Internal core profile for a turbine nozzle airfoil

Abstract

First stage nozzle airfoils have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X, Y and Z values are in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each radial distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.030 inches in directions normal to any internal core surface location.

Description

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

Many system requirements must be met for each stage of the hot gas path section of a gas turbine in order to meet design goals. Particularly, the nozzle segments of the first stage of the turbine section must meet the operating requirements for that particular stage and also meet requirements for nozzle airfoil cooling flow efficiency, life and wall thickness distribution.

BACKGROUND OF THE INVENTION

In accordance with a preferred embodiment of the present invention, there is provided a unique internal core profile for a nozzle airfoil of a gas turbine, preferably the first stage nozzle, which enhances the performance of the gas turbine. It will be appreciated that the external shape of the nozzle airfoil improves its interaction with the buckets forming the stages of the turbine. Concomitantly the internal core profile shape of the nozzle airfoil is also significant for structural reasons as well as to optimize internal cooling with appropriate wall thickness. The nozzle airfoil internal core profile is defined by a unique loci of points which achieve the necessary structural and cooling requirements whereby improved turbine performance is obtained. This unique loci of points define the internal nominal core profile and are identified by the X, Y and Z Cartesian coordinates of Table I which follows. The 1,200 points for the coordinate values shown in Table I are for a cold, i.e., room temperature nozzle airfoil at various cross-sections of the nozzle airfoil along its length. The positive X, Y and Z directions are axial toward the exhaust end of the turbine, tangential in the direction of engine rotation looking aft and radially outwardly toward the outer platform, respectively. 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 internal core profile cross-section. The Z coordinates are given in inches in distances along radii from the turbine axis. Each internal core profile section in the X, Y plane is joined smoothly with the adjacent profile sections in the Z direction to form, using the Table I coordinate values, the complete internal nozzle airfoil core profile.

Table I provides coordinate values for the complete internal core airfoil shape passing through the inner and outer platforms and the airfoil therebetween. The physical shape of the internal core profile between the inner and outer platforms is given in Table I by the airfoil sections defined between Z value limits of 22.200 and 25.050.

It will be appreciated that as each nozzle airfoil heats up in use, the internal core profile will change. Thus, the cold or room temperature profile is given by the X, Y and Z coordinates for manufacturing purposes. Because a manufactured internal nozzle airfoil core profile may be different from the nominal profile given by the following table, a distance of ±0.030 inches from the nominal profile in a direction normal to any surface location along the nominal profile defines a profile envelope for this internal nozzle airfoil core profile. The profile is robust to this variation without impairment of the mechanical cooling and aerodynamic functions of the airfoil.

In accordance with a preferred embodiment of the present invention, there is provided a turbine nozzle segment including inner and outer platforms and an airfoil extending between the platforms, the airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein the Z values between the limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between said Z value limits, the profile sections at the Z distances between the limits being joined smoothly with one another to form the airfoil internal core profile.

In accordance with a further embodiment of the present invention, there is provided a turbine comprising a plurality of nozzle segments arranged in a circumferential array about an axis of the turbine, each nozzle segment including inner and outer platforms and at least one airfoil extending between the platforms, each airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein said Z values between the limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between the Z value limits, the profile sections at the Z distances between the limits being joined smoothly with one another to form the airfoil internal core profile.

In accordance with a further embodiment of the present invention, there is provided a turbine nozzle segment including inner and outer platforms and an airfoil extending between the platforms, the airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the airfoil internal core profile.

In accordance with another embodiment of the present invention, there is provided a turbine comprising a plurality of nozzle segments in a circumferential array about an axis of the turbine, each segment having inner and outer platforms and at least one airfoil extending between the platforms, each airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from the turbine axis to planes extending normal to the radii, and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form the airfoil internal core profile.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic representation of a hot gas path through multiple stages of a gas turbine and illustrates a first stage nozzle airfoil according to a preferred embodiment of the present invention;

FIG. 2 is a perspective view of a nozzle segment with an internal nozzle airfoil core profile depicted in full lines according to a preferred embodiment of the present invention with the nozzle airfoil shown in conjunction with inner and outer platforms and remaining portions of the nozzle airfoil illustrated by the dashed lines;

FIG. 3 is a circumferential perspective view of the nozzle airfoil internal core profile of FIG. 2 and associated airfoil and platforms;

FIG. 4 is a perspective view from above the outer platform of the internal core profile including the associated airfoil and platform; and

FIG. 5 is a cross-sectional view of the nozzle airfoil taken generally about on line 5-5 in FIG. 3.

