Turbine blade internal rib profile

Abstract

A turbine blade has an airfoil having a rib dividing a portion of an internal space defined between suction and pressure sides and leading and trailing edges into at least two internal passages. The airfoil also has a platform. A portion of the rib has a nominal profile that substantially conforms to Cartesian coordinate values X, Y, and Z listed in Table I. The Cartesian coordinate values are non-dimensional values from 0% to 100% that are convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The Cartesian coordinate values X, Y, and Z are connected by smooth continuous arcs to define the nominal profile of the portion of the rib.

Description

Technical Field

[0001] The subject matter disclosed herein relates to turbines. More specifically, the subject matter disclosed herein relates to the profile of internal ribs for turbine blades. Background Technology

[0002] Some jet aircraft and simple or combined cycle power plant systems employ gas turbine engines, or so-called turbines, in their configuration and operation. Some gas turbine engines employ an expanding turbine with one or more stages of turbine blades that are exposed to fluid flows at high temperatures and pressures during operation. The turbine blades include airfoils configured to aerodynamically interact with the fluid flow and generate energy from these fluid flows as part of power generation. For example, airfoils can be used to generate thrust, convert kinetic energy into mechanical energy, and / or convert thermal energy into mechanical energy. The fluid flow may include hot combustion gases, thus requiring internal cooling of the turbine blade airfoils. Cooling can be provided using channels defined, for example, by various ribs within internal coolant channels. Due to physical and thermal interactions, the structure of the airfoils (e.g., the ribs within the internal coolant channels) is exposed to a variety of stresses that can negatively impact the life of the turbine blades. Summary of the Invention

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

[0004] One aspect of this disclosure includes a turbine blade comprising: an airfoil having: a suction side, a pressure side opposite to the suction side, a leading edge, a trailing edge, and a first rib dividing a portion of an internal space defined between the suction side and the pressure side and the leading edge and the trailing edge into at least two internal channels; and a platform connected to the airfoil along the suction side and the pressure side and the leading edge and the trailing edge, the airfoil and the platform being included at the leading edge of the airfoil. The origin at the junction with the platform; wherein a portion of the first rib has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin by multiplying the value by the height of the airfoil in units of distance, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of that portion of the first rib.

[0005] Another aspect of this disclosure includes any of the foregoing aspects, and the turbine blade includes a first-stage blade.

[0006] Another aspect of this disclosure includes any of the foregoing aspects, and the turbine also includes a fillet that connects the surface of the platform to the airfoil.

[0007] Another aspect of this disclosure includes any of the foregoing aspects, and the portion of the first rib includes a radially outer portion of the first rib positioned radially inside the radially outer ends of the at least two internal channels.

[0008] Another aspect of this disclosure includes any of the foregoing aspects, and the first rib extends from the second rib to the third rib, and wherein the second rib and the third rib further divide the portion of the interior space into the at least two interior channels.

[0009] Another aspect of this disclosure includes a rotor blade section for a turbine, the rotor blade section comprising: a set of rotating blades including at least one blade having: an airfoil having: a suction side, a pressure side opposite to the suction side, a leading edge, a trailing edge, and a first rib located within an internal space defined between the suction side and the pressure side and the leading edge and the trailing edge, the first rib dividing the internal space into at least two internal channels; and a platform along the suction side and the pressure side, and the leading edge and the trailing edge. The airfoil is connected to the platform, which includes an origin at the junction of the leading edge of the airfoil and the platform; wherein a portion of the first rib has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin by multiplying the value by the height of the airfoil in distance units, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of that portion of the first rib.

[0010] Another aspect of this disclosure includes any of the foregoing aspects, and the turbine also includes a fillet that connects the surface of the platform to the airfoil.

[0011] Another aspect of this disclosure includes any of the foregoing aspects, and the rotor blade section is a first-stage blade section.

[0012] Another aspect of this disclosure includes any of the foregoing aspects, and the portion of the first rib includes a radially outer portion of the first rib positioned radially inside the radially outer ends of the at least two internal channels.

[0013] Another aspect of this disclosure includes any of the foregoing aspects, and the first rib extends from the second rib to the third rib, and wherein the second rib and the third rib further divide the portion of the internal space located within a given blade into the at least two internal channels.

[0014] Another aspect of this disclosure includes a turbine comprising a plurality of turbine blades in a rotor blade section, at least one of the plurality of turbine blades comprising: an airfoil having: a suction side, a pressure side opposite to the suction side, a leading edge, a trailing edge, and a first rib dividing a portion of an internal space defined between the suction side and the pressure side and the leading edge and the trailing edge into at least two internal channels; and a platform connected to the airfoil along the suction side and the pressure side and the leading edge and the trailing edge, the airfoil... The platform includes the origin at the junction of the leading edge of the airfoil and the platform; wherein a portion of the first rib has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin by multiplying the value by the height of the airfoil in distance units, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of that portion of the first rib.

