Turbine blade tip shroud surface profiles

Description

FIELD OF THE DISCLOSURE

The subject matter disclosed herein relates to turbomachines. More particularly, the subject matter disclosed herein relates to turbine blade tip shroud surface profiles.

BACKGROUND OF THE DISCLOSURE

Some jet aircraft and simple or combined cycle power plant systems employ turbines, or so-called turbomachines, in their configuration and operation. Some of these turbines employ airfoils (e.g., turbine nozzles, blades, airfoils, etc.), which during operation are exposed to fluid flows at high temperatures and pressures. These airfoils are configured to aerodynamically interact with the fluid flows and to generate energy from these fluid flows as part of power generation. For example, the airfoils may be used to create thrust, to convert kinetic energy to mechanical energy, and/or to convert thermal energy to mechanical energy. As a result of this interaction and conversion, the aerodynamic characteristics of these airfoils may cause losses in system and turbine operation, performance, thrust, efficiency, reliability, and power.

In addition, during operation, tip shrouds on the radially outer end of the airfoils interact with stationary components to direct hot gases toward the airfoils. Due to this interaction and conversion, the aerodynamic characteristics of these tip shrouds may negatively affect system and turbine operation, performance, thrust, efficiency, reliability, and power.

BRIEF DESCRIPTION OF THE DISCLOSURE

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

An aspect of the disclosure provides a turbine blade tip shroud, comprising: a pair of opposed, axially extending wings configured to couple to an airfoil at a radial outer end of the airfoil, the airfoil having a pressure side and a suction side opposing the pressure side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a tip rail extending radially from the pair of opposed, axially extending wings, the tip rail having a downstream side, an upstream side opposing the downstream side and a forward-most and radially outermost origin, and wherein the upstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, and Z set forth in TABLE I and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by a minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail upstream side profile.

Another aspect of the disclosure includes any of the preceding aspects, and the airfoil is part of a third stage turbine blade.

Another aspect of the disclosure includes any of the preceding aspects, and the downstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, and Z set forth in TABLE II and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail downstream side profile.

Another aspect of the disclosure includes any of the preceding aspects, and further comprises a trailing Z-notch surface having a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE IV and originating at a forward-most and radially outermost origin of the tip rail, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a trailing Z-notch surface profile, wherein the thickness of the trailing Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value.

Another aspect of the disclosure includes any of the preceding aspects, and a radially outer surface of the wing on the upstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE V and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface profile.

Another aspect of the disclosure includes any of the preceding aspects, and a radially outer surface of the wing on the downstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE VI and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form a downstream side radial outer surface profile.

Another aspect of the disclosure includes a turbine blade tip shroud, comprising: a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end of the airfoil, the airfoil having a suction side and a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a tip rail extending radially from the pair of opposed, axially extending wings, the tip rail having a downstream side, an upstream side opposing the downstream side, and a forward-most and radially outermost origin, and a leading Z-notch surface having a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE III and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a leading Z-notch surface profile, wherein the thickness of the leading Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value.

Another aspect of the disclosure includes any of the preceding aspects, and the turbine blade includes a third stage blade.

Another aspect of the disclosure relates to a turbine blade tip shroud, comprising: a pair of opposed, axially extending wings configured to couple to an airfoil at a radial outer end of the airfoil, the airfoil having a pressure side and a suction side opposing the pressure side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a tip rail extending radially from the pair of opposed, axially extending wings, the tip rail having a downstream side and an upstream side opposing the downstream side and a forward-most and radially outermost origin; and a radially outer surface of the wing on the upstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE V and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by a minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface profile.

Another aspect of the disclosure includes any of the preceding aspects, and the airfoil is part of a third stage turbine blade.

Another aspect of the disclosure includes any of the preceding aspects, and the upstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, and Z set forth in TABLE I and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent expressed in units of distance, and wherein X, Y, and Z values are connected by lines to define a tip rail upstream side profile; and wherein the downstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, and Z set forth in TABLE II and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail downstream side profile.

Another aspect of the disclosure includes any of the preceding aspects, and further comprises a leading Z-notch surface having a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE III and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein X and Y values are joined smoothly with one another to form a leading Z-notch surface profile, wherein the thickness of the leading Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value; and further comprising a trailing Z-notch surface having a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE IV and originating at a forward-most and radially outermost origin of the tip rail, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a trailing Z-notch surface profile, wherein the thickness of the trailing Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value.

A final aspect of the disclosure includes a turbine blade tip shroud, comprising: a pair of opposed, axially extending wings configured to couple to an airfoil at a radial outer end of the airfoil, the airfoil having a pressure side and a suction side opposing the pressure side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a tip rail extending radially from the pair of opposed, axially extending wings, the tip rail having a downstream side and an upstream side opposing the downstream side, the tip rail having a forward-most and radially outermost origin; an upstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, and Z set forth in TABLE I and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by a minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail upstream side profile; a leading Z-notch surface having a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE III and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a leading Z-notch surface profile, wherein the thickness of the leading Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value; and a radially outer surface of the wing on the upstream side of the tip rail has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE V and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface profile.

Two or more aspects described in this disclosure, including those described in this summary section, may be combined to form implementations not specifically described herein.

The details of one or more implementations are set forth in the accompanying drawings and the description below. Other features, objects and advantages will be apparent from the description and drawings, and from the claims.

BRIEF DESCRIPTION OF THE DRAWINGS

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

FIG. 1 shows a schematic view of an illustrative turbomachine;

FIG. 2 shows a cross-sectional view of an illustrative gas turbine assembly with four stages that may be used with the turbomachine in FIG. 1;

FIG. 3 shows a schematic three-dimensional view of an illustrative turbine blade including a tip shroud on a radial outer end of an airfoil, according to various embodiments of the disclosure;

FIG. 4 shows a plan view of a tip shroud, according to various embodiments of the disclosure;

FIG. 5 shows an upstream side view of a tip shroud including points of an upstream tip rail surface profile, according to various embodiments of the disclosure;

FIG. 6 shows a downstream side view of a tip shroud including points of a downstream tip rail surface profile, according to various embodiments of the disclosure;

FIG. 7 shows a rearward perspective view of a tip shroud including points of a leading Z-notch surface profile, according to embodiments of the disclosure;

FIG. 8 shows a forward perspective view of a tip shroud including points of a trailing Z-notch surface profile, according to various embodiments of the disclosure;

FIG. 9 shows a rearward perspective view of a tip shroud including points of a radially outer wing upstream surface profile, according to various embodiments of the disclosure; and

FIG. 10 shows a side perspective view of the tip shroud including points of a radially outer wing downstream surface profile, according to various embodiments of the disclosure.

It is noted that the drawings of the disclosure are not necessarily to scale. The drawings are intended to depict only typical aspects of the disclosure and therefore should not be considered as limiting the scope of the disclosure. In the drawings, like numbering represents like elements between the drawings.

DETAILED DESCRIPTION OF THE DISCLOSURE

As an initial matter, in order to clearly describe the current technology, it will become necessary to select certain terminology when referring to and describing relevant machine components within a turbomachine. To the extent possible, common industry terminology will be used and employed in a manner consistent with its accepted meaning. Unless otherwise stated, such terminology should be given a broad interpretation consistent with the context of the present application and the scope of the appended claims. Those of ordinary skill in the art will appreciate that often a particular component may be referred to using several different or overlapping terms. What may be described herein as being a single part may include and be referenced in another context as consisting of multiple components. Alternatively, what may be described herein as including multiple components may be referred to elsewhere as a single part.

In addition, several descriptive terms may be used regularly herein, and it should prove helpful to define these terms at the onset of this section. These terms and their definitions, unless stated otherwise, are as follows. As used herein, “downstream” and “upstream” are terms that indicate a direction relative to the flow of a fluid, such as the working fluid through the turbine engine or, for example, the flow of air through the combustor or coolant through one of the turbine's component systems. The term “downstream” corresponds to the direction of flow of the fluid, and the term “upstream” refers to the direction opposite to the flow. The terms “forward” and “aft,” without any further specificity, refer to directions, with “forward” referring to the front or compressor end of the engine, and “aft” referring to the rearward or turbine end of the engine.

