Airfoil components for turbomachinery parts that use airfoil coolant for platform cooling.

Abstract

The present invention provides a turbomachinery component including an airfoil component having a cooling passage for platform cooling using coolant from the airfoil section. [Solution] A collection plenum 194 is defined in the airfoil body and configured to collect coolant exiting from the impact opening of the impact cooling member within it. A cooling passage 200 is defined within the airfoil body, fluidly communicating with the collection plenum, and extends to a first film cooling opening 202 in part of the airfoil body. A mount cooling plenum 210 is defined at least partially within the airfoil mount 154 and fluidly communicating with the collection plenum. A plurality of second cooling openings 220 are defined on the flow path opposing surface 160 of the airfoil mount downstream of the trailing edge and fluidly communicating with the mount cooling plenum. The second cooling openings 220 cool the airfoil mount and any platform 130 coupled thereto. The airfoil component 138 can be additively manufactured.

Description

Technical Field

[0001] The present disclosure generally relates to turbomachinery components, and more specifically to turbomachinery components including airfoil components having cooling passages for platform cooling using coolant from the airfoil.

Background Art

[0002] Turbomachinery components such as turbomachinery blades or nozzles include an airfoil body and platforms at the inner and optionally outer ends of the airfoil body. The high-temperature regions of the sidewalls of the platforms are typically cooled through openings in the sidewalls. One problem with such cooling is that the brazing material used to join the components of the turbomachinery nozzle may fill the cooling holes. Casting the cooling passages and film cooling holes for the sidewalls is very difficult because the cores are brittle, very complex, and expensive. In particular, providing film cooling passages and openings for the platform along the trailing edge of the airfoil body and along the sidewalls of the platform is difficult using conventional cast parts and drilling. Additive manufacturing such as direct metal laser melting (DMLM) or selective laser melting (SLM) is emerging as a reliable manufacturing method for producing industrial parts.

Summary of the Invention

[0003] All aspects, examples, and features described below can be combined in any technically possible way.

[0004] One aspect of the present disclosure includes an airfoil component comprising: an airfoil body having positive pressure side surfaces, negative pressure side surfaces, and a trailing edge; an airfoil mount coupled to at least one end of the airfoil body, each airfoil mount comprising a flow path facing surface and a side wall; a primary cooling plenum extending through the airfoil body to guide coolant; an impact cooling member within the primary cooling plenum, comprising a plurality of internally defined impact openings configured to guide coolant from the primary cooling plenum to the inner surface of a portion of the airfoil body; and an airfoil component configured to collect coolant exiting the plurality of impact openings. The airfoil comprises a collection plenum defined in the main body, a plurality of cooling passages defined within the airfoil body and in fluid communication with the collection plenum, each of which extends through one of the positive pressure side, negative pressure side, or trailing edge of the airfoil body to at least one first film cooling opening, a mount cooling plenum at least partially defined within each airfoil mount and in fluid communication with the collection plenum, and a plurality of second cooling openings defined on the flow path-facing surface of each airfoil mount downstream of the trailing edge, the plurality of second cooling openings in fluid communication with the mount cooling plenum.

[0005] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein a plurality of second cooling openings are arranged in a row parallel to the side walls of each airfoil mount.

[0006] Another aspect of the present disclosure includes any of the preceding aspects, wherein the sidewall of each airfoil mount downstream of the trailing edge is curved around the trailing edge of the airfoil body, and a plurality of second cooling openings are arranged in a row that curves parallel to the sidewall of each airfoil mount downstream of the trailing edge.

[0007] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein each of the plurality of second cooling openings includes a diffuser-shaped opening.

[0008] Another aspect of the present disclosure includes any of the preceding aspects, wherein a subset of cooling passages extends through the rear of the airfoil body to at least one first film cooling opening at the trailing edge, and a mount cooling plenum extends within the airfoil mount parallel to the subset of cooling passages extending through the rear of the airfoil body.

[0009] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein the airfoil component comprises a plurality of parallel sintered metal layers over its entire height.

[0010] Another aspect of the present disclosure includes any of the preceding aspects, wherein an airfoil mount coupled to at least one end of an airfoil body includes an outer airfoil mount on a first end of the airfoil body and an inner airfoil mount on an opposing second end of the airfoil body.

[0011] One aspect of the present disclosure includes a turbomachinery component comprising an airfoil component as described above, further comprising a platform coupled to each airfoil mount around a side wall, wherein coolant from a plurality of second cooling openings defined on the flow path-facing surface cools each platform.

[0012] Another aspect of the present disclosure includes a turbomachinery comprising a compressor, a combustor operatively coupled to the compressor, and a turbine operatively coupled to the combustor, wherein the turbine includes an airfoil component, the airfoil component comprising an airfoil body having a positive pressure side, a negative pressure side, and a trailing edge, an airfoil mount coupled to at least one end of the airfoil body, each airfoil mount comprising a flow path facing surface and a side wall, a primary cooling plenum extending through the airfoil body to guide coolant, and an impact cooling member within the primary cooling plenum comprising a plurality of internally defined impact openings configured to guide coolant from the primary cooling plenum to the inner surface of a portion of the airfoil body The airfoil includes a collection plenum defined in the airfoil body, configured to collect coolant exiting a plurality of impact openings; a plurality of cooling passages defined within the airfoil body and in fluid communication with the collection plenum, each of which extends through one of the positive pressure side, negative pressure side, or trailing edge of the airfoil body to at least one first film cooling opening; a mount cooling plenum at least partially defined within each airfoil mount and in fluid communication with the collection plenum; and a plurality of second cooling openings defined on the flow path-facing surface of each airfoil mount downstream of the trailing edge, the plurality of second cooling openings in fluid communication with the mount cooling plenum.

[0013] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein a plurality of second cooling openings are arranged in a row parallel to the side walls of each airfoil mount.

[0014] Another aspect of the present disclosure includes any of the preceding aspects, wherein the sidewall of each airfoil mount is located downstream of the trailing edge of the airfoil body and curves around the trailing edge of the airfoil body, and a plurality of second cooling openings are arranged in a row that curves parallel to the sidewall of each airfoil mount downstream of the trailing edge.

[0015] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein each of the plurality of second cooling openings includes a diffuser-shaped opening.

[0016] Another aspect of the present disclosure includes any of the preceding aspects, wherein a subset of cooling passages extends through the rear of the airfoil body to at least one first film cooling opening at the trailing edge, and a mount cooling plenum extends within the airfoil mount parallel to the subset of cooling passages extending through the rear of the airfoil body.

[0017] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein the airfoil component comprises a plurality of parallel sintered metal layers over its entire height.

[0018] Another aspect of the present disclosure includes any of the preceding aspects, wherein an airfoil mount coupled to at least one end of an airfoil body includes an outer airfoil mount on a first end of the airfoil body and an inner airfoil mount on an opposing second end of the airfoil body.

