Additive manufacturing optimized first stage vane

Abstract

An airfoil and turbine vanes and vane assemblies incorporating the same. The airfoil has an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to four decimal places. The Z values refer to a percentage of the radial span of the airfoil measured radially from a radially outwardly facing surface of the inner platform. The turbine vane includes an inner platform, an outer platform, and an airfoil such as the one discussed above extending radially outward from the inner platform toward the outer platform. And the vane assembly includes an inner platform, an outer platform, and two or more first stage vanes extending from the inner platform to the outer platform. Each of the two or more first stage vanes include an airfoil as discussed above.

Description

TECHNICAL FIELD

The present invention generally relates to gas turbine engines. More specifically, aspects of the invention are directed to a profile of a turbine vane such as that of a first stage turbine blade of a gas turbine engine.

BACKGROUND OF THE INVENTION

A typical gas turbine engine comprises a compressor, at least one combustor, and a turbine, with the compressor and turbine coupled together through an axial shaft. In operation, air passes through the compressor, where the pressure of the air increases and then passes to a combustion section, where fuel is mixed with the compressed air in one or more combustion chambers and ultimately ignited. The hot combustion gases then pass into the turbine and drive the turbine. As the turbine rotates, the compressor turns since they are coupled together along a common shaft. The turning of the shaft also drives a generator for electrical applications. The engine must operate within the confines of the environmental regulations for the area in which the engine is located. As a result, more advanced combustion systems have been developed to more efficiently mix fuel and air so as to provide more complete combustion, which results in lower emissions.

As the demand for more powerful and efficient turbine engines continues to increase, it is necessary to improve the efficiency at each stage of the turbine, so as to get the most work possible out of the turbine. To achieve this efficiency improvement, it is necessary to remove any design defects that limit the turbine from achieving its maximum performance. The stationary turbine vanes and rotating turbine blades have been known to be limited in power output by a variety of operating conditions. There thus remains a need an optimized profile of a turbine vane or blade to improve the vane's or blade's aerodynamic efficiency and performance.

BRIEF SUMMARY OF THE INVENTION

Embodiments of the present invention are directed towards an airfoil and turbine vanes and vane assemblies incorporating the same. The airfoil includes an improved profile substantially in accordance with the Cartesian coordinate values set forth in Table 1 herein.

More particularly, one embodiment of the invention is directed to an airfoil for a turbine vane. The airfoil has an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to four decimal places. The Z values refer to a percentage of the radial span of the airfoil measured radially from a radially outwardly facing surface of the inner platform.

Other embodiments of the invention are directed to a turbine vane. The turbine vane includes an inner platform, an outer platform, and an airfoil extending radially outward from the inner platform toward the outer platform. The airfoil has the uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1.

Still other embodiments of the invention are directed to a vane assembly for a first stage of a turbine. The vane assembly includes an inner platform, an outer platform, and a plurality of first stage vanes extending from the inner platform to the outer platform. Each of the plurality of first stage blades include an airfoil having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1.

Additional advantages and features of the present invention will be set forth in part in a description which follows, and in part will become apparent to those skilled in the art upon examination of the following or may be learned from practice of the invention.

BRIEF DESCRIPTION OF THE DRAWINGS

The present invention is described in detail below with reference to the attached drawing figures, wherein:

FIG. 1 is a perspective view of a turbine vane assembly including a plurality of turbine vanes according to one embodiment of the invention;

FIGS. 2-11 are scatter plots of X, Y coordinates from Table 1 at Z positions of 0%, 10%, 20%, 30%, 40%, 50%, 60%, 70%, 80%, and 90% of the vane airfoil's radial span, respectively, showing points along the outer aerodynamic surface of the vane airfoils shown in FIG. 1; and

FIG. 12 shows a series of smooth arcs connecting the points in the scatter plots of X, Y coordinates shown in FIGS. 2-11.

DETAILED DESCRIPTION OF THE INVENTION

The subject matter of the present invention is described with specificity herein to meet statutory requirements. However, the description itself is not intended to limit the scope of this patent. Rather, the inventors have contemplated that the claimed subject matter might also be embodied in other ways, to include different components, combinations of components, steps, or combinations of steps similar to the ones described in this document, in conjunction with other present or future technologies.