It is often required to describe parts that are disposed at differing radial positions with regard to a center axis. The term “radial” refers to movement or position perpendicular to an axis. For example, if a first component resides closer to the axis than a second component, it will be stated herein that the first component is “radially inward” or “inboard” of the second component. If, on the other hand, the first component resides further from the axis than the second component, it may be stated herein that the first component is “radially outward” or “outboard” of the second component. The term “axial” refers to movement or position parallel to an axis A, e.g., rotor shaft 110. Finally, the term “circumferential” refers to movement or position around an axis. It will be appreciated that such terms may be applied in relation to the center axis of the turbine.

In addition, several descriptive terms may be used regularly herein, as described below. The terms “first”, “second”, and “third” may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the 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 the terms “comprises” and/or “comprising,” when used in this specification, specify the presence of stated features, integers, steps, operations, elements, and/or components but do not preclude 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 subsequently described event or circumstance may or may not occur and that the description includes instances where the event occurs and instances where it does not.

Where an element or layer is referred to as being “on,” “engaged to,” “connected to,” or “coupled to” another element or layer, it may be directly on, engaged to, connected to, or coupled to the other element or layer, or intervening elements or layers may be present. In contrast, when an element is referred to as being “directly on,” “directly engaged to,” “directly connected to,” or “directly coupled to” another element or layer, there may be no intervening elements or layers present. Other words used to describe the relationship between elements should be interpreted in a like fashion (e.g., “between” versus “directly between,” “adjacent” versus “directly adjacent,” etc.). As used herein, the term “and/or” includes any and all combinations of one or more of the associated listed items.

Various aspects of the disclosure are directed toward surface profiles of a tip shroud of turbine rotor blades that rotate (hereinafter, “blade” or “turbine blade”). Embodiments of the tip shroud include a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end of the airfoil. The airfoil has a suction side and a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side. Generally, the pressure side faces upstream, and the suction side faces downstream.

The tip shrouds also include a tip rail extending radially from the pair of opposed, axially extending wings. The tip rail has a downstream side and an upstream side opposing the downstream side. The tip rail also includes a forward-most and radially outermost origin that acts as a reference point or origin for the surface profiles, as described herein. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading and/or trailing Z-notch of the tip shroud, and/or an upstream and/or downstream side radially outer surface of a wing of the tip shroud. Any combination of the six tip shroud surface profiles described herein in TABLES I-VI may be used in the present tip shroud, according to one or more aspects of the disclosure.

The surface profiles are stated as shapes having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z, and perhaps a thickness, set forth in a respective table. The Cartesian coordinates originate at the forward-most and radially outermost origin of the tip rail. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a particular normalizing parameter value expressed in units of distance. That is, the coordinate values in the tables are percentages of the normalized parameter, so the multiplication of the actual, desired distance of the normalized parameter renders the actual coordinates of the surface profile for a tip shroud having that actual, desired distance of the normalized parameter.

As will be described further herein, the normalizing parameter may vary depending on the particular surface profile. For purposes of this disclosure, the normalizing parameter may be a minimum tip rail X-wise extent 270 (FIG. 4) of tip rail 250. The actual X values of the tip rail surface profile can be rendered by multiplying values in the particular table by the actual, desired minimum tip rail X-wise extent 270 (e.g., 2.2 centimeters), as the case may be. In any event, the X and Y values, and Z values where provided, are connected by lines and/or arcs to define smooth surface profiles.

Referring to the drawings, FIG. 1 is a schematic view of an illustrative turbomachine 90 in the form of a combustion turbine or gas turbine (GT) system 100 (hereinafter “GT system 100”). GT system 100 includes a compressor 102 and a combustor 104. Combustor 104 includes a combustion region 105 and a fuel nozzle assembly 106. GT system 100 also includes a turbine 108 and a common compressor/turbine rotor shaft 110 (hereinafter referred to as “rotor shaft 110”). In one non-limiting embodiment, GT system 100 may be a 9HA.01 or 9HA.02 engine, commercially available from General Electric Company, Greenville, S.C. The present disclosure is not limited to any one particular GT system and may be implemented in connection with other engines including, for example, other HA, F, B, LM, GT, TM and E-class engine models of General Electric Company, and engine models of other companies. Further, the teachings of the disclosure are not necessarily applicable to only a GT system and may be applied to other types of turbomachines, e.g., steam turbines, jet engines, compressors, etc.

FIG. 2 shows a cross-section view of an illustrative portion of turbine 108 with four stages L0-L3 that may be used with GT system 100 in FIG. 1. The four stages are referred to as L0, L1, L2, and L3. Stage L0 is the first stage and is the smallest (in a radial direction) of the four stages. Stage L1 is the second stage and is the next stage in an axial direction (i.e., downstream of Stage L0). Stage L2 is the third stage and is the next stage in an axial direction (i.e., downstream of Stage L1). Stage L3 is the fourth, last stage (downstream of Stage L2) and is the largest (in a radial direction). It is to be understood that four stages are shown as one non-limiting example only, and each turbine may have more or less than four stages.

A set of stationary vanes or nozzles 112 cooperate with a set of rotating blades 114 to form each stage L0-L3 of turbine 108 and to define a portion of a flow path through turbine 108. Rotating blades 114 in each set are coupled to a respective rotor wheel 116 that couples them circumferentially to rotor shaft 110. That is, a plurality of rotating blades 114 is mechanically coupled in a circumferentially spaced manner to each rotor wheel 116. A static blade section 115 includes stationary nozzles 112 circumferentially spaced around rotor shaft 110. Each nozzle 112 may include at least one endwall (or platform) 120, 122 connected with airfoil 130. In the example shown, nozzle 112 includes a radially outer endwall 120 and a radially inner endwall 122. Radially outer endwall 120 couples nozzle 112 to a casing 124 of turbine 108.

In operation, air flows through compressor 102, and compressed air is supplied to combustor 104. Specifically, the compressed air is supplied to fuel nozzle assembly 106 that is integral to combustor 104. Fuel nozzle assembly 106 is in flow communication with combustion region 105. Fuel nozzle assembly 106 is also in flow communication with a fuel source (not shown in FIG. 1) and channels fuel and air to combustion region 105. Combustor 104 ignites and combusts fuel. Combustor 104 is in flow communication with turbine 108 within which gas stream thermal energy is converted to mechanical rotational energy. Turbine 108 is rotatably coupled to and drives rotor shaft 110. Compressor 102 may also be rotatably coupled to rotor shaft 110. In the illustrative embodiment, there are several combustors 104 and fuel nozzle assemblies 106. In the following discussion, unless otherwise indicated, only one of each component will be discussed. At least one end of rotating rotor shaft 110 may extend axially away from turbine 108 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.

FIG. 3 shows an enlarged perspective view of an illustrative turbine rotor blade 114 in detail as a blade 200. For purposes of description, a legend may be provided in the drawings in which the X-axis extends generally axially (i.e., along axis A of rotor shaft 110 (FIG. 1)), the Y-axis extends generally perpendicular to axis A of rotor shaft 110 (FIG. 1) (indicating a circumferential plane), and the Z-axis extends radially, relative to an axis A of rotor shaft 110 (FIG. 1). The Z-axis is perpendicular to both the X-axis and the Y-axis. Relative to FIG. 3, the legend arrowheads' directions show the direction of positive coordinate values.

Blade 200 is a rotatable (dynamic) blade, which is part of the set of turbine rotor blades 114 circumferentially dispersed about rotor shaft 110 (FIG. 1) in a stage of a turbine (e.g., turbine 108). That is, during operation of a turbine, as a working fluid (e.g., gas or steam) is directed across the blade's airfoil, blade 200 will initiate rotation of a rotor shaft (e.g., rotor shaft 110) and rotate about axis A defined by rotor shaft 110. It is understood that blade 200 is configured to couple (mechanically couple via fasteners, welds, slot/grooves, etc.) with a plurality of similar or distinct blades (e.g., blades 200 or other blades) to form a set of blades in a stage of the turbine. Referring to FIG. 2, in various non-limiting embodiments, blade 200 can include a first stage (L0) blade, second stage (L1) blade, third stage (L2) blade, or fourth stage (L3) blade. In particular embodiments, blade 200 is a third stage (L2) blade. In various embodiments, turbine 108 can include a set of blades 200 in only the first stage (L0) of turbine 108, or in only second stage (L1), or in only third stage (L2), or in only fourth stage (L3) of turbine 108.