DETAILED DESCRIPTION OF THE INVENTION

Referring now to the drawings, particularly to FIG. 1, there is illustrated a hot gas path, generally designated 10, of a gas turbine 12 including a plurality of turbine stages. Three stages are illustrated. For example, the first stage comprises a plurality of circumferentially spaced nozzles 14 and buckets 16. The nozzles 14 are circumferentially spaced one from the other and fixed about the axis of the rotor. First stage buckets 16 are mounted on the turbine rotor 17. A second stage of the turbine 12 is also illustrated, including a plurality of circumferentially spaced nozzles 18 and a plurality of circumferentially spaced buckets 20 mounted on the rotor 17. The third stage is also illustrated including a plurality of circumferentially spaced nozzles 22 and buckets 24 mounted on rotor 17. It will be appreciated that the nozzles and buckets lie in the hot gas path 10 of the turbine, the direction of flow of the hot gas through the hot gas path 10 being indicated by the arrow 26.

Referring now to FIG. 2, there is illustrated a nozzle segment generally designated 30 in which one or more airfoils 32 are disposed between inner and outer platforms 34 and 36, respectively. It will be appreciated that a plurality of nozzle segments 30 are disposed in a circumferential array about the turbine axis to form an annular flow path with the airfoils 32 guiding the hot gas to the follow-on buckets of the stage, e.g., the first stage buckets 16. The vanes 32 of the nozzle segments 30 are cooled by flowing air internally within the airfoils 32 and between the inner and outer platforms 34 and 36, respectively.

The internal core shape of the nozzle airfoil is indicated by the full lines 38 in the drawing figures. In FIG. 5, the internal core shape 38 is in the general form of an airfoil having internal wall surfaces 40 and 42 adjacent suction and pressure external surfaces of the airfoil, respectively, which, with the internal core profile 38, define an airfoil wall thickness t. The internal core profile extends through the inner and outer platforms 34 and 36.

To define the internal core shape of each nozzle airfoil including within the inner and outer platforms, there is provided a unique set of loci of points in space that meet the stage requirements, cooling areas, wall thickness, and can be manufactured. This unique loci of points which define the internal nozzle airfoil core profile 38 comprises a set of 1,200 points relative to the axis of rotation of the turbine. A Cartesian coordinate system of X, Y and Z values given in Table I below define this internal core profile 38 of the nozzle airfoil at various locations along its length. The coordinate values for the X and Y coordinates are set forth in inches in Table I although other units of dimensions may be used when the values are appropriately converted. The Z values set forth in Table I are radial distances from a turbine axis to planes extending normal to the radii. The Cartesian coordinate system has orthogonally related X, Y and Z axes and the X axis lies parallel to the turbine rotor center line, i.e., the rotary axis, and a positive x coordinate value is axial toward the aft, i.e., exhaust end of the turbine. The positive Y coordinate value extends tangentially in the direction of rotation of the rotor, looking aft, and the positive Z coordinate value is radially outwardly toward the outer platform.

By defining X and Y coordinate values at selected locations in a Z direction normal to the X, Y plane, the internal core profile 38 of the nozzle airfoil representatively illustrated by the full lines in the drawing figures, at each Z distance along the length of the nozzle airfoil can be ascertained. By connecting the X and Y values with smooth continuing arcs, each internal core profile section 38 at each distance Z is fixed. The internal core profiles of the various internal locations between the distances Z are determined by smoothly connecting the adjacent profile sections 38 to one another to form the core profile. These values represent the internal core profiles at ambient non-operating or non-hot conditions.

