First stage turbine nozzle airfoil

Information

  • Patent Grant
  • 6736599
  • Patent Number
    6,736,599
  • Date Filed
    Wednesday, May 14, 2003
    21 years ago
  • Date Issued
    Tuesday, May 18, 2004
    20 years ago
Abstract
The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.
Description




BACKGROUND OF INVENTION




1. Technical Field




The present invention relates to a turbine nozzle for a gas turbine and particularly relates to a first stage turbine nozzle airfoil profile.




2. Background of the Invention




In recent years, advanced gas turbines have trended toward increasing firing temperatures and efforts to improve cooling of the various turbine components. In a particular gas turbine design of the assignee, a high output turbine that uses air cooling is undergoing development. It will be appreciated that the design and construction of the turbine buckets and nozzles require optimized aerodynamic efficiency, as well as aerodynamic and mechanical loading.




SUMMARY OF INVENTION




In accordance with a preferred embodiment of the present invention, there is provided a unique airfoil profile for the nozzles of a turbine stage, preferably the first stage of a gas turbine. The nozzle airfoil profile is defined by a unique loci of points to achieve the necessary efficiency whereby improved turbine performance is obtained. These unique loci of points define the nominal airfoil profile and are identified by the X, Y and Z Cartesian coordinates of Table 1 which follows. The 1200 points for the coordinate values shown in Table 1 are for a cold, i.e., room temperature, profile at various planar cross sections of the nozzle airfoil along its length. The X and Y coordinates are given in distance dimensions, e.g., units of inches, and are joined smoothly at each Z location to form a smooth continuous airfoil cross section. The Z coordinates are given in nondimensionalized form from 0 to 1 along a nozzle stacking axis coincident with a radius from the axis of turbine rotation. By multiplying the airfoil height dimension, e.g., in inches, by the nondimensional Z value of Table 1 and adding that value to the root radius of the nozzle, the actual Z distance from the rotational axis, e.g., in inches, is obtained. Each defined cross section is then joined smoothly with adjacent cross sections to form the complete airfoil shape.




It will be appreciated that as each nozzle airfoil heats up in use, the profile will change as a result of stress and temperature. Thus, the cold or room temperature profile is given by the X, Y and Z coordinates for manufacturing purposes. Because the manufactured nozzle airfoil profile may be different from the nominal airfoil profile given by the following table, a distance of plus or minus 0.160 inches from the nominal profile in a direction normal to any surface location along the nominal profile defines the profile envelope for this nozzle airfoil. The envelope includes any possible airfoil surface coating process. The design is robust to this variation without impairment of the mechanical and aerodynamic functions.




It also will be appreciated that the airfoil can be scaled up or scaled down geometrically for introduction into similar turbine designs. Consequently, the X and Y coordinates in inches and the Z coordinates, when converted to inches, of the nominal airfoil profile given below are a function of the same constant or number. That is, the X and Y and optionally the Z coordinate values in inches may be multiplied or divided by the same constant or number to provide a scaled up or scaled down version of the nozzle airfoil profile while retaining the airfoil section shape.




In a preferred embodiment according to the present invention, there is provided a turbine nozzle having an airfoil shape in an envelope within ±0.160 inches in a direction normal to any airfoil surface location wherein the airfoil has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. Z is a nondimensional value along a nozzle stacking axis coincident with a radius from a turbine axis of rotation convertible to a Z distance in inches from said turbine axis by multiplying the Z value by a height of the airfoil and adding that product to a root radius of the nozzle. X and Y are distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape.




In a further preferred embodiment according to the present invention, there is provided a turbine nozzle having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. Z is a nondimensional value along a nozzle stacking axis coincident with a radius from a turbine axis of rotation convertible to a Z distance in inches from said turbine axis by multiplying the Z value by a height of the airfoil and adding that product to a root radius of the nozzle and wherein X and Y are distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape, the X and Y distances being scalable as a function of the same constant or number to provide a scaled up or scaled down nozzle airfoil.




In a further preferred embodiment according to the present invention, there is provided a turbine including a turbine nozzle arrangement having a number of nozzles, each of the nozzles having an airfoil shape in an envelope within ±0.160 inches in a direction normal to any airfoil surface location wherein the airfoil has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1, wherein Z is a nondimensional value along a nozzle centerline coincident with a radius from a turbine axis of rotation convertible to a Z distance in inches from said turbine axis by multiplying the Z value by a height of the airfoil and adding that product to a root radius of the nozzle, and wherein X and Y are distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape.




