INNER RIBBON PROFILE OF A TURBINE SHAFTS
The turbine blade design with a rib profile defined by Cartesian coordinates addresses stress-related issues in turbine blades, enhancing service life and coolant flow efficiency.
Patent Information
- Authority / Receiving Office
- DE · DE
- Patent Type
- Applications
- Current Assignee / Owner
- GENERAL ELECTRIC TECH GMBH
- Filing Date
- 2025-11-13
- Publication Date
- 2026-06-11
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Abstract
Description
TECHNICAL AREA
[0001] The subject matter disclosed herein relates to turbomachinery. In particular, the subject matter disclosed herein relates to an internal rib profile for turbine blades. STATE OF THE ART
[0002] Some jet aircraft and simple or combined-cycle power plant systems utilize a gas turbine engine, also known as a turbomachine, in their design and operation. Some gas turbine engines employ expansion turbines with one or more stages of turbine blades that are exposed to fluid flows at high temperatures and pressures during operation. These turbine blades incorporate guide vanes configured to interact aerodynamically with the fluid flows and generate energy from them as part of the power generation process. For example, the guide vanes can be used to generate thrust, converting kinetic energy into mechanical energy and / or converting thermal energy into mechanical energy. The fluid flow may include hot combustion gases, necessitating internal cooling of the turbine blade's guide vane.Cooling can be provided, for example, by using channels defined by various fins within an internal coolant channel. Due to physical and thermal interactions, the structures of the air guide vanes (e.g., the fins within the internal coolant channel) are subjected to a variety of stresses, which can negatively affect the service life of the turbine blades. SHORT DESCRIPTION
[0003] All aspects, examples and features mentioned below can be combined in any technically possible way.
[0004] One aspect of the disclosure includes a turbine blade comprising: an air guide plate having: an intake side, a pressure side opposite the intake side, a leading edge, a trailing edge and a first rib dividing a section of an interior space defined between the intake and pressure sides and the leading and trailing edges into at least two internal channels; and a platform connected to the air guide plate along the intake and pressure sides and the leading and trailing edges, the air guide plate and the platform enclosing an origin at a junction of the leading edge of the air guide plate and the platform;wherein a section of the first rib has a shape with a nominal profile which substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin by multiplying the values by a height of the air guide expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the section of the first rib.
[0005] Another aspect of the revelation includes any of the foregoing aspects, and the turbine blade includes a first-stage blade.
[0006] Another aspect of the disclosure includes any of the foregoing aspects and further comprises a concave groove connecting a surface of the platform to the air guide plate.
[0007] Another aspect of the disclosure includes any of the foregoing aspects, and the section of the first rib includes a radially outer section of the first rib that is positioned radially inside a radially outer end of the at least two inner channels.
[0008] Another aspect of the disclosure includes any of the foregoing aspects, and the first rib extends from a second rib to a third rib adjacent to an inner surface of a pressure sidewall of the air guide plate, the second rib and the third rib further subdividing the section of the interior into the at least two inner channels.
[0009] Another aspect of the disclosure includes a rotor blade section for a turbine, wherein the rotor blade section comprises: a set of rotating blades, the set of rotating blades including at least one blade having: an air guide plate having: an intake side, a pressure side opposite the intake side, a leading edge, a trailing edge and a first rib within an interior space defined between the intake and pressure sides and the leading and trailing edges, the first rib dividing the interior space into at least two internal channels; and a platform connected to the air guide plate along the intake and pressure sides and the leading and trailing edges, the air guide plate and the platform including an origin at a junction of the leading edge of the air guide plate and the platform;wherein a section of the first rib has a shape with a nominal profile which substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin by multiplying the values by a height of the air guide expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the section of the first rib.
[0010] Another aspect of the disclosure includes any of the foregoing aspects and further comprises a concave groove connecting a surface of the platform to the air guide plate.
[0011] Another aspect of the disclosure includes any of the foregoing aspects, and the rotor blade section is a first-stage blade section.
[0012] Another aspect of the disclosure includes any of the foregoing aspects, and the section of the first rib includes a radially outer section of the first rib that is positioned radially inside a radially outer end of the at least two inner channels.
[0013] Another aspect of the disclosure includes any of the foregoing aspects, and the first rib extends from a second rib to a third rib adjacent to an inner surface of a pressure sidewall of the air guide plate, the second rib and the third rib further subdividing the section of the interior into the at least two inner channels.
[0014] Another aspect of the disclosure includes a turbine with a plurality of turbine blades in a rotor blade section, wherein at least one of the plurality of turbine blades comprises: an air guide plate having: an intake side, a pressure side opposite the intake side, a leading edge, a trailing edge and a first rib dividing a section of an interior space defined between the intake and pressure sides and the leading and trailing edges into at least two internal channels; and a platform connected to the air guide plate along the intake and pressure sides and the leading and trailing edges, wherein the air guide plate and the platform include an origin at a junction of the leading edge of the air guide plate and the platform;wherein a section of the first rib has a shape with a nominal profile which substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin by multiplying the values by a height of the air guide expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the section of the first rib.
[0015] Another aspect of the disclosure includes any of the foregoing aspects and further comprises a concave groove connecting a surface of the platform to the air guide plate.
[0016] Another aspect of the revelation includes any of the foregoing aspects, and the turbine blade includes a first-stage blade.
[0017] Another aspect of the disclosure includes any of the foregoing aspects, and the section of the first rib includes a radially outer section of the first rib that is positioned radially inside a radially outer end of the at least two inner channels.