[0019] Another aspect of the present disclosure includes any of the aforementioned aspects, further comprising a platform coupled to each airfoil mount around a side wall, wherein coolant from a plurality of second cooling openings defined on the flow path-facing surface cools each platform.

[0020] Another aspect of the present disclosure is a step of additively manufacturing an airfoil component, wherein the airfoil component comprises an airfoil body having a positive pressure side, a negative pressure side, and a trailing edge; an airfoil mount coupled to at least one end of the airfoil body, each airfoil mount comprising a flow path facing surface and a side wall; a primary cooling plenum extending through the airfoil body to guide coolant; an impact cooling member within the primary cooling plenum, comprising a plurality of internally defined impact openings configured to guide coolant from the primary cooling plenum to the inner surface of a portion of the airfoil body; a collection plenum defined in the airfoil body configured to collect coolant exiting the plurality of impact openings; and a plurality of cooling passages defined within the airfoil body and in fluid communication with the collection plenum, each of the plurality of cooling passages comprising the positive pressure side, negative pressure side, and trailing edge of the airfoil body. A method comprising the steps of: a plurality of cooling passages extending through one of the sides or trailing edge to at least one first film cooling opening; a mount cooling plenum at least partially defined within each airfoil mount and in fluid communication with a collection plenum; a plurality of second cooling openings defined on the flow-opposite surface of each airfoil mount downstream of the trailing edge, the plurality of second cooling openings in fluid communication with the mount cooling plenum, wherein the airfoil component comprises a plurality of parallel sintered metal layers over its entire height; and a step of coupling the airfoil component to at least one platform having an opening configured to fit with an airfoil mount, wherein coolant from the plurality of second cooling openings defined on the flow-opposite surface of the airfoil mount cools the respective platform.

[0021] Another aspect of the present disclosure includes any of the aforementioned aspects, wherein a plurality of second cooling openings are arranged in a row parallel to the side walls of each airfoil mount.

[0022] Another aspect of the present disclosure includes any of the preceding aspects, wherein the sidewall of the airfoil mount is located downstream of the trailing edge of the airfoil body and curves around the trailing edge of the airfoil body, and a plurality of second cooling openings are arranged in a row that curves parallel to the sidewall of each airfoil mount downstream of the trailing edge.

[0023] Another aspect of the present disclosure includes any of the foregoing aspects, where a subset of the plurality of cooling passages extends through the rear portion of the airfoil body to at least one first film cooling aperture at the trailing edge, and the mount cooling plenum extends within the airfoil mount parallel to the subset of the plurality of cooling passages that extends through the rear portion of the airfoil body.

[0024] Two or more aspects described in this summary section, including those described above, may be combined to form embodiments not specifically described herein. That is, all embodiments described herein can be combined with each other.

[0025] Details of one or more embodiments are set forth in the accompanying drawings and the description below. Other features, objects, and advantages will be apparent from the description and drawings, and from the claims.

[0026] These features of the present disclosure and other features will be more readily understood by considering the following detailed description of various aspects of the present disclosure in conjunction with the accompanying drawings that illustrate various embodiments of the present disclosure.

Brief Description of the Drawings

[0027] [Figure 1] FIG. 1 is a schematic diagram of an exemplary turbomachine in the form of a gas turbine system including an airfoil component, according to an embodiment of the present disclosure. [Figure 2] FIG. 2 is a cross-sectional view of an exemplary gas turbine that can be used with the gas turbine system of FIG. 1 and includes an airfoil component, according to an embodiment of the present disclosure. [Figure 3] FIG. 3 is a perspective view of an exemplary turbomachine component in the form of a stationary nozzle and including an airfoil component, according to an embodiment of the present disclosure. [Figure 4] FIG. 4 is a side view of an exemplary turbomachine component in the form of a stationary nozzle and including an airfoil component, according to an embodiment of the present disclosure. [Figure 5]This is an enlarged perspective view of the rear of a turbomachinery component, which is a fixed nozzle configuration and includes an airfoil component, according to an embodiment of the present disclosure. [Figure 6] This is a cross-sectional view of an airfoil component along line 6-6 in Figure 4 according to an embodiment of the present disclosure. [Figure 7] This is a cross-sectional view of an airfoil component along line 7-7 in Figure 4 according to an embodiment of the present disclosure. [Figure 8] This is an enlarged perspective view of the rear of a turbomachinery component, which is in the form of a fixed nozzle and includes an airfoil component, according to another embodiment of the present disclosure. [Figure 9] This is a cross-sectional view of an airfoil component in Figure 8, similar to line 6-6 in Figure 4 according to another embodiment of the present disclosure. [Figure 10] This is a schematic block diagram of an exemplary additive manufacturing system for additive manufacturing airfoil components according to embodiments of the present disclosure. [Figure 11] This is a cross-sectional view of a plurality of parallel sintered metal layers of an airfoil component according to an embodiment of the present disclosure. [Modes for carrying out the invention]

[0028] Please note that the drawings in this disclosure are not necessarily to scale. The drawings are intended to illustrate only typical embodiments of this disclosure and should not be considered to limit the scope of this disclosure. In the drawings, the same reference numerals represent similar elements across drawings.

[0029] First, in order to clearly explain the current disclosure, it is necessary to select specific terminology when referring to and describing relevant machine parts in exemplary applications of turbomachinery. Wherever this is done, common industrial terminology will be used and adopted in a manner consistent with its accepted meaning. Unless otherwise stated, such terminology should be given a broad interpretation consistent with the context of this application and the appended claims. Those skilled in the art will understand that, in many cases, certain components may be referred to using several different or overlapping terms. What may be described herein as a single component may also be included in and referred to in another context as consisting of multiple components. Alternatively, what may be described herein as consisting of multiple components may be referred to elsewhere as a single component.

[0030] In addition, this specification may regularly use several descriptive terms, and it will be useful to define these terms at the beginning of this section. These terms and their definitions are as follows, unless otherwise specified: As used herein, “downstream” and “upstream” are terms indicating direction relative to the flow of a working fluid through a turbomachinery, or a fluid such as the flow of air through a combustor, or a coolant through one of the turbomachinery's component systems. The term “downstream” corresponds to the direction of the fluid flow, and the term “upstream” refers to the opposite direction of the flow. The terms “forward” and “rear” refer to directions unless otherwise specified, with “forward” referring to the front of the turbomachinery or compressor end, and “rear” referring to the rear of the turbomachinery or turbine end.

[0031] In addition, several descriptive terms may be used repeatedly 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 location or importance of any individual component.

[0032] The terms used herein are intended solely to describe specific embodiments and are not intended to limit the disclosure. As used herein, unless otherwise explicitly indicated in the context, the singular forms “a,” “an,” and “the” also include the plural forms. The terms “comprise” and / or “comprising,” as used herein, express the existence of the described features, integers, steps, actions, elements, and / or components, but will not be understood to exclude the existence or addition of one or more other features, integers, steps, actions, elements, components, and / or sets thereof. “Optional” or “optionally” means that the events described later may or may not occur, or the features described later may or may not exist, and this statement includes both instances in which the events occur or the features exist, and instances in which the events do not occur or the features do not exist.

