Airfoil shape for a compressor

Abstract

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

Description

RELATED APPLICATIONS

The present application is related to the following commonly assigned applications: Ser. Nos. 14/845,337; 14/845,347; 14/845,358; 14/845,340; 14/845,370; 14/845,360; 14/845,378; 14/845,388; 14/845,411; 14/845,421, filed concurrently herewith.

TECHNICAL FIELD

The present application and the resultant patent relate generally to gas turbine engines and more particularly relates to an airfoil profile or airfoil shape for use in a compressor.

BACKGROUND OF THE INVENTION

In a gas turbine engine, many system requirements should be met at each stage of the flow path therethrough to meet design goals. These design goals include, but are not limited to, overall improved efficiency, a reduction in vibratory response, improved airfoil loading capability, and the like. For example, a compressor airfoil profile should achieve thermal and mechanical operating requirements for a particular stage in the compressor. Moreover, component lifetime, reliability, and cost targets also should be met.

SUMMARY OF THE INVENTION

According to one aspect of the present application, an article of manufacture is provided with a nominal airfoil profile substantially in accordance with the Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

According to another aspect of the present application, an article of manufacture is provided with a suction-side nominal airfoil profile substantially in accordance with the suction-side Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined smoothly with one another to form a complete suction-side airfoil shape, the X, Y, and Z coordinate values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up, and scaled-down airfoil profile.

According to yet another aspect of the present application, a compressor is provided with a number of stator vanes, each of the stator vanes including an airfoil having a suction-side airfoil shape, the airfoil having a nominal profile substantially in accordance with the suction-side Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape.

These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic diagram of a gas turbine engine including a compressor, a combustor, a turbine, and a load.

FIG. 2 is a schematic diagram of a compressor with multiple stages and a flow path therethrough.

FIG. 3 is a perspective view of a stator vane airfoil as may be described herein.

FIG. 4 is a cross-sectional view of the stator vane airfoil taken along line 4-4 of FIG. 3.

DETAILED DESCRIPTION

Referring now to the drawings, in which like numerals refer to like elements throughout the several views, FIG. 1 shows a schematic view of gas turbine engine 10 as may be used herein. The gas turbine engine 10 may include a compressor 15. The compressor 15 compresses an incoming flow of air 20. The compressor 15 delivers the compressed flow of air 20 to a combustor 25. The combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35. Although only a single combustor 25 is shown, the gas turbine engine 10 may include any number of the combustors 25 arranged in a circumferential array or otherwise. The flow of combustion gases 35 is delivered in turn to a turbine 40. The flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work. The mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.

The gas turbine engine 10 may use natural gas, liquid fuels, various types of syngas, and/or other types of fuels and blends thereof. The gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like. The gas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.

FIG. 2 shows an example of the compressor 15. The compressor 15 may include a number of compressor stages with an axial compressor flow path 55 therethrough. As one non-limiting example only, the compressor flow path 55 may include about eighteen rotor/stator stages. The exact number of rotor and stator stages, however, may be a matter of engineering design choice and may be more or less than the illustrated eighteen stages. It is to be understood that any number of rotor and stator stages may be provided herein.

Each stage of the compressor 15 may include a number of circumferentially spaced rotor blades 60 mounted on a rotor wheel 65 and a number of circumferentially spaced stator vanes 70 attached to a static compressor case 75. Each of the rotor wheels 65 may be attached to an aft drive shaft 80, which may be connected to the turbine section of the engine. The rotor blades and stator vanes may lie in the flow path 55 of the compressor 15. The direction of airflow through the compressor flow path 55 flows generally from left to right in FIG. 2. Other components and other configurations may be used herein.

The compressor rotor blades 60 impart kinetic energy to the airflow and therefore bring about a desired pressure rise. Directly following the rotor blades 60 may be a stage of the compressor stator vanes 70. However, in some designs the stator vanes may precede the rotor blades. Both the rotor blades and stator vanes turn the airflow, slow the airflow velocity (in the respective airfoil frame of reference), and yield a rise in the static pressure of the airflow. Typically, multiple rows of rotor/stator stages are arranged in axial flow compressors to achieve a desired discharge to inlet pressure ratio. Each rotor blade and stator vane includes an airfoil, and these airfoils can be secured to rotor wheels or a stator case by an appropriate attachment configuration, often known as a “root,” “base” or “dovetail”. In addition, the compressor 15 also may include inlet guide vanes (IGV's) 85, variable stator vanes (VSV's) 90, and exit or exhaust guide vanes (EGV's) 95. All of these blades and vanes have airfoils that act on the medium (e.g., air) passing through the compressor flow path 55. Other components and other configurations may be used herein.

