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 and a tip shroud with a protrusion under a wing thereof.

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. 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 towards the airfoils. Due to this interaction and conversion, the aerodynamic characteristics of these tip shrouds may result in losses in 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 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, 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 substantially 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 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 turbine blade includes a second stage 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 substantially 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 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 comprising a leading Z-notch surface having a shape having a nominal profile substantially 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.

Another aspect of the disclosure includes any of the preceding aspects, and a radially inner surface of the wing on the downstream side of the tip rail having a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y, and Z values are joined smoothly with one another to form a downstream side radial inner 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 wherein the downstream side of the tip rail has a shape having a nominal profile substantially 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 a 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 downstream side profile.

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

Another aspect of the disclosure includes any of the preceding aspects, and a radially inner surface of the wing on the downstream side of the tip rail having a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y and Z values are joined smoothly with one another to form a downstream side radial inner 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 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 leading Z-notch surface having a shape having a nominal profile substantially 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 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 second stage blade.

Another aspect of the disclosure includes any of the preceding aspects, and further comprising a radially inner surface of the wing on the downstream side of the tip rail having a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y, and Z values are joined smoothly with one another to form a downstream side radial inner surface profile.

An 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; and a radially inner surface of the wing on the downstream side of the tip rail having a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y, and Z values are joined smoothly with one another to form a downstream side radial inner surface profile.

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

An aspect of the disclosure includes a turbine blade comprising: an airfoil that extends from a root end to a radial outer end, the airfoil having a pressure side and a suction side opposing the pressure side; a tip shroud extending from the radial outer end, the tip shroud including a wing; and a suction side fillet coupling the radial outer end to the tip shroud; and a protrusion extending along the radially outer end of the airfoil, the suction side fillet and a radial inner surface of the wing to an axial edge of the wing.

Another aspect of the disclosure includes any of the preceding aspects, and the protrusion extends along the radially outer end of the airfoil at a location within approximately a 25-35% of a chord length of the airfoil.

Another aspect of the disclosure includes any of the preceding aspects, and further comprising: a pair of opposed, axially extending wings configured to couple to the airfoil at a radial outer end of the airfoil; 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; and a radially inner surface of the wing on the downstream side of the tip rail defining at least part of the suction side fillet and the protrusion, the radially inner surface having a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y, and Z values are joined smoothly with one another to form a downstream side radial inner 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.

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 cross-sectional view of an illustrative turbomachine;

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

FIG. 3 shows a three-dimensional perspective 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 as in FIG. 3, according to various embodiments of the disclosure;

FIG. 5A shows a forward perspective view of a tip shroud as in FIG. 3, including points of an upstream tip rail surface profile, according to embodiments of the disclosure;

FIG. 5B shows a forward perspective view of a tip shroud as in FIG. 3, including points of a leading Z-notch surface profile, according to embodiments of the disclosure;

FIG. 6 shows a forward perspective view of a tip shroud as in FIG. 3, including points of a downstream tip rail surface profile, according to embodiments of the disclosure;

FIG. 7 shows a partial plan view of a tip shroud as in FIG. 3, including points of a leading Z-notch surface profile, according to various embodiments of the disclosure;

FIG. 8A shows an upward perspective view of a tip shroud as in FIG. 3, including points of a radially inner wing surface profile, according to various embodiments of the disclosure;

FIG. 8B shows an upward, partially cross-sectional view of a tip shroud as in FIG. 3, including points of a radially inner wing surface profile, according to various embodiments of the disclosure;

FIG. 9 shows an enlarged forward perspective and partially cross-sectional view of the tip shroud of FIGS. 8A-B, according to various embodiments of the disclosure; and

FIG. 10 shows a schematic plan view of the tip shroud of FIG. 9 with an airfoil superimposed thereunder (also includes view line 9-9 of FIG. 9), 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 different 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 element may or may not occur or be present and that the description includes instances where the event occurs or the element is present and instances where the event does not occur or the element is not present.

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, no intervening elements or layers are 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 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 Z-notch of the tip shroud, and a downstream side radially inner surface of a wing of the tip shroud.

The surface profiles are stated as shapes having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z, and 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). 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 using any now known or later developed curve fitting technique used to generate a curved surface appropriate for a turbine tip shroud. 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 may be performed manually and/or computationally, e.g., through statistical and/or numerical-analysis software.