[0018] Another aspect of the disclosure includes any of the foregoing aspects, and the first rib extends from a second rib to a third rib adjacent to an inner surface of a pressure sidewall of the air guide plate, the second rib and the third rib further subdividing the section of the interior into the at least two inner channels.
[0019] Two or more aspects described in this revelation can be combined to form implementations not specifically described herein.
[0020] The details of one or more implementations are set out in the attached drawings and the description below. Further features, functions, and advantages will become apparent from the description, the drawings, and the claims. BRIEF DESCRIPTION OF THE DRAWINGS
[0021] These and other features of this revelation will be better understood from the following detailed description of the various aspects of the revelation in conjunction with the accompanying drawings, which depict different embodiments of the revelation, in which the following applies: Fig. Figure 1 is a simplified cross-sectional view of an illustrated turbomachine; Fig. Figure 2 is a cross-sectional view of an illustrated turbine arrangement (e.g., an expansion turbine) with four stages, which is connected to the turbomachine in Fig. 1 can be used; Fig. Figure 3 is a schematic three-dimensional view of an illustrated turbine blade including an air guide plate without a casing, according to various embodiments of the disclosure; Fig. Figure 4 is an axial cross-sectional view along the view line 4-4 in Fig. 3 of an air guide plate including a rib with a profile according to various embodiments of the disclosure; Fig. Figure 5 is a radial, schematic cross-sectional view along the view line 5-5 in Fig. 3 of an air guide plate including a rib with a profile, according to various embodiments of the disclosure; Fig. Figure 6 is an enlarged cross-sectional view along the view line 6-6 in Fig. 3 of an intake side section of an air guide plate including a rib with a profile, according to various embodiments of the disclosure; Fig. Figure 7 is an enlarged cross-sectional view of an air guide plate from top to bottom, which includes a rib with a profile, according to various embodiments of the disclosure; and Fig. Figure 8 is an enlarged lateral cross-sectional view of an air guide plate enclosing a rib with a profile, according to various embodiments of the disclosure.
[0022] It is noted that the drawings in the Book of Revelation are not necessarily to scale. The drawings are intended only to represent typical aspects of the Book of Revelation and should therefore not be considered as limiting the scope of protection afforded by the Book of Revelation. In the drawings, identical numbers correspond to identical elements between the drawings. DETAILED DESCRIPTION
[0023] To clearly describe the current technology, a specific terminology must first be selected when referring to and describing relevant machine components within a turbomachine. Where possible, industry-standard terminology will be used and employed in a manner consistent with its recognized meaning. Unless otherwise specified, such terminology should be interpreted broadly, in accordance with the context of the present application and the scope of the accompanying claims. Those skilled in the art will recognize that a particular component may often be referred to using several different or overlapping terms. What may be described herein as a single part may include several components and, in another context, be described as consisting of such components.Alternatively, what may be described herein as including several components may elsewhere be referred to as a single part.
[0024] Furthermore, several descriptive terms may be used regularly herein, and it should prove helpful to define these terms at the beginning of this section. These terms and their definitions are, unless otherwise stated, as follows. As used here, "downstream" and "upstream" are expressions that indicate a direction relative to the flow of a fluid, such as the working fluid through the turbine engine, or, for example, the airflow through the combustion chamber, or the coolant through one of the turbine component systems. The term "downstream" corresponds to the direction of flow of the fluid, and the term "upstream" denotes the direction opposite to the flow. The terms "front" and "back" refer, without further specification, to directions, with "front" referring to the front or compressor end of the engine and "back" to the back or turbine end of the engine.
[0025] It is often necessary to describe parts that are positioned at different radial locations relative to a central axis. The term "radial" refers to a movement or position perpendicular to an axis. For example, if a first component is closer to the axis than a second component, this indicates that the first component is "radially inside" or "inward" of the second component. Conversely, if the first component is farther from the axis than the second component, this indicates that the first component is "radially outside" or "outward" of the second component. The term "axial" refers to a movement or position parallel to an axis. Finally, the term "circumferential" refers to a movement or position around an axis.It is understood that such terms can be applied in relation to the central axis of the turbomachine.
[0026] Furthermore, several descriptive terms can be used regularly here, as described below. The terms "first," "second," and "third" can be used interchangeably to distinguish one component from another and are not intended to indicate the location or importance of the individual components.
[0027] The terminology used herein serves only to describe certain embodiments and is not intended to limit the disclosure. As used herein, the singular forms "a," "an," and "the" are intended to include the plural forms unless the context clearly indicates otherwise. It is further understood that the terms "comprises" and / or "comprehensive," when used in this description, specify the presence of specified 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, element components, and / or groups thereof.“Optional” or “where applicable” means that the feature or element described below may or may not be present, and that the description includes cases where the feature is present and cases where it is not.
[0028] When an element or layer is described as "on," "interacting with," "connected with," or "coupled with" another element or layer, it may be directly on, connected, interacting with, or coupled to the other element or layer, or there may be intervening elements or layers. Conversely, when an element is described as "directly on," "directly interacting with," "directly connected with," or "directly coupled with" another element or layer, there are no intervening elements or layers. Other words used to describe the relationship between elements should be interpreted similarly (e.g., "between" versus "directly between," "adjacent" versus "directly adjacent," etc.).In the sense used herein, the term “and / or” includes any and all combinations of one or more of the associated listed items.