[0033] When an element or layer is referred to as "on top of," "engaged with," "connected to," "joined," or "attached" to another element or layer, it may be directly on top of, connected to, joined to, or attached to the other element or layer, and there may be an intervening element or layer. Conversely, when an element is referred to as "directly on top of," "directly engaged to," "directly connected to," or "directly joined" to another element or layer, there is no intervening element or layer. Other words used to describe relationships between elements should be interpreted similarly (e.g., "between" versus "directly between," "adjacent to" versus "directly adjacent to"). As used herein, the term "and / or" includes any of the related enumerated items and all combinations of one or more of them. The verb forms "join" and "attach" may be used interchangeably herein.

[0034] As described above, this disclosure provides an airfoil component and a turbomachinery component comprising an airfoil component. The airfoil component includes an airfoil body having positive pressure sides, negative pressure sides, and a trailing edge, and an airfoil mount coupled to at least one end of the airfoil body. Each airfoil mount includes a flow path facing surface and a side wall. A primary cooling plenum extends through the airfoil body to guide coolant. An impact cooling member is located within the primary cooling plenum and includes a plurality of impact openings defined within the primary cooling plenum, which are configured to guide coolant from the primary cooling plenum to the inner surface of a portion of the airfoil body. A collection plenum is defined within the airfoil body and is configured to collect coolant exiting the plurality of impact openings (i.e., post-impact coolant). A plurality of cooling passages are defined within the airfoil body and are in fluid communication with the collection plenum. Each cooling passage extends through one of the positive pressure side, negative pressure side, or trailing edge of the airfoil body to at least one cooling opening. A mount cooling plenum is defined at least partially within the airfoil mount and is in fluid communication with the collection plenum. Multiple cooling openings are defined on the flow path-facing surface of the airfoil mount downstream of the trailing edge and are in fluid communication with the mount cooling plenum. The airfoil component can be additively manufactured. The cooling arrangement provides more precise airfoil mount cooling and allows cooling of the platform in areas where connections such as fillet connections or brazed materials would normally block the cooling passages, such as between the trailing edge of the airfoil body and the sidewall of the platform. Thus, the airfoil component enables cooling in ways that were previously impossible using conventional manufacturing techniques, resulting in improved performance of turbomachinery components including the airfoil component and the overall turbomachinery.

[0035] Figure 1 is a schematic diagram of an exemplary turbomachinery that may include turbomachinery components, including airfoil components, as taught in this disclosure. In this example, the turbomachinery 100 is in the form of a combustion or gas turbine (GT) system. The turbomachinery 100 includes a compressor 102 and a combustor 104. The combustor 104 includes a combustion region 106 and a fuel nozzle assembly 108. The turbomachinery 100 also includes a turbine 110 (e.g., an expansion turbine) and a common compressor / turbine shaft or rotor 112.

[0036] In one embodiment, the turbomachinery 100 may be the 7HA.03 engine commercially available from GE Vernova. The disclosure is not limited to any one specific GT system and can be implemented in relation to other engines, including, for example, other HA, F, B, LM, GT, TM, and E class engine models from GE Vernova, as well as engine models from other companies. Furthermore, the disclosure is not limited to any specific turbomachinery and may be applicable to, for example, steam turbines, jet engines, compressors, turbofans, etc. The disclosure is also not limited to any specific turbomachinery component and may be applicable to any turbomachinery component that uses an airfoil, airfoil mount, and / or platform requiring cooling.

[0037] During operation, air flows through the compressor 102, and compressed air is supplied to the combustor 104. Specifically, the compressed air is supplied to a fuel nozzle assembly 108 integrated with the combustor 104. The fuel nozzle assembly 108 is in flow communication with the combustion region 106. The fuel nozzle assembly 108 is also in flow communication with a fuel source (not shown in Figure 1), supplying fuel and air to the combustion region 106. The combustor 104 ignites and burns the fuel. The combustor 104 is in flow communication with a turbine 110, where the thermal energy of the gas flow is converted into mechanical rotational energy. The turbine 110 is rotatably coupled to a rotor 112 and drives the rotor 112. The compressor 102 is also rotatably coupled to the rotor 112. In exemplary embodiments, there are multiple combustors 104 and fuel nozzle assemblies 108.

[0038] Figure 2 shows a cross-sectional view of an exemplary turbine 110 that may be used with the gas turbine system of Figure 1. The turbine 110 includes a row of nozzles or vanes 120 coupled to a fixed casing 122 of the turbomachinery 100 (Figure 1) and axially adjacent to a row 124 of rotating blades 132. Fixed vanes or nozzles 126 may be held in the turbine 110 by radially outer platforms 128 and radially inner platforms 130. The row of blades 124 in the turbine 110 includes rotating blades 132 coupled to and rotating with the rotor 112. The rotating blades 132 may include a radially inner platform 134 coupled to the rotor 112 (e.g., by a shank and / or dovetail) and optionally a radially outer tip shroud 136 (at the tip of the blade).

[0039] Platforms 128, 130, 134 may include any currently known or future-developed platform structures configured to define a portion of the high-temperature gas path adjacent to the airfoil body of the nozzle 126 or the rotating blade 132. Platforms 128, 130 are also configured to couple with the airfoil component 138 according to embodiments of the present disclosure. For example, platforms 128, 130 may include any currently known or future-developed opening 131 (Figures 3-5) configured to mate and couple with the airfoil mount 154 of the airfoil component 138 according to embodiments of the present disclosure. The connection may include, but is not limited to, any currently known or future-developed fastener structures such as mechanical fasteners and / or welds, which allow for the removal and / or replacement of the airfoil component 138 from platforms 128, 130 during maintenance of the turbine 110.

[0040] For convenience of explanation, the “turbomachinery component” will be described as the fixed nozzle 126. However, the teachings of this disclosure can also be applied to the airfoil body and platform 134 of the rotating blade 132. More specifically, embodiments of the disclosure described herein may include aspects applicable to any of the fixed nozzle 126, the turbine rotating blade 132, and / or any other turbomachinery component that uses an airfoil component including an airfoil body coupled to a platform. As described in more detail herein, the blade 132 or nozzle 126 may include an internal cooling structure including a coolant source, such as passages, conduits, and other structures that deliver coolant to its surface for film cooling in places. The coolant may include, for example, air from the compressor 102.

[0041] Figure 3 shows a perspective view of a turbomachinery component 140, for example, a fixed nozzle 126 (hereinafter "nozzle 126"), which includes at least one airfoil component 138 of a type that can employ embodiments of the present disclosure, Figure 4 shows a side view, and Figure 5 shows an enlarged perspective view (at the radially inner end). In Figures 3 to 5, the turbomachinery component 140 is shown in an exploded configuration with the airfoil component 138 separated from the platforms 128, 130 to more clearly show the various parts. Furthermore, Figure 6 shows a cross-sectional view of the airfoil component 138 along line 6-6 of Figure 4, and Figure 7 shows a cross-sectional view of the airfoil component 138 along line 7-7 of Figure 4 according to embodiments of the present disclosure.