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 rotor compressor/turbine shaft 110 (hereinafter referred to as “rotor shaft 110”). In one non-limiting embodiment, GT system 100 may be a 9F.03 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 F, HA, 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-sectional 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. Stage L2 is the third stage and is the next stage in an axial direction. Stage L3 is the fourth, last stage 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 are 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 is a plurality of 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, in detail, an enlarged perspective view of an illustrative turbine rotor blade 114 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). Relative to FIG. 3, the direction of each legend arrowhead shows the respective 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 second stage (L1) 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 (L3), 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 212 to a radial outer end 222. More particularly, blade 200 includes airfoil 202 coupled to an endwall 213 at root end 212 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 212 is illustrated as including a dovetail 224 in FIG. 3, but root end 212 can have any suitable configuration to connect to rotor shaft 110. Endwall 213 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 214 proximate a radially inner end 226 of airfoil 202, fillet 214 connecting airfoil 202 and endwall 213. Fillet 214 can include a weld or braze fillet, which may be formed via conventional MIG welding, TIG welding, brazing, etc. Fillet 214 can include such forms as integral to the investment casting process or definition. Root end 212 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 212 is intended to be located radially inboard of airfoil 202 and 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 connecting 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.

FIG. 4 shows a plan view of tip shroud 220; FIG. 5A shows a forward perspective view of an upstream side 252 of a tip rail 250; FIG. 5B shows a forward perspective view of upstream side 252 of tip rail 250, similar to FIG. 5A, but highlighting a leading edge Z-notch; and FIG. 6 shows a forward perspective view of a downstream side 254 of tip shroud 220. Data points illustrated in the drawings, e.g., FIGS. 5A-5B, 6, 8A-8B, are schematically represented and may not match data points in the tables described hereafter. With reference to FIGS. 3-6 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 (FIGS. 3 and 5A-B) of airfoil 202 (e.g., via fillet 228). More particularly, as shown in FIGS. 4-6, 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 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. 4-6, tip rail 250 also includes a forward-most and radially outermost origin (point) 260 at an axially forward end thereof, and a rearward-most and radially outermost origin (point) 262 (FIG. 4 only) at an axially rearward end thereof. Forward-most and radially outermost origin 260 may act as an origin for certain surface profiles described herein, and rearward-most and radially outermost point 262 may act as an origin for certain other surface profiles described herein.

FIG. 4 also shows a number of normalization parameters that, as will be described further, 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 “tip rail axial length LTR” is a distance between forward-most and radially outermost origin 260 and rearward-most and radially outermost origin 262 running perpendicular to axis A of rotor shaft 110 (FIG. 1), i.e., along the Y-axis. In addition, 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., perpendicular 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 the tip rail axial length that includes upstream side 252 and downstream side 254 in parallel, i.e., it excludes the angled ends of tip rail 250.

Referring to FIGS. 4-8B, 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 coordinates, and perhaps also Z coordinates and thickness, which are listed in a number of tables, i.e., TABLES I, II, III, and IV. The X, Y, and Z coordinate values and the thickness values in TABLES I-IV 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-IV 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 point, in units of distance, such as inches or meters, the non-dimensional values given in TABLE I-IV can be multiplied by a normalization parameter value. As noted, the normalization parameter used herein is 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-IV 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-IV. In one embodiment, a tolerance of about 10-20 percent can be applied. For example, a tolerance of about 10-20 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 10-20 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. This range of variation is encompassed by the phrase “substantially in accordance with the Cartesian coordinates” of a particular table, as used herein.

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 tip rail axial length or 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-IV 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 16 to 100. Any portion of Cartesian coordinate values of X, Y, Z and thicknesses set forth in TABLES I-IV may be employed. In the Figures, the X, Y, and Z coordinate points are represented schematically by plus (+) signs.

FIG. 5A shows a number of X, Y, and Z coordinate points that define a tip rail upstream side 252 surface profile.

In one embodiment, upstream side 252 of tip rail 250 has a shape having a nominal profile substantially 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, expressed in units of distance (e.g., centimeters). That is, the normalization parameter for the X, Y, and Z coordinates is minimum tip rail X-wise extent 270. 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 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. 5A, X, Y, and Z values may be connected by lines to define the tip rail upstream side surface profile. Relative to FIG. 5A, the direction of each legend arrowhead shows the respective direction of positive coordinate values (i.e., negative Z values are radially inward of the radially outermost origin 260).