[0029] As mentioned herein, various aspects of the disclosure are directed to rotating turbine blades (hereinafter referred to as "blade" or "turbine blade"). A turbine blade may include an air guide plate having: an intake side, a pressure side opposite the intake side, a leading edge, and a trailing edge. The air guide plate may also include a rib dividing a section of an interior space defined between the intake and pressure sides and the leading and trailing edges into at least two internal channels. The turbine blade may also include a platform connected to the air guide plate along the intake and pressure sides and the leading and trailing edges, i.e., as part of a root of the turbine blade. The air guide plate and the platform include an origin at a junction of the leading edge of the air guide plate and the platform.A section of the rib has a shape with a nominal profile that substantially corresponds to the Cartesian coordinate values of X, Y, and Z listed in TABLE I. The Cartesian coordinate values are dimensionless values from 0% to 100%, which can be converted into distances from the origin by multiplying the values by a height of the air guide expressed in distance units. The X and Y values, connected by smooth, continuous arcs, define rib profile sections at each distance Z along the rib's spacing. The profile sections at the Z distances are smoothly connected to each other to form the nominal profile. The section of the rib defined herein by the profile is positioned between two other ribs adjacent to an inner surface of a pressure sidewall of the air guide, at or slightly behind the area of maximum air guide thickness.The other two ribs further subdivide the interior section into at least two inner channels. The rib incorporates discrete areas of varying thickness and optimized rounding to reduce stress near bends between the channels on both sides of the rib. In particular, along one bend, the rib includes a complex fillet that separates the two inner channels.
[0030] Referring to the drawings, Fig. Figure 1 shows a schematic view of an illustrative, non-limiting turbomachine 90 in the form of a combustion turbine or gas turbine system (GT system) 100 (hereinafter referred to as “GT system 100”). The GT system 100 includes a compressor 102 and a combustion chamber 104. The combustion chamber 104 includes a combustion area 105 and a fuel nozzle assembly 106. The GT system 100 also includes a turbine 108 (i.e., an expansion turbine) and a conventional compressor / turbine rotor shaft 110 (hereinafter referred to as the “rotor shaft” 110).
[0031] In a non-restrictive embodiment, the GT-System 100 is a 7HA.03 engine commercially available from GE Vernova, Cambridge, MA, USA. The present disclosure is not limited to a specific GT-System 100 and can be implemented in conjunction with other propulsion machines, including, for example, the other HA, F, B, LM, GT, TM, and E-class propulsion machine models from GE Vernova and propulsion machine models from other companies. Furthermore, the teachings of the disclosure are not necessarily applicable only to a GT-System and can be applied to other types of turbomachinery, e.g., steam turbines, jet engines, compressors, etc.
[0032] Fig. Figure 2 shows a cross-sectional view of an illustrative, non-restrictive section of the four-stage turbine 108 S0-S3, which is connected to the GT system 100 in Fig. 1. The four stages are designated S0, S1, S2, and S3. Stage S0 is the first stage and the smallest (radially) of the four stages. Stage S1 is the second stage and the next stage axially. Stage S2 is the third stage and the next stage axially. Stage S3 is the fourth and final stage and the largest (radially). It should be noted that four stages are shown merely as a non-limiting example, and each turbine may have more or fewer than four stages.
[0033] A set of stationary guide vanes or nozzles 112 interacts with a set of rotating blades 114 such that they form each stage S0-S3 of the turbine 108 and define a section of a flow path through the turbine 108. The rotating blades 114 in each set are coupled to a respective rotor wheel 116, which they rotate circumferentially with the rotor shaft 110 ( Fig. 1) couples. That is, a plurality of rotating blades 114 are mechanically coupled to each rotor wheel 116 at circumferential intervals. A static blade section 115 encloses the stationary nozzles 112, which are spaced circumferentially around the rotor shaft 110. Each nozzle 112 can enclose at least one platform 120, 122, which is connected to the air guide vane 130. In the example shown in Fig. 2 The nozzle 112 includes a radially outer platform 120 and a radially inner platform 122. The radially outer end wall 120 couples the nozzle 112 to a housing 124 of the turbine 108.
[0034] During operation, air flows through the compressor 102 and is supplied to the combustion chamber 104 as compressed air. Specifically, the compressed air is supplied to the fuel nozzle assembly 106, which is integrated into the combustion chamber 104. The fuel nozzle assembly 106 is in flow communication with the combustion area 105. The fuel nozzle assembly 106 is also in flow communication with a fuel source (in Fig. (1 not shown) and directs fuel and air to the combustion chamber 105. The combustion chamber 104 ignites and burns the fuel. The combustion chamber 104 is in flow communication with the turbine 108, within which the thermal energy of the gas flow is converted into mechanical rotational energy. The turbine 108 is rotatably coupled to the rotor shaft 110 and drives it. The compressor 102 is also rotatably coupled to the rotor shaft 110. In the illustrative embodiment, there is a plurality of combustion chambers 104 and fuel nozzle assemblies 106. In the following, unless otherwise indicated, only one of each component will be described. At least one end of the rotating rotor shaft 110 can extend axially away from the turbine 108 (or compressor 102) and can be attached to a load or machine (not shown), such as, but not limited to, a generator, a load compressor, and / or another turbine.
