Turbine blade under-platform structure and pocket

Abstract

To provide a turbine blade under-platform structure and a pocket.SOLUTION: A turbine blade includes a root with a shank having a buttress extending from the shank bottom to an end of a turbine blade platform. The buttress provides increased structural integrity for a given shank mass, allowing mass reduction. With a shank wall and the platform bottom, the buttress defines a pocket below the platform that can be part of a cooling circuit of the blade. The pocket can be on a suction side or pressure side of the root and can include portions or pockets on both sides of the root that can be in fluid communication with one another.SELECTED DRAWING: Figure 6

Description

[Technical field]

[0001] The present disclosure relates generally to gas turbine systems, and more particularly to blades that include under-platform features that simultaneously reduce mass and improve performance. [Background technology]

[0002] Turbomachinery rotating blades, especially those in the hot gas path of the turbine, are multi-axial and operate under high loads at extremely high temperatures. As such, such blades must be manufactured from materials with high melting points that can withstand the loads they are subjected to. As such materials are expensive, blade designs are sought that perform the required function with as little material as possible. Summary of the Invention

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

[0004] The present disclosure provides a turbine blade that includes a root having a shank with a buttress that extends from the bottom of the shank to an end of the turbine blade platform. The buttress allows for increased structural integrity and reduced mass for a given shank mass. The buttress, along with the shank wall and the bottom of the platform, defines a pocket below the platform that may be part of a cooling circuit for the blade. The pocket may be on the suction side or pressure side of the root, and may include portions or pockets on both sides of the root that may be in fluid communication with one another.

[0005] More specifically, one aspect of the disclosure provides a turbine blade including an airfoil including a tip, a body, and a base, a platform connected to the base of the airfoil, a shank extending from the platform to a dovetail, the shank including forward and aft walls below and connected to corresponding forward and aft ends of the platform, and a first buttress disposed between the forward and aft walls on one of a suction side of the shank and a pressure side of the shank, the first buttress extending from a lower portion of the shank to a corresponding end of the platform, a first portion of the first buttress oriented at an angle of at least 30° relative to a first inner wall of the shank defining at least a first pocket between the first buttress and the first inner wall.

[0006] Another aspect of the present disclosure includes the above aspect, wherein the first pocket is further defined by a bottom of the platform.

[0007] Another aspect of the present disclosure includes any of the above aspects, wherein the first pocket is further defined by at least one of the front wall and the rear wall.

[0008] Another aspect of the present disclosure includes any of the above aspects, wherein the second portion of the first buttress is oriented at an angle of at least 30 degrees relative to at least one of the anterior wall and the posterior wall.

[0009] Another aspect of the present disclosure includes any of the aspects above, wherein the distance between the first interior wall and the first buttress varies between the anterior and posterior walls.

[0010] Another aspect of the present disclosure includes any of the aspects above, wherein the distance between the first interior wall and the first buttress varies with distance from the platform.

[0011] Another aspect of the present disclosure includes any of the aspects above, further including a second buttress disposed between the forward wall and the aft wall on the other of the suction side of the shank and the pressure side of the shank, the second buttress extending from a lower portion of the shank to a corresponding end of the platform, a first portion of the second buttress oriented at an angle of at least 30° relative to a second inner wall of the shank, defining a second pocket at least between the second buttress and the second inner wall.

[0012] Another aspect of the present disclosure includes any of the above aspects, wherein the first pocket is in fluid communication with the second pocket.

[0013] Another aspect of the present disclosure includes any of the above aspects, wherein at least one of the first pocket and the second pocket is in fluid communication with a cooling circuit of the turbine blade.

[0014] One aspect of the disclosure provides a gas turbine system including a turbine section including a hot gas path, and a plurality of turbine blades extending radially from a rotor of the turbine into the hot gas path and spaced circumferentially in the turbine section, each turbine blade including a root including a shank and a dovetail, the dovetail being attached to the rotor, a platform connected to the shank, and an airfoil supported by and extending radially away from the platform, the shank having a forward wall and an aft wall, the platform being connected to the forward wall and the aft wall of the platform. a forward wall and an aft wall underlying and connected to corresponding forward and aft ends of a foam, and a first buttress disposed between the forward wall and the aft wall on one of the suction side of the shank and the pressure side of the shank, the first buttress extending from a lower portion of the shank to a corresponding end of the platform, a first portion of the first buttress being oriented at an angle of at least 30° relative to a first inner wall of the shank and defining at least a first pocket between the first buttress and the first inner wall.

