow member 220 is made of a material having a melting temperature higher than the operating temperature of the turbine system. Therefore, the operation of the turbine system does not affect the hollow member 220, for example, its internal cross-sectional area does not change. The hollow member 220 may include, for example, a nickel-chromium-based superalloy, a cobalt-based superalloy, or a stainless steel such as, but not limited to: 625 (available from SMC International Superalloy Group (Special Metals Corporation)) or 300 series stainless steel. In one embodiment, the hollow member 220 can extend inwardly from the outer surface 212 at the outlet opening 222 by no less than the hydraulic diameter of the cooling channel 202. In certain embodiments, the hollow member 220 can extend inwardly from the outer surface 212 at the outlet opening 222 (see distance D) by a maximum of between a portion of the cooling channel length to the entire length of the cooling channel 202.

[0067] The hollow member 220 may have a variety of shapes. Figure 7 , the cooling channel 202 is shown as having a generally circular cross-section. Here, the hollow member 220 has an outer cross-section whose shape matches the shape of the inner cross-section of at least a portion of the cooling channel 202. In this example, the hollow member 220 may be tubular. The hollow member 220 may have a minimum wall thickness in the range of, for example, 0.1 mm to 0.3 mm, and the wall thickness is generally consistent along the length. The inner cross-section of the cooling channel 202 may have a variety of different shapes, and the hollow member 220 may be formed to accommodate these shapes. Figure 8 A schematic cross-sectional view of a cooling channel 202 according to another embodiment of the present disclosure is shown. Figure 8 Although the cooling passage 202 in the body 210 has a generally circular cross-section, it includes a plurality of turbulators 228, such as protrusions or pits, on its inner surface. The turbulators 228 may be configured, for example, to improve the cooling capacity of the coolant flow flowing therethrough. In addition to the circular shape, the cross-sectional shape may also be, for example, an elliptical or other rectangular, polygonal, etc. The hollow member 220 may have an accommodating external cross-section to allow insertion into and / or coupling to the original outlet opening 214 of the cooling passage 202 at the outer surface 212 in the body 210. For example, the circular cross-section of the hollow member 220 may be smaller than the minimum diameter between the turbulators 228, or it may include a seat to capture the turbulators 228, etc.

[0068] Fig. 9 A schematic transverse cross-sectional view of a hollow member 220 and a cooling channel 202 according to yet another embodiment of the present disclosure is shown. In certain embodiments, the hollow member 220 need not be tubular, for example, having an inner cross-sectional shape and an outer cross-sectional shape that are circular along its length. That is, the outer cross-sectional shape of the hollow member 220 may be different from the inner cross-sectional shape of the hollow member 220. The hollow member 220 may have an outer cross-sectional shape that matches the shape of the inner cross-sectional shape of at least a portion of the cooling channel 202. Fig. 9 For example, the outer cross-section of the hollow member 202 is generally circular to match the inner cross-section of at least a portion of the cooling channel 202, and the inner cross-section of the hollow member 220 (e.g., polygonal such as square) may be different from the outer cross-section (e.g., circular) of the hollow member 220. Both the outer cross-section and the inner cross-section of the hollow member 220 may be other shapes.

[0069] Fig.1020 and cooling channel 202 according to another embodiment of the present disclosure. In the previous embodiment, the hollow member 220 may have the same internal and external shapes along its length, and the internal and external shapes have the same size. That is, at any longitudinal cross-section, the wall thickness on both sides of the hollow member 220 will have a uniform longitudinal thickness. In an alternative embodiment, as Fig.10 As shown, the cross-sectional area of ​​the hollow member 220 at its inner end 230 inside the body 210 may be different from the member cross-sectional area at the outlet opening 222. In this case, the cross-sectional area of ​​the hollow member 220 where it fluidly converges with the channel cross-sectional area of ​​the cooling channel 202 in the body 210 is greater than the member cross-sectional area at the outlet opening 222. That is, as the coolant flow advances from the cooling channel 202 toward the outlet opening 222, the wall thickness of the hollow member increases and its cross-sectional area decreases. Therefore, the hollow member 220 narrows as the coolant flow advances from the cooling channel 202 to the outlet opening 222. The hollow member 220 may include a variety of other features, including but not limited to: flared ends, internal turbulators, etc.