[0035] Fig. Figure 3 illustrates a blade 200, which is used as a turbine rotor blade 114 ( Fig. 2) can be used. The shovel 200 is a rotating (dynamic) shovel which, as in Fig. Figure 2 shows that the blade 200 is part of a set of turbine rotor blades distributed circumferentially around a rotor shaft in a stage of a turbine (e.g., turbine 108). That is, when a working fluid (e.g., gas or steam) is guided over the blade's air guide plate during turbine operation, the blade 200 initiates the rotation of a rotor shaft 110 and rotates about an axis defined by the rotor shaft 110. It is understood that the blade 200 is configured to be coupled (mechanically coupled via fasteners, welds, slots / grooves, etc.) to a variety of similar or different blades (e.g., blades 200 or other blades) to form a set of blades in a stage of turbine 108 (e.g., stage S0 in Figure 2). Fig. 2) to form.
[0036] With reference to Fig. 3 The turbine blade 200 can enclose an air guide vane 202, which has an intake side 204 (hidden in this view) and a pressure side 206 opposite the intake side 204. The blade 200 can also include a leading edge 208 extending between the pressure side 206 and the intake side 204, and a trailing edge 210 opposite the leading edge 208 and extending between the pressure side 206 and the intake side 204. The leading edge 208 is defined as the edge or line at which the combustion flow diverges to flow over or past the pressure side 206 or the intake side 204.
[0037] As shown, the blade 200 can also include a platform 212, which is connected at a radial inner end 250 of the air guide vane 202 and at a pointed end 252 at an opposite end of the air guide vane 202. Fig. Figure 3 shows the tip end 252 without tip sheathing. Platform 212 is part of a root 214. The root 214 is in Fig. 3 is illustrated as a "block" for the sake of simplicity in representation and description, but the root 214 can have any suitable configuration to connect with the rotor shaft 110 ( Fig. 1) to be connected. The end wall 212 can be connected to the air guide vane 202 along the intake side 204, the pressure side 206, the trailing edge 210, and the leading edge 208. In various embodiments, the blade 200 includes a fillet 216 near a radially inner end 250 of the air guide vane 202. The fillet 216 connects the air guide vane 202 and the platform 212 (e.g., at a surface 224 of the platform 212). The fillet 216 can include a weld or brazed fillet, which can be formed by conventional MIG welding, TIG welding, brazing, etc. The fillet 216 can include such features as an integral part of the investment casting process or definition. Portions of the root 214 are configured to fit into a matching slot in the rotor shaft 110 ( Fig. 1) fit and align with adjacent components of other blades 200. For this purpose, the platform 212 is provided to be located radially inside the air guide vane 202 and to be designed in a configuration complementary to the rest of the root 214. The air guide vane 202 and the platform 212 enclose an origin 220 at a junction of the leading edge 208 of the air guide vane 202 and the platform 212, i.e., at a junction between the platform 212 and the air guide vane 202.
[0038] Referring again to Fig. 2 and Fig. 3. In various non-restrictive embodiments, the blade 200 can include a first-stage blade (S0), a second-stage blade (S1), a third-stage blade (S2), or a fourth-stage blade (S3). In certain embodiments, the blade 200 is a first-stage blade (S0). In various embodiments, the turbine 108 can include a set of blades 200 in only the first stage (S0), only the second stage (S3), only the third stage (S2), or only the fourth stage (S3) of the turbine 108.
[0039] Fig. Figure 4 shows an axial cross-sectional view of the air guide plate 202 along the view line 4-4 in Fig. 3, and Fig. Figure 5 shows a radial, schematic cross-sectional view of the air guide plate 202 along the view line 5-5 in Fig. 3. Fig. Figure 6 shows an enlarged cross-sectional and perspective view of the air guide plate 202, generally along the view line 6-6 in Fig. 3, of an intake side section including a rib 260 according to embodiments of the disclosure. Fig. Figure 7 shows an enlarged cross-sectional view from top to bottom and Fig. Figure 8 shows an enlarged lateral cross-sectional view of the air guide plate 202 including the rib 260 with a profile according to various embodiments of the disclosure.
[0040] With reference to Fig. 3-5 defines an interior space 262 of the air guide vane 202 within the intake side 204, the pressure side 206, the leading edge 208, and the trailing edge 210. The interior space 262 provides an internal coolant channel 264 that delivers coolant through the air guide vane 202 to cool the air guide vane 202. The coolant (arrows in Fig. 5) can be discharged to the air guide plate 202 in any currently known or subsequently developed manner, e.g. through channels in the root 214 in fluid communication with an outlet of the compressor 102 ( Fig. 1) As in Fig. 5 and Fig. As shown in Figure 8, the interior space 262 and the inner coolant channel 264 can terminate at a tip plate 270, which defines part of the tip 252 of the air guide vane 202. The interior space 262 is divided by any number of ribs 272 into at least two channels 266, 268, of which the rib 260 is one according to embodiments of the disclosure.
[0041] As in Fig. As shown in Figure 5, any number of ribs 272 can extend from the radially inner end 250 of the air guide plate 222 and terminate before the tip plate 270, and any number of ribs 272 can extend from the tip 252 of the air guide plate 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 in one direction and then radially outward in another direction, depending on their position in the air guide plate 202. In particular, various ribs 272, of which rib 260 is one, divide sections of the interior 262, which is defined between the intake 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. Other ribs 272 may define additional internal channels 294.The ribs 272 can define a series of adjacent cooling channels 264 along the intake side 204 and the pressure side 206 as "near-wall" cooling channels. The ends of certain ribs 272 represent problematic stress areas that can negatively affect the service life of the turbine blade 200 (. Fig. 3).