The rotor blades 60 and stator vanes 70 are merely exemplary of the stages of the compressor 15 described herein. In addition, each rotor blade 60, stator vane 70, inlet guide vane 85, variable stator vane 90, and exit guide vane 95 may be considered an article of manufacture. Further, the article of manufacture may include a stator vane configured for use with a compressor 15.

FIG. 3 shows an example of a stator vane 100 as may be described herein. In this example, the stator vane 100 includes an airfoil 105. Each of the stator vanes 100 may have an airfoil profile at any cross-section from an airfoil root 110 to an airfoil tip 120. The airfoil 105 may connect to a mounting base 130, which also may be referred to as a dovetail. The mounting base 130 fits into a complementary shaped groove or slot in case 75. Examples of the compressor 15 may include a variety of blades 60 and vanes 70, 85, 90, 95 arranged in multiple stages.

Referring to FIG. 4, the airfoil 105 may have a suction side 140 and a pressure side 150. The suction side 140 may be located on the opposing side of the airfoil 105 from the pressure side 150. Thus, each stator vane 60 may have an airfoil profile at any cross-section in the shape of the airfoil 105. The airfoil 105 also may include a leading edge 160 and a trailing edge 170 and with a chord length 180 extending therebetween. The root 110 of the airfoil 105 corresponds to the lowest non-dimensional Z value of scalable TABLE 1. The tip 120 of the airfoil 105 corresponds to the highest non-dimensional Z value of scalable TABLE 1. An airfoil 105 may extend beyond the compressor flowpath and may be tipped to achieve the desired endwall clearances. By way of example only, the airfoil may have a height from about one (1) inch to about twenty (20) inches (about 2.54 centimeters to about 50.8 centimeters) or more. Any specific airfoil height may be used herein as desired in a specific application. Other components and other configurations may be used herein.

The compressor flow path 55 requires airfoils 105 that meet system requirements of aerodynamic and mechanical blade/vane loading and efficiency. For example, it is desirable that the airfoils 105 are designed to reduce the vibratory response or vibratory stress response of the respective blades and/or vanes. Materials such as high strength alloys, non-corrosive alloys, and/or stainless steels may be used in the blades and/or vanes. To define the airfoil shape of each blade airfoil and/or vane airfoil, there is a unique set or loci of points in space that meet the stage requirements and can be manufactured. These unique loci of points meet the requirements for stage efficiency and may be arrived at by iteration between aerodynamic and mechanical loadings so as to enable the turbine and compressor to run in an efficient, safe, reliable, and smooth manner. These points are unique and specific to the system. The locus that defines the airfoil profile includes a set of points with X, Y, and Z coordinates relative to a reference origin coordinate system. The three-dimensional Cartesian coordinate system of X, Y, and Z values given in scalable TABLE 1 below defines the profile of the stator vane airfoil at various locations along its length. The scalable TABLE 1 lists data for a non-coated airfoil. The envelope/tolerance for the coordinates may be about +/−5% of the chord length 180 in a direction normal to any airfoil surface location or about +/−0.25 inches (about 6.36 millimeters) in a direction normal to any airfoil surface location. However, tolerances of about +/−0.15 inches to about +/−0.25 inches (about 6.36 millimeters), or about +/−3% to about +/−5% in a direction normal to an airfoil surface location may also be used, as desired in the specific application.

A point data origin 190 may be the mid-point of the suction or pressure side of the base or tip of the airfoil, the leading edge or trailing edge of the base of the airfoil, or any other suitable location as desired. The coordinate values for the X, Y, and Z coordinates are set forth in non-dimensionalized units in scalable TABLE 1, although other units of dimensions may be used when the values are appropriately converted. As one example only, the Cartesian coordinate values of X, Y, and Z may be convertible to dimensional distances by multiplying the X, Y, and Z values by a constant number (e.g., 100). The number, used to convert the non-dimensional values to dimensional distances, may be a fraction (e.g., ½, ¼, etc.), decimal fraction (e.g., 0.5, 1.5, 10.25, etc.), integer (e.g., 1, 2, 10, 100, etc.), a mixed number (e.g., 11/2, 101/4, etc.), and the like. The dimensional distances may be in any suitable format (e.g., inches, feet, millimeters, centimeters, meters, etc.) As one non-limiting example only, the Cartesian coordinate system has orthogonally-related X, Y, and Z axes and the X axis may lie generally parallel to the compressor rotor centerline, 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 and the positive Z coordinate value is radially outwardly toward the rotor blade tip or stator vane base. All the values in scalable TABLE 1 are given at room temperature and are unfilleted.