Returning to FIG. 3, blade 200 can include an airfoil 202 having a pressure side 204 (obstructed in this view) and a suction side 206 opposing pressure side 204. Blade 200 can also include a leading edge 208 spanning between pressure side 204 and suction side 206, and a trailing edge 210 opposing leading edge 208 and spanning between pressure side 204 and suction side 206. As noted, pressure side 204 of airfoil 202 generally faces upstream, and suction side 206 generally faces downstream.

As shown, blade 200 can also include airfoil 202 that extends from a root end 213 to a radial outer end 222. More particularly, blade 200 includes airfoil 202 coupled to a platform 212 at root end 213 and coupled to a turbine blade tip shroud 220 (hereinafter “tip shroud 220”) on a tip end or radial outer end 222 thereof. Root end 213 is illustrated as including a dovetail 224 in FIG. 3, but root end 213 can have any suitable configuration to connect to rotor shaft 110. Root end 213 can be connected, via platform 212, with airfoil 202 along pressure side 204, suction side 206, leading edge 208, and trailing edge 210.

In various embodiments, blade 200 includes a fillet 214 proximate a radially inner end 226 of airfoil 202, fillet 214 connecting airfoil 202 and platform 212. Fillet 214 can include a weld or braze fillet, which may be formed via conventional metal inert gas (MIG) welding, tungsten inert gas (TIG) welding, brazing, etc. Fillet 214 can include such forms as integral to the investment casting process or definition. Root end 213 is configured to fit into a mating slot (e.g., dovetail slot) in the turbine rotor shaft (e.g., rotor shaft 110) and to mate with adjacent components of other blades 200. Root end 213 is intended to be located radially inboard of airfoil 202 and to be formed in any complementary configuration to the rotor shaft.

Tip shroud 220 can be connected with airfoil 202 along pressure side 204, suction side 206, leading edge 208, and trailing edge 210. In various embodiments, blade 200 includes a fillet 228 proximate radially outer end 222 of airfoil 202. Fillet 228 may connect airfoil 202 and tip shroud 220. Fillet 228 can include a weld or braze fillet, which may be formed via conventional MIG welding, TIG welding, brazing, etc. Fillet 228 can include such forms as integral to the investment casting process or definition. In certain embodiments, fillets 214 and/or fillet 228 can be shaped to enhance aerodynamic efficiencies and to provide parts of certain surface profiles as described herein.

FIG. 4 shows a plan view of tip shroud 220, according to embodiments of the disclosure. FIG. 5 shows an upstream side perspective view of tip shroud 220 including points of an upstream tip rail surface profile, according to various embodiments of the disclosure; and FIG. 6 shows a downstream side view of a tip shroud including points of a downstream tip rail surface profile, according to various embodiments of the disclosure. FIG. 7 shows a rearward perspective view of an upstream side 252 of a tip rail 250 showing points of a leading edge Z-notch surface profile; and FIG. 8 shows a forward perspective view of a downstream side 254 of tip rail 250 showing points of a trailing edge Z-notch surface profile. FIG. 9 shows a rearward perspective view of an upstream side 252 of tip shroud 220 showing points of an upstream side, radial outer surface profile, and FIG. 10 shows a side perspective view of a downstream side 254 of tip shroud 220 showing points of a downstream side, radial outer surface profile. Data points illustrated in the drawings, e.g., FIGS. 4-10, are schematically represented, and may not match data points in the tables, described hereafter.

With reference to FIGS. 3-10 collectively, tip shroud 220 may include a pair of opposed, axially extending wings 230 configured to couple to airfoil 202 at radially outer end 222 of airfoil 202 (e.g., via fillet 228). More particularly, as shown best in FIGS. 4-8, tip shroud 220 may include an upstream side wing 232 and a downstream side wing 234. Upstream side wing 232 extends generally circumferentially away from tip rail 250 over pressure side 204 of airfoil 202, and downstream side wing 234 extends generally circumferentially away from tip rail 250 over suction side 206 of airfoil 202. Upstream side wing 232 includes a radial outer surface 236 facing generally radially outward from axis A of rotor shaft 110 (FIG. 1), and a radially inner surface 238 facing generally radially inward toward axis A of rotor shaft 110 (FIG. 1). Similarly, downstream side wing 234 includes a radial outer surface 240 facing generally radially outward from axis A of rotor shaft 110 (FIG. 1), and a radially inner surface 242 facing generally radially inward toward axis A of rotor shaft 110 (FIG. 1).

Tip shroud 220 also includes tip rail 250 extending radially from the pair of opposed, axially extending wings 230. Tip rail 250 has an upstream side 252 and a downstream side 254 opposing upstream side 252. Upstream side 252 of tip rail 250 faces generally circumferentially towards pressure side 204 of airfoil 202 and melds smoothly according to the surface profiles described herein with radial outer surface 236 of upstream side wing 232. Similarly, downstream side 254 of tip rail 250 faces generally circumferentially towards suction side 206 of airfoil 202 and melds smoothly according to the surface profiles described herein with radial outer surface 240 of downstream side wing 234. As shown in FIGS. 4-7 and 9, tip rail 250 includes a forward-most and radially outermost origin (point) 260 at an end thereof. (As shown for reference purposes only in FIGS. 4-6, 8 and 10, tip rail 250 may also include a rearward-most and radially outermost origin (point) 262 at an opposing end thereof). Forward-most and radially outermost origin 260 may act as an origin for certain surface profiles described herein.

FIG. 4 also shows a normalization parameter that may be used to make Cartesian coordinate values for the various surface profiles of tip shroud 220 non-denominational and scalable (and vice versa, make non-denominational Cartesian coordinate values actual coordinate values of a tip shroud). As shown in FIG. 4, a “minimum tip rail X-wise extent” 270 is a minimum distance between tip rail upstream side 252 and tip rail downstream side 254 extending in the X-direction, i.e., parallel to axis A of rotor shaft 110 (FIG. 1) along the X-axis. While shown at a particular location, it is recognized that minimum tip rail X-wise extent 270 can be anywhere along tip rail 250 that includes upstream side 252 and downstream side 254, i.e., it excludes the angled ends of tip rail 250.

Referring to FIGS. 5-10, various surface profiles of tip shroud 220 according to embodiments of the disclosure will now be described. The surface profiles are each identified in the form of X, Y, Z coordinates, and perhaps a thickness, listed in a number of tables, i.e., TABLES I-VI. The X, Y, and Z coordinate values and the thickness values in TABLES I-VI have been expressed in normalized or non-dimensionalized form in values of from 0% to 100%, but it should be apparent that any or all of the values could instead be expressed in distance units so long as the percentages and proportions are maintained. To convert X, Y, Z or thickness values of TABLE I-VI to actual respective X, Y or Z coordinate values from the relevant origin (e.g., origin 260 on tip rail 250) and thicknesses at respective data points, in units of distance, such as inches or meters, the non-dimensional values given in TABLE I-VI can be multiplied by a normalization parameter value. As noted, the normalization parameter used herein may be minimum tip rail X-wise extent 270. In any event, by connecting the X, Y and/or Z values with smooth continuing arcs or lines, depending on the surface profile, each surface profile can be ascertained, thus forming the various nominal tip shroud surface profiles.

The values in TABLES I-VI are non-dimensionalized values generated and shown to three decimal places for determining the various nominal surface profiles of tip shroud 220 at ambient, non-operating, or non-hot conditions, and do not take any coatings into account, though embodiments could account for other conditions and/or coatings. To allow for typical manufacturing tolerances and/or coating thicknesses, ±values can be added to the values listed in TABLE I-VI. In one embodiment, a tolerance of about 10-20 percent can be applied. For example, a tolerance of about 5-10 percent applied to a thickness of a Z-notch surface profile in a direction normal to any surface location along the relevant tip shroud radial outer surface can define a Z-notch thickness range at cold or room temperature. In other words, a distance of about 5-10 percent of a thickness of the relevant Z-notch edge can define a range of variation between measured points on an actual tip shroud surface and ideal positions of those points, particularly at a cold or room temperature, as embodied by the disclosure. The tip shroud surface profile configurations, as embodied herein, are robust to this range of variation without impairment of mechanical and aerodynamic functions.