[0042] Fig. Figures 6-8 show section 280 of rib 260 (in Fig. 6-8 highlighted and hereafter referred to as “rib section 280”), which has a shape with a nominal profile that substantially corresponds to the Cartesian coordinate values of X, Y, and Z listed in TABLE I below. Rib section 280 includes a radially outer section of rib 260, which extends radially within a radially outer end 282 ( Fig. 8) is positioned by at least two inner channels 266, 268 formed by the fin 260, i.e., within the top plate 270. Therefore, coolant can flow from one of the wall-adjacent channels 268 via the fin 260 and the fin section 280 into an adjacent central channel 266. Alternatively, coolant can flow from the central channel 266 via the fin 260 and the fin section 280 into the wall-adjacent channel 268.
[0043] In the example shown, the (first) rib 260 extends from a (second) rib 290 to a (third) rib 292 adjacent to an inner surface 296 of the pressure sidewall 298 of the air guide vane 202, and near-wall channels 268 are arranged along the pressure side 206. The near-wall channel 268, bounded by the (first) rib 260, is located at or slightly behind the area with the maximum thickness of the air guide vane 202. The rib 290 and the rib 292 further divide (or contribute to the division) the section of the interior 262 into another inner channel (or other inner channels), e.g. B. 294. For example, the rib 260 with the rib section 280 can have an end edge that is in contact with the second rib 290, which partially defines the central channel 294, and an opposite end edge that is in contact with the third rib 292, which partially defines one of the near-wall cooling channels 268 along the pressure side 206.
[0044] The nominal shape of the rib section 280 is configured to reduce the stresses acting on the rib 260 and to increase the service life of the turbine blade 200 ( Fig. 3) is increased. The rib section 280 can have a profile or shape as defined by the coordinate values. The rib section 280 is in the Fig. 6, Fig. 7 to Fig. Figure 8 is represented by a multitude of points corresponding to the X, Y, and Z coordinate values. Each point can be described by a specific set of X, Y, and Z coordinate values. For example, the coordinates in Table I can be provided to define each point. Note that the number of points shown in the drawings does not necessarily correspond to the values in Table I.
[0045] The Cartesian coordinate values are expressed in normalized or non-dimensional form as values from 0% to 100% (percentages). However, it should be obvious that any or all of the coordinate values could instead be expressed in distance units, as long as the percentages and ratios are maintained. To convert an X, Y, or Z value from TABLE I into a corresponding X, Y, or Z coordinate value in distance units, such as inches or centimeters, the dimensionless X, Y, or Z value given in TABLE I can be multiplied by a profile height H of the air deflector 202 in such distance units. The "air deflector height" H is defined as the radial distance from the origin 220 to a position of the tip 252 above it. Typical heights of the air deflector 202 can range from about 5.0 inches (~12.7 centimeters (cm)) to about 12.0 inches (~30.48 cm).In a particular embodiment of an S0 blade for a high-performance gas turbine engine GE Vernova 7HA.03, the height H of the air guide vane 202 can be approximately 7.89 inches (~20.04 cm).
[0046] By smoothly connecting the X, Y, and Z data points (with lines and / or arcs), a surface profile for rib section 280 can be formed using a curve-fitting technique currently known or subsequently developed, to create a curved surface suitable, for example, for an air deflector. The curve-fitting techniques may include, but are not limited to: extrapolation, interpolation, smoothing, polynomial regression, and / or other mathematical curve-fitting functions. The curve-fitting technique can be performed manually and / or computer-aided, e.g., using statistical software and / or numerical analysis software.
[0047] The values in TABLE I are non-dimensional percentages, generated and expressed to three decimal places, for determining the nominal profile of a rib section 280 under ambient, non-operating, or non-hot conditions and do not take into account coatings or fillets, although embodiments may take other conditions, coatings, and / or fillets into account. To accommodate typical manufacturing tolerances and / or coating thicknesses, ± values may be added to the values listed in TABLE I, particularly the X and Y values contained therein. For example, a tolerance of approximately 10–20 percent of a minimum thickness of the rib section 280 in a direction perpendicular to any surface position along the rib section 280 may define a profile wrap of the rib section 280 for a rib section design at cold or room temperature.In other words, a distance of approximately 10-20 percent of a minimum thickness of the rib section 280 in a direction perpendicular to any surface position thereof can define a range of variation between measured points on an actual rib section 280 and ideal positions of these points, particularly at cold or room temperature, as embodied in the disclosure. The design of the rib section 280, as embodied herein, is robust within this range of variation without impairing its mechanical and aerodynamic functions.
[0048] Likewise, the profile and / or design can be scaled up or down, geometrically, without affecting operation. Such scaling can be achieved by multiplying the normalized / non-dimensional percentage values by a common scaling factor, which may be a larger or smaller number of distance units than originally used for a rib 272 of a given altitude air deflector 202. For example, the non-dimensional percentage values in TABLE I, in particular the X and Y values, could 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 are scalable depending on the same constant or number to provide a further scaled rib section 280.Alternatively, the values could be multiplied by a larger or smaller desired air deflector height H. As indicated herein, the origin 220 of the X, Y, Z coordinate system is the point of connection between the leading edge of the air deflector 202 and the surface 224 of the platform 212.