[0070] Turbine system component 200 generally includes a plurality of cooling passages 202 , each of which may exit a body 210 at an exterior surface 212 . Fig.11 An end view of an outer surface 212 of a body 210 of a turbine system component 200 is shown, the body including a plurality of cooling passages 202 (inside the body 210). In this example, all of the cooling passages 202 (inside the body 210) include hollow members 220 therein. Thus, all of the cooling passages 202 have a smaller member cross-sectional area in the body 210. In this manner, the cooling capacity of all of the cooling passages 202 has been reduced. In alternative embodiments, only some of the cooling passages 202 may include hollow members 220 therein. Fig.12 An end view of an outer surface 212 of a body 210 of a turbine system component 200 is shown, the body including a plurality of cooling passages 202A, 202B (inside the body 210), some of the plurality of cooling passages including hollow members 220 and some of the cooling passages not including hollow members. In this case, the hollow members 220 may be used only in selected cooling passages 202A of the plurality of cooling passages defined in the body 210. Fig.12, the hollow member 220 defines an outlet opening 222 at the outer surface 212 of the body 210, which has a member cross-sectional area for each cooling channel in the selected cooling channel 202A of the plurality of cooling channels 202A, 202B. Therefore, each cooling channel in the selected cooling channel 202A of the plurality of cooling channels has a smaller member cross-sectional area in the body 210 at its outlet opening 222 in the outer surface 212 of the body 210. Other cooling channels 202B that do not include the hollow member 220 maintain a larger channel cross-sectional area at the original outlet opening 214. That is, multiple cooling channels in the other cooling channels 202B may be defined in the body 210, wherein each cooling channel in the cooling channels 202B in the body 210 leaves the outer surface 212 of the body 210 at the outlet opening 214 defined in the body 210 having a larger channel cross-sectional area. The cooling channel 202B also has an original larger cooling capacity. In a given turbine system component 200 , any number of cooling passages 202 or different groups of cooling passages 202 may be sized using the same sized hollow members 220 or different sized hollow members 220 .

[0071] The cooling passages 202A and 202B having outlet openings 222, 214, respectively, having different cross-sectional areas, may be arranged in any desired manner. Fig.12 In one embodiment, for example, two cooling channels 202B are separated by six cooling channels 202A in a pattern that may or may not repeat. Fig.13 As shown, the different cooling channels 202A, 202B may alternate along the outer surface 212 of the body 210. Any pattern may be used to achieve the desired cooling characteristics.

[0072] refer to Figures 14 to 16 , methods according to various embodiments of the present disclosure will be described. The cooling channels 202 that employ the hollow members 220 may be selected in a variety of ways. As noted, in one example, all cooling channels 202 may receive corresponding hollow members 220 ( Fig.11). In another example, the cooling passages 202 for receiving the respective hollow members 220 may be randomly selected. In another example, the cooling passages 202 for receiving the respective hollow members 220 may be selected to form a particular pattern. For example, in many other arrangements, the cooling passages 202A, 202B may be arranged with: alternating cooling passages; one or more cooling passages with hollow members adjacent to one or more cooling passages without hollow members; a repeating pattern; a percentage of cooling passages; and / or at a particular location on the turbine system component 200. In any case, at least one cooling passage 202 of the plurality of cooling passages may be identified to receive the hollow member 220 based on the cooling distribution of the turbine system component 200, the cooling distribution indicating any cooling passage 202 with excess cooling capacity. The cooling distribution may be determined using any now known or later developed software system that employs empirical data, measurement data, and / or thermal modeling. With respect to empirical data, in one non-limiting example, air flow may be measured on a turbine system component using a flow test bench that pressurizes the component and measures the air flow out of the cooling passage. The cooling profile may be generated based on cooling properties, measured flow characteristics, and / or other flow characteristics, and the cooling passage 202C may be identified as part of the method described herein. That is, the method may include identifying the cooling passage 202C from a plurality of cooling passages defined in the body 210 of the turbine system component 200 based on the cooling profile of the turbine system component. Alternatively, the cooling profile and / or identification may be obtained in other ways, for example, created by a third party and provided for use in the method described herein.

[0073] In any case, the cooling profile identifies cooling channels 202 that have excess cooling capacity. "Excess cooling capacity" can be identified, for example, by an excess air flow volume or flow rate compared to a required or desired airflow threshold, or it can be identified by cooling exceeding a predetermined cooling threshold, for example, exceeding a desired temperature, a common temperature among multiple cooling channels, and other options. The threshold of the desired parameter indicating excess cooling capacity can be adjusted for any performance reason. It may be advantageous to reduce the cooling channel 202 cross-sectional area of ​​the identified cooling channel to reduce its cooling capacity. The saved cooling capacity can be used in another location or for a different purpose, thereby increasing, for example, the overall efficiency of the turbine system component 200 and / or the turbine 100 (Figure 1). The cooling capacity of a particular cooling passage 202 may be based on a variety of factors, such as, but not limited to: outlet opening cross-sectional area; passage cross-sectional area; passage and outlet opening physical condition (e.g., physical closure); blockage; oxidation or other wear of the outer surface 212; condition of upstream cooling passages or circuits; number of cooling passages 202; inner and outer diameters of the hollow members 220 therein; and / or coolant temperature, pressure, flow rate. The hollow members 220 may be selected to achieve the desired cooling capacity.