The Table I values are generated and shown to three decimal places for determining the internal core profile of the nozzle airfoil. There are typical manufacturing tolerances as well as coatings which must be accounted for in the actual internal profile of the nozzle airfoil. Accordingly, the values for the profile given in Table I are for a nominal internal nozzle airfoil core profile. It will therefore be appreciated that ±typical manufacturing tolerances, i.e., ±values, including any coating thicknesses, are additive to the X and Y values given in Table I below. Accordingly, a distance of ±0.030 inches in a direction normal to any surface location along the internal core profile defines an internal core profile envelope for this particular nozzle airfoil design and turbine, i.e., a range of variation between measured points on the actual internal core profile at nominal cold or room temperature and the ideal position of those points as given in Table I below at the same temperature. The internal core profile is robust to this range of variation without impairment of mechanical and cooling functions.

The Table I values below provide the X, Y, Z Cartesian values for the internal core of the airfoil including through the inner and outer platforms. The physical configuration of the internal core profile between the inner and outer platforms is provided by Table I between Z value limits of 22.200 and 25.050. These Z value limits commence radially outwardly of the inner platform and radially inwardly of the outer platform, respectively and define the physical shape of the internal core profile between those limits.

The coordinate values given in Table I below provide the preferred nominal internal core profile envelope through the nozzle airfoil including through the inner and outer platforms.