FIG. 1 shows a vane assembly 10 of a gas turbine engine that incorporates a plurality of vane airfoils 18, 19 having an outer profile according to embodiments of the present invention. The vane assembly 10 generally includes an inner platform 12, an inner rail 14, an outer platform 16, and the plurality of airfoil vanes 18, 19. The airfoil vanes 18, 19 extend between the inner platform 12 and the outer platform 16 and, more particularly, extend from a radially outwardly facing surface 20 of the inner platform 12 toward the outer platform 16. The inner rails 14 serves to seal the rim cavity region from leakage of cooling air into the hot gas path instead of passing into an interior of the vane airfoils 18, 19, while also stiffening the inner platform 12.

In some embodiments, a plurality of the vane assemblies 10 shown in FIG. 1 are operatively connected to form a radial array of vane airfoils comprising, for example, a turbine stage of a gas turbine engine. For example, in some embodiments the vane assembly 10 may form a portion of a first stage of turbine, and the vane airfoils 18, 19 are thus first stage turbine vanes. In such embodiments, the vane airfoils 18, 19 will form part of the first airfoils encountered by the hot combustion gasses leaving the combustor of the gas turbine engine. More particularly, during use hot combustion gasses leaving the combustor flow over the outer surface of the vane airfoils 18, 19, which increase the velocity of the hot combustion gasses. The combustion gasses are then directed over the first stage turbine blades, which spin and turn an axial shaft of the gas turbine engine, thus extracting energy from the hot gasses. The hot combustion gasses continue in the axial direction to the second, third, fourth, etc., stages of vanes and blades in the turbine.

Aspects of the invention are directed to the improved aerodynamic profile of the vane airfoils 18, 19 shown in FIG. 1. More particularly, each of the first stage vane airfoils 18, 19 has an uncoated profile defined by the Cartesian coordinates set forth in Table 1, carried out to four decimal places. The X and Y coordinates in Table 1 are provided in inches although other units of dimensions may be used without departing from the scope of the invention. Moreover, in some embodiments, due to manufacturing tolerances, the actual coordinates of the vane airfoils 18, 19 can vary in profile and position by about +/−0.100 inches. The Z values provided in Table 1 are nondimensional and represent a percentage of the total radial span of the vane airfoil—i.e., a percentage of the distance measured radially from the radially outwardly facing surface 20 of the inner platform 12 to a radially inwardly facing surface of the outer platform 14. In that regard, to convert the Z value set forth in Table 1 to a Z coordinate in inches or other dimensional unit, the nondimensional Z value in Table 1 is multiplied by the height of airfoil 18, 19 in inches (or another dimension, if so desired). Again, the height of the airfoil is measured between the two platforms 12, 16.

Orthogonally related X, Y, and Z axes corresponding to coordinates provided in Table 1 are shown in FIG. 1. The X, Y, and Z axes in FIG. 1 are shown relative to vane airfoil 18. It should be appreciated that, because the Z axis aligns with the radial direction at each vane, the corresponding axes for each subsequent vane in the radial array of vanes forming the turbine stage of will be rotated to some degree from those shown in FIG. 1.

The vane assembly 10 and/or turbine airfoils 18, 19 can be fabricated through any desired process such as, but not limited to, an additive manufacturing process or a casting and machining process. In one embodiment, the vane airfoils 18, 19 are cast from a nickel-based superalloy. Examples of acceptable alloys include, but are not limited to, Rene 80, GTD111, and MGA2400. In some embodiments, as a result of the casting process, the profile of the vane airfoils 18, 19 can vary typically up to +/−0.100 inches relative to the nominal coordinates shown in Table 1. In order to provide further thermal capability, in some embodiments the vane airfoils 18, 19 of the vane assembly 10 comprise a MCrAlY bond coating and thermal barrier ceramic coating of approximately 0.055 inches thick, where M can be a variety of metals including, but not limited to Cobalt, Nickel, or a Cobalt Nickel mixture. By application of the bond and thermal barrier coating, the vane assembly 10 achieves an improved oxidation resistance over the prior-art configuration.

The vane airfoils 18, 19 of the present invention are generated by connecting X, Y coordinates with a smooth arc at a number of Z positions extending radially outward from the inner platform 12. More particularly, a plurality of sections of X, Y coordinate data are first connected together using a smooth arc. These sections, some of which are shown in FIGS. 2-12 as will be discussed below, are then connected together by a series of smooth curves to generate the vane airfoil 18, 19 surfaces.