[0042] The airfoil component 138 includes an airfoil body 142 having a positive pressure side surface 144, a negative pressure side surface 146, and a trailing edge 148. The airfoil body 142 also includes a leading edge 150 opposite the trailing edge 148. The trailing edge 148 is at the axial end of the rear portion 152 of the airfoil body 142. The airfoil component 138 also includes an airfoil mount 154 coupled to at least one end 156 of the airfoil body 142. Each airfoil mount 154 includes a flow path-facing surface 160 and a side wall 162. The flow path-facing surface 160 extends away from the respective ends 172, 176 of the airfoil body 142. In the illustrated example, the outer airfoil mount 170 is connected to the (first) outer end 172 of the airfoil body 142 such that the flow path opposing surface 160 of the airfoil body faces radially inward, and the inner airfoil mount 174 is connected to the (second) inner end 176 of the airfoil body 142 such that the flow path opposing surface 160 of the airfoil body faces radially outward.

[0043] The airfoil component 138 may also optionally include a fillet 164 between the trailing edge 148 of the airfoil body 142 and the flow path opposing surface 160 of each airfoil mount 154. It will be recognized that the fillet 164 may not be present in certain situations in which other connection mechanisms or airfoil profiles are used. As understood in the art, the airfoil component 138 is coupled to the respective platforms 128, 130 by the airfoil mount 154, for example, by mechanical coupling and / or welding / brazing. The fillet 164 can be any curved surface that connects the flow path opposing surface 160 of the airfoil mount 154 to an outer surface extending substantially radially of the airfoil body 142, for example, the trailing edge 148 or the leading edge 150, the positive pressure side outer wall 180 and / or the negative pressure side outer wall 182. The fillet 164 can be provided during the additive manufacturing of the airfoil body 142. Another fillet (separately unsigned) may be positioned between the airfoil mount 154 and the platform 128 or 130, and may be used to join the airfoil component 138 to the platform 128 or 130, for example, via welding or a mechanical connector, and may extend onto the flow path opposing surface 161 of each platform 128, 130. The fillet joining the airfoil component 138 to the platform 128 or 130 may similarly curve toward the fillet 164. As described above, in the conventional configuration, the airfoil body 142 and the platform joining fillet, or the brazing material used to join the components, may block the cooling passage between the trailing edge 148 of the airfoil body 142 and the side wall 163 of the platform 128 or 130, for example, in the area shown by the dashed box in Figure 5.

[0044] If the turbomachinery component 140 includes a nozzle 126, two airfoil mounts 170 and 174 are used, as shown in exploded view in Figures 3 and 4. Specifically, as previously described, the airfoil mount 154, coupled to at least one end 156 of the airfoil body 142, includes an outer airfoil mount 170 on a first (outer) end 172 of the airfoil body 142, and an inner airfoil mount 174 on an opposing second (inner) end 176 of the airfoil body 142. As shown in Figure 2, the platform 128 mounts the nozzle 126 to the fixed casing 122 (Figure 2) of the turbine 110. The platform 128 coupled to the airfoil mounts 170 may include any currently known or later developed mounting configurations for mounting to corresponding mounts within the casing. The inner platform 130 positions the nozzle 126 between the adjacent turbine rotating blade 132 (Figure 2) and its radially inner platform 134 (Figure 2). The outer platform 128 positions the nozzle 126 between the adjacent blade tip shroud 136 and / or other shrouds (not indicated) of the casing 122. Platforms 128, 130 define the outer and inner boundaries, respectively, of the high-temperature gas flow path (HGP) through the turbine 110.

[0045] The airfoil body 142 is understood to be an active component of the nozzle 126 that receives the flow of the working fluid 151 (Figure 2) and guides it toward the turbine rotating blades 132 (Figure 2). Furthermore, with respect to the airfoil body 142, as shown in Figures 3, 4, and 6, the positive pressure side 144 of the airfoil body 142 of the nozzle 126 includes a concave positive pressure side (PS) outer wall 180, and the negative pressure side 146 of the airfoil body 142 includes a convex negative pressure side (SS) outer wall 182 that is circumferentially or transversely opposed, extending axially between the opposing leading edge 150 and trailing edge 148, respectively. When the airfoil component 138 is coupled to the platforms 128, 130, the side outer walls 180 and 182 also extend radially from the outer airfoil mount 170 and outer platform 128 to the inner airfoil mount 174 and inner platform 130.

[0046] Referring to Figures 5 and 6, the airfoil component 138 also includes a primary cooling plenum 184 extending through the airfoil body 142 to guide coolant 185. In certain embodiments, the primary cooling plenum 184 extends mainly radially within the airfoil body 142, but some axial and / or circumferential extensions are also possible. That is, the primary cooling plenum 184 can take various forms, but generally includes a radially extending opening through which coolant can be passed from the compressor 102 (Figure 1) through the casing 122 (Figure 2) to cool a portion of the airfoil component 138, as described herein, for example. In Figure 6, the primary cooling plenum 184 is illustrated to have one section, but it can include any number of sections that are possibly sinusoidally fluid-coupled at the inner and outer ends of the airfoil body 142. Thus, the primary cooling plenum 184 can include a single passage, two passages, or three or more passages. The primary cooling plenum 184 is typically the maximum volume plenum of the airfoil body 142 and is typically the first passage through which the coolant 185 enters the airfoil body 142; therefore, it is referred to herein as the “primary”.

[0047] As shown in Figure 6, the airfoil component 138 also includes an impact cooling member 186 within the primary cooling plenum 184. The impact cooling member 186 may include any known or hereafter developed impact cooling structure, such as a sleeve or wall, which includes a plurality of impact openings 188 defined internally and configured to guide coolant 185 from the primary cooling plenum 184 to the inner surface 190 of a portion of the airfoil body 142. The inner surface 190 of a portion of the airfoil body 142 can take various forms depending on the characteristics of the impact cooling member 186, such as its length, cross-sectional or longitudinal shape, and / or the number of impact openings 188 within it. In the non-limiting example shown, the impact cooling member 186 has a substantially L-shape within the primary cooling plenum 184 and guides the coolant 185 toward the inner surface 190 of the airfoil body 142 in two directions (e.g., toward the leading edge 150 and the positive pressure side surface 144). As shown in the figure, various other cooling mechanisms 192 can also be provided within the airfoil body 142.

[0048] Figures 5 and 6 also show an airfoil component 138 including a collection plenum 194, which is defined on the airfoil body 142 and configured to collect coolant 185 (i.e., post-impact coolant) exiting a plurality of impact openings 188. The collection plenum 194 can have any form in which it can collect the coolant 185. In certain embodiments, the collection plenum 194 is an open volume between the impact cooling member 186 and the inner surface 190 of the positive pressure side surface 144 of the airfoil body 142. In the illustrated example, the collection plenum 194 is mainly along the positive pressure side surface outer wall 180, but may extend to other areas of the airfoil body 142 as described herein.