TABLE I

Tip Rail Upstream Side Surface Profile

[non-dimensionalized values]

Point
X
Y
Z

1
0.997
1.695
0.082

2
1.058
1.695
−0.577

3
1.119
1.695
−1.236

4
1.180
1.695
−1.894

5
0.996
2.542
0.120

6
1.058
2.542
−0.551

7
1.120
2.542
−1.222

8
1.182
2.542
−1.893

9
1.258
2.542
−2.563

10
1.425
2.542
−3.214

11
1.719
2.542
−3.819

12
0.995
3.390
0.158

13
1.057
3.390
−0.510

14
1.119
3.390
−1.179

15
1.181
3.390
−1.847

16
1.301
3.390
−2.507

17
1.543
3.390
−3.132

18
1.892
3.390
−3.704

19
2.338
3.390
−4.205

20
0.994
4.237
0.194

21
1.063
4.237
−0.547

22
1.132
4.237
−1.289

23
1.239
4.237
−2.025

24
1.506
4.237
−2.719

25
1.888
4.237
−3.358

26
2.361
4.237
−3.932

27
2.913
4.237
−4.431

28
3.540
4.237
−4.831

29
4.237
4.237
−5.086

30
0.993
5.085
0.229

31
1.062
5.085
−0.503

32
1.130
5.085
−1.235

33
1.285
5.085
−1.952

34
1.579
5.085
−2.625

35
1.968
5.085
−3.247

36
2.436
5.085
−3.814

37
2.971
5.085
−4.317

38
3.569
5.085
−4.742

39
4.237
5.085
−5.044

40
0.993
5.932
0.263

41
1.060
5.932
−0.466

42
1.136
5.932
−1.194

43
1.326
5.932
−1.899

44
1.625
5.932
−2.566

45
2.006
5.932
−3.191

46
2.460
5.932
−3.764

47
2.983
5.932
−4.274

48
3.575
5.932
−4.703

49
4.237
5.932
−5.009

50
0.992
6.780
0.294

51
1.060
6.780
−0.436

52
1.151
6.780
−1.164

53
1.342
6.780
−1.873

54
1.625
6.780
−2.550

55
1.994
6.780
−3.184

56
2.441
6.780
−3.766

57
2.963
6.780
−4.281

58
3.561
6.780
−4.705

59
4.237
6.780
−4.984

60
0.992
7.627
0.325

61
1.060
7.627
−0.412

62
1.157
7.627
−1.144

63
1.337
7.627
−1.861

64
1.603
7.627
−2.551

65
1.954
7.627
−3.201

66
2.393
7.627
−3.795

67
2.922
7.627
−4.311

68
3.541
7.627
−4.714

69
4.237
7.627
−4.954

70
0.992
8.475
0.354

71
1.060
8.475
−0.389

72
1.154
8.475
−1.130

73
1.319
8.475
−1.857

74
1.565
8.475
−2.561

75
1.903
8.475
−3.226

76
2.339
8.475
−3.831

77
2.880
8.475
−4.343

78
3.521
8.475
−4.721

79
4.237
8.475
−4.925

80
0.991
9.322
0.382

81
1.060
9.322
−0.369

82
1.146
9.322
−1.119

83
1.292
9.322
−1.859

84
1.515
9.322
−2.580

85
1.837
9.322
−3.262

86
2.274
9.322
−3.875

87
2.834
9.322
−4.380

88
3.504
9.322
−4.721

89
4.237
9.322
−4.897

90
0.990
10.169
0.408

91
1.061
10.169
−0.353

92
1.138
10.169
−1.114

93
1.264
10.169
−1.867

94
1.462
10.169
−2.605

95
1.763
10.169
−3.307

96
2.199
10.169
−3.932

97
2.786
10.169
−4.418

98
3.490
10.169
−4.711

99
4.237
10.169
−4.870

100
0.990
11.017
0.434

101
1.061
11.017
−0.338

102
1.133
11.017
−1.109

103
1.236
11.017
−1.878

104
1.407
11.017
−2.633

105
1.684
11.017
−3.356

106
2.123
11.017
−3.991

107
2.744
11.017
−4.448

108
3.479
11.017
−4.686

109
4.237
11.017
−4.845

110
0.989
11.864
0.458

111
1.062
11.864
−0.325

112
1.135
11.864
−1.108

113
1.217
11.864
−1.890

114
1.355
11.864
−2.663

115
1.604
11.864
−3.408

116
2.047
11.864
−4.052

117
2.707
11.864
−4.468

118
3.468
11.864
−4.660

119
4.237
11.864
−4.821

120
0.989
12.712
0.480

121
1.062
12.712
−0.312

122
1.136
12.712
−1.103

123
1.210
12.712
−1.894

124
1.323
12.712
−2.681

125
1.543
12.712
−3.442

126
1.990
12.712
−4.092

127
2.683
12.712
−4.468

128
3.459
12.712
−4.636

129
4.237
12.712
−4.798

130
0.988
13.559
0.501

131
1.062
13.559
−0.292

132
1.138
13.559
−1.083

133
1.225
13.559
−1.874

134
1.336
13.559
−2.661

135
1.546
13.559
−3.426

136
1.983
13.559
−4.083

137
2.681
13.559
−4.448

138
3.458
13.559
−4.615

139
4.237
13.559
−4.777

FIG. 6 shows a number of X, Y, and Z coordinate points that define a tip rail downstream side 254 surface profile.

In another embodiment, downstream side 254 of tip rail 250 has a shape having a nominal profile substantially 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 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 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.

TABLE II

Tip Rail Downstream Side Surface Profile

[non-dimensionalized values]