[0049] If a Z-value is used that is not explicitly listed in TABLE I, the corresponding X and Y values can be identified by extrapolation. For example, if a Z-layer is required at 87%, the X-value at 80% plus 0.7 times (70%) the difference between the X-value at 80% and 90% can be used. Similarly, the Y-value at 80% plus 0.7 times (70%) the difference between the Y-value at 80% and 90% can be used. Other extrapolation methods can also be employed. TABLE I [non-dimensional percentages] N X Y Z 1 0,245 0,177 0,853 2 0,269 0,204 0,911 3 0,258 0,174 0,853 4 0,269 0,167 0,853 5 0,275 0,155 0,854 6 0,275 0,153 0,841 7 0,269 0,164 0,840 8 0,258 0,172 0,839 9 0,245 0,174 0,839 10 0,244 0,172 0,826 11 0,258 0,170 0,826 12 0,269 0,162 0,826 13 0,275 0,151 0,827 14 0,248 0,179 0,864 15 0,243 0,179 0,864 16 0,248 0,183 0,880 17 0,244 0,183 0,881 18 0,249 0,187 0,898 19 0,244 0,187 0,898 20 0,250 0,191 0,915 21 0,245 0,191 0,916 22 0,254 0,190 0,918 23 0,262 0,192 0,918 24 0,267 0,197 0,919 25 0,269 0,205 0,919 26 0,276 0,166 0,920 27 0,281 0,173 0,920 28 0,288 0,177 0,920 29 0,296 0,178 0,920 30 0,310 0,172 0,917 31 0,303 0,175 0,917 32 0,309 0,169 0,898 33 0,302 0,172 0,898 34 0,308 0,165 0,879 35 0,301 0,168 0,879 36 0,307 0,162 0,861 37 0,300 0,164 0,861 38 0,302 0,161 0,849 39 0,288 0,167 0,849 40 0,277 0,176 0,849 41 0,269 0,188 0,849 42 0,268 0,203 0,849 43 0,268 0,199 0,837 44 0,268 0,185 0,837 45 0,276 0,172 0,837 46 0,288 0,164 0,837 47 0,302 0,160 0,837 48 0,302 0,158 0,826 49 0,288 0,163 0,826 50 0,276 0,170 0,826 51 0,269 0,182 0,826 52 0,268 0,196 0,826 53 0,268 0,208 0,859 54 0,268 0,199 0,859 55 0,267 0,212 0,878 56 0,268 0,203 0,878 57 0,268 0,216 0,896 58 0,268 0,206 0,896 59 0,268 0,218 0,915 60 0,268 0,209 0,915 61 0,297 0,177 0,916 62 0,291 0,177 0,916 63 0,286 0,176 0,916 64 0,281 0,173 0,916 65 0,277 0,168 0,917 66 0,276 0,163 0,917 67 0,298 0,174 0,898 68 0,293 0,175 0,898 69 0,287 0,174 0,899 70 0,281 0,171 0,899 71 0,277 0,166 0,900 72 0,275 0,160 0,901 73 0,298 0,170 0,881 74 0,293 0,172 0,881 75 0,287 0,171 0,882 76 0,280 0,168 0,883 77 0,277 0,163 0,884 78 0,275 0,158 0,885 79 0,295 0,168 0,865 80 0,291 0,170 0,868 81 0,285 0,170 0,870 82 0,279 0,166 0,871 83 0,276 0,161 0,871 84 0,275 0,156 0,869 85 0,284 0,172 0,855 86 0,284 0,174 0,859 87 0,280 0,173 0,863 88 0,275 0,169 0,865 89 0,273 0,165 0,862 90 0,272 0,163 0,859 91 0,264 0,172 0,858 92 0,265 0,173 0,861 93 0,269 0,176 0,864 94 0,273 0,180 0,862 95 0,274 0,183 0,858 96 0,274 0,183 0,854 97 0,269 0,194 0,862 98 0,270 0,190 0,865 99 0,269 0,185 0,868 100 0,265 0,181 0,869 101 0,259 0,178 0,868 102 0,255 0,178 0,866 103 0,253 0,182 0,882 104 0,258 0,182 0,882 105 0,264 0,184 0,882 106 0,268 0,189 0,881 107 0,270 0,194 0,880 108 0,269 0,199 0,879 109 0,269 0,202 0,895 110 0,269 0,197 0,896 111 0,267 0,192 0,897 112 0,263 0,188 0,898 113 0,258 0,186 0,899 114 0,253 0,186 0,899 115 0,253 0,190 0,914 116 0,258 0,190 0,915 117 0,263 0,191 0,915 118 0,267 0,195 0,914 119 0,269 0,200 0,913
[0050] The revealed shape of the rib section 280 provides a unique profile to achieve optimized stress relief at the rib 260, so that the specific performance targets of the machine in which the rotating blade 200 is used, and possibly other machines, are met.
[0051] Embodiments of the disclosure also include a rotor blade section for a turbine, e.g. a stage, including a set of rotating blades 200 including at least one blade 200 having a rib 260 with a rib section 280, as described herein.
[0052] Embodiments of the disclosure also include a turbine 108 including a plurality of turbine blades 200, as described herein.
[0053] Embodiments of the disclosure provide various technical and commercial advantages, examples of which are discussed herein. The rib described herein provides discrete areas of varying thickness and optimized rounding to reduce stress near bends between channels on both sides of the rib. In particular, along a bend therein, the rib incorporates a complex fillet shape that separates two internal channels, thereby reducing stress in the air guide vane and increasing the service life of the turbine blade, rotor blade section, and / or the turbine in which it is used.