[0015] Another aspect of this disclosure includes any of the foregoing aspects, and the turbine also includes a fillet that connects the surface of the platform to the airfoil.

[0016] Another aspect of this disclosure includes any of the foregoing aspects, and each turbine blade includes a first-stage blade.

[0017] Another aspect of this disclosure includes any of the foregoing aspects, and the portion of the first rib includes a radially outer portion of the first rib positioned radially inside the radially outer ends of the at least two internal channels.

[0018] Another aspect of this disclosure includes any of the foregoing aspects, and the first rib extends from the second rib to the third rib, and wherein the second rib and the third rib further divide the portion of the internal space located within a given blade into the at least two internal channels.

[0019] Two or more aspects described in this overview section may be combined to form specific implementations not specifically described herein.

[0020] Details of one or more specific embodiments are set forth in the following figures and description. Other features, objects, and advantages will be apparent from the specification, figures, and claims. Attached Figure Description

[0021] These and other features of the present disclosure will be more readily understood from the following detailed description of various aspects of the present disclosure, taken in conjunction with the accompanying drawings depicting various embodiments thereof, in which:

[0022] Figure 1 This is a simplified cross-sectional view of an illustrative turbine;

[0023] Figure 2 Is it possible to... Figure 1 A cross-sectional view of an exemplary turbine assembly (e.g., an expansion turbine) with four stages used together in a turbine;

[0024] Figure 3 This is a schematic three-dimensional view of an exemplary turbine blade including an unshielded airfoil according to various embodiments of the present disclosure;

[0025] Figure 4 It is an airfoil including contoured ribs according to various embodiments of this disclosure. Figure 3 The axial cross-sectional view taken from line 4-4 in the middle;

[0026] Figure 5 It is an airfoil including contoured ribs according to various embodiments of this disclosure. Figure 3 A schematic radial cross-sectional view taken from line 5-5 in the image;

[0027] Figure 6 It is the leading edge portion of an airfoil including contoured ribs according to various embodiments of this disclosure. Figure 3 Enlarged cross-sectional view taken from line 6-6 in the middle;

[0028] Figure 7 This is an enlarged top cross-sectional view of an airfoil including contoured ribs according to various embodiments of this disclosure; and

[0029] Figure 8 This is an enlarged side cross-sectional view of an airfoil including contoured ribs, according to various embodiments of this disclosure.

[0030] It should be noted that the accompanying drawings of this disclosure are not necessarily drawn to scale. The drawings are intended to depict only typical aspects of this disclosure and should therefore not be considered as limiting the scope of this disclosure. In the drawings, similar numbers denote similar elements between figures. Detailed Implementation

[0031] As a preliminary matter, in order to clearly describe the present art, it will be necessary to select certain terms when referring to and describing relevant machine parts within a turbine. To the extent possible, common industry terms will be used and adopted in a manner consistent with the accepted meaning of the terms. Unless otherwise stated, such terms should be given a broad interpretation consistent with the context of this application and the scope of the appended claims. Those skilled in the art will understand that several different or overlapping terms may generally be used to refer to a particular part. An object that can be described herein as a single part may include multiple parts and is referred to in another context as being composed of multiple parts. Alternatively, an object that can be described herein as comprising multiple parts may elsewhere be referred to as a single part.

[0032] Furthermore, several descriptive terms may be used regularly throughout this document, and it should prove helpful to define these terms at the beginning of this section. Unless otherwise stated, these terms and their definitions are as follows. As used herein, “downstream” and “upstream” are terms indicating the direction of fluid flow, such as the working fluid through a turbine engine, or, for example, the airflow through a combustor or the coolant through one of the components of a turbine system. The term “downstream” corresponds to the direction of fluid flow, and the term “upstream” refers to the direction opposite to the flow. Without any other particularity, the terms “front” and “rear” refer to directions, where “front” refers to the front end of the engine or the compressor end, and “rear” refers to the rear end of the engine or the turbine end.

[0033] It is often necessary to describe parts positioned at different radial locations relative to the central axis. The term "radial" refers to movement or position perpendicular to the axis. For example, if a first part is closer to the axis than a second part, this document will describe the first part as "radially inward" or "inner" of the second part. On the other hand, if the first part resides further away from the axis than the second part, this document may state that the first part is "radially outward" or "outer" of the second part. The term "axial" refers to movement or position parallel to the axis. Finally, the term "circumferential" refers to movement or position about the axis. It should be understood that such terms can be applied relative to the central axis of the turbine.

[0034] In addition, several descriptive terms may be used regularly in this document, 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 a single component.