[0015] Another aspect of the present disclosure includes any of the above aspects, wherein the first pocket is further defined by a bottom of the platform.

[0016] Another aspect of the present disclosure includes any of the above aspects, wherein the first pocket is further defined by at least one of the front wall and the rear wall.

[0017] Another aspect of the present disclosure includes any of the above aspects, wherein the second portion of the first buttress is oriented at an angle of at least 30 degrees relative to at least one of the anterior wall and the posterior wall.

[0018] Another aspect of the present disclosure includes any of the above aspects, wherein the distance between the first interior wall and the first buttress varies between the platform and the dovetail.

[0019] Another aspect of the present disclosure includes any of the aspects above, wherein the distance between the first interior wall of the shank and the first buttress varies with distance from the platform.

[0020] Another aspect of the present disclosure includes any of the aspects above, wherein the shank further includes a second buttress disposed between the forward wall and the aft wall on the other of the suction side of the shank and the pressure side of the shank, the second buttress extending from a lower portion of the shank to a corresponding end of the platform, a first portion of the second buttress oriented at an angle of at least 30° relative to a second inner wall of the shank, defining a second pocket at least between the second buttress and the second inner wall.

[0021] Another aspect of the present disclosure includes any of the above aspects, wherein at least one of the first pocket and the second pocket is in fluid communication with a cooling circuit of the turbine blade.

[0022] One aspect of the disclosure provides a turbine blade, the turbine blade including an airfoil including a tip, a body, and a base, a platform connected to the base of the airfoil, a root including a shank and a dovetail, the shank extending from the platform to the dovetail, the shank further including forward and aft walls below and connected to respective ends of the platform, and first and second inner walls on respective suction and pressure sides of the shank, the cross-sectional profile of the shank in a plane parallel to the platform being defined by the first inner wall and the second inner wall. the shank further includes a first buttress and a second buttress on the suction side and pressure side of the shank, respectively, each of the first buttress and the second buttress extending from a lower portion of the shank away from the respective first and second inner walls to a corresponding end of the platform, and at least the first buttress and the second buttress cooperating with the respective first and second inner walls and a bottom of the platform to define respective first and second pockets below the platform.

[0023] Another aspect of the present disclosure includes any of the aspects above, wherein a first portion of each buttress of the first and second buttresses is oriented at an angle of at least 30 degrees relative to the first and second inner walls, respectively.

[0024] Another aspect of the present disclosure includes any of the above aspects, wherein at least one of the first pocket and the second pocket is in fluid communication with a cooling circuit of the turbine blade.

[0025] Two or more aspects described in this disclosure (including those described in this Summary) may be combined to form an embodiment not specifically described herein.

[0026] The details of one or more embodiments are set forth in the accompanying drawings and the detailed description below. Other features, objects, and advantages will be apparent from the detailed description and drawings, and from the claims. [Brief description of the drawings]

[0027] These and other features of the present disclosure will be more readily understood from the following detailed description of the various aspects of the disclosure in conjunction with the drawings illustrating various embodiments of the disclosure. [Figure 1] 1 illustrates a schematic diagram of an exemplary turbomachine in the form of a gas turbine system; [Diagram 2] 2 illustrates a cross-sectional view of an exemplary turbine assembly that may be used with the gas turbine system of FIG. 1. [Diagram 3] 1 illustrates a perspective view of a turbine rotating blade of a type in which embodiments of the present disclosure may be employed; [Figure 4] 1 illustrates a partial side cross-sectional view of an exemplary blade showing a pocket formed on the suction side of the blade in accordance with an embodiment of the present disclosure. [Diagram 5] 1 shows an illustrative partial cross-sectional side view showing a pocket formed on the pressure side of a blade according to an embodiment of the present disclosure. [Figure 6] 4 and 5 according to an embodiment of the present disclosure. [Figure 7] 5A and 5B show cross-sectional views taken along line BB in FIGS. 4 and 5 according to an embodiment of the present disclosure. [Figure 8] 4 and 5 according to an embodiment of the present disclosure. [Figure 9] 6 shows a cross-sectional view taken along line DD in FIGS. 4 and 5 according to an embodiment of the present disclosure. [Figure 10] 8 illustrates a partial cross-sectional perspective view of an exemplary blade showing a pocket similar to FIG. 7 and including elements of a cooling circuit according to an embodiment of the present disclosure. [Figure 11]11 illustrates a partially enlarged perspective cross-sectional view of an exemplary blade similar to FIG. 10, including elements of a cooling circuit, according to another embodiment of the present disclosure. [Figure 12] 11 illustrates a partially enlarged perspective cross-sectional view of an exemplary blade similar to FIG. 10, including elements of a cooling circuit, according to yet another embodiment of the present disclosure.