X	Y	Z	X	Y	Z	X	Y	Z
−0.582	−2.413	21.250	−1.406	−3.884	21.250	−2.385	−3.350	21.250
−0.587	−2.466	21.250	−1.412	−2.397	21.250	−2.391	−4.162	21.250
−0.591	−2.361	21.250	−1.433	−3.930	21.250	−2.417	−3.392	21.250
−0.604	−2.516	21.250	−1.458	−2.423	21.250	−2.435	−4.134	21.250
−0.611	−2.312	21.250	−1.459	−3.976	21.250	−2.448	−3.435	21.250
−0.632	−2.560	21.250	−1.486	−4.021	21.250	−2.475	−4.099	21.250
−0.641	−2.269	21.250	−1.504	−2.449	21.250	−2.479	−3.478	21.250
−0.662	−2.604	21.250	−1.514	−4.067	21.250	−2.510	−4.059	21.250
−0.679	−2.233	21.250	−1.542	−4.111	21.250	−2.510	−3.520	21.250
−0.692	−2.648	21.250	−1.549	−2.476	21.250	−2.539	−4.015	21.250
−0.721	−2.692	21.250	−1.571	−4.155	21.250	−2.540	−3.564	21.250
−0.724	−2.205	21.250	−1.594	−2.505	21.250	−2.562	−3.967	21.250
−0.750	−2.736	21.250	−1.602	−4.199	21.250	−2.567	−3.610	21.250
−0.773	−2.185	21.250	−1.634	−4.241	21.250	−2.581	−3.918	21.250
−0.779	−2.781	21.250	−1.638	−2.534	21.250	−2.588	−3.658	21.250
−0.807	−2.826	21.250	−1.669	−4.280	21.250	−2.588	−3.658	21.250
−0.825	−2.174	21.250	−1.681	−2.565	21.250	−2.595	−3.867	21.250
−0.834	−2.871	21.250	−1.708	−4.316	21.250	−2.602	−3.709	21.250
−0.862	−2.916	21.250	−1.723	−2.597	21.250	−2.604	−3.815	21.250
−0.877	−2.173	21.250	−1.752	−4.345	21.250	−2.607	−3.762	21.250
−0.889	−2.961	21.250	−1.764	−2.630	21.250	−0.555	−2.141	21.725
−0.916	−3.007	21.250	−1.801	−4.364	21.250	−0.564	−2.197	21.725
−0.930	−2.181	21.250	−1.804	−2.665	21.250	−0.565	−2.086	21.725
−0.943	−3.052	21.250	−1.843	−2.701	21.250	−0.585	−2.250	21.725
−0.970	−3.098	21.250	−1.853	−4.372	21.250	−0.594	−2.037	21.725
−0.980	−2.198	21.250	−1.880	−2.738	21.250	−0.607	−2.303	21.725
−0.997	−3.143	21.250	−1.906	−4.369	21.250	−0.628	−2.355	21.725
−1.023	−3.189	21.250	−1.917	−2.776	21.250	−0.637	−2.000	21.725
−1.028	−2.219	21.250	−1.953	−2.815	21.250	−0.649	−2.408	21.725
−1.050	−3.235	21.250	−1.958	−4.359	21.250	−0.671	−2.461	21.725
−1.076	−3.281	21.250	−1.989	−2.854	21.250	−0.688	−1.975	21.725
−1.077	−2.239	21.250	−2.008	−4.343	21.250	−0.692	−2.513	21.725
−1.101	−3.327	21.250	−2.024	−2.894	21.250	−0.714	−2.566	21.725
−1.126	−2.260	21.250	−2.058	−4.324	21.250	−0.735	−2.619	21.725
−1.127	−3.374	21.250	−2.059	−2.933	21.250	−0.744	−1.966	21.725
−1.152	−3.421	21.250	−2.093	−2.974	21.250	−0.757	−2.671	21.725
−1.174	−2.281	21.250	−2.106	−4.302	21.250	−0.778	−2.724	21.725
−1.177	−3.467	21.250	−2.127	−3.015	21.250	−0.800	−2.777	21.725
−1.202	−3.514	21.250	−2.154	−4.279	21.250	−0.800	−1.972	21.725
−1.222	−2.303	21.250	−2.160	−3.056	21.250	−0.821	−2.829	21.725
−1.227	−3.560	21.250	−2.193	−3.097	21.250	−0.842	−2.882	21.725
−1.252	−3.607	21.250	−2.201	−4.255	21.250	−0.853	−1.993	21.725
−1.270	−2.326	21.250	−2.226	−3.139	21.250	−0.864	−2.935	21.725
−1.278	−3.653	21.250	−2.248	−4.231	21.250	−0.885	−2.987	21.725
−1.303	−3.699	21.250	−2.258	−3.180	21.250	−0.897	−2.028	21.725
−1.318	−2.349	21.250	−2.290	−3.223	21.250	−0.907	−3.040	21.725
−1.329	−3.746	21.250	−2.295	−4.208	21.250	−0.928	−3.093	21.725
−0.983	−2.103	21.725	−1.899	−2.955	21.725	−0.678	−2.351	22.200