Point
X
Y
Z

1
0.000
0.000
0.000

2
−0.203
0.000
−0.588

3
−0.404
0.000
−1.176

4
−0.579
0.000
−1.772

5
−0.647
0.000
−2.390

6
−0.712
0.000
−3.008

7
−0.976
0.000
−3.563

8
−1.501
0.000
−3.880

9
0.000
0.847
0.042

10
−0.194
0.847
−0.524

11
−0.389
0.847
−1.089

12
−0.565
0.847
−1.660

13
−0.637
0.847
−2.253

14
−0.703
0.847
−2.847

15
−0.955
0.847
−3.383

16
−1.428
0.847
−3.739

17
−2.009
0.847
−3.868

18
−2.603
0.847
−3.815

19
0.000
1.695
0.082

20
−0.207
1.695
−0.519

21
−0.414
1.695
−1.120

22
−0.586
1.695
−1.732

23
−0.650
1.695
−2.364

24
−0.792
1.695
−2.980

25
−1.186
1.695
−3.471

26
−1.753
1.695
−3.747

27
−2.384
1.695
−3.801

28
−3.009
1.695
−3.690

29
0.000
2.542
0.120

30
−0.206
2.542
−0.478

31
−0.412
2.542
−1.077

32
−0.584
2.542
−1.685

33
−0.648
2.542
−2.314

34
−0.809
2.542
−2.921

35
−1.216
2.542
−3.399

36
−1.779
2.542
−3.681

37
−2.405
2.542
−3.752

38
−3.029
2.542
−3.647

39
0.000
3.390
0.158

40
−0.206
3.390
−0.441

41
−0.412
3.390
−1.039

42
−0.583
3.390
−1.647

43
−0.648
3.390
−2.277

44
−0.822
3.390
−2.881

45
−1.235
3.390
−3.354

46
−1.798
3.390
−3.636

47
−2.424
3.390
−3.709

48
−3.047
3.390
−3.605

49
−0.052
4.237
0.194

50
−0.255
4.237
−0.404

51
−0.458
4.237
−1.003

52
−0.590
4.237
−1.620

53
−0.648
4.237
−2.250

54
−0.838
4.237
−2.848

55
−1.255
4.237
−3.318

56
−1.819
4.237
−3.597

57
−2.444
4.237
−3.670

58
−3.066
4.237
−3.564

59
−0.164
5.085
0.229

60
−0.363
5.085
−0.365

61
−0.525
5.085
−0.969

62
−0.590
5.085
−1.592

63
−0.653
5.085
−2.214

64
−0.877
5.085
−2.794

65
−1.298
5.085
−3.253

66
−1.852
5.085
−3.541

67
−2.469
5.085
−3.628

68
−3.086
5.085
−3.526

69
−0.166
5.932
0.263

70
−0.362
5.932
−0.325

71
−0.525
5.932
−0.922

72
−0.587
5.932
−1.538

73
−0.675
5.932
−2.150

74
−0.935
5.932
−2.709

75
−1.352
5.932
−3.165

76
−1.887
5.932
−3.470

77
−2.493
5.932
−3.581

78
−3.104
5.932
−3.488

79
−0.166
6.780
0.294

80
−0.358
6.780
−0.284

81
−0.520
6.780
−0.870

82
−0.584
6.780
−1.476

83
−0.728
6.780
−2.066

84
−1.014
6.780
−2.603

85
−1.420
6.780
−3.054

86
−1.932
6.780
−3.381

87
−2.520
6.780
−3.527

88
−3.123
6.780
−3.453

89
−0.165
7.627
0.325

90
−0.354
7.627
−0.242

91
−0.516
7.627
−0.818

92
−0.603
7.627
−1.408

93
−0.801
7.627
−1.972

94
−1.102
7.627
−2.488

95
−1.497
7.627
−2.935

96
−1.984
7.627
−3.281

97
−2.549
7.627
−3.466

98
−3.142
7.627
−3.418

99
−0.164
8.475
0.354

100
−0.351
8.475
−0.206

101
−0.518
8.475
−0.772

102
−0.642
8.475
−1.348

103
−0.863
8.475
−1.896

104
−1.170
8.475
−2.399

105
−1.558
8.475
−2.843

106
−2.027
8.475
−3.200

107
−2.575
8.475
−3.412

108
−3.160
8.475
−3.384

109
−0.170
9.322
0.382

110
−0.357
9.322
−0.174

111
−0.526
9.322
−0.735

112
−0.673
9.322
−1.302

113
−0.906
9.322
−1.840

114
−1.217
9.322
−2.336

115
−1.601
9.322
−2.779

116
−2.060
9.322
−3.141

117
−2.598
9.322
−3.367

118
−3.179
9.322
−3.353

119
−0.174
10.169
0.408

120
−0.361
10.169
−0.147

121
−0.533
10.169
−0.706

122
−0.689
10.169
−1.269

123
−0.929
10.169
−1.803

124
−1.242
10.169
−2.297

125
−1.625
10.169
−2.739

126
−2.083
10.169
−3.103

127
−2.619
10.169
−3.334

128
−3.197
10.169
−3.322

129
−0.171
11.017
0.434

130
−0.358
11.017
−0.125

131
−0.530
11.017
−0.689

132
−0.681
11.017
−1.258

133
−0.920
11.017
−1.796

134
−1.236
11.017
−2.293

135
−1.625
11.017
−2.736

136
−2.090
11.017
−3.097

137
−2.633
11.017
−3.318

138
−3.216
11.017
−3.292

139
−0.163
11.864
0.458

140
−0.353
11.864
−0.114

141
−0.518
11.864
−0.692

142
−0.640
11.864
−1.282

143
−0.862
11.864
−1.841

144
−1.177
11.864
−2.353

145
−1.580
11.864
−2.800

146
−2.069
11.864
−3.147

147
−2.640
11.864
−3.330

148
−3.235
11.864
−3.264

149
−0.162
12.712
0.480

150
−0.359
12.712
−0.113

151
−0.522
12.712
−0.714

152
−0.592
12.712
−1.335

153
−0.765
12.712
−1.933

154
−1.068
12.712
−2.478

155
−1.492
12.712
−2.933

156
−2.029
12.712
−3.247

157
−2.640
12.712
−3.349

158
−3.254
12.712
−3.238

159
−0.162
13.559
0.501

160
−0.367
13.559
−0.116

161
−0.529
13.559
−0.745

162
−0.591
13.559
−1.392

163
−0.687
13.559
−2.035

164
−0.953
13.559
−2.625

165
−1.403
13.559
−3.089

166
−1.997
13.559
−3.342

167
−2.643
13.559
−3.344

168
−3.281
13.559
−3.212

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

FIG. 7 shows a partial plan view of tip shroud 220 at a leading Z-notch surface 276. As understood in the field, leading and trailing Z-notch surfaces 276, 278 (latter only in FIG. 4) 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. FIG. 5B shows a forward perspective view of tip shroud 220 including points of a leading Z-notch surface profile 276. Each Z-notch surface 276 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. 5B and 7) can have a shape having a nominal profile substantially 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, 5, 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 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]