[0035] The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit this disclosure. As used herein, the singular forms “a,” “an,” and “the” are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that, when used in the specification, the terms “comprising” and / or “including” specify the presence of the stated features, integers, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. “Optional” or “optionally” means that the features or elements subsequently described may or may not be present, and the description includes instances where the features are present and instances where the features are not present.

[0036] When an element or layer is referred to as “on another element or layer,” “joined to another element or layer,” “connected to another element or layer,” or “linked to another element or layer,” it may be directly on, joined to, connected to, or linked to another element or layer, or an intervening element or layer may be present. In contrast, when an element is referred to as “directly on,” “directly joined to,” “directly connected to,” or “directly linked to” another element or layer, an intervening element or layer may not be present. Other terms used to describe the relationship between elements should be interpreted in a similar manner (e.g., “between” vs. “directly between,” “adjacent” vs. “directly adjacent,” etc.). As used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items.

[0037] As described herein, various aspects of this disclosure relate to rotating turbine blades (hereinafter referred to as "blades" or "turbine blades"). A turbine blade may include an airfoil having: a suction side, a pressure side opposite to the suction side, a leading edge, and a trailing edge. The airfoil may also include ribs that divide a portion of an internal space defined between the suction side and the pressure side and the leading edge and the trailing edge into at least two internal channels. The turbine blade may also include a platform connected to the airfoil along the suction side and the pressure side, as well as the leading edge and the trailing edge, i.e., as part of the root of the turbine blade. The airfoil and the platform include an origin at the junction of the leading edge of the airfoil and the platform. A portion of the rib has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I. The Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin by multiplying the value by the airfoil's height, expressed in distance units. The X and Y values, connected by smooth, continuous arcs, define the rib profile section at each distance Z along this portion of the rib. The profile sections at distance Z smoothly interlock to form the nominal profile. The portion of the rib defined by the profile described herein is generally closer to the leading edge of the airfoil and closer to the suction side than the pressure side. The rib provides discrete regions of varying thicknesses and optimized fillets to reduce stress near the bends between the channels on both sides of the rib. More specifically, the rib includes a complex fillet shape along its bends that separates the two internal channels.

[0038] Refer to the attached diagram. Figure 1 This is a schematic view of an exemplary, non-limiting turbine 90 in the form of a combustion turbine or gas turbine (GT) system 100 (hereinafter “GT system 100”). The GT system 100 includes a compressor 102 and a combustor 104. The combustor 104 includes a combustion zone 105 and a fuel nozzle assembly 106. The GT system 100 also includes a turbine 108 (e.g., an expansion turbine) and a conventional rotary compressor / turbine shaft 110 (hereinafter referred to as “rotor shaft 110”).

[0039] In one non-limiting embodiment, the GT system 100 is a 7HA.03 engine, commercially available from GE Vernova Corporation of Cambridge, Massachusetts, USA. This disclosure is not limited to any particular GT system 100 and can be combined with 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 teachings of this disclosure are not necessarily limited to GT systems and can be applied to other types of turbines, such as steam turbines, jet engines, compressors, etc.

[0040] Figure 2 It shows that it can be used with Figure 1 A cross-sectional view of an exemplary, non-limiting portion of a turbine 108 having four stages S0 to S3, used in conjunction with the GT system 100. These four stages are referred to as S0, S1, S2, and S3. Stage S0 is the first stage and the smallest of the four stages (in the radial direction). Stage S1 is the second stage and the next stage in the axial direction. Stage S2 is the third stage and the next stage in the axial direction. Stage S3 is the fourth (last) stage and the largest (in the radial direction). It should be understood that the four stages are shown only as a non-limiting example, and each turbine may have more or fewer than four stages.

[0041] A set of stationary blades or nozzles 112 engages with a set of rotating blades 114 to form each stage S0-S3 of the turbine 108 and define a portion of the flow path through the turbine 108. The rotating blades 114 in each set are coupled to a corresponding rotor wheel 116, which circumferentially connects them to the rotor shaft 110. Figure 1 That is, multiple rotating blades 114 are mechanically coupled to each rotor wheel 116 in a circumferentially spaced manner. The stationary blade section 115 includes stationary nozzles 112 circumferentially spaced around the rotor shaft 110. Each nozzle 112 may include at least one platform 120, 122 connected to the airfoil 130. Figure 2 In the example shown, nozzle 112 includes a radially outer platform 120 and a radially inner platform 122. The radially outer platform 120 connects nozzle 112 to housing 124 of turbine 108.