−0.993	−3.251	21.725	−1.919	−4.432	21.725	−0.682	−1.761	22.200
−1.014	−3.303	21.725	−1.938	−2.996	21.725	−0.694	−2.411	22.200
−1.026	−2.141	21.725	−1.976	−4.429	21.725	−0.710	−2.470	22.200
−1.036	−3.356	21.725	−1.977	−3.038	21.725	−0.726	−2.529	22.200
−1.058	−3.408	21.725	−2.015	−3.080	21.725	−0.742	−2.588	22.200
−1.069	−2.178	21.725	−2.032	−4.421	21.725	−0.742	−1.768	22.200
−1.080	−3.461	21.725	−2.054	−3.122	21.725	−0.758	−2.647	22.200
−1.102	−3.513	21.725	−2.088	−4.410	21.725	−0.775	−2.706	22.200
−1.112	−2.215	21.725	−2.092	−3.164	21.725	−0.791	−2.765	22.200
−1.125	−3.565	21.725	−2.130	−3.206	21.725	−0.794	−1.799	22.200
−1.148	−3.618	21.725	−2.143	−4.395	21.725	−0.808	−2.824	22.200
−1.155	−2.253	21.725	−2.168	−3.248	21.725	−0.825	−2.883	22.200
−1.171	−3.670	21.725	−2.197	−4.378	21.725	−0.831	−1.848	22.200
−1.194	−3.721	21.725	−2.206	−3.291	21.725	−0.842	−2.942	22.200
−1.198	−2.290	21.725	−2.243	−3.334	21.725	−0.859	−3.000	22.200
−1.218	−3.773	21.725	−2.250	−4.358	21.725	−0.865	−1.899	22.200
−1.240	−2.327	21.725	−2.280	−3.377	21.725	−0.877	−3.059	22.200
−1.243	−3.824	21.725	−2.303	−4.337	21.725	−0.895	−3.118	22.200
−1.268	−3.875	21.725	−2.317	−3.420	21.725	−0.900	−1.949	22.200
−1.283	−2.365	21.725	−2.354	−3.464	21.725	−0.913	−3.176	22.200
−1.294	−3.926	21.725	−2.354	−4.313	21.725	−0.931	−3.235	22.200
−1.321	−3.976	21.725	−2.390	−3.507	21.725	−0.936	−1.999	22.200
−1.326	−2.403	21.725	−2.404	−4.285	21.725	−0.950	−3.293	22.200
−1.350	−4.025	21.725	−2.426	−3.551	21.725	−0.969	−3.351	22.200
−1.368	−2.440	21.725	−2.450	−4.252	21.725	−0.971	−2.049	22.200
−1.379	−4.074	21.725	−2.450	−4.252	21.725	−0.989	−3.409	22.200
−1.410	−4.121	21.725	−2.463	−3.595	21.725	−1.007	−2.099	22.200
−1.411	−2.478	21.725	−2.491	−4.213	21.725	−1.009	−3.467	22.200
−1.443	−4.168	21.725	−2.498	−3.639	21.725	−1.030	−3.524	22.200
−1.453	−2.517	21.725	−2.525	−4.167	21.725	−1.043	−2.148	22.200
−1.478	−4.212	21.725	−2.532	−3.685	21.725	−1.051	−3.582	22.200
−1.494	−2.555	21.725	−2.552	−4.117	21.725	−1.073	−3.639	22.200
−1.516	−4.255	21.725	−2.562	−3.733	21.725	−1.080	−2.197	22.200
−1.536	−2.594	21.725	−2.574	−4.064	21.725	−1.096	−3.696	22.200
−1.556	−4.295	21.725	−2.585	−3.785	21.725	−1.117	−2.246	22.200
−1.577	−2.633	21.725	−2.589	−4.010	21.725	−1.119	−3.753	22.200
−1.600	−4.331	21.725	−2.599	−3.840	21.725	−1.143	−3.809	22.200
−1.618	−2.672	21.725	−2.599	−3.954	21.725	−1.155	−2.294	22.200
−1.647	−4.363	21.725	−2.603	−3.897	21.725	−1.168	−3.865	22.200
−1.659	−2.712	21.725	−0.559	−1.877	22.200	−1.192	−2.343	22.200
−1.697	−4.390	21.725	−0.568	−1.937	22.200	−1.195	−3.920	22.200
−1.700	−2.752	21.725	−0.579	−1.820	22.200	−1.222	−3.975	22.200
−1.740	−2.792	21.725	−0.584	−1.996	22.200	−1.230	−2.391	22.200
−1.750	−4.410	21.725	−0.599	−2.055	22.200	−1.251	−4.029	22.200
−1.780	−2.832	21.725	−0.615	−2.115	22.200	−1.269	−2.438	22.200
−1.806	−4.424	21.725	−0.624	−1.779	22.200	−1.281	−4.082	22.200
−1.346	−4.186	22.200	−2.509	−4.296	22.200	−1.017	−2.034	22.675
−1.382	−4.235	22.200	−2.520	−3.783	22.200	−1.023	−3.527	22.675
−1.386	−2.580	22.200	−2.542	−4.244	22.200	−1.043	−3.590	22.675