In a further preferred embodiment according to the present invention, there is provided a turbine including a turbine nozzle arrangement having a number of nozzles, each of the nozzles having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1, wherein Z is a nondimensional value along a nozzle centerline coincident with a radius from a turbine axis of rotation convertible to a Z distance in inches from said turbine axis of rotation by miultiplying the Z value by a height of the airfoil and adding that product to a root radius of the nozzle and wherein X and Y are distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape. The X and Y distances being scalable as a function of the same constant or number to provide a scaled up or scaled down nozzle airfoil.











These and other features of the present invention will become apparent upon review of the following detailed description when taken in conjunction with the drawings and the appended claims.




BRIEF DESCRIPTION OF DRAWINGS





FIG. 1

is a schematic illustration of a turbine having a first stage turbine nozzle arrangement employing the nozzles and nozzle airfoils hereof.





FIG. 2

is a frontal view of a first stage turbine nozzle including an airfoil and sidewalls in accordance with a preferred embodiment of the present invention.





FIG. 3

is a suction side view of a first stage turbine nozzle including an airfoil and sidewalls in accordance with a preferred embodiment of the present invention.





FIG. 4

is a pressure side isometric view of a first stage turbine nozzle including an airfoil and sidewalls in accordance with a preferred embodiment of the present invention.





FIG. 5

is a schematic illustration of a turbine having a first stage turbine nozzle arrangement employing the nozzles and nozzle airfoils hereof.











DETAILED DESCRIPTION




Referring now to

FIG. 1

, there is illustrated a portion of a turbine in which a first stage turbine nozzle having an airfoil profile as defined herein may be utilized. The turbine includes first, second and third stage nozzle arrangements having nozzles in conjunction with the respective buckets of the various stages of the rotor. It will be appreciated that a three stage turbine is illustrated.




Referring now to

FIG. 1

, there is illustrated a portion of a turbine, generally designated


10


, having a first stage nozzle, generally designated


12


. The first stage nozzle


12


includes a number of vanes


14


having an airfoil shape or profile spaced circumferentially one from the other. The first stage nozzle


12


is arranged in conjunction with a number of buckets


16


. The buckets


16


are circumferentially spaced about a rotatable turbine wheel


18


.




The illustrated turbine


10


includes three stages, the first stage


12


; the second stage


20


, also including a number of circumferentially spaced nozzle vanes


22


and a number of circumferentially spaced buckets


24


mounted on a second stage wheel


26


; and a third stage


28


also including a number of circumferentially spaced nozzle vanes


30


and a number of circumferentially spaced buckets


32


mounted on a third stage wheel


34


. It will be appreciated that the nozzle vanes and buckets lie in the hot gas path of the turbine. The gases flow through the turbine


10


in the direction of the arrow


36


.




Referring to

FIGS. 2

,


3


, and


4


, the nozzle vanes


14


of the first stage


12


are disposed between inner and outer sidewalls


38


and


40


, respectively, by which the nozzles


12


form an annulus about the rotor axis. As illustrated, the nozzle vanes


14


have leading and trailing edges


42


and


44


, respectively, with hooks


46


and


48


for securing the nozzle vane segments to the nonrotatable casing of the turbine. As will be appreciated, the nozzle vanes


14


have various passages therethrough for flowing a cooling medium through the vanes. In the preferred and illustrated embodiment of the first stage nozzle


12


for this particular turbine, there are thirty two (


32


) nozzles vanes


14


mounted on the first stage nozzle arrangement.




Referring now to

FIG. 5

, there is illustrated a nozzle vane


14


for the first stage constructed in accordance with a three dimensional compound curvature. A Cartesian coordinate system of X, Y and Z values given in Table 1 defines the profile of nozzle airfoil. The coordinate values for the X and Y coordinates are set forth in inches in Table 1 although other units of dimensions may be used. The Z values are set forth in Table 1 in nondimensional form from 0 to 1 along a nozzle stacking axis


50


coincident with a radius


52


from the turbine axis of rotation


54


.