For example, FIGS. 2-11 show a plurality of cross-sectional profiles—profiles 22, 24, 26, 28, 30, 32, 34, 36, 38, and 40, respectively—of the vane airfoil 18 shown in FIG. 1 extending radially outward from the inner platform 12. Again, in some embodiments the vane airfoil 18 may be part of a first stage turbine vane in a gas turbine engine. Each profile is shown at a 10% increment in the total height of the vane airfoil 18 in the radial (i.e., the Z coordinate) direction. More particularly, profile 22 is shown at Z=0%, which is at the interface of vane airfoil 18 with the radially outwardly facing surface 20 of the inner platform 12. Profile 40 is shown at Z=90%; that is 90% of the radial span of the vane airfoil 18. And profiles 24, 26, 28, 30, 32, 34, 36, and 38 are shown at Z=10%, Z=20%, Z=30%, Z=40%, Z=50%, Z=60%, Z=70%, and Z=80%, respectively. As can be seen in FIG. 2, the X, Y, and Z Cartesian coordinates set forth in Table 1 are measured relative to an origin located proximate an apex of the vane airfoil 18's concave (i.e., pressure) side. The dimensions in the radial direction (i.e., Z direction) can be scaled according to application without departing from the scope of the invention. Furthermore the X, Y, and Z coordinates may be multiplied or divided by the same constant or number/factor to provide a scaled up or scaled down version of the vane airfoil 18 according to application without departing from the scope of the invention.

The vane airfoil 18 of the present invention is generated by connecting the X, Y coordinates shown in each of the scatter plots with a smooth arc to form a plurality of profile sections, and by connecting those profile sections together by a series of smooth curves to generate the airfoil surface. More particularly, FIG. 12 shows profiles 22′, 24′, 26′, 28′, 30′, 32′, 34′, 36′, 38′, and 40′, which are formed by connecting the X, Y coordinates shown in each of the scatter plots 22, 24, 26, 28, 30, 32, 34, 36, 38, and 40, respectively, with a smooth arc to form the plurality of profile sections. These profiles 22′, 24′, 26′, 28′, 30′, 32′, 34′, 36′, 38′, and 40′ are in turn connected together by a series of smooth curves to generate the surface of vane airfoils 18, 19.

As best seen in FIG. 12, each profile 22′, 24′, 26′, 28′, 30′, 32′, 34′, 36′, 38′, and 40′ has an open trailing edge. This is because the particular trailing edge geometry of the vane airfoils 18, 19 may vary from application to application without departing from the scope of the invention. Put another way, the trailing edge points are undefined in Table 1 because any trailing edge exit airflow profile and pressure to suction side connection geometry can be integrated into the attached airfoil point geometry without departing from the scope of this invention.

The values given in Table 1 below represent the vane airfoil 18 profiles at ambient, non-operating (i.e., non-hot) conditions, for an uncoated airfoil 18. thus, it should be appreciated that the actual dimensions of a turbine vane according to aspects of the invention may vary from the coordinates shown in Table 1 when coated and/or when in use and thus subjected to hot combustion gasses. And again, due to manufacturing tolerances or the like, the actual coordinates of the vane airfoils 18, 19 can vary in profile and position by about +/−0.100 inches.

In another embodiment of the present invention, a plurality of vane airfoils 18, 19 are secured to an inner platform 12 to form the vane assembly 10. The plurality of vane airfoils 18, 19 each have an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1.