[0074] Fig.14 An end view of an outer surface 212 of a body 210 of a turbine system component 200 is shown, the body including a plurality of cooling passages 202 (inside the body 210 ). A particular cooling passage 202C has been identified as a location with excess cooling capacity and is therefore intended to receive a hollow member 220 . Fig.15 The hollow member 220 is shown coupled to cooling channels 202C (six shown) in the outer surface 212 of the body 212 of the turbine system component 200. As noted, the cooling channels 202C defined in the body 210 have a channel cross-sectional area. Cleaning of the cooling channels 202C (e.g., the inner surface thereof) may optionally be performed prior to inserting the hollow member 210 into the cooling channels 202C. Cleaning may include, but is not limited to, chemical or abrasive / mechanical cleaning that can ensure that the hollow member 220 is properly coupled with any joining technology employed.

[0075] like Fig.15 As shown, coupling may include inserting the hollow member 220 into the selected cooling channel 202C. The hollow member 220 may extend inwardly from the outer surface 212 at the outlet opening 222 by no less than the hydraulic diameter of the cooling channel 202. The extent to which the hollow member 220 extends into the cooling channel 202C may be set, for example, by the length of the cooling channel or the extent to which the hollow member 220 is positioned in the cooling channel 202C. Fig.15It is also shown that the hollow member 220 is physically connected to the corresponding cooling channel 202C, that is, the hollow member cannot be removed. The physical connection may include performing a joining process, such as a brazing process, on the hollow member 220. The brazing process may include forming a brazing material 226 between at least a portion of the hollow member 220 and the corresponding cooling channel 202C in the body 210. For example, the brazing material may be applied as follows: liquid brazing material wicked between the turbine system component 200 and the hollow member 220 at the outlet of the cooling channel 202, brazing foil between the hollow member 220 and the turbine system component 200, dry brazing powder or brazing paste / paste positioned between the turbine system component 200 and the hollow member 220, and the like. The brazing process may also include performing a heat treatment process. The brazing process can be customized for the specific brazing material used and / or the materials of the body 210 and the hollow member 220. The connection can be performed using any suitable connecting device 240. As Fig.15 As shown, a portion 242 of the hollow member 220 extends outwardly beyond the outer surface 212 of the body 210 .

[0076] Fig.16 An end view of turbine system component 200 is shown, with portion 242 of hollow member 220 extending beyond outer surface 212 of body 210 ( Fig.15 ) is removed, for example, by cutting or grinding it away. After removal, the hollow member 220 defines an outlet opening 222 that is in fluid communication with the cooling channel 202C at the outer surface 212 of the body 210, as described herein. The hollow member 220 at the outlet opening 222 has a member cross-sectional area that is smaller than the channel cross-sectional area, thereby reducing the coolant flowing through the cooling channel 202C. The body 210 may also include a cooling channel 202B that has a larger original outlet opening 214 in the outer surface 212 of the body 210 of the turbine system component 200. That is, the cooling channel 202B is defined in the body 210 and has a larger channel cross-sectional area in the body 210 at the original outlet opening 214 in the outer surface 212 of the body 210. In one example, the channel cross-sectional area may be between 1.31 square millimeters and 1.70 square millimeters (mm 2 ) and the cross-sectional area of ​​the member may be between 0.58 mm 2 Up to 0.62mm 2 As noted, other cross-sectional areas are possible.

[0077] Embodiments of the present disclosure provide a turbine system component and method to allow for reduction of the cross-sectional area of ​​the outlet opening of a cooling passage and selectively reduce the cooling capacity of the cooling passage. The cooling profile of the turbine system component can be used to identify those cooling passages with excessive cooling so that these cooling passages can have their outlet opening cross-sectional area reduced, thereby allowing the saved cooling potential energy to be used more efficiently elsewhere in the turbine or turbine system component.