[0028] 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 disclosure and therefore should not be considered as limiting the scope of the disclosure. In the drawings, like numbers represent like elements throughout. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0029] First, in order to clearly describe the subject matter of the present disclosure, it becomes necessary to select certain terms when referring to and describing the relevant machine components in the exemplary application of a turbine blade with structural and thermal management features below the platform. In making this description, common industry terms are used and adopted, whenever possible, in a manner consistent with their accepted meaning in the industry. Unless otherwise stated, the above terms should be given a broad interpretation consistent with the context of the present application and the scope of the claims. Those skilled in the art can understand that in many cases, a particular component may be referred to using several different or overlapping terms. What is described herein as a single part may in another context include and be referred to as comprising multiple components. Alternatively, what is described herein as comprising multiple components may be referred to elsewhere as a single part.

[0030] Additionally, certain descriptive terms may be used regularly herein and it is useful to define these terms at the beginning of the detailed description. These terms and their definitions are as follows, unless otherwise noted: As used herein, the terms "downstream" and "upstream" are terms that indicate a direction relative to the flow of a fluid (such as a working fluid through a turbomachine or, for example, air through a combustor or a coolant through one of the component systems of a turbomachine). The term "downstream" corresponds to the direction in which the fluid flows and the term "upstream" refers to the opposite direction to that flow. The terms "forward" and "aft" refer to directions unless otherwise noted, with "forward" referring to the front or compressor end of the turbomachine and "aftward" referring to the aft or turbine end of the turbomachine.

[0031] It is often necessary to account for parts located at different radial positions relative to a central axis. The term "axial" refers to movement or position parallel to an axis (e.g., the axis of a turbomachine) (the axis indicated by the arrow in the "X" direction in FIG. 3). The term "radial" refers to movement or position perpendicular to an axis (e.g., the axis of a turbomachine) (the axis indicated by the arrow in the "Z" direction in FIG. 3). If a first component is closer to the axis than a second component, the first component is described herein as being "radially inward" or "inside" the second component. On the other hand, if a first component is farther from the axis than the second component, the first component may be described herein as being "radially outward" or "outside" the second component. The term "axial" refers to movement or position parallel to an axis. Finally, the term "circumferential" refers to movement or position around an axis, for example, the circumferential inner surface of a casing that extends relative to the axis of a turbomachine (the axis indicated by the arrow in the "Y" direction in FIG. 3). As noted above, it will be understood that such terms may be applied with respect to the axis of the turbine machine and, on a component scale, with respect to the central axes of the individual components (e.g., rotating blades) of the turbine machine.

[0032] Furthermore, certain descriptive terms may be used regularly in this specification, as explained below: The terms "first," "second," and "third" may be used interchangeably to distinguish one component from another, and are not intended to imply the location or importance of the respective components.

[0033] The terms used in the specification are for the purpose of describing particular embodiments only and are not intended to be limiting of the disclosure. As used herein, the singular forms "a", "an" and "the" are intended to include the plural unless the context clearly indicates otherwise. It is further understood that the terms "comprises" and / or "comprising", as used herein, state the presence of a referenced feature, integer, step, operation, element, and / or component, but do not preclude the presence and addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. "Optional" or "optionally" means that the subsequently described event or circumstance may or may not occur, or that the subsequently described component or element may or may not be present, and that the description includes instances in which the event occurs or the component is present as well as instances in which the event does not occur or the component is absent.

[0034] When an element or layer is referred to as being "on," "engaged with," "connected to," "coupled to," or "attached to" another element or layer, the element or layer may be in direct contact with, directly engaged, connected, coupled, or attached to the other element or layer, or there may be intervening elements or layers present. In contrast, when an element is referred to as being "directly on," "directly engaged with," "directly connected to," or "directly coupled to" another element or layer, there are no intervening elements or layers present. Other words used to describe relationships between elements should be interpreted in a similar manner (e.g., "between" and "directly between," "adjacent" and "directly adjacent," etc.). As used herein, the term "and / or" includes any combination of one or more items of the associated multiple listed items. As used herein, the verb forms of "couple" and "attach" can be used interchangeably.