Point
X
Y
Z
THICKNESS

1
−0.611
−0.382
−2.018
2.966

2
−0.693
−0.340
−2.908
2.059

3
−0.161
−0.181
−0.479
4.585

4
0.000
0.000
0.000
5.093

5
0.997
1.319
0.064
5.424

6
1.055
1.439
−0.564
4.822

7
1.114
1.560
−1.192
4.212

8
1.173
1.681
−1.819
3.610

9
1.231
1.802
−2.447
2.966

10
1.324
1.965
−3.059
2.441

11
1.527
2.272
−3.581
2.025

12
1.841
2.711
−3.925
1.864

13
2.197
3.198
−4.141
1.881

14
2.583
3.675
−4.323
1.966

15
3.062
4.002
−4.593
1.958

16
4.217
4.121
−5.087
1.771

17
5.769
4.143
−5.410
1.559

18
3.614
4.153
−4.880
1.873

19
7.264
4.497
−5.707
1.195

20
8.661
5.152
−5.970
0.915

21
9.929
6.042
−6.199
0.805

22
11.066
7.102
−6.397
0.805

FIG. 8A shows an upward perspective view of a tip shroud 220, and FIG. 8B shows an upward cross-sectional view of tip shroud 220, i.e., partially through airfoil 202. FIGS. 8A-B include points of a downstream radially wing inner surface 242 profile on suction side 206 of airfoil 202, according to various embodiments of the disclosure. As understood in the field, radial inner surface 242 may also include part of a (suction side) fillet 280 coupling tip shroud 220 to airfoil 202.

Radial inner surface 242 of wing 234 on downstream side 254 of tip rail 220 may have a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV (below) and originating at forward-most and radially outermost origin 260 (FIG. 8A, partially hidden in FIG. 8B). 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 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 IV 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 inner surface 242 profile. The actual X, Y, and Z coordinate values can be joined smoothly with one another to form the downstream side radial inner surface 242 profile.

TABLE IV

Downstream Side Radial Inner Surface

Profile [non-dimensionalized values]