[0042] During operation, air flows through compressor 102, and compressed air is supplied to burner 104. Specifically, compressed air is supplied to fuel nozzle assembly 106, which is integral with burner 104. Fuel nozzle assembly 106 is in fluid communication with combustion zone 105. Fuel nozzle assembly 106 is also in communication with fuel source ( Figure 1 (Not shown) is in fluid communication with and delivers fuel and air to combustion zone 105. Burner 104 is ignited and fuel is burned. Burner 104 is in fluid communication with turbine 108, within which the thermal energy of the gas flow is converted into mechanical rotational energy. Turbine 108 is rotatably coupled to and drives rotor shaft 110. Compressor 102 is also rotatably coupled to rotor shaft 110. In an exemplary embodiment, multiple burners 104 and fuel nozzle assemblies 106 are present. In the following discussion, unless otherwise specified, only one component of each component will be discussed. At least one end of the rotating rotor shaft 110 may extend axially away from turbine 108 or (compressor 102) and may be attached to a load or machinery (not shown), such as, but not limited to, a generator, a load compressor, and / or another turbine.

[0043] Figure 3 An example is shown of a turbine rotor blade 114 ( Figure 2 The blade 200 is a rotatable (dynamic) blade, such as... Figure 2 As shown, the rotatable (dynamic) blade is part of a set of turbine blades circumferentially distributed around the rotor shaft in the first stage of a turbine (e.g., turbine 108). That is, during turbine operation, when a working fluid (e.g., gas or steam) is guided through the airfoil of the blade, the blade 200 initiates rotation of the rotor shaft 110 and rotates about an axis defined by the rotor shaft 110. It should be understood that the blade 200 is configured to be coupled (mechanically coupled via fasteners, welding, slots / grooves, etc.) to multiple similar or different blades (e.g., blade 200 or other blades) to form the first stage of turbine 108 (e.g., turbine 108). Figure 2 A set of blades in the S0 stage.

[0044] refer to Figure 3 The turbine blade 200 may include an airfoil 202 having a suction side 204 (partially obscured in this view) and a pressure side 206 opposite to the suction side 204. The blade 200 may also include a leading edge 208 bridging the pressure side 206 and the suction side 204, and a trailing edge 210 opposite to the leading edge 208 and bridging the pressure side 206 and the suction side 204. The leading edge 208 is defined such that the combustion flow diverges therefrom to cross or pass over the edge or line of the pressure side 206 or the suction side 204.

[0045] As shown in the figure, the blade 200 may further include a platform 212 connected to the radially inner end 250 of the airfoil 202 and a pointed end 252 on the opposite end of the airfoil 202. Figure 3 The tip 252 without a tip shield is shown in the diagram. Platform 212 is part of root 214. For ease of depiction and description, root 214 is shown in... Figure 3 The example is "block", but the root 214 may have any suitable connection to the rotor shaft 110 ( Figure 1 The configuration is as follows: Platform 212 can be connected to airfoil 202 along suction side 204, pressure side 206, trailing edge 210, and leading edge 208. In various embodiments, blade 200 includes a fillet 216 near the radially inner end 250 of airfoil 202. Fillet 216 connects airfoil 202 and platform 212 (e.g., at surface 224 of platform 212). Fillet 216 may include weld fillet or brazed fillet, which may be formed via conventional MIG welding, TIG welding, brazing, etc. Fillet 216 may include such forms as those used in investment casting processes or defined integrally. The portions of root 214 are configured to be fitted to rotor shaft 110 ( Figure 1The platform 212 is located in the mating groove of the airfoil 202 and mates with adjacent components of other blades 200. The platform 212 is intended to be located radially inward of the airfoil 202 and formed in any complementary configuration relative to the rest of the root 214. The airfoil 202 and the platform 212 include an origin 220 at the junction of the leading edge 208 of the airfoil 202 and the platform 212 (i.e., at the junction between the platform 212 and the airfoil 202).

[0046] Refer again Figure 2 and Figure 3 In various non-limiting embodiments, blade 200 may include first-stage (S0) blades, second-stage (S1) blades, third-stage (S2) blades, or fourth-stage (S3) blades. In a particular embodiment, blade 200 is a first-stage (S0) blade. In various embodiments, turbine 108 may include a set of blades 200 only in the first stage (S0) of turbine 108, or only in the second stage (S3), or only in the third stage (S2), or only in the fourth stage (S3) of turbine 108.

[0047] Figure 4 The airfoil 202 is shown along Figure 3 The axial cross-sectional view taken from line 4-4 in the image, and Figure 5 The airfoil 202 is shown along Figure 3 The radial schematic cross-sectional view taken from line 5-5 in the image. Figure 6 The diagram shows a general outline of the leading edge portion (i.e., near the leading edge 208) of the rib 260 according to an embodiment of the present disclosure. Figure 3 An enlarged three-dimensional cross-sectional view of the airfoil 202 in line of sight 6-6. Figure 7 An enlarged top-view cross-sectional view is shown, and Figure 8 An enlarged side cross-sectional view of an airfoil 202 including a contoured rib 260 according to various embodiments of the present disclosure is shown.