[0054] While the devices and apparatus of the present disclosure are intended for use in a high-performance turbomachine employed in a power generation system, the rib 260 of the present disclosure can also be used for turbine blades 200 for other systems not described here, which can benefit from the increased stress relief associated with the improved profile of the rib section 280.
[0055] An approximation language, such as that used throughout this description and the claims, may be applied to modify any quantitative representation that could permissibly vary without altering the fundamental function to which it relates. Accordingly, a value modified by a term or terms such as "approximately," "approximately," and "essentially" is not limited to the precisely specified value. At least in some cases, the approximation formulation may correspond to the accuracy of an instrument used to measure the value. Here, and throughout this patent specification and the claims, range limitations may be combined and / or interchanged; such ranges are identified and include all subranges contained therein unless context or formulation indicates otherwise.“Approximately”, relative to a specific value of a range, applies to both end values and, unless otherwise stated, may be + / - 10% of the stated value(s), depending on the accuracy of the device measuring the value.
[0056] The corresponding structures, materials, actions, and equivalents of all means or stages plus functional elements in the following claims are intended to include any structure, material, or action for performing the function in combination with other claimed elements, as specifically claimed. The description of the present disclosure has been provided for illustrative and descriptive purposes but is not intended to be exhaustive or limited to the disclosure as disclosed. To those skilled in the art, many modifications and variations are apparent without departing from the scope of protection and spirit of the disclosure.The embodiment was chosen and described to best explain the principles of the disclosure and its practical application, and to enable other skilled persons to understand the disclosure so that various modifications suitable for a particular use may further be considered.
[0057] Further aspects are provided by the subject of the following paragraphs: 1. Turbine blade, comprising: an air guide plate which has: an intake side, a pressure side opposite the intake side, a front edge, a rear edge and a first rib, which forms a section of a between the intake and The printed side and the front and rear edges of the defined interior space are divided into at least two inner channels; and a platform that is aligned with the air guide plate along the intake and pressure side and the front and rear edges are connected, with the air guide plate and the platform including an origin at a connection point of the front edge of the air guide plate and the platform; wherein a section of the first rib has a shape with a nominal profile which substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin by multiplying the values by a height of the air guide expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the section of the first rib. 2. Turbine blade according to any of the preceding paragraphs, wherein the turbine blade includes a first-stage blade. 3. Turbine blade according to any of the preceding paragraphs, further comprising a groove connecting a surface of the platform to the air guide plate. 4. Turbine blade according to any of the preceding paragraphs, wherein the section of the first rib includes a radially outer section of the first rib which is positioned radially inside a radially outer end of the at least two inner channels. 5. Turbine blade according to any of the preceding paragraphs, wherein the first rib extends from a second rib to a third rib adjacent to an inner surface of a pressure side wall of the air guide plate, wherein the second rib and the third rib further subdivide the section of the interior into the at least two inner channels. 6. Rotor blade section for a turbine, wherein the rotor blade section comprises: a set of rotating blades, wherein the set of rotating blades includes at least one blade which has: an air guide plate comprising: an intake side, a pressure side opposite the intake side, a leading edge, a trailing edge and a first rib within an interior space defined between the intake and pressure sides and the leading and trailing edges, wherein the first rib divides the interior space into at least two internal channels; and a platform that is aligned with the air guide plate along the intake and pressure side and the front and rear edges are connected, with the air guide plate and the platform including an origin at a connection point of the front edge of the air guide plate and the platform; wherein a section of the first rib has a shape with a nominal profile which substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin by multiplying the values by a height of the air guide expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the section of the first rib. 7. Rotor blade section according to one of the preceding paragraphs, further comprising a groove connecting a surface of the platform to the air guide plate. 8. Rotor blade section according to any of the preceding paragraphs, wherein the rotor blade section is a first-stage blade section. 9. Rotor blade section according to any of the preceding paragraphs, wherein the first rib section includes a radially outer section of the first rib which is positioned radially inside a radially outer end of the at least two inner channels. 10. Rotor blade section according to one of the preceding paragraphs, wherein the first rib extends from a second rib to a third rib adjacent to an inner surface of a pressure sidewall of the air guide vane, wherein the second rib and the third rib further subdivide the section of the interior into the at least two inner channels. 11. Turbine comprising a plurality of turbine blades in a rotor blade section, wherein at least one of the plurality of turbine blades comprises: an air guide plate which has: an intake side, a pressure side opposite the intake side, a front edge, a rear edge and a first rib, which forms a section of a between the intake and The printed side and the front and rear edges of the defined interior space are divided into at least two inner channels; and a platform that is aligned with the air guide plate along the intake and pressure side and the front and rear edges are connected, with the air guide plate and the platform including an origin at a connection point of the front edge of the air guide plate and the platform; wherein a section of the first rib has a shape with a nominal profile which substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin by multiplying the values by a height of the air guide expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the section of the first rib. 12. Turbine according to any of the preceding paragraphs, further comprising a groove connecting a surface of the platform to the air guide plate. 13. Turbine according to any of the preceding paragraphs, wherein each turbine blade includes a first-stage blade. 14. The turbine according to any of the preceding paragraphs, wherein the section of the first rib includes a radially outer section of the first rib which is positioned radially inside a radially outer end of the at least two inner channels. 15. Turbine according to any of the preceding paragraphs, wherein the first rib extends from a second rib to a third rib adjacent to an inner surface of a pressure side wall of the air guide plate, wherein the second rib and the third rib further subdivide the section of the interior into the at least two inner channels.