The surface profiles can be scaled larger or smaller, such as geometrically, without impairment of operation. Such scaling can be facilitated by multiplying the normalized/non-dimensionalized values by a common scaling factor (i.e., the actual, desired distance of the normalization parameter), which may be a larger or smaller number of distance units than might have originally been used for a tip shroud, e.g., of a given minimum tip rail X-wise extent, as appropriate. For example, the non-dimensionalized values in TABLE I, particularly the X and Y values, could be multiplied uniformly by a scaling factor of 2, 0.5, or any other desired scaling factor of the relevant normalized parameter. In various embodiments, the X, Y, and Z distances and Z-notch thicknesses are scalable as a function of the same constant or number (e.g., minimum tip rail X-wise extent) to provide a scaled up or scaled down tip shroud. Alternatively, the values could be multiplied by a larger or smaller desired constant.

While the Cartesian values in TABLE I-VI provide coordinate values at predetermined locations, only a portion of Cartesian coordinate values set forth in each table may be employed. In one non-limiting example, with reference to FIG. 6, tip rail downstream side 254 surface profile may use a portion of X, Y, Z coordinate values defined in TABLE II, i.e., from points 5 to 12. Any portion of Cartesian coordinate values of X, Y, Z and thicknesses set forth in TABLES I-VI may be employed.

FIG. 5 shows a number of X, Y, and Z coordinate points that define a tip rail upstream side 252 surface profile. In certain embodiments, upstream side 252 of tip rail 250 has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, and Z set forth in TABLE I (below) and originating at forward-most and radially outermost origin 260. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying: the X, Y, and Z values by a minimum tip rail X-wise extent 270 (FIG. 4), expressed in units of distance. That is, the normalization parameter for the X, Y, and Z coordinates is minimum tip rail X-wise extent 270 (FIG. 4). When scaling up or down, the X, Y, and Z coordinate values in TABLE I can be multiplied by the actual, desired minimum tip rail X-wise extent 270 (FIG. 4) to identify the corresponding actual X, Y, and Z coordinate values of the tip shroud upstream side 252 surface profile. Collectively, the actual X, Y, and Z coordinate values created identify the tip rail upstream side 252 surface profile, according to embodiments of the disclosure, at any desired size of tip shroud. As shown in FIG. 5, X, Y, and Z values may be connected by lines to define the tip rail upstream side 252 surface profile at a common Z height near the radially outermost edge of tip rail 250.

TABLE I

Tip Rail Upstream Side Surface Profile [non-dimensionalized values]

X
Y
Z

1
1.050
1.458
−0.769

2
1.054
4.078
−0.769

3
1.058
6.697
−0.769

4
1.094
9.316
−0.769

5
1.133
11.935
−0.769

6
1.172
14.555
−0.769

7
1.211
17.174
−0.769

8
1.493
17.912
−0.769

9
2.102
18.396
−0.769

10
2.099
22.890
−0.769

11
1.499
23.371
−0.769

12
1.217
24.100
−0.769

13
1.161
26.564
−0.769

14
1.105
29.028
−0.769

15
1.049
31.492
−0.769

16
1.044
33.957
−0.769

17
1.038
36.421
−0.769

18
1.031
38.886
−0.769

FIG. 6 shows a number of X, Y, and Z coordinate points that define a tip rail downstream side 254 surface profile. In certain embodiments, downstream side 254 of tip rail 250 has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, and Z set forth in TABLE II (below) and originating at forward-most and radially outermost origin 260. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z by a minimum tip rail X-wise extent 270, expressed in units of distance. Here again, the normalization parameter for the X, Y, and Z coordinates is minimum tip rail X-wise extent 270 (FIG. 4) of tip rail 250. When scaling up or down, the X, Y, and Z coordinate values in TABLE II can be multiplied by the desired minimum tip rail X-wise extent 270 (FIG. 4) of tip rail 250 to identify the corresponding actual X, Y, and Z coordinate values of the tip shroud downstream side 254 surface profile. Collectively, the actual X, Y, and Z coordinate values created identify the tip rail downstream side 254 surface profile, according to embodiments of the disclosure, at any desired size of tip shroud. As shown in FIG. 6, X, Y, and Z values may be connected by lines to define the tip rail downstream side 254 surface profile at a common Z height near the radially outermost edge of tip rail 250.

TABLE II

Tip Rail Downstream Side Surface Profile [non-dimensionalized values]

X
Y
Z

1
−0.047
−0.002
−0.769

2
−0.051
2.325
−0.769

3
−0.055
4.652
−0.769

4
−0.060
6.980
−0.769

5
−0.099
9.306
−0.769

6
−0.137
11.633
−0.769

7
−0.176
13.960
−0.769

8
−0.215
16.287
−0.769

9
−0.496
17.022
−0.769

10
−1.102
17.506
−0.769

11
−1.100
22.011
−0.769

12
−0.492
22.493
−0.769

13
−0.208
23.228
−0.769

14
−0.153
26.077
−0.769

15
−0.098
28.925
−0.769

16
−0.048
31.774
−0.769

17
−0.042
34.623
−0.769

18
−0.035
37.472
−0.769

In another embodiment, tip shroud 220 may also include both upstream and downstream side tip rail surface profiles, as described herein relative to TABLES I and II.

FIG. 7 shows a forward perspective view of tip shroud 220 including points of a leading Z-notch surface profile 276. As understood in the field, leading and trailing Z-notch surfaces 276, 278 (latter in FIGS. 4 and 8) of adjacent tip shrouds 220 on adjacent blades 200 (FIG. 3) mate to collectively define a radially inner surface for a hot gas path in turbine 108 (FIG. 1), e.g., via wings 230. Each Z-notch surface 276, 278 has a thickness or radial extent (“Thk”) that varies along its length, and which can be part of a Z-notch surface profile, according to embodiments of the disclosure.

Leading Z-notch surface 276 (FIGS. 4 and 7) can have a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and thickness (Thk) values set forth in TABLE III (below) and originating at forward-most and radially outermost origin 260. The Cartesian coordinate (and thickness) values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a minimum tip rail X-wise extent 270 (FIGS. 4 and 7). That is, the normalization parameter for the X, Y, and Z coordinates and the thickness (Thk) are the same: minimum tip rail X-wise extent 270 of tip rail 250. When scaling up or down, the X, Y, Z coordinate and thickness (Thk) values in TABLE III can be multiplied by the actual, desired minimum tip rail X-wise extent 270 to identify the corresponding actual X, Y, Z coordinate and/or thickness (Thk) values of the leading Z-notch surface profile. The stated thickness (Thk) of leading Z-notch surface 276 profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value. That is, the Z coordinate values are those of a radially outer wing surface 236 of upstream wing 232 or radially outer wing surface 240 of downstream wing 234, from which thickness (Thk) extends radially inward (down on page). The actual X and Y coordinate values can be joined smoothly with one another to form the leading Z-notch surface profile.

TABLE III

Leading Z-notch Surface Profile [non-dimensionalized values]

X
Y
Z
Thickness

1
−1.120
−0.472
−6.169
0.909

2
−0.327
−0.014
−5.355
1.875

3
−0.246
−0.011
−4.016
3.267

4
−0.164
−0.007
−2.678
4.627

5
−0.082
−0.004
−1.339
5.987

6
0.000
0.000
0.000
7.347

7
1.000
1.328
0.043
7.599

8
1.044
1.444
−0.679
6.885

9
1.089
1.560
−1.401
6.170

10
1.142
1.687
−2.121
5.463

11
1.254
1.891
−2.815
4.792

12
1.425
2.170
−3.470
4.165

13
1.643
2.509
−4.081
3.599

14
1.907
2.871
−4.661
3.078

15
2.252
3.130
−5.251
2.563

16
2.686
3.258
−5.825
2.093

17
3.191
3.176
−6.343
1.706

18
3.516
3.061
−6.617
1.516

19
3.854
2.938
−6.870
1.352

20
4.363
3.610
−7.223
1.118

21
4.945
4.267
−7.522
1.005

22
5.595
4.894
−7.732
1.053

23
6.815
5.840
−8.016
1.372

24
8.153
6.611
−8.337
1.788

25
9.579
7.189
−8.684
2.155

26
11.066
7.567
−9.050
2.291

27
12.587
7.740
−9.429
2.097

28
14.117
7.705
−9.814
1.661

FIG. 8 shows a forward perspective view of a tip shroud including points of a trailing Z-notch surface 278 profile, according to various embodiments of the disclosure. As noted, leading and trailing Z-notch surfaces 276, 278 (former in FIGS. 4 and 7) of adjacent tip shrouds 220 on adjacent blades 200 (FIG. 3) mate to collectively define a radially inner surface for a hot gas path in turbine 108 (FIG. 1), e.g., via wings 230. Each trailing Z-notch surface 278 has a thickness or radial extent Thk that varies along its length, and which can be part of a Z-notch surface profile, according to embodiments of the disclosure.