TABLE 1
X	Y	Z
3.2119	2.6161	0%
3.0622	2.5811	0%
2.9127	2.5457	0%
2.7633	2.5096	0%
2.6141	2.4729	0%
2.4650	2.4357	0%
2.3160	2.3979	0%
2.1673	2.3594	0%
2.0186	2.3204	0%
1.8702	2.2808	0%
1.7218	2.2406	0%
1.5737	2.1998	0%
1.4257	2.1584	0%
1.2779	2.1163	0%
1.1303	2.0736	0%
0.9829	2.0302	0%
0.8357	1.9860	0%
0.6887	1.9410	0%
0.5421	1.8951	0%
0.3957	1.8483	0%
0.2497	1.8003	0%
0.1041	1.7512	0%
−0.0410	1.7008	0%
−0.1857	1.6489	0%
−0.3297	1.5954	0%
−0.4731	1.5401	0%
−0.6157	1.4828	0%
−0.7574	1.4233	0%
−0.8980	1.3612	0%
−1.0373	1.2965	0%
−1.1753	1.2288	0%
−1.3116	1.1579	0%
−1.4461	1.0836	0%
−1.5785	1.0056	0%
−1.7087	0.9239	0%
−1.8363	0.8383	0%
−1.9611	0.7487	0%
−2.0831	0.6552	0%
−2.2018	0.5577	0%
−2.3172	0.4562	0%
−2.4290	0.3508	0%
−2.5371	0.2416	0%
−2.6411	0.1284	0%
−2.7406	0.0114	0%
−2.8353	−0.1097	0%
−2.9247	−0.2346	0%
−3.0085	−0.3634	0%
−3.0861	−0.4960	0%
−3.1565	−0.6326	0%
−3.2181	−0.7734	0%
−3.2686	−0.9184	0%
−3.3039	−1.0679	0%
−3.3180	−1.2208	0%
−3.3032	−1.3734	0%
−3.2521	−1.5179	0%
−3.1655	−1.6443	0%
−3.0496	−1.7446	0%
−2.9127	−1.8136	0%
−2.7633	−1.8482	0%
−2.6100	−1.8468	0%
−2.4612	−1.8099	0%
−2.3248	−1.7399	0%
−2.2045	−1.6445	0%
−2.0978	−1.5340	0%
−2.0003	−1.4153	0%
−1.9079	−1.2925	0%
−1.8173	−1.1684	0%
−1.7255	−1.0452	0%
−1.6304	−0.9245	0%
−1.5315	−0.8068	0%
−1.4293	−0.6921	0%
−1.3238	−0.5803	0%
−1.2155	−0.4714	0%
−1.1045	−0.3651	0%
−0.9910	−0.2614	0%
−0.8756	−0.1600	0%
−0.7585	−0.0605	0%
−0.6399	0.0372	0%
−0.5200	0.1333	0%
−0.3989	0.2279	0%
−0.2768	0.3212	0%
−0.1538	0.4133	0%
−0.0299	0.5042	0%
0.0949	0.5939	0%
0.2205	0.6825	0%
0.3469	0.7699	0%
0.4740	0.8562	0%
0.6019	0.9414	0%
0.7305	1.0255	0%
0.8597	1.1086	0%
0.9896	1.1908	0%
1.1201	1.2720	0%
1.2510	1.3524	0%
1.3824	1.4321	0%
1.5143	1.5110	0%
1.6465	1.5893	0%
1.7791	1.6670	0%
1.9120	1.7441	0%
2.0453	1.8207	0%
2.1788	1.8966	0%
2.3128	1.9720	0%
2.4470	2.0467	0%
2.5816	2.1209	0%
2.7165	2.1945	0%
2.8518	2.2675	0%
2.9873	2.3398	0%
3.1232	2.4116	0%
3.2594	2.4829	0%
3.4013	2.6646	10%
3.2463	2.6291	10%
3.0914	2.5931	10%
2.9366	2.5566	10%
2.7819	2.5194	10%
2.6274	2.4817	10%
2.4730	2.4434	10%
2.3188	2.4045	10%
2.1647	2.3651	10%
2.0108	2.3250	10%
1.8570	2.2843	10%
1.7034	2.2430	10%
1.5500	2.2010	10%
1.3967	2.1584	10%
1.2437	2.1151	10%
1.0908	2.0711	10%
0.9382	2.0262	10%
0.7859	1.9804	10%
0.6339	1.9337	10%
0.4821	1.8860	10%
0.3307	1.8373	10%
0.1797	1.7873	10%
0.0292	1.7360	10%
−0.1209	1.6832	10%
−0.2704	1.6289	10%
−0.4192	1.5727	10%
−0.5672	1.5145	10%
−0.7143	1.4541	10%
−0.8604	1.3912	10%
−1.0053	1.3255	10%