[0048] refer to Figures 3 to 5 The internal space 262 of the airfoil 202 is collectively defined within the suction side 204, the pressure side 206, the leading edge 208, and the trailing edge 210. The internal space 262 provides an internal coolant flow channel 264 that delivers coolant through the airfoil 202 to cool it. The coolant (arrow) can be delivered to the airfoil 202 in any manner now known or later developed, for example, via a compressor 102 (…). Figure 1 The outlet fluid is connected to the flow channel in the root 214. For example... Figure 5 and Figure 8As shown, the internal space 262 and the internal coolant flow channel 264 may terminate at a tip plate 270 that defines a portion of the tip 252 of the airfoil 202. The internal space 262 is divided into at least two channels 266, 268 by any number of ribs 260, with one rib 272 according to an embodiment of the present disclosure.

[0049] like Figure 5 As shown, any number of ribs 272 may extend from the radially inner end 250 of the airfoil 222 and terminate before the tip plate 270, and any number of ribs 272 may extend from the tip 252 of the airfoil 202 and terminate, for example, before the root 214. The ribs 272 can thus form channels 266, 268 for guiding coolant through a serpentine cooling channel in which the coolant is guided radially inward and then radially outward, depending on their position within the airfoil 202. More specifically, various ribs 272 (rib 260 being one of them) divide portions of the internal space 262 defined between the suction side 204 and the pressure side 206 and the leading edge 208 and trailing edge 210 into at least two internal channels 266, 268. Other ribs 272 may define additional internal channels 294. Ribs 272 may define a series of adjacent cooling channels 294 along the suction side 204 and the pressure side 206 as “near-wall” cooling channels. The end portions of some ribs 272 may extend to the turbine blades 200 (…). Figure 3 Challenging stress areas that negatively impact the lifespan of [the product / service].

[0050] Figures 6 to 8 A portion 280 of the rib 260 is shown (in Figures 6 to 8 Highlighted in the image and referred to hereinafter as "rib portion 280"), this portion has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I below. Rib portion 280 includes a radially outer portion of rib 260, which is positioned at the radially outer end 282 of at least two internal channels 266, 268 formed by rib 260. Figure 8 The coolant is located radially inside the rib 260, specifically within the tip plate 270. Therefore, coolant can flow from the near-wall channel 268 through the rib 260 and rib portion 280, and into the central channel 266. The radially outer end 282 defines a fluidly connected air chamber between the near-wall channel 268 and the central channel 266. In other embodiments, the coolant flow may originate from the central channel 266 and be directed through the rib 260 and rib portion 280 into the near-wall channel 268.

[0051] In the example shown, the (first) rib 260 extends between the (second) rib 290 and the (third) rib 292, and connects to the second rib 290 and the third rib 292 (in other words, the rib 260 extends from the rib 290 to the rib 292). The ribs 290 and 292 further divide this portion of the interior space 262 into other interior channels (e.g., 294). For example, the rib 290 may have an end edge along the suction sidewall 206 and define one or more near-wall channels 264, 294 along the suction side 206, while the rib 292 may be positioned closer to the leading edge 208 and span from the suction side 204 to the pressure side 206, thereby defining the front coolant channels 264, 294. The rib portion 280 of the rib 260 extends from the rib 292 toward the midpoint of the rib 260 (i.e., the midpoint between the rib 292 and the rib 290).

[0052] The nominal shape of the rib portion 280 is configured to reduce the stress experienced by the rib 260 and increase the turbine blade 200 ( Figure 3 The lifespan of the rib portion 280 may be defined by coordinate values. Figure 6 and Figure 8 The rib-shaped portion 280 shown includes multiple points corresponding to coordinate values ​​X, Y, and Z. Each point can be described by a corresponding set of coordinate values ​​X, Y, and Z. For example, coordinates from Table I can be provided to define each point. Note that the number of points shown in the figures may not necessarily match the values ​​in Table I.

[0053] Cartesian coordinate values ​​are expressed in normalized or dimensionless form as values ​​from 0% to 100% (percentages), but it should be understood that any or all coordinate values ​​may alternatively be expressed in distance units, as long as percentages and proportions are maintained. To convert the X, Y, or Z values ​​in Table I to corresponding X, Y, and Z coordinate values ​​in distance units (such as inches or centimeters), the dimensionless X, Y, or Z values ​​given in Table I can be multiplied by the airfoil height H of airfoil 202 in such distance units. The “airfoil height” H is defined as the radial distance from the origin 220 to the position of the tip 252 above it. A representative height of airfoil 202 can range from approximately 5.0 inches (approximately 12.7 centimeters (cm)) to approximately 12.0 inches (approximately 30.48 cm). In a specific embodiment for the S0 blade of the GE Vernova 7HA.03 heavy-duty gas turbine engine, the height H of airfoil 202 can be approximately 7.89 inches (approximately 20.04 cm).