[0049] As shown in Figure 6, the airfoil component 138 also includes a plurality of cooling passages 200 defined within the airfoil body 142 and in fluid communication with the collection plenum 194. Each cooling passage 200 extends through the positive pressure side 144, negative pressure side 146 and / or trailing edge 148 of the airfoil body 142 to at least one first film cooling opening 202. In the example of Figure 6, the cooling passages 200 supply the cooling openings 202 on the positive pressure side 144, negative pressure side 146 and / or trailing edge 148. The cooling openings 202 can take different forms. For example, the cooling opening 202 may be a diffuser-shaped opening 204 for forming a cooling film (not shown) along the negative pressure side 146, i.e., the negative pressure side outer wall 182. Although unlikely, it may also be possible for a cooling opening 202 in the form of a diffuser-shaped opening 204 to form a cooling film (not shown) along the positive pressure side 144, i.e., the positive pressure side outer wall 180. In another example, the cooling opening 202 could be an outlet opening 206 at the trailing edge 148. It will be recognized that not all of the shown cooling passages 200 and cooling openings 202 are necessary for use in all situations.

[0050] In certain embodiments, as shown in Figures 5 and 6, a distribution plenum 211 may be positioned between the collection plenum 194 and a plurality of cooling passages 200, if necessary. The distribution plenum 211 may be desirable to direct (after impact) coolant 185 to any number of cooling passages 200 that cannot be easily connected to the collection plenum 194, for example, due to intervening structures. If necessary, one or more connecting passages 212 (Figures 5 and 6) may fluidly couple the collection plenum 194 and the distribution plenum 211. The distribution plenum 211 may pass through the airfoil body 142 in any way to deliver coolant 185, if necessary. In any case, the coolant 185 can pass through the cooling passages 200 to cool, for example, a portion of the rear 152 of the airfoil body 142 and exit through the cooling opening 202, regardless of location.

[0051] To address the cooling of the airfoil mount 154 and the flow path-facing surfaces 161 of the respective platforms 128, 130, the airfoil component 138 includes a mount cooling plenum 210 that is at least partially defined on each airfoil mount 154 and is in fluid communication with the collection plenum 194. The mount cooling plenum 210 may be in fluid communication with the collection plenum 194 directly or via a distribution plenum 211. As shown in Figures 5 to 7, the mount cooling plenum 210 extends toward and possibly beyond the trailing edge 148 of the airfoil body 142 within the airfoil mount 154. The majority of the mount cooling plenum 210 extends substantially axially toward the trailing edge 148 and lies within the radial range of the airfoil mount 154, i.e., radially arranged within the airfoil mount 154 between the flow path-facing surface 160 and the surface 214 of the airfoil mount 154 facing outward from the flow path, but does not necessarily extend radially into the airfoil body 142. In this way, the mount cooling plenum 210 cools the airfoil mount 154. However, in some cases, a small vertical portion of the mount cooling plenum 210 (not part of the collection plenum 194 or distribution plenum 211) may extend radially outward into the airfoil body 142 (e.g., into the fillet 164, if provided) beyond the flow path-facing surface 160 of the airfoil mount 154.

[0052] A subset of the multiple cooling passages 200 extends through the rear 152 of the airfoil body 142 to the exit opening 206 at the trailing edge 148. The mount cooling plenum 210 can extend within each airfoil mount 154, parallel to the subset of the multiple cooling passages 200 extending through the rear 152 of the airfoil body 142. This arrangement can be observed in Figures 5 to 7 by the approximately overlapping position of the cooling passages 200 extending through the rear 152 of the airfoil body 142 and the mount cooling plenum 210 located below the cooling passages 200 within the airfoil mount 154.

[0053] As shown in Figures 4 to 7, the airfoil component 138 also includes a plurality of second cooling openings 220 defined on the flow path-facing surface 160 of each airfoil mount 154 downstream of the trailing edge 148. The plurality of second cooling openings 220 are in fluid communication with the mount cooling plenum 210, for example, directly or through several respective connecting passages 222 (Figures 5 and 7). The plurality of second cooling openings 220 can have any shape, but in the particular embodiment shown, each includes a diffuser-shaped opening (i.e., widening in the flow direction as shown in Figure 5) which helps to create a film of coolant over the flow path-facing surface 160 of the airfoil mount 154, as well as over the flow path-facing surface 161 and sidewalls 163 of the platform 128 or 130. In this way, the coolant 185 can pass through the airfoil mount 154 and be directed to cool the flow path-facing surface 161 and side wall 163 of the platform 128 or 130, areas that are not normally cooled (see dashed rectangle in Figure 5). Multiple second cooling openings 220 are arranged in a row parallel to the side wall 162 of each airfoil mount 154, and the side wall 162 of each airfoil mount 154 fits into the opening 131 of the platform 128 or 130. That is, they are aligned along the mating surface where cooling is desired. For example, in a particular embodiment, as shown in Figure 7, the side wall 162 of each airfoil mount 154 downstream of the trailing edge 148 curves around the trailing edge 148 of the airfoil body 142, and the cooling openings 220 are arranged in a row curving parallel to the side wall 162 of each airfoil mount 154 downstream of the trailing edge 148. In this way, the coolant 185 can pass through the airfoil mount 154 and be guided along the curved side wall 162 of the airfoil mount 154, onto the flow path opposing surfaces 160, 161 and side wall 163.

[0054] It will be understood that the teachings of this disclosure can be applied to airfoil mounts 154 coupled to one or more ends 156 of the airfoil body 142. That is, the teachings of this disclosure can be applied to an outer airfoil mount 170 on a first (outer) end 172 of the airfoil body 142 and / or an inner airfoil mount 174 on an opposing second (inner) end 176 of the airfoil body 142, as shown in Figures 3 and 4. The teachings of this disclosure can also be applied to radially inner airfoil mounts of the platform 134 (Figure 2) of the turbine rotating blade 132 (Figure 2), in a manner similar to that described herein.

[0055] In accordance with other embodiments of the present disclosure, Figure 8 shows an enlarged perspective view of the rear of the airfoil component 138 in the form of a fixed nozzle, and Figure 9 shows a cross-sectional view of the airfoil component of Figure 8 (similar to line 6-6 in Figure 4). Figures 8 and 9 show embodiments in which the collection plenum 294 (two are shown, reference numeral 294A and 294B) is mainly along the negative pressure side wall 182 rather than along the positive pressure side wall 180 (collection plenum 194) as in Figures 5-6. Here, the airfoil component 138 includes one or more collection plenums 294A, 294B defined on the airfoil body 142 and configured to collect coolant 185 that exits through a plurality of impact openings 188 and passes through other cooling mechanisms 192 that are closer to the negative pressure side 146 than to the positive pressure side 144. The collection plenums 294A, 294B may have any form that allows them to collect the coolant 185 after it has passed through the other cooling mechanisms 192. While specific arrangements of other cooling mechanisms 192 are shown, they can take on various forms.