−1.1488	1.2569	10%
−1.2907	1.1850	10%
−1.4308	1.1097	10%
−1.5689	1.0308	10%
−1.7047	0.9481	10%
−1.8381	0.8614	10%
−1.9688	0.7708	10%
−2.0966	0.6761	10%
−2.2212	0.5773	10%
−2.3423	0.4742	10%
−2.4597	0.3669	10%
−2.5731	0.2554	10%
−2.6821	0.1395	10%
−2.7862	0.0193	10%
−2.8849	−0.1054	10%
−2.9779	−0.2344	10%
−3.0645	−0.3678	10%
−3.1442	−0.5055	10%
−3.2159	−0.6474	10%
−3.2782	−0.7937	10%
−3.3287	−0.9445	10%
−3.3633	−1.0997	10%
−3.3760	−1.2580	10%
−3.3593	−1.4159	10%
−3.3063	−1.5654	10%
−3.2175	−1.6969	10%
−3.0990	−1.8023	10%
−2.9584	−1.8760	10%
−2.8045	−1.9145	10%
−2.6458	−1.9161	10%
−2.4911	−1.8809	10%
−2.3484	−1.8113	10%
−2.2222	−1.7148	10%
−2.1101	−1.6021	10%
−2.0079	−1.4802	10%
−1.9116	−1.3536	10%
−1.8177	−1.2253	10%
−1.7232	−1.0973	10%
−1.6258	−0.9715	10%
−1.5249	−0.8486	10%
−1.4203	−0.7288	10%
−1.3121	−0.6122	10%
−1.2005	−0.4989	10%
−1.0858	−0.3887	10%
−0.9683	−0.2815	10%
−0.8486	−0.1767	10%
−0.7270	−0.0742	10%
−0.6038	0.0264	10%
−0.4792	0.1252	10%
−0.3534	0.2225	10%
−0.2265	0.3185	10%
−0.0987	0.4131	10%
0.0300	0.5066	10%
0.1595	0.5990	10%
0.2898	0.6902	10%
0.4209	0.7802	10%
0.5528	0.8692	10%
0.6854	0.9570	10%
0.8187	1.0438	10%
0.9526	1.1295	10%
1.0872	1.2143	10%
1.2225	1.2980	10%
1.3582	1.3809	10%
1.4945	1.4629	10%
1.6313	1.5441	10%
1.7685	1.6245	10%
1.9062	1.7041	10%
2.0443	1.7830	10%
2.1828	1.8612	10%
2.3218	1.9387	10%
2.4611	2.0154	10%
2.6009	2.0913	10%
2.7410	2.1665	10%
2.8816	2.2410	10%
3.0225	2.3147	10%
3.1638	2.3877	10%
3.3055	2.4600	10%
3.4476	2.5315	10%
3.5907	2.7131	20%
3.4303	2.6771	20%
3.2699	2.6405	20%
3.1097	2.6035	20%
2.9496	2.5658	20%
2.7897	2.5277	20%
2.6299	2.4889	20%
2.4702	2.4496	20%
2.3107	2.4096	20%
2.1513	2.3691	20%
1.9921	2.3279	20%
1.8330	2.2861	20%
1.6741	2.2436	20%
1.5155	2.2004	20%
1.3570	2.1565	20%
1.1987	2.1118	20%
1.0407	2.0662	20%
0.8830	2.0198	20%
0.7255	1.9723	20%
0.5684	1.9238	20%
0.4116	1.8741	20%
0.2552	1.8233	20%
0.0993	1.7711	20%
−0.0562	1.7174	20%
−0.2111	1.6622	20%
−0.3653	1.6051	20%
−0.5188	1.5460	20%
−0.6714	1.4847	20%
−0.8230	1.4209	20%
−0.9733	1.3543	20%
−1.1223	1.2847	20%
−1.2698	1.2119	20%
−1.4154	1.1356	20%
−1.5591	1.0556	20%
−1.7007	0.9719	20%
−1.8398	0.8842	20%
−1.9763	0.7924	20%
−2.1098	0.6966	20%
−2.2402	0.5964	20%
−2.3671	0.4918	20%
−2.4901	0.3826	20%
−2.6089	0.2689	20%
−2.7229	0.1504	20%
−2.8317	0.0271	20%
−2.9346	−0.1012	20%
−3.0311	−0.2343	20%
−3.1206	−0.3723	20%
−3.2023	−0.5149	20%
−3.2755	−0.6622	20%
−3.3385	−0.8141	20%
−3.3890	−0.9705	20%
−3.4229	−1.1313	20%
−3.4342	−1.2952	20%