[0054] By smoothly connecting the X, Y, and Z data points to each other (using lines and / or arcs), any curve fitting technique now known or developed in the future can be used to form the surface profile of the rib portion 280 to produce a curved surface suitable for, for example, an airfoil. Curve fitting techniques may include, but are not limited to: extrapolation, interpolation, smoothing, polynomial regression, and / or other mathematical curve fitting functions. Curve fitting techniques can be performed manually and / or computationally, for example, using statistical and / or numerical analysis software.

[0055] The values ​​in Table I are dimensionless percentages, shown to three decimal places, used to determine the nominal profile of the rib portion 280 under environmental, non-operating, or non-thermal conditions, and do not take into account any coatings or fillets, although other conditions, coatings, and / or fillets may be considered in the embodiments. To allow for typical manufacturing tolerances and / or coating thicknesses, ± values ​​can be added to the values ​​listed in Table I, particularly to the X and Y values ​​therein. For example, a tolerance of approximately 10% to 20% of the minimum thickness of the rib portion 280 in a direction perpendicular to any surface location of the rib portion 280 can define the profile envelope of the rib portion 280 for designs at cold temperatures or room temperature. In other words, a distance of approximately 10% to 20% of the minimum thickness of the rib portion 280 in a direction perpendicular to any surface location of its rib portion can define the range of variation between the measurement points on the actual rib portion 280 and the ideal locations of those points, particularly at cold temperatures or room temperature, as embodied in this disclosure. As demonstrated in this paper, the 280 configuration of the rib section is robust to this range of variations without compromising mechanical and aerodynamic functions.

[0056] Similarly, the profile and / or configuration can be scaled up or down, such as geometrically, without impairing operation. Such scaling can be facilitated by multiplying normalized / dimensionless percentage values ​​by a common scaling factor, which can be a number of distance units larger or smaller than the rib 272 of the airfoil 202 initially used for a given height. For example, the dimensionless percentage values ​​in Table I (specifically the X and Y values) can be uniformly multiplied by a scaling factor of 2, 0.5, or any other desired scaling factor. In various embodiments, the X, Y, and Z distances can be scaled as a function of the same constant or number to provide a scaled-up or scaled-down rib portion 280. Alternatively, these values ​​can be multiplied by a larger or smaller desired airfoil height H. As referenced herein, the origin 220 of the X, Y, Z coordinate system is the leading edge engagement point of the airfoil 202 with the surface 224 of the platform 212.

[0057] When using Z values ​​not explicitly listed in Table I, the corresponding X and Y values ​​can be determined by extrapolation. For example, if an 87% Z layer is required, the X value can be 80% plus 0.7 times the difference between the 80% and 90% X values ​​(70%). Similarly, the Y value can be 80% plus 0.7 times the difference between the 80% and 90% Y values ​​(70%). Other extrapolation methods can also be used.

[0058]

[0059]

[0060]

[0061] The disclosed shape of the rib portion 280 provides a unique profile to achieve optimized stress relief at the rib 260, thereby meeting performance objectives specific to the machine using the rotating blade 200 and possibly other machines.

[0062] Embodiments of this disclosure also include a rotor blade section for a turbine, for example, a first stage, the rotor blade section including a set of rotating blades 200, the set of rotating blades including at least one blade 200 having a rib 260 having a rib portion 280 as described herein.

[0063] Embodiments of this disclosure also include a turbine 108, which includes a plurality of turbine blades 200, as described herein.

[0064] The embodiments disclosed herein offer various technical and commercial advantages, examples of which are discussed herein. The ribs described herein provide discrete regions of varying thicknesses and optimized fillets to reduce stress near the bends between the channels on either side of the rib. More specifically, the ribs include complex fillet shapes along their bends that separate the two internal channels, which reduces stress in the airfoil and increases the life of the turbine blades, rotor blade sections, and / or the turbines used therein.

[0065] While the apparatus and devices of this disclosure are envisioned for use in heavy-duty turbines deployed in power generation systems, the rib 260 of this disclosure can also be used in turbine blades 200 of other systems not described herein, which may benefit from increased stress relief associated with the improved profile of the rib portion 280.

[0066] As used throughout the specification and claims, approximate language may be used to modify any quantitative expression that may be varied without causing a change in the essential function associated with it. Therefore, values ​​modified by one or more terms (such as “about,” “approximately,” and “substantially”) are not limited to specified exact values. In at least some cases, approximate language may correspond to the precision of the instrument used to measure the value. Range limitations may be combined and / or interchanged herein and throughout the specification and claims; unless otherwise indicated by context or language, these ranges are identified and include all subranges contained therein. The term “about” applied to a specific value within a range applies to both ends of the range and may indicate + / - 10% of the value unless otherwise dependent on the precision of the instrument used to measure it.