To convert the Z value to a Z coordinate value, e.g., in inches, from the turbine axis of rotation


54


, the nondimensional Z value given in the table is multiplied by the height of the airfoil


14


in inches and that product is added to a root radius


56


in inches. The airfoil


14


height is measured from the intersection of the nozzle stacking axis


50


, which is along the radius


52


from the centerline or axis of the turbine


54


, and the root radius


56


of the defined airfoil geometry. The root radius


56


extends along the base of the vane


14


from the nozzle stacking line


50


. The Z coordinate value of this intersection with the root radius


56


for each nozzle vane


14


of the first stage


12


in a preferred embodiment is approximately 21.25 inches. The height of the first stage airfoil nozzle vane


14


from the root radius


56


in this preferred embodiment is approximately 4.275 inches. The Cartesian coordinate system has orthogonally related X, Y and Z axes with the Z axis extending perpendicular to a plane normal to a plane containing the X and Y values. When converted to inches, the Z distance commences at 0 at the turbine centerline. The Y axis lies parallel to the turbine rotor centerline, i.e., the rotary axis


54


.




By defining X and Y coordinate values at selected locations in a Z direction normal to the X, Y plane, the profile of the airfoil


14


can be ascertained. By connecting the X and Y values with smooth continuing arcs, each profile section at each distance Z is fixed. The surface profiles of the various surface locations between the distances Z are determined by smoothly connecting the adjacent crosssections to one another to form the airfoil surface. These values represent the airfoil profiles at ambient, nonoperating or nonhot conditions and are for an uncoated airfoil. The sign convention assigns a positive value to Z values and positive and negative values for the X and Y coordinates as typically used in Cartesian coordinate systems.




The Table 1 values are generated and shown to three decimal places for determining the profile of the airfoil


14


. There are typical manufacturing tolerances as well as coatings, which must be accounted for in the actual profile of the airfoil


14


. Accordingly, the values for the profile given in Table 1 are for a nominal airfoil. It will therefore be appreciated that plus or minus typical manufacturing tolerances, i.e. plus or minus values, including any coating thicknesses, are additive to the X and Y values given in Table 1 below. Accordingly, a distance of ±0.160 inches in a direction normal to any surface location along the airfoil profile defines an airfoil profile envelope for this particular nozzle airfoil design and turbine.




Table 1: The coordinate values given below provide the preferred nominal profile envelope.

