[0035] FIG. 1 is a schematic diagram of an exemplary turbomachine. In this example, the turbomachine 100 is in the form of a combustion section or gas turbine system. The turbomachine 100 includes a compressor 102 and a combustor 104. The combustor 104 includes a combustion section 106 and a fuel nozzle assembly 108. The turbomachine 100 also includes a turbine assembly 110 (e.g., an expansion turbine) and a compressor / turbine common shaft 112 (sometimes referred to as a rotor 112). In one embodiment, the turbomachine 100 is a 7HA.03 engine available from General Electric Company, Greenville, South Carolina. The present disclosure is not limited to a particular GT system and may be applied to other engines (including, for example, other HA, F, B, LM, GT, TM and E class engine models from General Electric, as well as engine models from other companies). The present disclosure is not limited to a particular turbine or turbomachine and may be applied to, for example, steam turbines, jet engines, compressors, turbofans, etc. Additionally, the present disclosure is not limited to any particular turbomachine, but may be applied to any form of component exposed to a hot gas path and requiring cooling and stress relief.

[0036] In operation, air flows through the compressor 102 and the compressed air is delivered to the combustor 104. Specifically, the compressed air is delivered to a fuel nozzle assembly 108 integrated into the combustor 104. The assembly 108 is in fluid communication with the combustion zone 106. The fuel nozzle assembly 108 is also in fluid communication with a fuel source (not shown) and delivers fuel and air to the combustion zone 106. The combustor 104 ignites and combusts the fuel to generate a hot gas stream. The combustor 104 is in fluid communication with a turbine assembly 110 in which thermal energy of the gas stream is converted to mechanical rotational energy. The turbine assembly 110 includes a turbine 111 that is rotatably coupled to and drives a rotor 112. The compressor 102 is also rotatably coupled to the rotor 112. In the illustrated embodiment, there are multiple combustors 104 and multiple fuel nozzle assemblies 108.

[0037] FIG 2 illustrates a cross-sectional view of an exemplary turbine assembly 110 of the turbomachine 100 (FIG 1) that may be used with the gas turbine system of FIG 1. As illustrated, the turbine 111 of the turbine assembly 110 includes three turbine stages, each including a row 120 of nozzles 126 coupled to a stationary casing 122 of the turbomachine 100 (FIG 1) and a row 124 of axially adjacent rotating blades 132. The nozzles 126 (also referred to as vanes) may be retained in the turbine assembly 110 by a radially outer platform 128 and a radially inner platform 130. Each stage 124 of blades of the turbine assembly 110 includes a rotating blade 132 that is coupled to and rotates with the rotor 112. 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 adjacent stages of the nozzles 126 and the rotating blades 132. In some turbine assemblies 110, four turbine stages may be used.

[0038] A working fluid 140 (such as combustion gases in the example gas turbine) flows through the turbine 111 in what is referred to as the hot gas path (hereinafter simply "HGP"). The HGP may be the area of ​​the turbine 111 that is exposed to high temperatures. Parts of the turbine 111 or other machine that are exposed to the HGP are referred to as "HGP components." In the turbine 111, the nozzle 126, the blades 132, and the shroud 138 are exemplary HGP components. In the exemplary turbine 111, the blades 132 may benefit from the teachings of the present disclosure.

[0039] FIG. 3 illustrates a perspective view of a turbine rotating blade 132 of a type in which an embodiment of the present disclosure may be employed. The turbine rotating blade 132 includes a root 142 by which the rotating blade 132 is attached to the rotor 112 (FIG. 2). The root 142 may include a dovetail 144 configured to be attached to a corresponding dovetail slot disposed about the periphery of a rotor wheel 146 (FIG. 2) of the rotor 112 (FIG. 2). The root 142 may further include a shank 148 between the dovetail 144 and the platform 134. The platform 134 is disposed at the junction of an airfoil 152 and the root 142 and defines a portion of the inner boundary of the HGP of the turbine assembly 110 (FIG. 2). It is understood that the airfoil 152 is the active component of the rotating blade 132 that blocks the flow of the working fluid and causes the rotor wheel 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 opposed convex suction side (SS) outer wall 156 that extend axially between opposed leading and trailing edges 158, 160. The sidewalls 154 and 156 also extend radially from the platform 134 to a radially outer tip 136. The tip 136 may include any now known or future developed tip (e.g., a tip with or without a tip shroud).