[0067] All means or steps plus functional elements in the following claims are intended to include any structure, material, action, and equivalent for performing a function in conjunction with other claimed elements of a particular claim. This disclosure has been described for purposes of illustration and description, but it is not intended to be exhaustive or to limit the disclosure to the forms disclosed. 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 were chosen and described in order to best explain the principles of this disclosure and its practical application, and to enable others skilled in the art to understand this disclosure so that it is suitable for various modifications to further contemplated particular uses.

[0068] Other aspects of the invention are provided by the subject matter of the following provisions:

[0069] Clause 1: A turbine blade comprising: an airfoil having: a suction side, a pressure side opposite the suction side, a leading edge, a trailing edge, and a first rib dividing a portion of an internal space defined between the suction side and the pressure side and the leading edge and the trailing edge into at least two internal channels; and a platform connected to the airfoil along the suction side and the pressure side and the leading edge and the trailing edge, the airfoil and the platform including an origin at the junction of the leading edge of the airfoil and the platform; wherein a portion of the first rib is shaped to have a nominal profile substantially conforming to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, the dimensionless values ​​being convertible to a distance from the origin by multiplying the values ​​by the height of the airfoil in distance units, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of the portion of the first rib.

[0070] Clause 2: Turbine blades according to any of the preceding clauses, wherein the turbine blades include first-stage blades.

[0071] Clause 3: The turbine blade according to any of the preceding clauses further includes a fillet that connects the surface of the platform to the airfoil.

[0072] Clause 4: A turbine blade according to any of the preceding clauses, wherein said portion of the first rib includes a radially outer portion of the first rib, said radially outer portion being located radially inner to the radially outer ends of the at least two internal channels.

[0073] Clause 5: A turbine blade according to any of the preceding clauses, wherein the first rib extends from the second rib to the third rib, and wherein the second rib and the third rib further divide the portion of the interior space into the at least two interior channels.

[0074] Clause 6: A rotor blade section for a turbine, the rotor blade section comprising: a set of rotating blades, the set of rotating blades including at least one blade, the at least one blade having: an airfoil having: a suction side, a pressure side opposite to the suction side, a leading edge, a trailing edge, and a first rib located within an internal space defined between the suction side and the pressure side and the leading edge and the trailing edge, the first rib dividing the internal space into at least two internal channels; and a platform along the suction side and the pressure side and the leading edge and the trailing edge, and the airfoil having: The airfoil and the platform are connected, with the origin at the junction of the leading edge of the airfoil and the platform; wherein a portion of the first rib has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin by multiplying the value by the height of the airfoil in distance units, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of the portion of the first rib.

[0075] Clause 7: The rotor blade section according to any of the preceding clauses further includes a fillet that connects the surface of the platform to the airfoil.

[0076] Clause 8: The rotor blade section described in any of the preceding clauses, wherein the rotor blade section is a first-stage blade section.

[0077] Clause 9: The rotor blade section according to any of the preceding clauses, wherein the portion of the first rib includes a radially outer portion of the first rib, the radially outer portion being located radially inner to the radially outer ends of the at least two internal channels.

[0078] Clause 10: A rotor blade section according to any of the preceding clauses, wherein the first rib extends from the second and third ribs, and wherein the second and third ribs further divide the portion of the internal space located within a given blade into the at least two internal channels.

[0079] Clause 11: A turbine comprising a plurality of turbine blades in a rotor blade section, at least one of the plurality of turbine blades comprising: an airfoil having: a suction side, a pressure side opposite to the suction side, a leading edge, a trailing edge, and a first rib dividing a portion of an internal space defined between the suction side and the pressure side and the leading edge and the trailing edge into at least two internal channels; and a platform connected to the airfoil along the suction side and the pressure side and the leading edge and the trailing edge, the airfoil and the... The platform includes an origin at the junction of the leading edge of the airfoil and the platform; wherein a portion of the first rib has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin by multiplying the values ​​by the height of the airfoil in units of distance, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of the portion of the first rib.

[0080] Clause 12: The turbine according to any of the preceding clauses further includes a fillet that connects the surface of the platform to the airfoil.

[0081] Clause 13: A turbine according to any of the preceding clauses, wherein each turbine blade includes a first-stage blade.

[0082] Clause 14: The turbine according to any of the preceding clauses, wherein the portion of the first rib includes a radially outer portion of the first rib, the radially outer portion being located radially inner to the radially outer ends of the at least two internal channels.

[0083] Clause 15: A turbine according to any of the preceding clauses, wherein the first rib extends from the second rib to the third rib, and wherein the second rib and the third rib further divide the portion of the internal space located within a given blade into the at least two internal channels.