X




Y




Z′

























−2.301




−4.340




0.000






−2.702




−3.689




0.000






−2.583




−4.160




0.000






−2.595




−3.462




0.000






−1.542




−4.320




0.000






−2.225




−4.378




0.000






−2.521




−4.218




0.000






−1.442




−4.184




0.000






−2.675




−4.020




0.000






−1.991




−4.473




0.000






−2.640




−3.533




0.000






−2.635




−4.094




0.000






−1.230




−3.820




0.000






−2.149




−4.414




0.000






−1.909




−4.488




0.000






−2.452




−4.265




0.000






−2.716




−3.857




0.000






−1.271




−3.894




0.000






−2.072




−4.447




0.000






−1.600




−4.381




0.000






−1.742




−4.469




0.000






−1.824




−4.488




0.000






−2.546




−3.393




0.000






−1.397




−4.113




0.000






−2.702




−3.940




0.000






−2.716




−3.773




0.000






−1.667




−4.432




0.000






−1.353




−4.041




0.000






−2.677




−3.609




0.000






−2.377




−4.303




0.000






−1.312




−3.967




0.000






−1.490




−4.254




0.000






−1.835




−2.563




0.000






−1.150




−3.671




0.000






−2.346




−3.122




0.000






−1.899




−2.618




0.000






−2.295




−3.055




0.000






−1.110




−3.597




0.000






−0.825




−3.080




0.000






−1.632




−2.412




0.000






−0.948




−3.301




0.000






−0.989




−3.375




0.000






−0.699




−2.861




0.000






−0.907




−3.227




0.000






−1.961




−2.675




0.000






−2.134




−2.859




0.000






−2.397




−3.189




0.000






−0.866




−3.153




0.000






−1.701




−2.460




0.000






−0.783




−3.007




0.000






−2.242




−2.989




0.000






−1.029




−3.449




0.000






−2.447




−3.257




0.000






−2.078




−2.796




0.000






−1.769




−2.510




0.000






−2.497




−3.325




0.000






−2.020




−2.735




0.000






−1.070




−3.523




0.000






−0.613




−2.715




0.000






−1.190




−3.745




0.000






−2.189




−2.923




0.000






−0.656




−2.788




0.000






−0.741




−2.934




0.000






−0.130




−1.480




0.000






−0.440




−2.426




0.000






−0.396




−2.353




0.000






−0.464




−1.737




0.000






−0.535




−1.784




0.000






−0.570




−2.643




0.000






−0.308




−2.210




0.000






−0.264




−2.138




0.000






−0.067




−1.424




0.000






−1.122




−2.116




0.000






−0.220




−2.066




0.000






−0.175




−1.995




0.000






0.130




−1.923




0.000






−0.041




−1.780




0.000






0.004




−1.709




0.000






−0.824




−1.956




0.000






−1.562




−2.365




0.000






−0.751




−1.915




0.000






0.049




−1.637




0.000






−0.898




−1.997




0.000






−0.194




−1.535




0.000






−1.047




−2.076




0.000






0.094




−1.566




0.000






0.140




−1.495




0.000






0.972




−2.037




0.000






0.185




−1.424




0.000






−1.417




−2.278




0.000






−1.196




−2.155




0.000






−0.527




−2.570




0.000






−0.395




−1.689




0.000






−0.606




−1.829




0.000






−0.484




−2.498




0.000






−0.327




−1.639




0.000






−0.260




−1.588




0.000






−1.490




−2.321




0.000






−0.353




−2.281




0.000






−0.005




−1.367




0.000






−1.270




−2.196




0.000






−0.678




−1.872




0.000






−1.344




−2.236




0.000






−0.086




−1.852




0.000






0.116




−1.249




0.000






0.500




−0.925




0.000






0.347




−1.004




0.000






0.459




−0.879




0.000






0.175




−1.189




0.000






0.402




−0.940




0.000






0.320




−1.210




0.000






0.233




−1.128




0.000






0.230




−1.352




0.000






0.275




−1.281




0.000






0.365




−1.139




0.000






0.056




−1.309




0.000






0.410




−1.067




0.000






0.455




−0.996




0.000






0.500




−0.925




0.000






0.291




−1.066




0.000






−1.178




−3.966




0.111






−2.219




−4.499




0.111






−2.135




−4.523




0.111






−2.301




−4.470




0.111






−2.642




−4.213




0.111






−2.049




−4.540




0.111






−2.693




−3.793




0.111






−1.963




−4.550




0.111






−2.591




−4.283




0.111






−1.875




−4.551




0.111






−1.789




−4.542




0.111






−2.529




−4.344




0.111






−1.704




−4.521




0.111






−2.458




−4.395




0.111






−1.624




−4.488




0.111






−2.512




−3.498




0.111






−2.381




−4.436




0.111






−1.549




−4.443




0.111






−1.480




−4.389




0.111






−1.310




−4.191




0.111






−2.567




−3.566




0.111






−1.418




−4.328




0.111






−2.619




−3.636




0.111






−2.662




−3.711




0.111






−1.362




−4.262




0.111






−1.219




−4.043




0.111






−2.712




−3.878




0.111






−1.263




−4.118




0.111






−2.716




−3.965




0.111






−2.706




−4.051




0.111






−2.681




−4.135




0.111






−1.138




−3.888




0.111






−0.894




−3.329




0.111






−1.064




−3.730




0.111






−1.624




−2.538




0.111






−0.994




−3.570




0.111






−0.961




−3.493




0.111






−0.927




−3.409




0.111






−1.688




−2.598




0.111






−1.751




−2.659




0.111






−0.861




−3.248




0.111






−0.829




−3.167




0.111






−0.796




−3.056




0.111






−1.813




−2.720




0.111






−1.874




−2.782




0.111






−0.731