−1.420	−4.283	22.200	−2.554	−3.833	22.200	−1.049	−2.092	22.675
−1.425	−2.627	22.200	−2.567	−4.189	22.200	−1.064	−3.652	22.675
−1.461	−4.329	22.200	−2.581	−3.888	22.200	−1.082	−2.149	22.675
−1.465	−2.673	22.200	−2.585	−4.130	22.200	−1.086	−3.714	22.675
−1.505	−4.371	22.200	−2.596	−3.948	22.200	−1.108	−3.776	22.675
−1.506	−2.719	22.200	−2.596	−4.070	22.200	−1.116	−2.205	22.675
−1.546	−2.765	22.200	−2.601	−4.009	22.200	−1.132	−3.838	22.675
−1.553	−4.410	22.200	−0.578	−1.672	22.675	−1.150	−2.262	22.675
−1.587	−2.811	22.200	−0.590	−1.609	22.675	−1.156	−3.899	22.675
−1.603	−4.444	22.200	−0.591	−1.737	22.675	−1.181	−3.960	22.675
−1.629	−2.856	22.200	−0.604	−1.801	22.675	−1.184	−2.318	22.675
−1.658	−4.473	22.200	−0.617	−1.866	22.675	−1.208	−4.020	22.675
−1.670	−2.901	22.200	−0.630	−1.930	22.675	−1.219	−2.374	22.675
−1.712	−2.945	22.200	−0.638	−1.564	22.675	−1.236	−4.080	22.675
−1.715	−4.496	22.200	−0.643	−1.995	22.675	−1.254	−2.429	22.675
−1.754	−2.990	22.200	−0.656	−2.059	22.675	−1.265	−4.139	22.675
−1.774	−4.512	22.200	−0.670	−2.124	22.675	−1.290	−2.485	22.675
−1.796	−3.034	22.200	−0.683	−2.188	22.675	−1.296	−4.197	22.675
−1.834	−4.521	22.200	−0.697	−2.252	22.675	−1.326	−2.540	22.675
−1.839	−3.078	22.200	−0.701	−1.552	22.675	−1.328	−4.254	22.675
−1.882	−3.122	22.200	−0.711	−2.317	22.675	−1.363	−2.594	22.675
−1.895	−4.525	22.200	−0.725	−2.381	22.675	−1.363	−4.310	22.675
−1.925	−3.166	22.200	−0.740	−2.445	22.675	−1.400	−2.648	22.675
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−1.612	−3.485	24.575	−0.540	−2.406	25.050	−1.179	−2.896	25.050
−1.640	−5.105	24.575	−0.554	−2.480	25.050	−1.203	−4.723	25.050
−1.656	−3.545	24.575	−0.569	−2.554	25.050	−1.213	−2.964	25.050
−1.701	−5.147	24.575	−0.584	−2.628	25.050	−1.239	−4.789	25.050
−1.702	−3.603	24.575	−0.588	−1.687	25.050	−1.247	−3.031	25.050
−1.750	−3.660	24.575	−0.599	−2.702	25.050	−1.278	−4.854	25.050
−1.767	−5.180	24.575	−0.614	−2.776	25.050	−1.282	−3.098	25.050
−1.800	−3.715	24.575	−0.629	−2.850	25.050	−1.318	−3.164	25.050
−1.838	−5.202	24.575	−0.645	−2.924	25.050	−1.319	−4.917	25.050
−1.851	−3.769	24.575	−0.652	−1.726	25.050	−1.355	−3.230	25.050
−1.904	−3.821	24.575	−0.661	−2.998	25.050	−1.363	−4.979	25.050
−1.912	−5.209	24.575	−0.677	−3.072	25.050	−1.393	−3.296	25.050
−1.959	−3.870	24.575	−0.687	−1.792	25.050	−1.409	−5.038	25.050
−1.986	−5.202	24.575	−0.693	−3.145	25.050	−1.431	−3.361	25.050
−2.016	−3.918	24.575	−0.710	−3.219	25.050	−1.459	−5.095	25.050
−2.057	−5.182	24.575	−0.716	−1.862	25.050	−1.471	−3.425	25.050
−2.075	−3.964	24.575	−0.727	−3.293	25.050	−1.512	−3.489	25.050
−2.125	−5.152	24.575	−0.745	−3.366	25.050	−1.512	−5.149	25.050
−2.135	−4.007	24.575	−0.746	−1.931	25.050	−1.554	−3.552	25.050
−2.189	−5.114	24.575	−0.762	−3.439	25.050	−1.569	−5.198	25.050
−2.196	−4.049	24.575	−0.775	−2.001	25.050	−1.597	−3.614	25.050
−2.250	−5.072	24.575	−0.781	−3.513	25.050	−1.630	−5.243	25.050
−2.259	−4.089	24.575	−0.799	−3.586	25.050	−1.641	−3.675	25.050
−2.308	−5.025	24.575	−0.805	−2.070	25.050	−1.687	−3.735	25.050
−2.322	−4.128	24.575	−0.819	−3.659	25.050	−1.695	−5.282	25.050