[0040] The cooling circuits may be used, for example, in the airfoil 152, platform 134, or other portions of the rotating blade 132. For example, cooling passages (not numbered) may be formed in the platform 134 with openings in the slash face 135. The seal rails 280 extend from a forward wall 284 and an aft wall 286 of the shank 148, which extend from and are connected to corresponding ends of the platform 134. The forward wall 284 of the shank is radially inward relative to the forward end of the platform 134 and the leading edge 158 of the airfoil 152. The aft wall 286 is radially inward relative to the aft end of the platform 134 and the trailing edge 160 of the airfoil 152.

[0041] To provide a rotating blade for a turbomachine that provides the necessary strength with less added mass than using conventional techniques, an embodiment includes a wall formed from the bottom of the side of the blade's shank to the end of the blade's platform. This wall is referred to herein as a "buttress" because it resembles an architectural buttress when viewed in cross section. The buttress may be formed on one or both of the suction side and pressure side of the shank, with the new buttress, the existing shank inner wall, and the platform defining a pocket on each side. The rear and front walls of the shank may also define pockets. The resulting pockets may be advantageously used for cooling circuits, etc., while the buttress may provide improved structural and thermal performance with less added material and associated mass.

[0042] Figure 4 shows a partial cross-sectional side view of the suction side of blade 300 (such as a turbine blade), and Figure 5 shows a partial cross-sectional side view of the pressure side of blade 300. Thus, Figures 4 and 5 show opposite sides of blade 300. View lines AA, BB, CC, and DD shown in Figures 4 and 5 are used to indicate cuts of blade 300 shown in Figures 6-9, respectively.

[0043] 4-9, the blade 300 may include a root portion 302, a platform 304, and an airfoil 306. The root portion 300 may include a dovetail 308 and a shank 310 extending between the dovetail 308 and the platform 304. The platform 304 may be connected to a base 312 of the airfoil 306 and may support the airfoil 306. A body portion 314 of the airfoil 306 extends toward a tip 316 of the airfoil 306. As seen at the bottom of FIGS. 6-8 and in FIG. 9, one or more pockets 320, 330 may be defined in part by walls of the root portion 302 and the platform 304, as described below. As described above with reference to the blade 132, the body portion 314 of the airfoil 306 has a concave pressure side 354 and a convex suction side 356. Additionally, blade 300 has an aft end and a forward end or side, as shown in Figures 4 and 5. For convenience, elements are considered to be in contact with or have a pressure side or end, a suction side or end, an aft end or side, and a forward end or side.

[0044] 6-9. The pockets 320, 330 may be defined by at least the buttresses 322, 332 of the shank 310 and the inner walls 324, 334 of the shank 310. The buttresses 322, 332 in embodiments may extend from the bottom of the shank 310 to the corresponding ends 326, 336 of the platform 304, further enhancing the overall structural integrity of the shank 310 and root 302. The presence of the buttresses 322, 332 may allow the use of a shank 310 with reduced mass while still meeting design criteria. Additionally, the pockets 320, 330 may be further defined by the bottom of the platform 304 and the forward and / or aft walls 340, 342 of the shank 310. In embodiments, the pockets 320, 330 may be part of and / or in fluid communication with the blade's cooling circuit, as described.

[0045] As seen particularly in FIGS. 6-8 , the first pocket 320 may be located on the suction side of the root portion 302 and may be defined by at least a suction side or first buttress 322 of the shank 310 and a suction side or first inner wall 324 of the shank 310. For example, the suction side or first buttress 322 may extend from a lower portion of the shank 310, leaving the suction side or first inner wall 324, to a corresponding end 326 on the suction side of the platform 304. The suction side or first buttress 322 may include a first portion that couples to the shank 310 adjacent the dovetail 308. At least a first portion of the first buttress 322 may form an angle α of at least 30° with the first inner wall 324. Further, as can be particularly seen in FIG. 9 , at least a second portion of the first buttress 322 (the portion near the platform 304) can form an angle γ, γ′ of at least 30° relative to one or both of the anterior wall 340 and the posterior wall 342 of the shank 310.

[0046] Alternatively, or in addition to the first pocket 320, a second pocket 330 may be formed on the pressure side of the root 302 and may be defined by at least a pressure side or second buttress 332 and a pressure side or second inner wall 334 of the shank 310. For example, the pressure side or second buttress 332 may extend from a lower portion of the shank 310, leaving the pressure side or second inner wall 334, to a corresponding end 336 on the pressure side of the platform 304. The pressure side of the second buttress 332 may include a first portion that couples to the shank 310 adjacent the dovetail 308. At least a first portion of the second buttress 332 may form an angle β of at least 30° with the second inner wall 334. Further, as can be particularly seen in FIG. 9 , at least a second portion of the second buttress 332 (the portion near the platform 304) can form an angle δ, δ′ of at least 30° relative to one or both of the forward wall 340 and the rearward wall 342 of the shank 310.