−2.924




0.111






−1.101




−3.809




0.111






−1.995




−2.907




0.111






−2.055




−2.971




0.111






−2.114




−3.035




0.111






−2.172




−3.100




0.111






−2.230




−3.165




0.111






−1.935




−2.844




0.111






−2.288




−3.231




0.111






−2.345




−3.297




0.111






−2.401




−3.363




0.111






−2.457




−3.430




0.111






−0.698




−2.844




0.111






−0.763




−3.005




0.111






−1.029




−3.650




0.111






−0.534




−1.535




0.111






−0.594




−1.599




0.111






−1.560




−2.479




0.111






−0.655




−1.661




0.111






−0.716




−1.723




0.111






−1.431




−2.363




0.111






−0.842




−1.843




0.111






−0.907




−1.902




0.111






−0.332




−1.957




0.111






−0.971




−1.961




0.111






−0.665




−2.763




0.111






−0.779




−1.783




0.111






−1.037




−2.019




0.111






−1.102




−2.076




0.111






−0.632




−2.682




0.111






−0.599




−2.601




0.111






−0.566




−2.521




0.111






−0.533




−2.440




0.111






−0.500




−2.359




0.111






−0.467




−2.279




0.111






−1.168




−2.133




0.111






−1.234




−2.191




0.111






−0.433




−2.198




0.111






−0.400




−2.118




0.111






−0.366




−2.037




0.111






−0.298




−1.876




0.111






−0.230




−1.716




0.111






−0.196




−1.636




0.111






−1.299




−2.248




0.111






−0.162




−1.555




0.111






−0.128




−1.475




0.111






−1.365




−2.305




0.111






−0.264




−1.796




0.111






−1.496




−2.421




0.111






−0.418




−1.405




0.111






−0.476




−1.470




0.111






0.100




−0.704




0.111






0.052




−0.777




0.111






0.192




−0.556




0.111






−0.046




−0.921




0.111






0.242




−0.590




0.111






0.004




−0.850




0.111






−0.096




−0.992




0.111






−0.148




−1.063




0.111






−0.200




−1.133




0.111






−0.253




−1.202




0.111






0.109




−0.912




0.111






−0.094




−1.395




0.111






−0.060




−1.314




0.111






−0.307




−1.270




0.111






−0.026




−1.234




0.111






0.008




−1.154




0.111






0.041




−1.073




0.111






0.145




−0.630




0.111






0.075




−0.993




0.111






0.142




−0.832




0.111






0.176




−0.751




0.111






0.209




−0.671




0.111






0.242




−0.590




0.111






−0.362




−1.338




0.111






−1.675




−4.612




0.222






−1.764




−4.635




0.222






−1.591




−4.576




0.222






−1.314




−4.341




0.222






−1.259




−4.268




0.222






−1.078




−3.950




0.222






−1.374




−4.410




0.222






−1.440




−4.474




0.222






−1.209




−4.191




0.222






−1.119




−4.032




0.222






−1.162




−4.113




0.222






−1.512




−4.530




0.222






−0.937




−3.612




0.222






−0.710




−2.915




0.222






−0.789




−3.178




0.222






−1.004




−3.782




0.222






−1.506




−2.567




0.222






−1.566




−2.636




0.222






−1.627




−2.704




0.222






−0.685




−2.827




0.222






−1.040




−3.866




0.222






−0.905




−3.526




0.222






−0.845




−3.353




0.222






−0.817




−3.266




0.222






−0.969




−3.697




0.222






−0.736




−3.003




0.222






−0.875




−3.440




0.222






−0.763




−3.091




0.222






−2.604




−4.368




0.222






−1.855




−4.646




0.222






−2.515




−3.629




0.222






−2.713




−4.120




0.222






−2.453




−3.562




0.222






−2.577




−3.697




0.222






−2.631




−3.770




0.222






−2.674




−3.851




0.222






−2.703




−3.938




0.222






−2.716




−4.028




0.222






−2.692




−4.209




0.222






−2.655




−4.293




0.222






−2.467




−4.489




0.222






−2.387




−4.533




0.222






−2.540




−4.434




0.222






−2.303




−4.570




0.222






−2.216




−4.599




0.222






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1.000






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1.000






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1.000






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1.000






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1.000






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1.000






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1.000






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1.000






0.011




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1.000






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1.000






−0.007




−0.700




1.000






−0.247




−0.872




1.000






−0.292




−0.970




1.000














It also will be appreciated that the airfoil disclosed in Table 1 may be scaled up or down geometrically for use in similar turbine designs. Consequently, the coordinate values set forth in Table 1 may be scaled upwardly or downwardly such that the airfoil section shape remains unchanged. A scaled version of the coordinates in Table 1 would be represented by X, Y and, optionally, Z coordinate values (after the Z values have been converted to inches) multiplied or divided by the same constant or number.




It should be apparent that the foregoing relates only to the preferred embodiments of the present invention and that numerous changes and modifications may be made herein without departing from the spirit and scope of the invention as defined by the following claims and equivalents thereof.