Trailing Z-notch surface 278 (FIGS. 4 and 8) can have a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z and thickness (Thk) values set forth in TABLE IV (below) and originating at forward-most and radially outermost origin 260. The Cartesian coordinate (and thickness) values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a minimum tip rail X-wise extent 270 (FIG. 4). That is, the normalization parameter for the X, Y, and Z coordinates and the thickness (Thk) are the same: minimum tip rail X-wise extent 270 (FIG. 4) of tip rail 250. When scaling up or down, the X, Y, Z coordinate and thickness (Thk) values in TABLE IV can be multiplied by the actual, desired minimum tip rail X-wise extent 270 to identify the corresponding actual X, Y, Z coordinate and/or thickness (Thk) values of the leading Z-notch surface profile. The stated thickness (Thk) of leading Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value. That is, the Z coordinate values are those of a radially outer wing surface 236 of upstream wing 232 or radially outer wing surface 240 of downstream wing 234, from which thickness (Thk) extends radially inward (down on page). The actual X and Y coordinate values can be joined smoothly with one another to form the leading Z-notch surface profile.

TABLE IV

Trailing Z-notch Surface Profile [non-dimensionalized values]

X
Y
Z
Thickness

1
−7.692
39.813
−4.844
0.878

2
−6.945
39.334
−5.008
0.878

3
−6.197
38.855
−5.173
0.878

4
−5.450
38.376
−5.338
0.878

5
−4.700
37.895
−5.489
0.895

6
−3.941
37.409
−5.529
1.023

7
−3.185
36.925
−5.440
1.282

8
−2.450
36.454
−5.211
1.674

9
−1.722
36.140
−4.807
2.245

10
−1.062
36.275
−4.218
3.007

11
−0.608
36.711
−3.577
3.782

12
−0.290
37.132
−2.847
4.611

13
−0.113
37.368
−1.998
5.516

14
−0.055
37.445
−1.100
6.431

15
0.000
37.518
−0.201
7.347

16
1.000
38.845
−0.262
7.599

17
1.067
38.933
−1.359
6.523

18
1.134
39.022
−2.456
5.448

19
1.200
39.110
−3.553
4.372

20
1.267
39.199
−4.650
3.296

21
1.334
39.288
−5.746
2.221

22
1.517
39.521
−6.782
1.244

23
2.321
39.893
−7.369
0.876

24
3.291
39.488
−7.593
0.876

In another embodiment, tip shroud 220 may also include profiles of both leading and trailing Z-notch surfaces 276, 278, as described herein relative to TABLES III and IV. Other embodiments of the disclosure may include any combination of surface profiles described herein.

FIG. 9 shows a rearward perspective view of a tip shroud 220 including points of a radially outer, upstream wing surface profile, according to various embodiments of the disclosure. As shown in FIG. 9, radially outer surface 236 of wing 232 on upstream side 252 of tip rail 250 has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE V and originating at forward-most and radially outermost origin 260. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by minimum tip rail X-wise extent 270. That is, the normalization parameter for the X, Y, and Z coordinates are the same, minimum tip rail X-wise extent 270 of tip rail 250. When scaling up or down, the X, Y, Z coordinate values in TABLE V can be multiplied by the actual, desired minimum tip rail X-wise extent 270 of tip rail 250 to identify the corresponding actual X, Y, Z coordinate values of the upstream side radial outer surface 236 profile. The actual X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface 236 profile.

TABLE V

Upstream Side Radial Outer Wing Surface Profile

[non-dimensionalized values]