[0047] While the illustrated example includes two pockets, referred to as a "first" pocket and a "second" pocket, it should be understood that an embodiment may use only one pocket, if suitable and / or necessary. In an embodiment, the first pocket 320 may be in fluid communication with the second pocket 330. Additionally, while a pocket may be one of the first and second pockets 320, 330, in some embodiments, the first pocket 320 may be a first pocket portion on a suction side of the root and the second pocket 330 may be a second pocket portion on a pressure side of the root, and the first pocket portion may be in fluid communication with the second pocket portion, such that what is shown as the first pocket 320 and the second pocket 330 may effectively form a single pocket under the platform 304 of the root 302 of the blade 300.

[0048] As can also be seen in Figures 4-9, the shank 310 varies in size, location, and shape in a variety of ways. For example, as shown in Figure 9, a cross-sectional profile of the shank 310 in a plane parallel to the platform 304 can show a solid portion defined by a first inner wall 324 and a second inner wall 334, with first and second pockets 320, 330 present between the first and second inner walls 324, 334 and the first and second buttresses 322, 332. As can be seen particularly in Figure 9, but also suggested by Figures 6-8, the solid portion of the interior of the shank 310 varies with the area of ​​the shank 310 (i.e., between the platform 304 and the dovetail 308). Additionally, the cross-sectional profile of the shank 310 varies with distance from the platform 304, tending to become narrower the further away from the platform 304.

[0049] FIG. 10 shows a partial cross-sectional perspective view of blade 300 illustrating an exemplary blade open area similar to FIG. 7 and including elements of one or more cooling circuits. In FIG. 10, the cooling circuit of blade 300 may include a root passage 311 in fluid communication with airfoil passage 313. Additionally, platform 304 may include a serpentine cooling passage 305. Serpentine cooling passage 305 may be in fluid communication with the cooling circuit including root passage 311 and airfoil passage 313 or may be part of a separate cooling circuit. FIG. 10 shows first pocket 320 and second pocket 330 of blade 300 including such a cooling circuit, although here first pocket 320 and second pocket 330 are not in fluid communication with the cooling circuit.

[0050] 11 illustrates a non-limiting example of providing fluid communication between the cooling circuits of the blade 300 and the second pocket 330. More specifically, the platform conduits 331 may extend from the airfoil passages 313 to a plenum 333, which is in fluid communication with the second pocket 330. The second pocket 330 may receive coolant from the airfoil passages 313 and the plenum 333 and distribute the coolant to the cooling holes 337 in the surface of the platform 304 (e.g., through passages 345 (represented by dashed arrows) that extend from the second pocket 330 to the cooling holes 337 in the surface of the platform 304).

[0051] Another non-limiting example can be seen in FIG. 12 where a platform chamber 335 can be included, for example, to impingement cool the platform 304 and / or to aid in distributing coolant from the second pocket 330 to the cooling holes 337. For example, an intermediate wall 339 can be formed in the second pocket 330 spaced apart from a bottom surface 341 of the platform 304 to define the platform chamber 335. Coolant supplied to the second pocket 330 (e.g., coolant supplied by a passageway, not shown, coupled to the root passageway 311 or the airfoil passageway 313) can flow through the impingement holes 347 into the platform chamber 335 and impinge against the bottom surface 341 of the platform 304 to impingement cool the platform 304. The coolant can then exit the platform chamber 335 through the cooling holes 337 extending from the bottom surface 341 of the platform 304 to the top surface of the platform 304 to further cool the platform 304. To strengthen the intermediate wall 339, support members 343 (such as pins) may extend between the intermediate wall 339 and the bottom surface 341 of the platform 304. Although the examples shown in Figures 11 and 12 depict the second pocket 330 as part of and / or in fluid communication with the cooling circuit of the blade 300, it should be understood that similar connections may be made to the first pocket 320 instead of or in addition to the connections made to the second pocket 330, as necessary and / or appropriate in an embodiment.