[0056] In the illustrated example, the cooling mechanism 192 may include an impact opening 198 through an impact cooling member 186 that fluidly couples the primary cooling plenum 184 to a collection plenum 194 on the positive pressure side 144 and / or leading edge 150; an impact opening 298 through the wall 296 of the leading edge 150 that fluidly couples the collection plenum 194 to the leading edge cooling plenum; and an impact opening 288 through an impact cooling member 286 along the negative pressure side 146 that delivers coolant to the collection plenums 294A and 294B. After passing through the impact opening 188 of the impact cooling member 186, the coolant 185 can be supplied to other cooling mechanisms 192 in any way, for example, through an opening 298 in the wall 296 facing the leading edge, as shown in Figure 9. In certain embodiments, the collection plenums 294A and 294B are open volumes between any various secondary impingement cooling members 286 of the other cooling mechanism 192 and the inner surface 290 of the negative pressure side surface 146 of the airfoil body 142. In the illustrated example, two collection plenums 294A and 294B are shown, but any number may be provided. In Figures 8 and 9, the connecting passage 312A fluid-couples the collection plenum 294A to the distributing plenum 211, and the connecting passage 312B fluid-couples the collection plenum 294B to the distributing plenum 211. However, it is emphasized that, if necessary, only one of the collection plenums 294A and 294B may be used (in which case a single connecting passage may also be used).

[0057] Embodiments of the present disclosure may also include a turbomachinery 100, as shown in Figures 1-2, comprising a compressor 102, a combustor 104 operatively coupled to the compressor 102, and a turbine 110 operatively coupled to the combustor 104. The turbine 110 comprises one or more turbomachinery components 140, including an airfoil component 138 as described herein, and a platform 128 or 130. As described above, each platform 128 or 130 is coupled to an airfoil mount 154 around its sidewall 162. As described above, coolant from a plurality of second cooling openings 220 defined in the flow-through-facing surface 160 of the airfoil mount 154 cools each platform 128 or 130, for example, its flow-through-facing surface 161 and sidewall 163.

[0058] A method according to an embodiment of the present disclosure may include the steps of additively manufacturing an airfoil component 138 as described herein, and integrating the airfoil component 138 onto at least one platform 128, 130 having an opening 131 configured to fit with an airfoil mount 154 of the airfoil component 138, i.e., to form a turbomachinery component 140 used in a turbomachinery 100. Furthermore, as described above, coolant from a plurality of second cooling openings 220 defined in the flow path-facing surface 160 of the airfoil mount 154 cools the airfoil mount and the respective platform 128 or 130, e.g., its flow path-facing surface 161 and sidewall 163. Figure 10 shows a schematic / block diagram of an exemplary computerized metal powder additive manufacturing system 310 (hereinafter, "AM system 310") for producing an airfoil component 138 (separately, and possibly platforms 128, 130), of which only a single layer is shown. The teachings of this disclosure describe constructing an airfoil component 138 using multiple molten beam sources 312, 314, 316, and 318, but it will be emphasized and readily apparent that the teachings of this disclosure are equally applicable to constructing an airfoil component 138 using any number of molten beam sources. In this example, the AM system 310 is configured for direct metal laser melting (DMLM). It will be understood that the general teachings of this disclosure are equally applicable to selective laser melting (SLM) and, in some cases, other forms of additive manufacturing (i.e., other than metal powder applications) such as other forms of additive manufacturing (i.e., other than metal powder applications). Although the layers of the airfoil component 138 on the construction platform 320 are shown as circular elements in Figure 10, it will be understood that the additive manufacturing process can be readily adapted to manufacture any shape on the construction platform 320, for example, the shape of the airfoil body 142 or the airfoil mount 154.

[0059] The AM system 310 generally includes an additive manufacturing control system 330 ("Control System") and an AM printer 332. As described later, the Control System 330 executes a set of computer executable instructions or code 334 to fabricate an airfoil component 138 using a plurality of melt beam sources 312, 314, 316, 318. In the illustrated example, the four melt beam sources may include four lasers. However, the teachings of this disclosure are applicable to any melt beam source, e.g., an electron beam, a laser, etc. The Control System 330 is shown as being implemented in a computer 336 as computer program code. In this sense, the computer 336 is shown including a memory 338 and / or storage system 340, a processor unit (PU) 344, an input / output (I / O) interface 346, and a bus 348. Furthermore, the computer 336 is shown to communicate with an external I / O device / resource 350. Generally, the processor unit (PU) 344 executes computer program code 334 stored in memory 338 and / or storage system 340. While executing the computer program code 334, the processor unit (PU) 344 can read and write data to and from memory 338, storage system 340, I / O devices 350, and / or AM printer 332. Bus 348 provides communication links between each of the components in the computer 336, and I / O devices 350 may include any devices (e.g., keyboard, pointing device, display, etc.) that enable interaction with the computer 336 for the user.

[0060] Computer 336 merely represents various possible combinations of hardware and software. For example, the processor unit (PU) 344 may consist of a single processing unit or may be distributed across one or more processing units in one or more locations on a client and a server, for example. Similarly, the memory 338 and / or storage system 340 may reside in one or more physical locations. The memory 338 and / or storage system 340 may consist of any combination of various types of non-temporary computer-readable storage media, including magnetic media, optical media, random access memory (RAM), read-only memory (ROM), etc. Computer 336 may consist of any type of computing device, such as an industrial controller, a network server, a desktop computer, a laptop, or a handheld device.

[0061] As described above, the AM system 310, in particular the control system 330, executes code 334 to generate the airfoil component 138 (and optionally the platforms 128, 130). Code 334 may include, in particular, a set of computer-executable instructions 334S (also referred herein as “code 334S”) for operating the system (i.e., the AM printer 332) and a set of computer-executable instructions 334O (also referred herein as “code 334O”) that define the object to be physically produced by the AM printer 332 (i.e., the airfoil component 138). As described herein, the additive manufacturing process is initiated from a non-temporary computer-readable storage medium (e.g., memory 338, storage system 340, etc.) storing code 334. The set of computer-executable instructions 334S for operating the AM printer 332 may include any currently known or future-developed software code capable of operating the AM printer 332.

[0062] A set of computer-executable instructions 334O defining the airfoil component 138 may include a precisely defined 3D model of the airfoil component 138 and may be generated from any of the wide variety of well-known computer-aided design (CAD) software systems, such as AutoCAD®, TurboCAD®, and DesignCAD 3D Max. In this regard, code 334O may include any currently known or future-developed file format. Furthermore, code 334O representing a component to be constructed, such as the airfoil component 138 or platforms 128, 130, and 134, may be converted between different formats. For example, code 334O may include a Standard Tessellation Language (STL) file generated for a stereolithography CAD program of a 3D system, or an Additive Manufacturing File (AMF), which is an Extensible Markup Language (XML)-based format, a standard of the American Society of Mechanical Engineers (ASME), designed to allow any CAD software to describe the shape and structure of any three-dimensional object to be manufactured on any AM printer. The code 334O representing the airfoil component 138 may be further converted into a set of data signals, transmitted, received as a set of data signals, and converted back into code and stored as needed. The code 334O may be configured according to embodiments of the present disclosure to enable the formation of boundaries and internal sections within overlapping field regions, as described. In any case, the code 334O may be an input to the AM system 310 and may come from a component designer, intellectual property (IP) provider, design company, operator or owner of the AM system 310, or other source. In any case, the control system 330 executes the codes 334S and 334O and divides the airfoil component 138 (and optionally platforms 128, 130) into a series of thin slices, which are assembled in continuous layers of material using the AM printer 332.