X
Y
Z

1
1.000
1.328
0.043

2
1.058
1.479
−0.902

3
1.117
1.632
−1.847

4
1.244
1.873
−2.765

5
1.000
2.016
0.064

6
1.058
2.101
−0.889

7
1.117
2.182
−1.843

8
1.473
2.245
−3.617

9
1.244
2.252
−2.790

10
1.689
2.579
−4.192

11
1.217
2.648
−2.686

12
1.496
2.678
−3.723

13
1.122
2.688
−1.906

14
1.027
2.743
−0.358

15
1.063
2.767
−0.948

16
1.099
2.791
−1.539

17
1.000
2.794
0.086

18
1.966
2.930
−4.774

19
3.854
2.938
−6.870

20
1.222
3.120
−2.761

21
3.297
3.139
−6.436

22
1.494
3.148
−3.775

23
2.329
3.167
−5.365

24
1.129
3.191
−2.007

25
2.781
3.262
−5.933

26
4.234
3.449
−7.142

27
1.027
3.578
−0.335

28
1.226
3.592
−2.847

29
1.063
3.601
−0.926

30
1.000
3.610
0.108

31
1.501
3.619
−3.861

32
1.099
3.624
−1.516

33
1.956
3.645
−4.843

34
2.581
3.669
−5.746

35
3.354
3.690
−6.526

36
1.137
3.713
−2.125

37
4.649
3.947
−7.384

38
1.233
4.159
−2.959

39
1.499
4.184
−3.940

40
1.938
4.208
−4.890

41
2.543
4.230
−5.763

42
3.290
4.249
−6.518

43
4.143
4.264
−7.125

44
1.027
4.414
−0.314

45
1.000
4.427
0.129

46
5.103
4.430
−7.584

47
1.063
4.436
−0.904

48
1.099
4.458
−1.495

49
1.150
4.498
−2.317

50
1.126
4.524
−1.936

51
1.239
4.725
−3.074

52
1.496
4.748
−4.021

53
1.920
4.770
−4.938

54
2.504
4.790
−5.781

55
3.226
4.808
−6.510

56
4.049
4.822
−7.096

57
4.933
4.832
−7.523

58
5.595
4.894
−7.732

59
1.000
5.244
0.149

60
1.027
5.250
−0.294

61
1.126
5.259
−1.919

62
1.063
5.271
−0.885

63
1.162
5.284
−2.506

64
1.245
5.291
−3.184

65
1.099
5.292
−1.475

66
1.493
5.312
−4.099

67
1.903
5.332
−4.985

68
2.467
5.351
−5.799

69
3.164
5.367
−6.503

70
3.959
5.380
−7.069

71
4.813
5.390
−7.481

72
5.420
5.593
−7.671

73
1.251
5.856
−3.280

74
1.491
5.876
−4.167

75
1.888
5.894
−5.025

76
2.434
5.911
−5.814

77
3.109
5.926
−6.496

78
3.880
5.938
−7.044

79
4.707
5.947
−7.443

80
1.000
6.061
0.167

81
1.173
6.076
−2.663

82
1.027
6.086
−0.276

83
1.063
6.106
−0.866

84
1.099
6.126
−1.457

85
5.276
6.278
−7.620

86
1.255
6.421
−3.356

87
1.489
6.439
−4.219

88
1.876
6.456
−5.055

89
2.408
6.472
−5.823

90
3.066
6.485
−6.488

91
3.816
6.496
−7.022

92
4.622
6.504
−7.411

93
1.000
6.878
0.183

94
1.045
6.878
−0.551

95
1.090
6.878
−1.285

96
1.135
6.878
−2.019

97
1.180
6.878
−2.753

98
1.000
6.878
0.183

99
1.272
6.892
−3.465

100
1.517
6.909
−4.318

101
1.900
6.925
−5.118

102
2.411
6.939
−5.843

103
3.036
6.951
−6.473

104
3.986
6.964
−7.120

105
4.575
6.969
−7.389

106
5.192
6.973
−7.585

107
1.199
7.798
−2.842

108
1.013
7.814
0.200

109
1.176
7.914
−2.436

110
1.110
7.914
−1.369

111
1.045
7.914
−0.303

112
1.343
7.922
−3.780

113
5.094
7.923
−7.543

114
3.848
7.933
−7.050

115
1.857
7.933
−5.073

116
2.723
7.937
−6.206

117
1.218
8.675
−2.938

118
1.026
8.750
0.216

119
1.189
8.835
−2.435

120
1.124
8.835
−1.368

121
1.059
8.835
−0.302

122
4.947
9.285
−7.484

123
1.367
9.296
−3.892

124
3.758
9.297
−7.014

125
1.857
9.303
−5.127

126
2.683
9.303
−6.208

127
1.237
9.552
−3.038

128
1.039
9.686
0.230

129
1.203
9.755
−2.434

130
1.138
9.755
−1.368

131
1.072
9.755
−0.301

132
1.256
10.429
−3.138

133
1.052
10.622
0.241

134
4.800
10.648
−7.429

135
3.668
10.661
−6.981

136
2.644
10.669
−6.214

137
1.390
10.669
−4.008

138
1.858
10.672
−5.184

139
1.216
10.676
−2.433

140
1.151
10.676
−1.367

141
1.086
10.676
−0.301

142
1.275
11.305
−3.245

143
1.065
11.558
0.251

144
1.230
11.597
−2.432

145
1.165
11.597
−1.366

146
1.100
11.597
−0.300

147
4.631
12.011
−7.372

148
3.563
12.025
−6.950

149
2.598
12.035
−6.226

150
1.855
12.041
−5.255

151
1.415
12.041
−4.145

152
1.296
12.178
−3.373

153
1.079
12.494
0.259

154
1.244
12.517
−2.431

155
1.179
12.517
−1.365

156
1.113
12.517
−0.299

157
1.293
12.575
−3.223

158
1.318
13.047
−3.524

159
4.415
13.376
−7.308

160
3.427
13.390
−6.918

161
2.534
13.401
−6.248

162
1.848
13.409
−5.349

163
1.440
13.413
−4.324

164
1.092
13.430
0.266

165
1.257
13.438
−2.431

166
1.192
13.438
−1.364

167
1.127
13.438
−0.298

168
1.306
13.481
−3.223

169
1.340
13.917
−3.673

170
1.271
14.359
−2.430

171
1.206
14.359
−1.363

172
1.141
14.359
−0.297

173
1.106
14.366
0.270

174
1.320
14.387
−3.222

175
4.241
14.740
−7.258

176
3.319
14.754
−6.894

177
2.486
14.767
−6.269

178
1.846
14.777
−5.431

179
1.465
14.784
−4.473

180
1.361
14.791
−3.789

181
1.285
15.279
−2.429

182
1.219
15.279
−1.363

183
1.154
15.279
−0.296

184
1.333
15.294
−3.221

185
1.120
15.302
0.273

186
1.380
15.668
−3.892

187
4.103
16.104
−7.221

188
3.235
16.119
−6.878

189
2.451
16.133
−6.290

190
1.848
16.145
−5.501

191
1.490
16.153
−4.600

192
1.347
16.200
−3.220

193
1.298
16.200
−2.428

194
1.233
16.200
−1.362

195
1.168
16.200
−0.296

196
1.134
16.238
0.274

197
1.405
16.498
−4.099

198
1.460
16.796
−4.926

199
3.040
16.803
−6.954

200
2.683
16.935
−6.865

201
2.386
17.154
−6.791

202
1.779
17.166
−6.409

203
1.515
17.174
−5.742

204
1.454
17.174
−4.738

205
1.393
17.174
−3.733

206
1.331
17.174
−2.729

207
1.270
17.174
−1.724

208
1.208
17.174
−0.720

209
1.148
17.174
0.273

210
1.957
17.378
−6.554

211
1.629
17.480
−6.058

212
1.249
17.628
0.272

213
1.618
17.632
−5.736

214
1.556
17.632
−4.731

215
1.495
17.632
−3.727

216
1.433
17.632
−2.722

217
1.372
17.632
−1.718

218
1.311
17.632
−0.714

219
2.120
17.661
−6.554

220
2.228
17.894
−6.443

221
1.868
17.894
−6.058

222
1.526
18.010
0.270

223
1.587
18.012
−0.697

224
1.648
18.012
−1.701

225
1.710
18.012
−2.706

226
1.771
18.012
−3.710

227
1.833
18.012
−4.714

228
1.894
18.012
−5.719

229
2.298
18.250
−5.694

230
2.237
18.250
−4.690

231
2.175
18.250
−3.685

232
2.114
18.250
−2.681

233
2.053
18.250
−1.676

234
1.991
18.250
−0.672

235
1.934
18.250
0.269

FIG. 10 shows a side perspective view of the tip shroud 220 including points of a radially outer, downstream wing surface profile, according to various embodiments of the disclosure. As shown in FIG. 10, radially outer surface 240 of wing 234 on downstream side 254 of tip rail 250 has a shape having a nominal profile in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE VI and originating at forward-most and radially outermost origin 260. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by minimum tip rail X-wise extent 270. That is, the normalization parameter for the X, Y, and Z coordinates are the same, minimum tip rail X-wise extent 270 of tip rail 250. When scaling up or down, the X, Y, Z coordinate values in TABLE VI can be multiplied by the actual, desired minimum tip rail X-wise extent 270 of tip rail 250 to identify the corresponding actual X, Y, Z coordinate values of the downstream side radial outer surface 240 profile. The actual X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface 240 profile.

TABLE VI

Downstream Side Radial Outer Wing Surface Profile

[non-dimensionalized values]