−2.363	−4.976	24.575	−0.835	−2.140	25.050	−1.734	−3.794	25.050
−2.386	−4.166	24.575	−0.838	−3.732	25.050	−1.763	−5.314	25.050
−1.885	−3.963	25.050	−0.571	−3.174	25.525	−1.322	−5.185	25.525
−1.910	−5.349	25.050	−0.588	−3.250	25.525	−1.337	−3.437	25.525
−1.939	−4.016	25.050	−0.604	−3.325	25.525	−1.373	−3.505	25.525
−1.985	−5.350	25.050	−0.618	−1.892	25.525	−1.377	−5.239	25.525
−1.995	−4.067	25.050	−0.621	−3.401	25.525	−1.409	−3.574	25.525
−2.052	−4.116	25.050	−0.638	−3.476	25.525	−1.437	−5.289	25.525
−2.060	−5.339	25.050	−0.652	−1.962	25.525	−1.447	−3.642	25.525
−2.112	−4.162	25.050	−0.656	−3.552	25.525	−1.485	−3.709	25.525
−2.132	−5.316	25.050	−0.674	−3.627	25.525	−1.500	−5.333	25.525
−2.173	−4.206	25.050	−0.685	−2.032	25.525	−1.524	−3.775	25.525
−2.200	−5.284	25.050	−0.692	−3.702	25.525	−1.565	−3.841	25.525
−2.237	−4.247	25.050	−0.711	−3.777	25.525	−1.568	−5.371	25.525
−2.264	−5.244	25.050	−0.717	−2.102	25.525	−1.608	−3.906	25.525
−2.302	−4.285	25.050	−0.731	−3.852	25.525	−1.638	−5.403	25.525
−2.324	−5.199	25.050	−0.750	−2.172	25.525	−1.652	−3.970	25.525
−2.369	−4.320	25.050	−0.751	−3.927	25.525	−1.697	−4.032	25.525
−2.380	−5.148	25.050	−0.771	−4.002	25.525	−1.711	−5.429	25.525
−2.432	−5.093	25.050	−0.782	−2.243	25.525	−1.745	−4.093	25.525
−2.434	−4.359	25.050	−0.793	−4.076	25.525	−1.785	−5.450	25.525
−2.481	−5.035	25.050	−0.815	−2.313	25.525	−1.795	−4.152	25.525
−2.492	−4.407	25.050	−0.815	−4.150	25.525	−1.847	−4.210	25.525
−2.525	−4.974	25.050	−0.838	−4.224	25.525	−1.861	−5.466	25.525
−2.536	−4.468	25.050	−0.847	−2.384	25.525	−1.902	−4.264	25.525
−2.561	−4.908	25.050	−0.861	−4.298	25.525	−1.938	−5.479	25.525
−2.561	−4.907	25.050	−0.879	−2.454	25.525	−1.959	−4.316	25.525
−2.567	−4.537	25.050	−0.886	−4.372	25.525	−2.015	−5.486	25.525
−2.586	−4.610	25.050	−0.911	−2.525	25.525	−2.019	−4.366	25.525
−2.586	−4.835	25.050	−0.912	−4.444	25.525	−2.082	−4.411	25.525
−2.596	−4.685	25.050	−0.939	−4.517	25.525	−2.092	−5.487	25.525
−2.596	−4.760	25.050	−0.943	−2.595	25.525	−2.147	−4.454	25.525
−0.343	−1.956	25.525	−0.968	−4.589	25.525	−2.169	−5.479	25.525
−0.353	−2.033	25.525	−0.975	−2.666	25.525	−2.213	−4.493	25.525
−0.366	−1.883	25.525	−0.998	−4.660	25.525	−2.213	−4.493	25.525
−0.366	−2.109	25.525	−1.006	−2.736	25.525	−2.245	−5.463	25.525
−0.380	−2.186	25.525	−1.030	−4.731	25.525	−2.283	−4.527	25.525
−0.394	−2.262	25.525	−1.038	−2.807	25.525	−2.318	−5.437	25.525
−0.408	−2.338	25.525	−1.063	−4.801	25.525	−2.353	−4.560	25.525
−0.421	−1.830	25.525	−1.070	−2.878	25.525	−2.386	−5.400	25.525
−0.422	−2.414	25.525	−1.099	−4.869	25.525	−2.420	−4.599	25.525
−0.436	−2.490	25.525	−1.102	−2.948	25.525	−2.446	−5.352	25.525
−0.450	−2.566	25.525	−1.135	−3.018	25.525	−2.479	−4.648	25.525
−0.465	−2.642	25.525	−1.138	−4.936	25.525	−2.498	−5.294	25.525
−0.479	−2.718	25.525	−1.167	−3.089	25.525	−2.525	−4.710	25.525
−0.494	−2.794	25.525	−1.179	−5.002	25.525	−2.539	−5.229	25.525
−0.495	−1.811	25.525	−1.200	−3.159	25.525	−2.559	−4.780	25.525
−0.509	−2.870	25.525	−1.223	−5.066	25.525	−2.572	−5.159	25.525
−0.524	−2.946	25.525	−1.234	−3.229	25.525	−2.581	−4.854	25.525