Point
X
Y
Z

1
−1.417
0.000
−4.801

2
−0.283
0.000
−5.037

3
−2.564
0.847
−4.519

4
−2.050
0.847
−4.626

5
−1.444
0.847
−4.754

6
−0.838
0.847
−4.885

7
−0.232
0.847
−5.015

8
0.374
0.847
−5.144

9
−2.813
1.695
−4.438

10
−2.176
1.695
−4.587

11
−1.542
1.695
−4.741

12
−0.906
1.695
−4.896

13
−0.271
1.695
−5.050

14
0.364
1.695
−5.202

15
1.002
1.695
−5.347

16
−2.840
2.542
−4.442

17
−2.203
2.542
−4.615

18
−1.565
2.542
−4.792

19
−0.930
2.542
−4.971

20
−0.293
2.542
−5.149

21
0.344
2.542
−5.325

22
0.983
2.542
−5.493

23
1.625
2.542
−5.653

24
−2.868
3.390
−4.473

25
−2.300
3.390
−4.649

26
−1.733
3.390
−4.829

27
−1.168
3.390
−5.011

28
−0.603
3.390
−5.194

29
−0.036
3.390
−5.375

30
0.531
3.390
−5.554

31
1.098
3.390
−5.727

32
1.669
3.390
−5.893

33
2.243
3.390
−6.048

34
−2.895
4.237
−4.517

35
−2.375
4.237
−4.699

36
−1.857
4.237
−4.886

37
−1.339
4.237
−5.075

38
−0.822
4.237
−5.266

39
−0.305
4.237
−5.457

40
0.212
4.237
−5.647

41
0.731
4.237
−5.835

42
1.250
4.237
−6.018

43
1.772
4.237
−6.196

44
2.296
4.237
−6.365

45
2.824
4.237
−6.524

46
3.356
4.237
−6.667

47
−2.924
5.085
−4.562

48
−2.269
5.085
−4.823

49
−1.616
5.085
−5.091

50
−0.964
5.085
−5.361

51
−0.314
5.085
−5.634

52
0.336
5.085
−5.907

53
0.987
5.085
−6.177

54
1.641
5.085
−6.442

55
2.297
5.085
−6.699

56
2.960
5.085
−6.941

57
3.631
5.085
−7.158

58
4.312
5.085
−7.343

59
5.004
5.085
−7.476

60
5.706
5.085
−7.535

61
6.409
5.085
−7.490

62
7.095
5.085
−7.329

63
7.760
5.085
−7.095

64
8.430
5.085
−6.873

65
−2.952
5.932
−4.598

66
−2.297
5.932
−4.894

67
−1.645
5.932
−5.199

68
−0.996
5.932
−5.508

69
−0.347
5.932
−5.819

70
0.301
5.932
−6.131

71
0.950
5.932
−6.440

72
1.601
5.932
−6.746

73
2.255
5.932
−7.045

74
2.914
5.932
−7.333

75
3.580
5.932
−7.604

76
4.256
5.932
−7.848

77
4.947
5.932
−8.050

78
5.653
5.932
−8.184

79
6.370
5.932
−8.212

80
7.079
5.932
−8.097

81
7.756
5.932
−7.855

82
8.409
5.932
−7.556

83
9.055
5.932
−7.238

84
9.723
5.932
−6.975

85
−2.977
6.780
−4.625

86
−2.260
6.780
−4.978

87
−1.553
6.780
−5.349

88
−0.852
6.780
−5.730

89
−0.152
6.780
−6.114

90
0.548
6.780
−6.500

91
1.248
6.780
−6.884

92
1.951
6.780
−7.264

93
2.657
6.780
−7.637

94
3.369
6.780
−7.998

95
4.092
6.780
−8.338

96
4.830
6.780
−8.645

97
5.588
6.780
−8.892

98
6.374
6.780
−9.031

99
7.169
6.780
−8.988

100
7.933
6.780
−8.758

101
8.654
6.780
−8.417

102
9.332
6.780
−7.997

103
9.988
6.780
−7.540

104
10.691
6.780
−7.166

105
−3.000
7.627
−4.651

106
−2.386
7.627
−4.969

107
−1.782
7.627
−5.308

108
−1.188
7.627
−5.664

109
−0.599
7.627
−6.027

110
−0.014
7.627
−6.397