X
Y
Z

1
−0.934
22.157
0.237

2
−0.972
22.157
−0.394

3
−1.015
22.157
−1.101

4
−1.059
22.157
−1.807

5
−1.102
22.157
−2.513

6
−1.145
22.157
−3.219

7
−1.188
22.157
−3.925

8
−1.234
22.157
−4.671

9
−1.367
22.219
−5.110

10
−0.784
22.393
−3.950

11
−0.741
22.393
−3.244

12
−0.529
22.393
0.234

13
−0.698
22.393
−2.538

14
−0.655
22.393
−1.831

15
−0.611
22.393
−1.125

16
−0.568
22.393
−0.419

17
−0.672
22.568
−4.705

18
−1.019
22.680
−5.466

19
−0.251
22.771
0.229

20
−0.292
22.771
−0.436

21
−0.335
22.771
−1.142

22
−0.378
22.771
−1.848

23
−0.421
22.771
−2.555

24
−0.464
22.771
−3.261

25
−0.507
22.771
−3.967

26
−1.720
22.805
−5.706

27
−0.668
23.220
−5.327

28
−1.237
23.223
−5.743

29
−0.147
23.228
0.222

30
−0.188
23.228
−0.442

31
−0.231
23.228
−1.149

32
−0.274
23.228
−1.855

33
−0.317
23.228
−2.561

34
−0.361
23.228
−3.267

35
−0.404
23.228
−3.973

36
−0.449
23.228
−4.719

37
−1.882
23.234
−5.768

38
−0.170
24.010
−0.400

39
−0.344
24.010
−3.251

40
−0.305
24.010
−2.601

41
−0.216
24.010
−1.150

42
−0.262
24.010
−1.900

43
−0.888
24.048
−5.020

44
−1.459
24.049
−5.438

45
−0.519
24.053
−4.445

46
−0.132
24.055
0.209

47
−2.119
24.057
−5.616

48
−0.379
24.064
−3.839

49
−2.738
24.069
−5.566

50
−1.186
24.884
−4.736

51
−1.638
24.884
−5.066

52
−0.816
24.886
−4.324

53
−2.143
24.887
−5.295

54
−0.545
24.890
−3.860

55
−2.667
24.892
−5.413

56
−0.378
24.896
−3.378

57
−3.177
24.899
−5.426

58
−0.306
24.903
−2.906

59
−3.648
24.907
−5.352

60
−0.152
24.960
−0.401

61
−0.198
24.960
−1.151

62
−0.244
24.960
−1.901

63
−0.115
24.985
0.193

64
−3.733
25.842
−5.349

65
−0.283
25.843
−2.824

66
−3.246
25.851
−5.426

67
−0.357
25.852
−3.312

68
−2.719
25.858
−5.412

69
−0.529
25.859
−3.809

70
−2.179
25.864
−5.291

71
−0.808
25.865
−4.288

72
−1.657
25.867
−5.055

73
−1.191
25.868
−4.714

74
−0.134
25.911
−0.402

75
−0.180
25.911
−1.152

76
−0.225
25.911
−1.902

77
−0.098
25.915
0.175

78
−3.817
26.777
−5.347

79
−0.260
26.784
−2.745

80
−3.317
26.823
−5.427

81
−0.335
26.829
−3.246

82
−0.082
26.845
0.155

83
−0.116
26.861
−0.403

84
−0.161
26.861
−1.153

85
−0.207
26.861
−1.904

86
−2.775
26.863
−5.414

87
−0.513
26.868
−3.758

88
−2.217
26.893
−5.288

89
−0.801
26.896
−4.252

90
−1.678
26.910
−5.045

91
−1.196
26.911
−4.692

92
−3.901
27.712
−5.348

93
−0.237
27.725
−2.667

94
−0.065
27.775
0.134

95
−3.393
27.811
−5.430

96
−0.097
27.811
−0.404

97
−0.143
27.811
−1.154

98
−0.189
27.811
−1.905

99
−0.313
27.822
−3.177

100
−2.837
27.898
−5.415

101
−0.496
27.906
−3.702

102
−2.262
27.962
−5.285

103
−0.794
27.967
−4.211

104
−1.705
27.998
−5.032

105
−1.204
27.999
−4.666

106
−3.986
28.647
−5.350

107
−0.215
28.666
−2.591

108
−0.049
28.704
0.110

109
−0.079
28.762
−0.405

110
−0.125
28.762
−1.155

111
−0.171
28.762
−1.906

112
−3.475
28.805
−5.433

113
−0.291
28.821
−3.104

114
−2.909
28.943
−5.416

115
−0.479
28.955
−3.638

116
−2.317
29.046
−5.280

117
−0.790
29.054
−4.162

118
−1.739
29.104
−5.015

119
−1.217
29.106
−4.634

120
−4.086
29.582
−5.351

121
−0.191
29.608
−2.501

122
−0.032
29.634
0.085

123
−0.061
29.712
−0.406

124
−0.107
29.712
−1.157

125
−0.153
29.712
−1.907

126
−3.573
29.790
−5.434

127
−0.269
29.812
−3.017

128
−2.996
29.974
−5.415

129
−0.463
29.991
−3.562

130
−2.384
30.113
−5.270

131
−0.787
30.124
−4.102

132
−1.782
30.190
−4.992

133
−1.235
30.194
−4.593

134
−4.230
30.519
−5.342

135
−0.165
30.552
−2.368

136
−0.016
30.564
0.058

137
−0.043
30.662
−0.407

138
−0.089
30.662
−1.158

139
−0.134
30.662
−1.908

140
−3.704
30.761
−5.428

141
−0.245
30.789
−2.897

142
−3.107
30.975
−5.406

143
−0.449
30.997
−3.461

144
−2.469
31.139
−5.253

145
−0.789
31.153
−4.024

146
−1.836
31.230
−4.960

147
−1.261
31.234
−4.539

148
−4.298
31.453
−5.354

149
0.000
31.494
0.029

150
−0.029
31.494
−0.439

151
−0.115
31.494
−1.845

152
−0.072
31.494
−1.142

153
−0.143
31.494
−2.315

154
−3.762
31.705
−5.442

155
−0.225
31.739
−2.854

156
−3.153
31.929
−5.420

157
−0.433
31.955
−3.430

158
−4.361
32.033
−5.357

159
−2.501
32.100
−5.263

160
−0.782
32.117
−4.006

161
−0.139
32.137
−2.270

162
−0.101
32.144
−1.642

163
−0.069
32.155
−1.124

164
−0.035
32.167
−0.559

165
0.000
32.178
0.007

166
−1.854
32.195
−4.963

167
−1.265
32.201
−4.532

168
−3.821
32.298
−5.446

169
−0.227
32.386
−2.817

170
−3.205
32.535
−5.423

171
−0.442
32.603
−3.402

172
−2.546
32.719
−5.264

173
−0.799
32.762
−3.987

174
−1.890
32.826
−4.959

175
−1.291
32.841
−4.522

176
−4.496
32.944
−5.355

177
−0.101
33.024
−1.672

178
−0.069
33.035
−1.154

179
−0.035
33.048
−0.589

180
−0.131
33.057
−2.162

181
0.000
33.061
−0.024

182
−3.933
33.207
−5.448

183
−0.221
33.303
−2.733

184
−3.294
33.442
−5.425

185
−0.444
33.516
−3.341

186
−2.612
33.625
−5.262

187
−0.812
33.672
−3.946

188
−1.935
33.732
−4.949

189
−1.319
33.748
−4.498

190
−4.594
33.853
−5.363

191
−0.101
33.903
−1.704

192
−0.069
33.916
−1.186

193
−0.035
33.930
−0.621

194
0.000
33.944
−0.055

195
−0.125
33.975
−2.095

196
−4.007
34.096
−5.461

197
−0.218
34.199
−2.690

198
−3.347
34.312
−5.440

199
−0.445
34.391
−3.318

200
−2.648
34.480
−5.276

201
−0.819
34.530
−3.938

202
−1.959
34.579
−4.959

203
−1.333
34.596
−4.501

204
−4.692
34.763
−5.373

205
−0.069
34.797
−1.220

206
−0.035
34.811
−0.654

207
0.000
34.826
−0.089

208
−0.118
34.895
−2.029

209
−4.077
34.968
−5.476

210
−0.215
35.078
−2.652

211
−3.394
35.150
−5.457

212
−0.446
35.234
−3.301

213
−2.678
35.292
−5.292

214
−0.824
35.345
−3.937

215
−1.977
35.377
−4.973

216
−1.344
35.395
−4.510

217
−0.069
35.677
−1.255

218
−0.035
35.693
−0.689

219
0.000
35.709
−0.124

220
−4.797
35.719
−5.386

221
−0.112
35.860
−1.960

222
−4.159
35.869
−5.492

223
−0.217
35.994
−2.634

224
−3.460
36.004
−5.477

225
−0.469
36.104
−3.329

226
−2.734
36.111
−5.317

227
−1.348
36.166
−4.509

228
−1.998
36.199
−4.984

229
−0.840
36.435
−3.940

230
−4.882
36.469
−5.396

231
−0.069
36.558
−1.291

232
−0.035
36.574
−0.726

233
−4.223
36.576
−5.505

234
0.000
36.591
−0.161

235
−0.106
36.619
−1.905

236
−2.763
36.654
−5.327

237
−3.506
36.673
−5.490

238
−0.214
36.706
−2.599

239
−0.456
36.912
−3.277

240
−3.526
37.143
−5.496

241
−4.961
37.152
−5.406

242
−4.286
37.221
−5.516

243
−0.210
37.240
−2.562

244
−0.103
37.381
−1.884

245
−0.069
37.426
−1.329

246
−0.035
37.472
−0.765

247
0.000
37.518
−0.201

248
−4.303
37.641
−5.526

249
−5.074
38.135
−5.422

In another embodiment, tip shroud 220 may also include both upstream and downstream radially outer wing surface profiles, as described herein relative to TABLES V and VI. Further, any of the surface profiles described herein can be used with any of the other surface profiles described herein in any combination, e.g., a tip shroud 220 including surface profiles as described relative to TABLES I, III and V.

The disclosed surface profiles provide unique shapes to achieve, for example: 1) improved interaction between other stages in turbine 108 (FIG. 1); 2) improved turbine longevity and reliability by reducing creep; and 3) normalized aerodynamic and mechanical blade or tip shroud loadings. The disclosed loci of points defined in TABLE I-VI allow GT system 100 or any other suitable turbine system to run in an efficient, safe and smooth manner. As also noted, any scale of tip shroud 220 may be adopted as long as: 1) interaction between other stages in the pressure of turbine 108 (FIG. 1); 2) aerodynamic efficiency; and 3) normalized aerodynamic and mechanical blade or airfoil loadings, are maintained in the scaled turbine.