It will also be appreciated that the internal core profile of the nozzle airfoil disclosed in the above table may be scaled up or down geometrically for use in other similar turbine designs. Consequently, the coordinate values set forth in Table I may be scaled upwardly or downwardly such that the internal profile shape of the nozzle airfoil remains unchanged. A scaled version of the coordinates of Table I would be represented by X, Y and Z coordinate values of Table I multiplied or divided by a constant number.

While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims

1. A turbine nozzle segment including inner and outer platforms and an airfoil extending between said platforms, said airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein said Z values between said limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between said Z value limits, the profile sections at the Z distances between said limits being joined smoothly with one another to form said airfoil internal core profile.

2. A turbine nozzle segment according to claim 1 forming part of a first stage of a turbine.

3. A turbine nozzle segment according to claim 1 wherein said internal core profile lies in an envelope within ±0.030 inches in a direction normal to any internal core surface location.

4. A turbine nozzle segment according to claim 1 wherein the X, Y and Z distances are scalable as a function of the same constant or number to provide a scaled-up or scaled-down internal core profile.

5. A turbine comprising a plurality of nozzle segments arranged in a circumferential array about an axis of the turbine, each said nozzle segment including inner and outer platforms and at least one airfoil extending between said platforms, each said airfoil having an internal nominal core profile at least a portion of which is substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I between Z value limits of 22.200 and 25.050, wherein said Z values between said limits are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil between said Z value limits, the profile sections at the Z distances between said limits being joined smoothly with one another to form said airfoil internal core profile.

6. A turbine according to claim 5 forming part of a first stage of a turbine.

7. A turbine according to claim 5 wherein said internal core profile lies in an envelope within ±0.030 inches in a direction normal to any internal core surface location.

8. A turbine nozzle segment including inner and outer platforms and an airfoil extending between said platforms, said airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from a turbine axis to planes extending normal to the radii and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form said airfoil internal core profile.

9. A turbine nozzle segment according to claim 8 forming part of a first stage of a turbine.

10. A turbine nozzle segment according to claim 8 wherein said internal core profile lies in an envelope within ±0.030 inches in a direction normal to any internal core surface location.

11. A turbine comprising a plurality of nozzle segments in a circumferential array about an axis of the turbine, each said segment having inner and outer platforms and at least one airfoil extending between said platforms, each said airfoil having an internal nominal core profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein the Z values are radial distances from said turbine axis to planes extending normal to the radii, and wherein the X and Y values are distances in inches which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z along the airfoil, the profile sections at the Z distances being joined smoothly with one another to form said airfoil internal core profile.

12. A turbine according to claim 11 forming part of a first stage of a turbine.

13. A turbine according to claim 11 wherein said internal core profile lies in an envelope within ±0.030 inches in a direction normal to any internal core surface location.