[0078] In the implementation scheme, additional reference is made to Fig.17 , the method 300 may be used to redirect the coolant flow. In summary, the method 300 may include identifying a hot spot P310 on the outer surface 212 of the body 210 of the component 200 of the turbine system 110, identifying a cold spot P320 on the outer surface 212, and reconfiguring the plurality of cooling passages 220 to direct a portion of the coolant from the cold spot to the hot spot P330. When the hot spot P310 is identified, a first parameter of the component 200 may indicate a temperature T of the outer surface 212 in the hot spot. ex Exceeding the first threshold T 5 P312, and the first parameter of the component may be measured after operation of the turbine system 110. When the cold spot P320 is identified, the second parameter of the component 200 may indicate the temperature T of the outer surface 212 in the cold spot. ex Below the second threshold T 2 P322, and a cooling profile of the component 200 may be used. As described above, such a cooling profile may be based at least in part on the flow of coolant through the plurality of cooling passages 220. Identifying cold spots may include identifying cold spot cooling passages having excess cooling capacity, such as by using a cooling profile of the component 200.

[0079] The threshold value may be a temperature range, such as the temperature range T 1 -T 2 Can indicate areas of components with excessive cooling capacity. Temperature Range T 3 -T 4 can indicate areas with sufficient or satisfactory cooling capacity, while the temperature range T 5 or higher may indicate an area of ​​the component where cooling capacity is insufficient. n ) indicates relative temperature, such as T 1 Less than T 2 , T 2 Less than T 3 , and so on. In this example, T 3 -T 4 The areas of the component within the range have adequate cooling and are preferably not modified. However, the temperature range T 1 -T 2Areas of the components within the T are operating at temperatures below the desired temperature, so some of the coolant flow from these areas can be redirected to the T 5 In this way, hot areas of the component can receive increased cooling flow so that these areas can be lowered to a temperature range of T 3 -T 4 Three threshold temperature ranges are described, but it should be understood that 1, 2, or 3 or more thresholds or temperature ranges may be used with the methods described herein.

[0080] As described above, the outer surface 212 may include a plurality of cooling channels 202 extending thereto, and each cooling channel 202 may have a first cross-sectional area and a first outlet opening 214 in the outer surface 212. Redirecting the coolant P330 may include changing the cross-sectional area P332 of the cold spot cooling channel in the cold spot to have a second cross-sectional area that is less than the first cross-sectional area. Changing the cross-sectional area P332 of the cold spot cooling channel may include inserting the hollow member 220 into the cold spot cooling channel P334, and coupling the hollow member 220 to the cold spot cooling channel P336. The hollow member 220 may have a second cross-sectional area and may define a second outlet opening 222 having a second cross-sectional area in the outer surface 212. In an embodiment, the cold spot cooling channel may include a first group of a plurality of cooling channels 202, and changing the cross-sectional area P332 of the cold spot cooling channel may include changing the cross-sectional area of ​​each cold spot cooling channel of the first group according to a pattern as described above.

[0081] In other words, further reference Fig.18 , the method 300 may include identifying a first region P350 of an outer surface 212 of a body 210 of a component 200 of a turbine system 110, wherein the first region requires more cooling P352 than the first region currently receives. The first region may include a first cooling channel of a plurality of cooling channels 202, which is defined in the body 210 of the component 200 and extends to its outer surface 212. Each cooling channel 202 of the plurality of cooling channels may have a first cross-sectional area and a first outlet opening 214. The first cooling channel requires more cooling than the first cooling channel currently receives. The method 300 may also include: identifying that a second region P360 of the outer surface 212 may include a second cooling channel of the plurality of cooling channels 202, which receives more cooling P362 than the second cooling channel currently requires. In addition, the method 300 may include reconfiguring one or more cooling channels of the cooling channels to direct a portion of the coolant from the second cooling channel to the first cooling channel P370, which may include reducing the cross-sectional area P372 of the second cooling channel.

[0082] Identifying the first region P350 may include using a cooling profile P354 of the component 200, which may include creating a cooling profile P356 of the component 200. Such a cooling profile may be based on a parameter of the outer surface 212 after the component 200 is used in the turbine system 110. The parameter may include, for example, oxidation, creep, cracking, voiding, dimensional deformation, discoloration, coating peeling, or another suitable parameter that is now known to be suitable or will be known to be suitable in the future. In addition, such a parameter may be measured in an embodiment, while in other embodiments, such a parameter may be predicted using a digital model of the component 200. As described above, the cooling profile may also be based on the flow rate of the coolant through the plurality of cooling channels 202.

[0083] In an embodiment, reducing the cross-sectional area of ​​the cold cooling channel may include inserting a hollow member 220 into the cold cooling channel P374, as described above. The hollow member may extend to the outer surface 212 of the body 210 and may define a second outlet opening 222 therein, the second outlet opening 222 in the hollow member 220 having a second cross-sectional area smaller than the first cross-sectional area, also as described above.