[0063] The AM printer 332 may include a sealed processing chamber 360 to provide a controlled atmosphere for printing the airfoil parts 138. A construction platform 320 on which the airfoil parts 138 are constructed is positioned within the processing chamber 360. Several melt beam sources 312, 314, 316, 318 are configured to melt a layer of metal powder on the construction platform 320 to produce the airfoil parts 138 (and optionally platforms 128, 130 separately). Although four melt beam sources 312, 314, 316, 318 are shown, it is emphasized that the teachings of this disclosure are applicable to systems using, for example, one, two, three, five or any number of sources. As understood in the art, each melt beam source 312, 314, 316, 318 may have a field containing a non-overlapping field region that can melt only metal powder, and two or more sources may contain at least one overlapping field region that can melt metal powder. In this regard, each melting beam source 312, 314, 316, and 318 can generate a melting beam that melts particles for each slice, as defined by code 334O. For example, in Figure 10, melting beam source 312 is shown generating a layer of airfoil component 138 using melting beam 362 in one region, and melting beam source 314 is shown generating a layer of airfoil component 138 using melting beam 362' in another region. Each melting beam source 312, 314, 316, and 318 is calibrated in any currently known or future-developed manner. That is, each melting beam source 312, 314, 316, and 318 correlates the expected position of its laser or electron beam relative to the construction platform 320 with its actual position in order to provide individual position corrections (not shown) to ensure its individual accuracy. In one embodiment, each of the multiple molten beam sources 312, 314, 316, and 318 can generate molten beams, e.g., 362, 362', having the same cross-sectional dimensions (e.g., shape and size in operation), output, and scanning speed.

[0064] Continuing to refer to Figure 10, the applicator (or recoater blade) 370 generates a thin layer of raw material 372, which is spread out as a blank canvas from which a series of slices of the final airfoil parts 138 will be generated. Various parts of the AM printer 332 can be moved to accommodate the addition of each new layer; for example, after each layer, the construction platform 320 can be lowered, as well as the chamber 360 and / or applicator 370 can be raised. This process can use different raw materials in the form of fine-grained metal powder, the stock of which can be held in a chamber 368 accessible by the applicator 370.

[0065] The processing chamber 360 is filled with an inert gas such as argon or nitrogen and controlled to reduce or eliminate oxygen. The control system 330 is configured to control the flow of the gas mixture 374 into the processing chamber 360 from the inert gas source 376. In this case, the control system 330 can control the pump 380 and / or the flow valve system 382 for the inert gas to control the content of the gas mixture 374. The flow valve system 382 may include one or more computer-controllable valves, flow sensors, temperature sensors, pressure sensors, etc., capable of precisely controlling the flow of a specific gas. The pump 380 may or may not include the valve system 382. If the pump 380 is omitted, the inert gas can simply enter a conduit or manifold before being introduced into the processing chamber 360. The inert gas source 376 can take the form of any conventional source for the material contained inside, e.g., a tank, reservoir, or other source. Any sensors (not shown) necessary to measure the gas mixture 374 may be provided. The gas mixture 374 may be filtered using a filter 386 in a conventional manner.

[0066] During operation, a construction platform 320 having metal powder on it is provided within a processing chamber 360, and a control system 330 controls the flow of a gas mixture 374 from an inert gas source 376 into the processing chamber 360. The control system 330 also controls an AM printer 332, in particular an applicator 370 and melt beam sources 312, 314, 316, 318 to continuously melt the layer of metal powder on the construction platform 320 to produce a desired part according to embodiments of the present disclosure. While a specific AM system 310 is described herein, it is emphasized that the teachings of the present disclosure are not limited to any specific additive manufacturing system or method.

[0067] Once the airfoil component 138 is formed and the turbomachinery component 140 is formed by joining the platforms 128, 130 and / or 134, the component 140 can be installed together with the other components of the turbine 110 to form the turbine 110, as shown in Figure 2. Installation may include any currently known or future-developed techniques for installing the particular turbomachinery component 140 used. As described above, the airfoil component 138 and / or (separately) the platforms 128, 130, 134 can be additively manufactured using any currently known or future-developed techniques. As a result, any portion of the airfoil component 138 includes multiple parallel sintered metal layers 400 over its entire height, as shown in the cross-section in Figure 11.

[0068] This disclosure offers various technical and commercial advantages, examples of which are described herein. The cooling arrangement provides more precise cooling of the airfoil mount and platform surface and sidewalls in a manner previously impossible using conventional manufacturing techniques, resulting in improved overall performance of the component and turbomachinery. The implementation of diffuser-shaped cooling holes originating just downstream of the trailing edge fillet of the airfoil body can provide cooling of the airfoil mount, as well as sidewall film cooling of both the surface and sidewalls of the respective platform. The airfoil components can be advantageously additively manufactured.

[0069] Throughout this specification and the claims, the approximation language used herein may be applied to modify any quantitative expression that is permitted to vary without altering the fundamental function of the subject. Thus, values ​​modified with terms such as “approximately,” “about,” and “substantially” are not limited to the exact values ​​specified. In at least some examples, the approximation language may correspond to the precision of the instrument used to measure the value. Herein, and throughout this specification and the claims, limitations on ranges are interchangeable and / or substitutable, and unless the context or wording specifically indicates otherwise, such ranges are identified and include all subranges encompassed therein. “Approximately” or “about” applied to specific values ​​within a range may indicate + / - 10% of the stated value, unless applied to the values ​​at both ends and particularly dependent on the precision of the instrument used to measure the value.