Claims

1. A turbine blade (200), the turbine blade comprising: An airfoil (202) having: a suction side (204), a pressure side (206) opposite to the suction side (202), a leading edge (208), a trailing edge (210), and a first rib (260) dividing a portion of an internal space (262) defined between the suction side (204) and the pressure side (206) and the leading edge (208) and the trailing edge (210) into at least two internal channels (266, 268); and Platform (212), which is connected to airfoil (202) along the suction side (204) and the pressure side (206) as well as the leading edge (208) and the trailing edge (210), the airfoil (202) and the platform (212) including the origin (220) at the junction of the leading edge of the airfoil (202) and the platform (212). A portion of the first rib (260) has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin (220) by multiplying the value by the height of the airfoil (202) in distance units, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of the portion of the first rib (260).

2. The turbine blade (200) according to claim 1, wherein the turbine blade (200) comprises a first-stage blade.

3. The turbine blade according to any of the preceding claims, the turbine blade further comprising a fillet (216) that connects the surface of the platform (212) to the airfoil (202).

4. The turbine blade (200) according to any of the preceding claims, wherein the portion of the first rib (260) includes a radially outer portion of the first rib (260) located radially inside the radially outer ends (282) of the at least two internal channels (266, 268).

5. The turbine blade (200) according to any of the preceding claims, wherein the first rib (260) extends from the second rib to the third rib, and wherein the second rib and the third rib further divide the portion of the interior space into the at least two interior channels (266, 268).

6. A rotor blade section for a turbine (108), the rotor blade section comprising: A set of rotating blades (200), the set of rotating blades (200) including at least one blade (200), the at least one blade having: An airfoil (202) having: a suction side (204), a pressure side (206) opposite to the suction side (204), a leading edge (208), a trailing edge (210), and a first rib (260) located within an internal space (262) defined between the suction side (204) and the pressure side (206) and the leading edge (208) and the trailing edge (210), the first rib (260) dividing the internal space into at least two internal channels (266, 268); and Platform (212) is connected to airfoil (202) along the suction side (204) and the pressure side (206), as well as the leading edge (208) and the trailing edge (210). Airfoil (202) and platform (212) include an origin (220) at the junction of the leading edge (208) of airfoil (202) and platform (212). A portion of the first rib (260) has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin (220) by multiplying the value by the height of the airfoil (202) in distance units, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of the portion of the first rib (260).

7. The rotor blade section according to claim 6, wherein the rotor blade section further includes a fillet (216) that connects the surface of the platform (212) to the airfoil (202).

8. The rotor blade section according to any one of claims 6 to 7, wherein the rotor blade section is a first-stage blade section.

9. The rotor blade section according to any one of claims 6 to 8, wherein the portion of the first rib (260) includes a radially outer portion of the first rib (260) located radially inside the radially outer ends (282) of the at least two internal channels (266, 268).

10. The rotor blade section according to any one of claims 6 to 9, wherein the first rib (260) extends from the second rib and the third rib, and wherein the second rib and the third rib further divide the portion of the internal space (262) located within a given blade into the at least two internal channels (266, 268).

11. A turbine comprising a plurality of turbine blades in a rotor blade section, at least one of the plurality of turbine blades comprising: An airfoil (202) having: a suction side (204), a pressure side (206) opposite to the suction side (204), a leading edge (208), a trailing edge (210), and a first rib (260) dividing a portion of an internal space (262) defined between the suction side (204) and the pressure side (206) and the leading edge (208) and the trailing edge (210) into at least two internal channels (266, 268); and Platform (212) is connected to airfoil (202) along the suction side (204) and the pressure side (206), as well as the leading edge (208) and the trailing edge (210). Airfoil (202) and platform (212) include an origin (220) at the junction of the leading edge (208) of airfoil (202) and platform (212). A portion of the first rib (260) has a nominal profile that substantially conforms to the Cartesian coordinate values ​​X, Y, and Z listed in Table I, wherein the Cartesian coordinate values ​​are dimensionless values ​​from 0% to 100%, which can be converted to a distance from the origin (220) by multiplying the value by the height of the airfoil (202) in distance units, and wherein the Cartesian coordinate values ​​X, Y, and Z are connected by smooth, continuous arcs to define the nominal profile of the portion of the first rib (260).

12. The turbine of claim 11, further comprising a fillet (216) connecting the surface of the platform (212) to the airfoil (202).

13. The turbine according to any one of claims 11 to 12, wherein each turbine blade comprises a first-stage blade.

14. The turbine according to any one of claims 11 to 13, wherein the portion of the first rib (260) includes a radially outer portion of the first rib (260) located radially inside the radially outer ends (282) of the at least two internal channels (266, 268).

15. The turbine according to any one of claims 11 to 14, wherein the first rib (260) extends from the second rib to the third rib, and wherein the second rib and the third rib further divide the portion of the internal space (262) located within a given blade into the at least two internal channels (266, 268).

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