Claims
  • 1. A turbine nozzle comprising an airfoil shape in an envelope within ±0.160 inches in a direction normal to any airfoil surface location wherein the airfoil comprises a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1, wherein the Z coordinate comprises a nondimensional value along a nozzle stacking line coincident with a radius from a turbine axis of rotation and convertible to a Z distance in inches by multiplying the Z value by a height of the airfoil and adding that product to a root radius of the nozzle, and wherein X and Y comprise distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape.
  • 2. The turbine nozzle according to claim 1, wherein X and Y comprise distances being scalable as a function of the same constant or number to provide a scaled up or scaled down nozzle airfoil.
  • 3. A turbine nozzle according to claim 1 forming part of a first stage of a turbine.
  • 4. A turbine nozzle according to claim 1, wherein the Z value is measured from an intersection of a nozzle centerline along the radius from the turbine axis and the root radius of a flowpath through the turbine.
  • 5. A turbine nozzle according to claim 1, wherein the root radius of the nozzle airfoil comprises approximately 21.25 inches and the airfoil comprises a height from the root radius of approximately 4.275 inches.
  • 6. A turbine nozzle comprising an airfoil shape with an uncoated nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1, wherein Z comprises a nondimensional value along a nozzle stacking axis coincident with a radius from a turbine axis of rotation and convertible to a Z distance in inches from said turbine axis by multiplying the Z value by a height of the airfoil and adding that product to a root radius of the nozzle, wherein X and Y comprise distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape.
  • 7. The turbine nozzle according to claim 6, wherein X and Y comprise distances being scalable as a function of the same constant or number to provide a scaled up or scaled down nozzle airfoil.
  • 8. A turbine nozzle according to claim 6 forming part of a first stage of a turbine.
  • 9. A turbine nozzle according to claim 6, wherein the root radius of the nozzle airfoil comprises approximately 21.25 inches and the airfoil comprises a height from the root radius of approximately 4.275 inches.
  • 10. A turbine comprising a nozzle arrangement comprising a plurality of nozzles, with each nozzle comprising an airfoil shape in an envelope within ±0.160 inches in a direction normal to any airfoil surface location wherein the airfoil comprises a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1, wherein the Z coordinate comprises a nondimensional value along a nozzle stacking axis coincident with a radius from a turbine axis of rotation convertible to a Z distance in inches from said turbine axis by multiplying the Z value by a height of the airfoil and adding that product to a root radius of the nozzle, and wherein the X and Y values comprise distances in inches defining the airfoil profile at each distance Z, the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape.
  • 11. The turbine according to claim 10, wherein X and Y comprise distances being scalable as a function of the same constant or number to provide a scaled up or scaled down nozzle airfoil.
  • 12. A turbine according to claim 10 wherein the turbine comprises a first stage of a turbine.
  • 13. A turbine according to claim 10, wherein the turbine comprises approximately 32 nozzles and Y represents a distance parallel to the turbine axis of rotation.
  • 14. A turbine according to claim 10, wherein the root radius of the nozzle airfoil comprises approximately 21.25 inches and the airfoil comprises a height from the root radius of approximately 4.275 inches.
  • 15. A turbine comprising a nozzle arrangement comprising a plurality of nozzles, each of said nozzles comprising an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1, wherein the Z coordinate comprises a nondimensional value along a nozzle stacking axis coincident with a radius from a turbine axis of rotation convertible to a Z distance in inches from said turbine axis of rotation by multiplying the Z value by a height of the airfoil and adding that product to a root radius of the nozzle, wherein X and Y comprises distances in inches defining the airfoil profile at each distance Z, and the profiles at the Z distances being joined smoothly with one another to form a complete airfoil shape.
  • 16. The turbine according to claim 15, wherein X and Y comprise distances being scalable as a function of the same constant or number to provide a scaled up or scaled down nozzle airfoil.
  • 17. A turbine according to claim 15, wherein the nozzle arrangement comprises a first stage of a turbine.
  • 18. A turbine according to claim 15, wherein the nozzle arrangement comprises approximately thirty two (32) nozzles and Y comprises a distance parallel to the turbine axis of rotation.
  • 19. A turbine according to claim 15, wherein the root radius of the nozzle airfoil comprises approximately 21.25 inches and the airfoil comprises a height from the root radius of approximately 4.275 inches.
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