Claims
[1] Turbine blade (200), comprising: an air guide plate (202) comprising: an intake side (204), a pressure side (206) opposite the intake side (204), a leading edge (208), a trailing edge (210) and a first rib (260) forming a section of a space between the intake side (204) and the pressure side (206) and The interior space (262) defined by the leading edge (208) and the trailing edge (210) is subdivided into at least two inner channels (266, 268); and a platform (212) which is connected to the air guide plate (202) along the intake side (204) and the pressure side (206) and the leading edge (208) and the trailing edge (210), wherein the air guide plate (202) and the platform (212) include an origin (220) at a connection point of the leading edge (208) of the air guide plate (202) and the platform (212); wherein a section of the first rib (260) has a shape with a nominal profile that substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin (220) by multiplying the values by a height of the air guide vane (202) expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the first rib section (260). [2] Turbine blade (200) according to claim 1, wherein the turbine blade (200) includes a first stage blade. [3] Turbine blade (200) according to one of claims 1 to 2, further comprising a groove (216) connecting a surface of the platform (212) with the air guide plate (202). [4] Turbine blade (200) according to claim 1, wherein the section of the first rib (260) includes a radially outer section of the first rib (260) which is positioned radially inside a radially outer end of the at least two inner channels (266, 268). [5] Turbine blade (200) according to claim 1, wherein the first rib (260) extends from a second rib (290) to a third rib (292) adjacent to an inner surface (296) of a pressure side wall (298) of the air guide plate (202), wherein the second rib (290) and the third rib (292) further subdivide the section of the interior (262) into the at least two inner channels (266, 268). [6] Rotor blade section for a turbine, wherein the rotor blade section comprises: a set of rotating blades (200), wherein the set of rotating blades (200) includes at least one blade (200) which has: an air guide plate (202) comprising: an intake side (204), a pressure side (206) opposite the intake side (204), a leading edge (208), a trailing edge (210) and a first rib (260) within an interior space (262) located between the intake side (204) and the pressure side (206) and the leading edge (208) and the trailing edge (210) is defined, wherein the first rib (260) divides the interior (262) into at least two inner channels (266, 268); and a platform (212) which is connected to the air guide plate (202) along the intake side (204) and the pressure side (206) and the leading edge (208) and the trailing edge (210), wherein the air guide plate (202) and the platform (212) have an origin (220) at a connection point of the leading edge (208) of the air guide plate (202) and include the platform (212); wherein a section of the first rib (260) has a shape with a nominal profile which substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin (220) by multiplying the values by a height of the air guide vane (202) expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the section of the first rib (260). [7] Rotor blade section according to claim 6, further comprising a groove (216) connecting a surface of the platform (212) with the air guide plate (202). [8] Rotor blade section according to one of claims 6 to 7, wherein the rotor blade section is a blade section of the first stage. [9] Rotor blade section according to one of claims 6 to 8, wherein the section of the first rib (260) includes a radially outer section of the first rib (206) which is positioned radially inside a radially outer end of the at least two inner channels (266, 268). [10] Rotor blade section according to one of claims 6 to 9, wherein the first rib (260) extends from a second rib (290) to a third rib (292) adjacent to an inner surface (296) of a pressure side wall (298) of the air guide plate (202), wherein the second rib (290) and the third rib (292) further subdivide the section of the interior (262) into the at least two inner channels (266, 268). [11] Turbine (108) comprising a plurality of turbine blades in a rotor blade section, wherein at least one of the plurality of turbine blades comprises: an air guide plate (202) comprising: an intake side (204), a pressure side (206) opposite the intake side (204), a leading edge (208), a trailing edge (210) and a first rib (260) forming a section of a space between the intake side (204) and the pressure side (206) and The interior space (262) defined by the leading edge (208) and the trailing edge (210) is subdivided into at least two inner channels (266, 268); and a platform (212) which is connected to the air guide plate (202) along the intake side (204) and the pressure side (206) and the leading edge (208) and the trailing edge (210), wherein the air guide plate (202) and the platform (212) include an origin (220) at a connection point of the leading edge (208) of the air guide plate (202) and the platform (212); wherein a section of the first rib (260) has a shape with a nominal profile that substantially corresponds to the Cartesian coordinate values of X, Y and Z listed in TABLE I, wherein the Cartesian coordinate values are dimensionless values from 0% to 100% which can be converted into distances from the origin (220) by multiplying the values by a height of the air guide vane (202) expressed in distance units, and wherein the Cartesian coordinate values of X, Y and Z are connected by smooth, continuous arcs to define the nominal profile of the first rib section (260). [12] Turbine according to claim 11, further comprising a groove (216) connecting a surface of the platform (212) to the air guide plate (202). [13] Turbine according to one of claims 11 to 12, wherein each turbine blade includes a blade of the first stage. [14] Turbine according to one of claims 11 to 13, wherein the section of the first rib (260) includes a radially outer section of the first rib (260) which is positioned radially inside a radially outer end of the at least two inner channels (266, 268). [15] Turbine according to one of claims 11 to 14, wherein the first rib (260) extends from a second rib (290) to a third rib (292) adjacent to an inner surface (296) of a pressure side wall (298) of the air guide plate (202), wherein the second rib (290) and the third rib (292) further subdivide the section of the interior (262) into the at least two inner channels (266, 268).