[0070] All corresponding structures, materials, actions, and equivalents of all means-plus-function elements or step-plus-function elements in the following claims are intended to include any structures, materials, or actions for performing a function in combination with other specifically claimed elements. The descriptions in this disclosure are presented for illustrative and explanatory purposes and are not intended to be exhaustive or to limit the disclosure to the forms disclosed herein. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of this disclosure. The embodiments have been selected and described to best illustrate the principles and practical applications of this disclosure and to enable those other skilled in the art to understand this disclosure in terms of various embodiments with various modifications suitable for the particular intended use. [Explanation of symbols]

[0071] 100 Turbo Machinery 102 Compressor 104 Combustor 106 Combustion Region 108 Fuel Nozzle Assembly 110 Turbine 112 Rotor 120 columns 122 Fixed casing 124 columns 126 nozzles 128 platforms 130 platforms 131 Opening 132 Rotating Blades 134 platforms 136 Shroud 138 Airfoil components 140 Turbo Machine Parts 142 Airfoil section 144 Positive pressure side 146 Negative pressure side 148 Trailing edge 150 leading edge 151 Working fluid 152 Rear 154 Wing section mount 156 End 160 Flow path opposing surface 161 Flow path opposing surface 162 Side wall 163 Side wall 164 fillets 170 Outer airfoil mount 172 End 174 Inner airfoil mount 176 End 180 Positive pressure side exterior wall 182 Negative pressure side exterior wall 184 Primary Cooling Plenum 185 Coolant 186 Impact Cooling Component 188 Collision opening 190 Inner self 192 Cooling mechanism 194 Collection Plenum 198 Collision opening 200 Cooling passage 202 Opening 204 Opening 206 Opening 210 Mount Cooling Plenum 211 Distribution Plenum 212 Connecting passage 214 Surface 220 Second cooling opening 222 Connecting passage 286 Impact Cooling Component 288 Collision opening 290 Inner self 294 Collecting Plenum 296 Wall 298 Collision opening 310 Additive Manufacturing Systems, AM Systems 312A Connecting Passage 312B Connecting passage 312 Melting beam source 314 Melting beam source 316 Melting beam source 318 Melting beam source 320 Construction Platforms 330 Control System 332 Printers 334 Code 336 Computer 338 memory 340 Memory Systems 344 processor units 346 Interfaces 348 Bus 350 I / O devices 360 Processing Chamber 362 Melting beam 368 Chambers 370 Applicators 372 Ingredients 374 Gas mixtures 376 Inert gas source 380 pumps 382 Valve System 386 filters 400 Sintered metal layer

Claims

1. Airfoil component (138), The airfoil body (142) has a positive pressure side (144), a negative pressure side (146), and a trailing edge (148), Airfoil mounts (154, 170, 174) are connected to at least one end (156, 172, 176) of the airfoil body (142), wherein each airfoil mount (154, 170, 174) includes a flow path facing surface (160) and a side wall (162), A primary cooling plenum (184) extends through the airfoil body (142) to guide the coolant (185), The impact cooling member (186) within the primary cooling plenum (184) includes a plurality of internally defined impact openings (188) configured to guide the coolant (185) from the primary cooling plenum (184) to the inner surface (190) of a portion of the airfoil body (142), A collection plenum (194) defined on the airfoil body (142) is configured to collect the coolant (185) exiting the plurality of collision openings (188), A plurality of cooling passages (200) defined within the airfoil body (142) and in fluid communication with the collection plenum (194), wherein each of the plurality of cooling passages (200) extends through one of the positive pressure side (144), the negative pressure side (146), or the trailing edge (148) of the airfoil body (142) to at least one first film cooling opening (202), A mount cooling plenum (210) is defined at least partially within each airfoil mount (154, 170, 174) and is in fluid communication with the collection plenum (194), A plurality of second cooling openings (220) defined on the flow path opposing surface (160) of each airfoil mount (154, 170, 174) downstream of the trailing edge (148), wherein the plurality of second cooling openings (220) are in fluid communication with the mount cooling plenum (210) and A wing-shaped component (138) is provided.

2. The airfoil component (138) according to claim 1, wherein the plurality of second cooling openings (220) are arranged in a row parallel to the respective side walls (162) of each airfoil mount (154, 170, 174).

3. The airfoil component (138) according to claim 1, wherein the side walls (162) of each airfoil mount (154, 170, 174) downstream of the trailing edge (148) are curved around the trailing edge (148) of the airfoil body (142), and the plurality of second cooling openings (220) are arranged in a row that curves parallel to the side walls (162) of each airfoil mount (154, 170, 174) downstream of the trailing edge (148).

4. The airfoil component (138) according to claim 1, wherein each of the plurality of second cooling openings (220) includes a diffuser-shaped opening.

5. The airfoil component (138) according to claim 1, wherein a subset of the plurality of cooling passages (200) extends through the rear portion (152) of the airfoil body (142) to the at least one first film cooling opening (202, 206) of the trailing edge (148), and the mount cooling plenum (210) extends within the airfoil mount (154, 170, 174) parallel to the subset of the plurality of cooling passages (200) extending through the rear portion (152) of the airfoil body (142).

6. The airfoil component (138) according to claim 1, wherein the airfoil component (138) includes a plurality of parallel sintered metal layers (400) over its entire height.

7. The airfoil component (138) according to claim 1, wherein the airfoil mounts (154, 170, 174) coupled to at least one end (156, 172, 176) of the airfoil body (142) include an outer airfoil mount (170) on the first end (172) of the airfoil body (142) and an inner airfoil mount (174) on the opposing second end (176) of the airfoil body (142).

8. A turbomachinery component (140) comprising an airfoil component (138) according to any one of claims 1 to 7, further comprising platforms (128, 130) coupled to each airfoil mount (154, 170, 174) around its side wall (162), wherein coolant (185) from a plurality of second cooling openings (220) defined on the flow path opposite surface (160) cools each platform (128, 130).

9. A turbomachinery (100), Compressor (102), A combustor (104) is operatively coupled to the compressor (102), A turbine (110) operatively coupled to the combustor (104), the turbine (110) including the airfoil component described in any one of claims 1 to 7 A turbomachinery (100) equipped with the following:

10. The turbomachinery (100) according to claim 9, further comprising platforms (128, 130) coupled around the side walls (162) of each airfoil mount (154, 170, 174), wherein coolant (185) from a plurality of second cooling openings (220) defined on the flow path opposite surface (160) cools each platform (128, 130).

11. It is a method, A step of manufacturing an airfoil component (138), wherein the airfoil component (138) is defined in any one of claims 1 to 7, A step of connecting the airfoil component (138) to at least one platform (128, 130) having an opening (131) configured to fit with the airfoil mount (154), wherein the coolant (185) from the plurality of second cooling openings (220) defined on the flow path-facing surface (160) of the airfoil mount (154) cools each of the platforms (128, 130); Methods that include...

12. The method according to claim 11, wherein the plurality of second cooling openings (220) are arranged in a row parallel to the side walls (162) of each airfoil mount (154).

13. The method according to claim 11, wherein the side wall (162) of the airfoil mount (154) is located downstream of the trailing edge (148) of the airfoil body (142) and curves around the trailing edge (148) of the airfoil body (142), and the plurality of second cooling openings (220) are arranged in a row that curves parallel to the side wall (162) of each airfoil mount (154) downstream of the trailing edge (148).

14. The method according to claim 11, wherein a subset of the plurality of cooling passages (200) extends through the rear portion (152) of the airfoil body (142) to the at least one first film cooling opening (202, 206) of the trailing edge (148), and the mount cooling plenum (210) extends within the airfoil mount (154) parallel to the subset of the plurality of cooling passages (200) that extends through the rear portion (152) of the airfoil body (142).

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