111
0.570
7.627
−6.768

112
1.155
7.627
−7.138

113
1.741
7.627
−7.507

114
2.328
7.627
−7.873

115
2.918
7.627
−8.235

116
3.510
7.627
−8.592

117
4.109
7.627
−8.939

118
4.716
7.627
−9.272

119
5.336
7.627
−9.580

120
5.975
7.627
−9.844

121
6.641
7.627
−10.031

122
7.330
7.627
−10.088

123
−3.023
8.475
−4.678

124
−2.395
8.475
−5.021

125
−1.781
8.475
−5.390

126
−1.180
8.475
−5.779

127
−0.589
8.475
−6.184

128
−0.005
8.475
−6.598

129
0.575
8.475
−7.018

130
1.154
8.475
−7.440

131
1.733
8.475
−7.862

132
2.311
8.475
−8.284

133
2.890
8.475
−8.705

134
3.469
8.475
−9.127

135
4.049
8.475
−9.547

136
4.632
8.475
−9.963

137
5.220
8.475
−10.371

138
−3.047
9.322
−4.700

139
−2.459
9.322
−5.040

140
−1.886
9.322
−5.402

141
−1.326
9.322
−5.785

142
−0.778
9.322
−6.186

143
−0.241
9.322
−6.599

144
0.290
9.322
−7.023

145
0.814
9.322
−7.454

146
1.334
9.322
−7.889

147
1.852
9.322
−8.328

148
2.366
9.322
−8.770

149
2.878
9.322
−9.216

150
3.386
9.322
−9.667

151
3.887
9.322
−10.124

152
4.382
9.322
−10.588

153
−3.071
10.169
−4.713

154
−2.484
10.169
−5.074

155
−1.911
10.169
−5.458

156
−1.352
10.169
−5.862

157
−0.807
10.169
−6.285

158
−0.275
10.169
−6.725

159
0.242
10.169
−7.181

160
0.747
10.169
−7.652

161
1.243
10.169
−8.131

162
1.733
10.169
−8.617

163
2.217
10.169
−9.108

164
2.694
10.169
−9.606

165
3.163
10.169
−10.113

166
3.617
10.169
−10.632

Other embodiments of the disclosure may include any combination of surface profiles described herein.

FIG. 9 shows an enlarged forward perspective and partially cross-sectional view of a turbine blade 200 including tip shroud 220 of FIGS. 8A-B. In certain embodiments, turbine blade 200 includes airfoil 202 that extends from root end 212 (FIG. 3) to radial outer end 222. As noted, airfoil 202 has pressure side 204 (obscured in FIG. 9) and suction side 206 opposing pressure side 204. Tip shroud 220 extends from radial outer end 222 and includes downstream side wing 234. Turbine blade 200 also includes a suction side fillet 280 coupling radial outer end 222 to tip shroud 220. Per the previously described surface profile defined by the coordinates in TABLE IV, turbine blade 200 also includes a bulge or protrusion 282 extending along radially outer end 222 of airfoil 202, suction side fillet 280 and radial inner surface 242 of wing 234 to an axial edge 284 of wing 234 (edge of paper, as drawn in FIG. 9). In this embodiment, radially inner surface 242 of wing 234 on downstream side 254 of tip rail 250 defines at least part of suction side fillet 280 and protrusion 282 per the coordinates in TABLE IV.