−3.4156	−1.4583	20%
−3.3606	−1.6129	20%
−3.2697	−1.7494	20%
−3.1484	−1.8599	20%
−3.0042	−1.9382	20%
−2.8457	−1.9806	20%
−2.6817	−1.9851	20%
−2.5211	−1.9517	20%
−2.3722	−1.8825	20%
−2.2400	−1.7850	20%
−2.1226	−1.6700	20%
−2.0158	−1.5450	20%
−1.9154	−1.4147	20%
−1.8181	−1.2822	20%
−1.7207	−1.1496	20%
−1.6211	−1.0188	20%
−1.5181	−0.8906	20%
−1.4112	−0.7657	20%
−1.3002	−0.6443	20%
−1.1855	−0.5265	20%
−1.0671	−0.4123	20%
−0.9457	−0.3015	20%
−0.8217	−0.1934	20%
−0.6956	−0.0878	20%
−0.5678	0.0157	20%
−0.4385	0.1173	20%
−0.3079	0.2172	20%
−0.1763	0.3158	20%
−0.0437	0.4131	20%
0.0897	0.5092	20%
0.2240	0.6041	20%
0.3591	0.6980	20%
0.4949	0.7906	20%
0.6315	0.8822	20%
0.7688	0.9727	20%
0.9068	1.0621	20%
1.0455	1.1505	20%
1.1849	1.2378	20%
1.3249	1.3241	20%
1.4655	1.4095	20%
1.6066	1.4938	20%
1.7483	1.5773	20%
1.8906	1.6598	20%
2.0334	1.7414	20%
2.1766	1.8221	20%
2.3204	1.9020	20%
2.4647	1.9809	20%
2.6095	2.0589	20%
2.7547	2.1360	20%
2.9004	2.2122	20%
3.0466	2.2875	20%
3.1933	2.3620	20%
3.3403	2.4356	20%
3.4878	2.5083	20%
3.6357	2.5802	20%
3.7801	2.7616	30%
3.6142	2.7250	30%
3.4485	2.6879	30%
3.2828	2.6503	30%
3.1173	2.6122	30%
2.9519	2.5736	30%
2.7867	2.5343	30%
2.6215	2.4945	30%
2.4565	2.4541	30%
2.2917	2.4131	30%
2.1270	2.3715	30%
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0.7062	2.0373	80%
0.5179	1.9796	80%
0.3300	1.9203	80%
0.1427	1.8594	80%
−0.0439	1.7967	80%
−0.2300	1.7320	80%
−0.4152	1.6650	80%
−0.5995	1.5955	80%
−0.7826	1.5232	80%
−0.9645	1.4477	80%
−1.1449	1.3686	80%
−1.3236	1.2859	80%
−1.5005	1.1992	80%
−1.6754	1.1086	80%
−1.8480	1.0139	80%
−2.0183	0.9149	80%
−2.1858	0.8114	80%
−2.3503	0.7031	80%
−2.5111	0.5894	80%
−2.6677	0.4700	80%
−2.8192	0.3441	80%
−2.9645	0.2112	80%
−3.1025	0.0707	80%
−3.2318	−0.0778	80%
−3.3511	−0.2344	80%
−3.4588	−0.3993	80%
−3.5538	−0.5718	80%
−3.6353	−0.7510	80%
−3.7025	−0.9360	80%
−3.7531	−1.1263	80%
−3.7828	−1.3209	80%
−3.7858	−1.5176	80%
−3.7557	−1.7120	80%
−3.6880	−1.8966	80%
−3.5831	−2.0628	80%
−3.4450	−2.2027	80%
−3.2792	−2.3082	80%
−3.0939	−2.3736	80%
−2.8986	−2.3955	80%
−2.7034	−2.3728	80%
−2.5184	−2.3063	80%
−2.3510	−2.2031	80%
−2.2015	−2.0752	80%
−2.0660	−1.9323	80%
−1.9405	−1.7805	80%
−1.8211	−1.6239	80%
−1.7047	−1.4650	80%
−1.5891	−1.3056	80%
−1.4723	−1.1470	80%
−1.3522	−0.9909	80%
−1.2266	−0.8393	80%
−1.0941	−0.6935	80%
−0.9550	−0.5541	80%
−0.8102	−0.4207	80%
−0.6609	−0.2923	80%
−0.5081	−0.1680	80%
−0.3527	−0.0470	80%
−0.1952	0.0713	80%
−0.0361	0.1873	80%
0.1243	0.3016	80%
0.2857	0.4145	80%
0.4479	0.5262	80%