[0052] An embodiment may include, for example, comprising a gas turbine system (such as turbomachine 100 shown in FIGS. 1 and 2 ), for example, blade 300. Thus, an embodiment may include a gas turbine system 100 in which a turbine assembly 110 includes a hot gas flow path HGP ( FIG. 2 ). With reference to FIG. 2 , a plurality of circumferentially spaced rotating blades 132 (such as blade 300) of the turbine assembly 110 may extend radially from a rotor 112 of a turbine 111 of the turbine assembly 110 into the hot gas flow path HGP. Each blade 300 may include features as described above with reference to FIGS. 4-12 and as described herein.

[0053]

[0013] Embodiments of the present disclosure provide various technical and commercial advantages, examples of which are described herein. In particular, by forming a buttress on one or both of the suction and pressure sides of the root of the blade as described above, the structural integrity of the blade may be enhanced while adding less mass to the blade than using prior art techniques. The buttress may define one or more pockets below the platform of the blade that may be advantageously used in the cooling circuit of the blade or in other systems where useful use of the pockets may improve the performance of the turbomachine (such as a gas turbine system) in which the blade is employed.

[0054] Approximate language used throughout the specification and claims can be applied to modify any quantitative expression that can be reasonably varied without causing a change in the basic function involved. Thus, values ​​modified by one or more terms (such as "approximately", "about", and "sufficiently") are not limited to the exact value specified. In at least some instances, approximate language may correspond to the precision of the instrument for measuring the value. Range limitations can be combined and / or substituted herein and throughout the specification and claims. Unless the context or language indicates otherwise, such ranges are identified and include all subranges encompassed therein. "About" or "approximately" applied to a particular value in a range applies to both ends of the range and can indicate + / - 10% of the stated value, unless otherwise dependent on the precision of the instrument for measuring the value.

[0055] The corresponding structures, materials, acts, and equivalents of all means-plus-function or step-plus-function elements in the claims are intended to encompass any structures, materials, or acts for performing that function in combination with other specifically claimed claim elements. The description of the present disclosure has been presented for purposes of illustration and description, and is not intended to be all inclusive or to limit the disclosure to the disclosed form. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the disclosure. The present embodiment has been chosen and described in order to best explain the principles of the disclosure and the practical application of such techniques, and to enable others skilled in the art to understand the disclosure and appreciate the possibility of various modifications of the embodiments of the disclosure as may be suitable for the particular use envisaged. [Explanation of symbols]

[0056] 100 Turbomachinery 102 Compressor 104 Combustor 106 Combustion Zone 108 Fuel Nozzle Assembly 110 Turbine Assembly 111 Turbine 112 Shaft 120 columns 122 Stationary Casing 126 Nozzle 128 Platform 130 Platform 132 Blade 134 Platform 135 Slash Surface 136 Tip 138 Shroud 140 Working Fluid 142 Root 144 Dovetail 146 Rotor Wheel 148 Shank 152 Airfoil 158 Leading Edge 160 Trailing edge 280 Seal Rail 284 Front Wall 286 Back wall 300 Blade 302 Root 304 Platform 305 Serpentine cooling passage 306 Airfoil 308 Dovetail 310 Shank 311 Route Passage 312 Base 313 Airfoil Passage 314 Main body 316 Tip 320 Pocket 320 First Pocket 322 First Buttress 324 First Inner Wall 326 End 330 Second Pocket 331 Platform Conduit 332 Second Buttress 333 Plenum 334 Second Inner Wall 335 Platform Chamber 336 End 337 Cooling hole 339 Intermediate Wall 340 Front Wall 341 Bottom 342 Back wall 343 Supporting member 345 Aisle 347 Impingement hole

Claims

1. A turbine (111) blade (132, 300), an airfoil (152, 306) including a tip portion (136, 316), a body portion (314), and a base portion (312); a platform (134, 304) connected to a base (312) of said airfoil (152, 306); a shank (148, 310) extending from said platform (134, 304) to said dovetail (144, 308), said shank (148, 310) comprising: forward and aft walls (286, 342) located below and connected to corresponding forward and aft ends of said platform (134, 304); and a first buttress (322, 332) disposed between the forward wall and the aft wall on one of a suction side of the shank (148, 310) and a pressure side of the shank (148, 310), the first buttress (322, 332) extending from a lower portion of the shank (148, 310) to a corresponding end (326, 336) of the platform (134, 304), a first portion of the first buttress (322, 332) being oriented at an angle of at least 30° relative to a first inner wall (324, 334) of the shank (148, 310), defining at least a first pocket (320, 330) between the first buttress (322, 332) and the first inner wall (324, 334); Shank (148, 310) A turbine (111) blade (132, 300).