[0084] As used throughout the specification and claims, approximate language can be used to modify any quantitative representation that can be permitted to vary without resulting in a change in the basic function to which it is associated. Therefore, values ​​modified by one or more terms (such as "about", "approximately" and "substantially") are not limited to the precise values ​​specified. In at least some cases, approximate language can correspond to the precision of the instrument used to measure the value. Here and throughout the specification and claims, range limitations can be combined and / or interchanged; unless the context or language indicates otherwise, these ranges are identified and include all subranges contained therein. "Approximately" applied to a particular value of a range applies to both end values ​​and may indicate + / -10% of the value unless otherwise dependent on the precision of the instrument measuring the value.

[0085] The corresponding structures, materials, actions and equivalents of all means or steps plus function elements in the following claims are intended to include any structure, material or action for performing functions in conjunction with other claimed elements specifically claimed. A description of the present disclosure has been given for the purpose of illustration and description, but it is not intended to be exhaustive or to limit the present disclosure to the disclosed form. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and essence of the present disclosure. Embodiments have been selected and described in order to best explain the principles and practical applications of the present disclosure, and to enable other persons of ordinary skill in the art to understand the various embodiments of the present disclosure with various modifications suitable for the intended specific use.

Claims

1. A method (300), comprising: Identifying a hot spot on an outer surface (212) of a body (210) of a component (200) of a turbine system (110), wherein a first parameter of the component (200) indicates that a temperature of the outer surface (212) in the hot spot exceeds a first threshold; identifying a cold spot on the exterior surface (212), wherein a second parameter of the component (200) indicates that the temperature of the exterior surface (212) in the cold spot is below a second threshold; as well as A plurality of cooling channels (202) are reconfigured to direct a portion (242) of the coolant from the cold spot to the hot spot.

2. The method (300) of claim 1, wherein the outer surface (212) includes the plurality of cooling channels (202) extending therefrom, each cooling channel (202) having a first cross-sectional area and having a first outlet opening (214) in the outer surface (212), and wherein redirecting the coolant includes changing the cross-sectional area of ​​the cold spot cooling channel (202) in the cold spot to have a second cross-sectional area that is less than the first cross-sectional area.

3. The method (300) of claim 2, wherein changing the cross-sectional area of ​​the cold spot cooling channel (202) comprises inserting a hollow member (220) into the cold spot cooling channel (202), the hollow member (220) having the second cross-sectional area, and coupling the hollow member (220) to the cold spot cooling channel (202).

4. The method (300) of claim 3, wherein the hollow member (220) defines a second outlet opening (222) in the outer surface (212) having the second cross-sectional area.

5. The method (300) of claim 2, wherein the cold spot cooling channel (202) comprises a first group of the plurality of cooling channels (202), and changing the cross-sectional area of ​​the cold spot cooling channel (202) comprises changing the cross-sectional area of ​​each cold spot cooling channel (202) of the first group according to a pattern. The method (300) of any preceding claim, wherein identifying the hot spot comprises measuring the first parameter of the component (200) after operation of the turbine system (110).

7. The method (300) of claim 1, wherein identifying the cold spot comprises using a cooling profile of the component (200).

8. The method (300) of claim 7, wherein the cooling profile is based at least in part on a flow rate of a coolant through the plurality of cooling channels (202).

9. The method (300) of claim 1, wherein identifying the cold spot comprises identifying a cold spot cooling channel (202) having excess cooling capacity.

10. A method (300), comprising: identifying a first region of an outer surface (212) of a body (210) of a component (200) of a turbine system (110), wherein the first region requires more cooling than the first region currently receives, the first region comprising a first cooling channel (202) of a plurality of cooling channels (202) defined in the body (210) of the component (200) and extending to the outer surface (212) thereof, each cooling channel (202) of the plurality of cooling channels (202) having a first cross-sectional area and a first outlet opening (214), and the first cooling channel (202) requiring more cooling than the first cooling channel (202) currently receives; identifying a second region of the outer surface (212) including a second cooling channel (202) of the plurality of cooling channels (202) that receives more cooling than currently required by the second cooling channel (202); as well as One or more of the cooling channels (202) are reconfigured to direct a portion of the coolant from the second cooling channel (202) to the first cooling channel (202).

11. The method (300) of claim 10, wherein identifying the first region comprises using a cooling profile of the component (200).

12. The method (300) of claim 11, wherein using the cooling profile of the component (200) comprises creating a cooling profile of the component (200).

13. The method (300) of claim 11, wherein the cooling profile is based on parameters of the outer surface (212) after the component (200) is used in the turbine system (110).

14. The method (300) of claim 13, wherein the parameter is oxidation of the outer surface (212).

15. The method (300) of claim 13, wherein the parameter is creep.

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