Tip shroud 220 surface profile(s) described herein thus improves overall GT system 100 reliability and efficiency. Tip shroud 220 surface profile(s) also meet all aeromechanical and stress requirements. Turbine blades including tip shrouds 220, described herein, have very specific aerodynamic requirements. Significant cross-functional effort was required to meet these goals. Tip shroud 220 surface profile(s) of turbine blade 200 thus possess specific shapes to meet aerodynamic, mechanical, and heat transfer requirements in an efficient and cost effective manner.

The apparatus and devices of the present disclosure are not limited to any one particular turbomachine, engine, turbine, jet engine, power generation system or other system, and may be used with turbomachines such as aircraft systems, power generation systems (e.g., simple cycle, combined cycle), and/or other systems (e.g., nuclear reactor). Additionally, the apparatus of the present disclosure may be used with other systems not described herein that may benefit from the increased efficiency of the apparatus and devices described herein.

Approximating language, as used throughout the specification and claims, may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about,” “approximately” and “substantially,” are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value. Here and throughout the specification and claims, range limitations may be combined and/or interchanged; such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise. “Approximately” as applied to a particular value of a range applies to both end values and, unless otherwise dependent on the precision of the instrument measuring the value, may indicate +/−10% of the stated value(s).

The corresponding structures, materials, acts, and equivalents of all means or step plus function elements in the claims below are intended to include any structure, material, or act for performing the function in combination with other claimed elements as specifically claimed. The description of the present disclosure has been presented for purposes of illustration and description but is not intended to be exhaustive or limited to the disclosure in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the disclosure. The embodiment was chosen and described in order to best explain the principles of the disclosure and the practical application and to enable others of ordinary skill in the art to understand the disclosure for various embodiments with various modifications as are suited to the particular use contemplated.

Claims

1. A turbine blade tip shroud, comprising: a pair of opposed, axially extending wings configured to couple to an airfoil at a radial outer end of the airfoil, the airfoil having a pressure side and a suction side opposing the pressure side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; anda tip rail extending radially from the pair of opposed, axially extending wings, the tip rail having a downstream side, an upstream side opposing the downstream side and a forward-most and radially outermost origin; andwherein the upstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE I and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by a minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail upstream side profile.
2. The turbine blade tip shroud of claim 1, wherein the airfoil is part of a third stage turbine blade.
3. The turbine blade tip shroud of claim 1, wherein the downstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE II and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail downstream side profile.
4. The turbine blade tip shroud of claim 1, further comprising a leading Z-notch surface having a shape having a nominal profile and a thickness in accordance with Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE III and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a leading Z-notch surface profile, wherein the thickness of the leading Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value.
5. The turbine blade tip shroud of claim 4, further comprising a trailing Z-notch surface having a shape having a nominal profile and a thickness in accordance with Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE IV and originating at the forward-most and radially outermost origin of the tip rail, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a trailing Z-notch surface profile, wherein the thickness of the trailing Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value.
6. The turbine blade tip shroud of claim 1, wherein the pair of opposed, axially extending wings includes a wing on the upstream side of the tip rail and a wing on the downstream side of the tip rail; wherein a radially outer surface of the wing on the upstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, Z set forth in TABLE V and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface profile.
7. The turbine blade tip shroud of claim 6, wherein a radially outer surface of the wing on the downstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, Z set forth in TABLE VI and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form a downstream side radial outer surface profile.
8. A turbine blade tip shroud, comprising: a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end of the airfoil, the airfoil having a suction side and a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side;a tip rail extending radially from the pair of opposed, axially extending wings, the tip rail having a downstream side, an upstream side opposing the downstream side, and a forward-most and radially outermost origin; anda leading Z-notch surface having a shape having a nominal profile and a thickness in accordance with Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE III and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a leading Z-notch surface profile,wherein the thickness of the leading Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value.
9. The turbine blade tip shroud of claim 8, wherein the airfoil is part of a third stage turbine blade.
10. The turbine blade tip shroud of claim 9, wherein the upstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE I and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail upstream side profile.
11. The turbine blade tip shroud of claim 10, wherein the downstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE II and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail downstream side profile.
12. The turbine blade tip shroud of claim 8, further comprising a trailing Z-notch surface having a shape having a nominal profile and a thickness in accordance with Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE IV and originating at the forward-most and radially outermost origin of the tip rail, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a trailing Z-notch surface profile, wherein the thickness of the trailing Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value.
13. The turbine blade tip shroud of claim 8, wherein a radially outer surface of the wing on the upstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, Z set forth in TABLE V and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface profile.
14. The turbine blade tip shroud of claim 13, wherein a radially outer surface of the wing on the downstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, Z set forth in TABLE VI and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form a downstream side radial outer surface profile.
15. A turbine blade tip shroud, comprising: a pair of opposed, axially extending wings configured to couple to an airfoil at a radial outer end of the airfoil, the airfoil having a pressure side and a suction side opposing the pressure side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side;a tip rail extending radially from the pair of opposed, axially extending wings, the tip rail having a downstream side and an upstream side opposing the downstream side and a forward-most and radially outermost origin; anda radially outer surface of the wing on the upstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, Z set forth in TABLE V and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by a minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface profile.
16. The turbine blade tip shroud of claim 15, wherein the airfoil is part of a third stage turbine blade.
17. The turbine blade tip shroud of claim 15, wherein the upstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE I and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail upstream side profile; and wherein the downstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE II and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail downstream side profile.
18. The turbine blade tip shroud of claim 15, further comprising a leading Z-notch surface having a shape having a nominal profile and a thickness in accordance with Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE III and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a leading Z-notch surface profile, wherein the thickness of the leading Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value; andfurther comprising a trailing Z-notch surface having a shape having a nominal profile and a thickness in accordance with Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE IV and originating at the forward-most and radially outermost origin of the tip rail, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a trailing Z-notch surface profile,wherein the thickness of the trailing Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value.
19. The turbine blade tip shroud of claim 15, wherein a radially outer surface of the wing on the downstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, Z set forth in TABLE VI and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form a downstream side radial outer surface profile.
20. A turbine blade tip shroud, comprising: a pair of opposed, axially extending wings configured to couple to an airfoil at a radial outer end of the airfoil, the airfoil having a pressure side and a suction side opposing the pressure side, a leading edge spanning between the pressure side and the suction side, and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side;a tip rail extending radially from the pair of opposed, axially extending wings, the tip rail having a downstream side and an upstream side opposing the downstream side, the tip rail having a forward-most and radially outermost origin;B an upstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE I and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by a minimum tip rail X-wise extent expressed in units of distance, and wherein the X, Y, and Z values are connected by lines to define a tip rail upstream side profile;a leading Z-notch surface having a shape having a nominal profile and a thickness in accordance with Cartesian coordinate values of X, Y, Z and thickness values set forth in TABLE III and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by the minimum tip rail X-wise extent, and wherein the X and Y values are joined smoothly with one another to form a leading Z-notch surface profile,wherein the thickness of the leading Z-notch surface profile at each X and Y coordinate value extends radially inwardly from a corresponding Z value; anda radially outer surface of the wing on the upstream side of the tip rail has a shape having a nominal profile in accordance with Cartesian coordinate values of X, Y, Z set forth in TABLE V and originating at the forward-most and radially outermost origin, wherein the Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, and Z values by the minimum tip rail X-wise extent, and wherein the X, Y, and Z values are joined smoothly with one another to form an upstream side radial outer surface profile.

US Referenced Citations (11)

Number	Name	Date	Kind
7771171	Mohr et al.	Aug 2010	B2
20050013692	Snook	Jan 2005	A1
20050036889	Tomberg	Feb 2005	A1
20090053047	Chiurato	Feb 2009	A1
20090123268	Brittingham	May 2009	A1
20090263248	Brittingham	Oct 2009	A1
20160115795	Munoz	Apr 2016	A1
20170298744	Zhang et al.	Oct 2017	A1
20180202298	Zemitis	Jul 2018	A1
20180230816	Zemitis	Aug 2018	A1
20190292914	Zemitis	Sep 2019	A1

Foreign Referenced Citations (1)

Number	Date	Country
19904229	Aug 2000	DE

Turbine blade tip shroud surface profiles

Information

Patent Number

Date Filed

Date Issued

Inventors

Original Assignees

Examiners

Agents

CPC

Field of Search

CPC

International Classifications

Abstract

Description

Claims

US Referenced Citations (11)

Foreign Referenced Citations (1)