2. The turbine (111) blade (132, 300) of claim 1, wherein the first pocket (320, 330) is further defined by a bottom of the platform (134, 304).

3. The turbine (111) blade (132, 300) of claim 1, wherein the first pocket (320, 330) is further defined by at least one of the forward wall (284, 340) and the aft wall (286, 342).

4. 4. The turbine blade of claim 3, wherein the second portion of the first buttress is oriented at an angle of at least 30 degrees relative to at least one of the forward wall and the aft wall.

5. 2. The turbine blade of claim 1, wherein a distance between the first inner wall and the first buttress varies between the platform and the dovetail.

6. The turbine (111) blade (132, 300) of claim 5, wherein a distance between the first inner wall (324, 334) and the first buttress (322, 332) varies with distance from the platform (134, 304).

7. a second buttress (322, 332) disposed between the forward wall (284, 340) and the aft wall (286, 342) on the other of the suction side of the shank (148, 310) and the pressure side of the shank (148, 310), the second buttress (322, 332) extending from a lower portion of the shank (148, 310) to a corresponding end (326, 332) of the platform (134, 304). 6), a first portion of said second buttress (322, 332) being oriented at an angle of at least 30° relative to a second inner wall (324, 334) of said shank (148, 310) to define a second pocket (320, 330) at least between said second buttress (322, 332) and said second inner wall (324, 334).

8. The turbine (111) blade (132, 300) of claim 7, wherein the first pocket (320, 330) is in fluid communication (140) with the second pocket (320, 330).

9. 8. The turbine (111) blade (132, 300) of claim 7, wherein at least one of the first pocket (320, 330) and the second pocket (320, 330) is in fluid communication (140) with a cooling circuit of the turbine (111) blade (132, 300).

10. A gas turbine (111) system (100), comprising: a turbine (111) section including a hot gas path; and a plurality of turbine (111) blades (132, 300) extending radially from a rotor (112) of the turbine (111) into the hot gas path and spaced circumferentially about the turbine (111), each turbine (111) blade (132, 300) comprising: a root (142, 300, 302) including a shank (148, 310) and a dovetail (144, 308), the dovetail (144, 308) being attached to the rotor (112); a platform (134, 304) connected to said shank (148, 310); an airfoil (152, 306) supported by said platform (134, 304) and extending radially away from said platform (134, 304); Including, The shank (148, 310) forward and aft walls (286, 342) located below and connected to corresponding forward and aft ends of said platform (134, 304); and a first buttress (322, 332) disposed between the forward wall and the aft wall on one of the suction side of the shank (148, 310) and the pressure side of the shank (148, 310), the first buttress (322, 332) extending from a lower portion of the shank (148, 310) to a corresponding end (326, 336) of the platform (134, 304); a first portion of the first buttress (322, 332) oriented at an angle of at least 30° relative to a first inner wall (324, 334) (324) of the shank (148, 310) and defining a first pocket (320, 330) (320) between at least the first buttress (322, 332) and the first inner wall (324, 334) (324); A gas turbine (111) system (100) comprising:

11. 11. The gas turbine system of claim 10, wherein the first pocket is further defined by at least one of a bottom of the platform, the forward wall, and the aft wall.

12. 12. The gas turbine system of claim 11, wherein the second portion of the first buttress is oriented at an angle of at least 30 degrees relative to at least one of the forward wall and the aft wall.

13. 11. The gas turbine system of claim 10, wherein a distance between the first inner wall and the first buttress varies between the platform and the dovetail.

14. The shank (148, 310) further includes a second buttress (322, 332) disposed between the forward wall and the aft wall (286, 342) on the other of the suction side of the shank (148, 310) and the pressure side of the shank (148, 310), the second buttress (322, 332) extending from a lower portion of the shank (148, 310) to a corresponding end (304) of the platform (134, 304).

11. The gas turbine system (100) of claim 10, wherein a first portion of said second buttress (322, 332) extends to a second inner wall (324, 334) of said shank (148, 310) and a first portion of said second buttress (322, 332) is oriented at an angle of at least 30° relative to a second inner wall (324, 334) of said shank (148, 310) to define a second pocket (320, 330) between at least said second buttress (322, 332) and said second inner wall (324, 334).

15. 15. The gas turbine system of claim 14, wherein at least one of the first pocket and the second pocket is in fluid communication with a cooling circuit of the turbine blade.

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