FIG. 10 shows a schematic plan view of tip shroud 220 with airfoil 202 superimposed thereunder—see also view line 9-9 for FIG. 9. As illustrated, protrusion 282 may extend along radially outer end 222 of airfoil 202 at a location at about 25-35% of a chord length 286 of airfoil 202; see centered line through length of airfoil 202. Protrusion 282 provides a number of advantages. For example, protrusion 282 increases an effective height of structural tip rail 250 above the gas path, which increases the second moment of area in the direction of radial bending due to pull load. Protrusion 282 may extend to an edge of wing 234, allowing radial load from a tip of wing 234 to be transferred to suction side fillet 280, rather than carried by tip rail 250 alone. Consequently, protrusion 282 acts to move a net gas pressure load radially inboard of wing 234. In this manner, protrusion 282 may reduce wing 234 pull-load by approximately 1% compared to airfoil not having the surface profile providing protrusion 282. Protrusion 282 thus increases tip shroud 220 stiffness and resistance to creep damage to reduce repair costs. Protrusion 282 tapers off upstream and downstream, so material is only added where necessary, reducing overall mass addition. Protrusion 282 may also allow for larger cooling passages to be provided in wing 234, thus allowing the blade to advantageously work at higher temperatures.

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-IV 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) and protrusion 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. Notably, downstream side radially inner surface 242 of wing 234 induces aerodynamic forces that decrease airfoil 202 suction side 206 winglet pull by approximately 1% compared to conventional systems.

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 herein 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;wherein the upstream side of the tip rail has a shape having a nominal profile substantially 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 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 turbine blade includes a second stage 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 substantially 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 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 substantially 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.
5. The turbine blade tip shroud of claim 1, wherein a radially inner surface of the wing on the downstream side of the tip rail has a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y, and Z values are joined smoothly with one another to form a downstream side radial inner surface profile.
6. 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; 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;wherein the downstream side of the tip rail has a shape having a nominal profile substantially 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 a 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 downstream side profile.
7. The turbine blade tip shroud of claim 6, wherein the turbine blade includes a second stage blade.
8. The turbine blade tip shroud of claim 7, wherein the upstream side of the tip rail has a shape having a nominal profile substantially 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.
9. The turbine blade tip shroud of claim 6, further comprising a leading Z-notch surface having a shape having a nominal profile substantially 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.
10. The turbine blade tip shroud of claim 6, wherein a radially inner surface of the wing on the downstream side of the tip rail has a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y and Z values are joined smoothly with one another to form a downstream side radial inner surface profile.
11. 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 leading Z-notch surface having a shape having a nominal profile substantially 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 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.
12. The turbine blade tip shroud of claim 11, wherein the turbine blade includes a second stage blade.
13. The turbine blade tip shroud of claim 12, wherein the upstream side of the tip rail has a shape having a nominal profile substantially 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.
14. The turbine blade tip shroud of claim 12, wherein the downstream side of the tip rail has a shape having a nominal profile substantially 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 X, Y, and Z values are connected by lines to define a tip rail downstream side profile.
15. The turbine blade tip shroud of claim 11, further comprising a radially inner surface of the wing on the downstream side of the tip rail having a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y, and Z values are joined smoothly with one another to form a downstream side radial inner surface profile.
16. 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; anda radially inner surface of the wing on the downstream side of the tip rail having a shape having a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X, Y, Z set forth in TABLE IV 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 X, Y, and Z values are joined smoothly with one another to form a downstream side radial inner surface profile.
17. The turbine blade tip shroud of claim 16, wherein the turbine blade includes a second stage blade.
18. The turbine blade tip shroud of claim 17, wherein the upstream side of the tip rail has a shape having a nominal profile substantially 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.
19. The turbine blade tip shroud of claim 17, wherein the downstream side of the tip rail has a shape having a nominal profile substantially 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 X, Y, and Z values are connected by lines to define a tip rail downstream side profile.
20. The turbine blade tip shroud of claim 17, further comprising a leading Z-notch surface having a shape having a nominal profile substantially 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.

Provisional Applications (1)

	Number	Date	Country
	63158605	Mar 2021	US

TURBINE BLADE TIP SHROUD SURFACE PROFILES

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Provisional Applications (1)