0.6109	0.6368	80%
0.7745	0.7463	80%
0.9389	0.8548	80%
1.1040	0.9622	80%
1.2698	1.0685	80%
1.4363	1.1737	80%
1.6034	1.2779	80%
1.7713	1.3809	80%
1.9399	1.4826	80%
2.1094	1.5830	80%
2.2798	1.6817	80%
2.4511	1.7789	80%
2.6234	1.8743	80%
2.7967	1.9679	80%
2.9710	2.0596	80%
3.1463	2.1494	80%
3.3226	2.2371	80%
3.4999	2.3229	80%
3.6781	2.4069	80%
3.8571	2.4889	80%
4.0370	2.5691	80%
4.2176	2.6476	80%
4.3991	2.7242	80%
4.5813	2.7990	80%
4.7642	2.8719	80%
4.9152	3.0517	90%
4.7168	3.0118	90%
4.5185	2.9715	90%
4.3202	2.9309	90%
4.1220	2.8898	90%
3.9240	2.8482	90%
3.7260	2.8061	90%
3.5282	2.7635	90%
3.3305	2.7203	90%
3.1329	2.6764	90%
2.9355	2.6317	90%
2.7383	2.5863	90%
2.5413	2.5400	90%
2.3445	2.4928	90%
2.1479	2.4446	90%
1.9516	2.3953	90%
1.7557	2.3448	90%
1.5600	2.2931	90%
1.3647	2.2400	90%
1.1697	2.1857	90%
0.9752	2.1299	90%
0.7811	2.0727	90%
0.5874	2.0141	90%
0.3941	1.9539	90%
0.2015	1.8920	90%
0.0094	1.8283	90%
−0.1821	1.7626	90%
−0.3727	1.6947	90%
−0.5624	1.6242	90%
−0.7510	1.5509	90%
−0.9384	1.4743	90%
−1.1242	1.3942	90%
−1.3084	1.3103	90%
−1.4907	1.2225	90%
−1.6711	1.1307	90%
−1.8493	1.0347	90%
−2.0250	0.9344	90%
−2.1981	0.8296	90%
−2.3682	0.7198	90%
−2.5346	0.6047	90%
−2.6967	0.4836	90%
−2.8537	0.3558	90%
−3.0043	0.2207	90%
−3.1473	0.0775	90%
−3.2812	−0.0742	90%
−3.4045	−0.2346	90%
−3.5154	−0.4038	90%
−3.6126	−0.5813	90%
−3.6956	−0.7658	90%
−3.7636	−0.9564	90%
−3.8141	−1.1523	90%
−3.8431	−1.3524	90%
−3.8447	−1.5546	90%
−3.8127	−1.7542	90%
−3.7428	−1.9437	90%
−3.6355	−2.1149	90%
−3.4945	−2.2595	90%
−3.3251	−2.3695	90%
−3.1353	−2.4386	90%
−2.9349	−2.4635	90%
−2.7341	−2.4425	90%
−2.5432	−2.3765	90%
−2.3700	−2.2724	90%
−2.2151	−2.1424	90%
−2.0748	−1.9966	90%
−1.9450	−1.8413	90%
−1.8218	−1.6808	90%
−1.7020	−1.5177	90%
−1.5834	−1.3537	90%
−1.4641	−1.1902	90%
−1.3418	−1.0290	90%
−1.2139	−0.8722	90%
−1.0787	−0.7216	90%
−0.9363	−0.5778	90%
−0.7877	−0.4405	90%
−0.6342	−0.3086	90%
−0.4770	−0.1811	90%
−0.3170	−0.0572	90%
−0.1548	0.0639	90%
0.0091	0.1826	90%
0.1743	0.2994	90%
0.3405	0.4149	90%
0.5075	0.5293	90%
0.6753	0.6425	90%
0.8438	0.7546	90%
1.0129	0.8657	90%
1.1828	0.9757	90%
1.3533	1.0847	90%
1.5246	1.1925	90%
1.6965	1.2993	90%
1.8691	1.4050	90%
2.0425	1.5093	90%
2.2168	1.6121	90%
2.3921	1.7133	90%
2.5683	1.8128	90%
2.7456	1.9104	90%
2.9240	2.0061	90%
3.1034	2.0996	90%
3.2840	2.1910	90%
3.4657	2.2802	90%
3.6483	2.3673	90%
3.8320	2.4523	90%
4.0166	2.5353	90%
4.2020	2.6163	90%
4.3884	2.6954	90%
4.5755	2.7724	90%
4.7634	2.8475	90%
4.9522	2.9205	90%

The present invention has been described in relation to particular embodiments, which are intended in all respects to be illustrative rather than restrictive. Alternative embodiments will become apparent to those of ordinary skill in the art to which the present invention pertains without departing from its scope.

From the foregoing, it will be seen that this invention is one well adapted to attain all the ends and objects set forth above, together with other advantages which are obvious and inherent to the system and method. It will be understood that certain features and sub-combinations are of utility and may be employed without reference to other features and sub-combinations. This is contemplated by and within the scope of the claims.

Claims

1. An airfoil for a turbine vane having an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to four decimal places, wherein X and Y are in inches, and Z is a percentage of the radial span of the airfoil measured radially from a radially outwardly facing surface of an inner platform and wherein the X and Y coordinates, when connected by smooth arcs, define an airfoil profile section at each Z coordinate.

2. The airfoil of claim 1, wherein the X and Y coordinate values of the airfoil have manufacturing tolerances of ±0.100 inches.

3. The airfoil of claim 1, wherein the airfoil is fabricated from a nickel-based alloy.

4. The airfoil of claim 1 further comprising a coating up to 0.055 inches thick.

5. The airfoil of claim 4, wherein the coating is at least a MCrAlY bond coating.

6. The airfoil of claim 1, wherein the turbine vane forms part of a first stage of a turbine.

7. A turbine vane comprising an inner platform, an outer platform, and an airfoil extending radially outward from the inner platform toward the outer platform, wherein the airfoil has an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to four decimal places, wherein X and Y are in inches, and Z is a percentage of the radial span of the airfoil measured radially from a radially outwardly facing surface of an inner platform and wherein the X and Y coordinates, when connected by smooth arcs, define an airfoil profile section at each Z coordinate.

8. The turbine vane of claim 7, wherein the X and Y coordinate values of the airfoil have manufacturing tolerances of ±0.100 inches.

9. The turbine vane of claim 7 further comprising an inner rail radially inward of the inner platform.

10. The turbine vane of claim 7, wherein the vane is fabricated from a nickel-based alloy.

11. The turbine vane of claim 7 further comprising at least a MCrAlY bond coating applied to the airfoil.

12. The turbine vane of claim 11, wherein the coating is applied up to 0.055 inches thick.

13. The turbine vane of claim 7, wherein the turbine vane forms a part of a first stage of a turbine.

14. A vane assembly for a first stage of a turbine, the vane assembly comprising: an inner platform; an outer platform; and a plurality of first stage vanes extending from the inner platform to the outer platform, each of the plurality of first stage blades comprising an airfoil including an uncoated profile substantially in accordance with Cartesian coordinate values of X, Y, and Z as set forth in Table 1, carried to four decimal places, wherein X and Y are in inches, and Z is a percentage of the radial span of the airfoil measured radially from a radially outwardly facing surface of an inner platform and wherein the X and Y coordinates, when connected by smooth arcs, define an airfoil profile section at each Z coordinate.

15. The vane assembly of claim 14, wherein the X and Y coordinate values of each airfoil have manufacturing tolerances of ±0.100 inches.

16. The vane assembly of claim 14 further comprising an inner rail radially inward of the inner platform.

17. The vane assembly of claim 14, wherein each of the plurality of first stage vanes is fabricated from a nickel-based alloy.

18. The vane assembly of claim 14 further comprising at least a MCrAlY bond coating applied to each airfoil.

19. The vane assembly of claim 18, wherein the coating is applied up to 0.055 inches thick.

20. The vane assembly of claim 14, wherein the plurality of first stage vanes are radially arrayed about a center axis of the turbine.