By defining X and Y coordinate values at selected locations in a Z direction (or height) normal to the X, Y plane, the profile section or airfoil shape of the airfoil, at each Z height along the length of the airfoil may be ascertained. By connecting the X and Y values with smooth continuing arcs, each profile section at each Z height may be fixed. The airfoil profiles of the various surface locations between each Z height may be determined by smoothly connecting the adjacent profile sections to one another to form the airfoil profile.

The values in TABLE 1 may be generated and shown from zero to four or more decimal places for determining the profile of the airfoil. As the airfoil heats up the associated stress and temperature may cause a change in the X, Y, and Z values. Accordingly, the values for the profile given in TABLE 1 represent ambient, non-operating or non-hot conditions (e.g., room temperature) and may be for an uncoated airfoil.

There are typical manufacturing tolerances as well as optional coatings which may be accounted for in the actual profile of the airfoil. Each section may be joined smoothly with the other sections to form the complete airfoil shape. 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 1 below. Accordingly, a distance of about +/−5% of chord length and/or +/−0.25 inches (about 6.36 millimeters) in a direction normal to a surface location along the airfoil profile defines an airfoil profile envelope for this particular airfoil design and compressor, i.e., a range of variation between measured points on the actual airfoil surface at nominal cold or room temperature and the ideal position of those points as given in the TABLE 1 below at the same temperature. Additionally, a distance of about +/−5% of a chord length in a direction normal to an airfoil surface location along the airfoil profile also may define an airfoil profile envelope for this particular airfoil design. The data is scalable and the geometry pertains to all aerodynamic scales, at, above and/or below about 3,000 RPM. The stator vane airfoil design is robust to this range of variation without impairment of mechanical and aerodynamic functions.

The coordinate values given in scalable TABLE 1 below provide the nominal profile for exemplary stages of a compressor stator vane. Specifically, a fifth stage stator vane of, for example, a 7HA.01 compressor, a 9HA.01 compressor, and the like:

TABLE 1
SUCTION SIDE	PRESSURE SIDE
X	Y	Z	X	Y	Z
−2.976525	3.369375	−1.205775	3.800475	−4.324275	−1.205775
−2.990925	3.360375	−1.205775	3.801375	−4.322475	−1.205775
−3.004875	3.34305	−1.205775	3.803175	−4.318875	−1.205775
−3.0168	3.317625	−1.205775	3.8061	−4.311	−1.205775
−3.0258	3.28545	−1.205775	3.809475	−4.295025	−1.205775
−3.032775	3.2418	−1.205775	3.808575	−4.269375	−1.205775
−3.036825	3.184425	−1.205775	3.790575	−4.227075	−1.205775
−3.0357	3.112425	−1.205775	3.743325	−4.187475	−1.205775
−3.0285	3.0258	−1.205775	3.676725	−4.1382	−1.205775
−3.0159	2.923425	−1.205775	3.594375	−4.075875	−1.205775
−2.997225	2.80395	−1.205775	3.488625	−3.993075	−1.205775
−2.9709	2.66355	−1.205775	3.3687	−3.894975	−1.205775
−2.936475	2.502	−1.205775	3.242925	−3.787425	−1.205775
−2.892825	2.320875	−1.205775	3.10365	−3.66435	−1.205775
−2.837025	2.121075	−1.205775	2.9511	−3.5253	−1.205775
−2.769525	1.902375	−1.205775	2.78505	−3.370275	−1.205775
−2.6892	1.66545	−1.205775	2.613825	−3.206025	−1.205775
−2.597625	1.4211	−1.205775	2.43765	−3.032325	−1.205775
−2.494125	1.169775	−1.205775	2.256075	−2.84895	−1.205775
−2.37825	0.9117	−1.205775	2.069325	−2.65635	−1.205775
−2.24865	0.647325	−1.205775	1.877175	−2.4543	−1.205775
−2.10465	0.376875	−1.205775	1.680075	−2.242575	−1.205775
−1.945575	0.101925	−1.205775	1.478025	−2.02185	−1.205775
−1.771875	−0.175275	−1.205775	1.2708	−1.791675	−1.205775
−1.588725	−0.444825	−1.205775	1.06515	−1.56015	−1.205775
−1.395675	−0.706275	−1.205775	0.860625	−1.327725	−1.205775
−1.192725	−0.959625	−1.205775	0.657	−1.094175	−1.205775
−0.980775	−1.20555	−1.205775	0.454275	−0.860175	−1.205775
−0.76005	−1.444275	−1.205775	0.25155	−0.626175	−1.205775
−0.53055	−1.676025	−1.205775	0.0495	−0.3915	−1.205775
−0.291825	−1.90035	−1.205775	−0.15165	−0.15615	−1.205775
−0.0441	−2.116575	−1.205775	−0.352125	0.0801	−1.205775
0.210375	−2.324025	−1.205775	−0.55215	0.316575	−1.205775
0.471375	−2.52315	−1.205775	−0.7515	0.5535	−1.205775
0.738225	−2.71395	−1.205775	−0.9495	0.79155	−1.205775
1.001925	−2.89125	−1.205775	−1.1385	1.023525	−1.205775
1.261125	−3.055725	−1.205775	−1.31895	1.2492	−1.205775
1.514475	−3.208275	−1.205775	−1.4904	1.4688	−1.205775
1.7613	−3.35025	−1.205775	−1.6533	1.6821	−1.205775
2.00115	−3.482325	−1.205775	−1.80765	1.888875	−1.205775
2.23335	−3.605625	−1.205775	−1.9539	2.0889	−1.205775
2.45745	−3.721275	−1.205775	−2.092275	2.28195	−1.205775
2.67255	−3.82995	−1.205775	−2.217375	2.459025	−1.205775
2.86875	−3.9276	−1.205775	−2.329875	2.6199	−1.205775
3.0456	−4.015125	−1.205775	−2.43045	2.763675	−1.205775
3.20265	−4.093425	−1.205775	−2.519325	2.89035	−1.205775
3.3489	−4.16835	−1.205775	−2.5974	2.9997	−1.205775
3.4749	−4.23495	−1.205775	−2.664225	3.0915	−1.205775
3.571425	−4.286925	−1.205775	−2.722275	3.16935	−1.205775
3.64815	−4.329225	−1.205775	−2.772675	3.23325	−1.205775
3.705975	−4.360275	−1.205775	−2.8179	3.282975	−1.205775
3.7548	−4.36185	−1.205775	−2.8575	3.318975	−1.205775
3.779325	−4.3497	−1.205775	−2.890575	3.34395	−1.205775
3.791925	−4.337325	−1.205775	−2.9169	3.359925	−1.205775
3.7971	−4.330125	−1.205775	−2.94075	3.369825	−1.205775
3.799575	−4.3263	−1.205775	−2.96145	3.372525	−1.205775
−2.9709	3.17745	−0.489825	3.851775	−4.0068	−0.489825
−2.984175	3.168225	−0.489825	3.852675	−4.005	−0.489825
−2.997675	3.151575	−0.489825	3.854475	−4.0014	−0.489825
−3.0087	3.127275	−0.489825	3.857175	−3.993975	−0.489825
−3.0168	3.09645	−0.489825	3.86055	−3.978225	−0.489825
−3.022875	3.054375	−0.489825	3.85965	−3.953475	−0.489825
−3.02535	2.999475	−0.489825	3.841425	−3.9132	−0.489825
−3.02175	2.93085	−0.489825	3.795075	−3.875625	−0.489825
−3.0114	2.847825	−0.489825	3.7305	−3.8286	−0.489825
−2.994975	2.749725	−0.489825	3.650625	−3.768975	−0.489825
−2.9718	2.6361	−0.489825	3.5478	−3.689775	−0.489825
−2.9403	2.502675	−0.489825	3.43125	−3.595725	−0.489825
−2.899575	2.349675	−0.489825	3.309075	−3.493125	−0.489825
−2.848725	2.177325	−0.489825	3.1734	−3.37545	−0.489825
−2.7846	1.9872	−0.489825	3.02445	−3.242925	−0.489825
−2.707875	1.77975	−0.489825	2.862225	−3.095325	−0.489825
−2.6181	1.555875	−0.489825	2.694825	−2.938725	−0.489825
−2.51685	1.325925	−0.489825	2.5218	−2.773575	−0.489825
−2.4039	1.090575	−0.489825	2.3436	−2.5992	−0.489825
−2.2788	0.849825	−0.489825	2.16	−2.4165	−0.489825
−2.140425	0.60435	−0.489825	1.970775	−2.2248	−0.489825
−1.988325	0.35415	−0.489825	1.77615	−2.02455	−0.489825
−1.821375	0.100125	−0.489825	1.576125	−1.81575	−0.489825
−1.6389	−0.1575	−0.489825	1.3707	−1.5984	−0.489825
−1.44675	−0.408825	−0.489825	1.166175	−1.379925	−0.489825
−1.24605	−0.651825	−0.489825	0.96255	−1.161	−0.489825
−1.03725	−0.8865	−0.489825	0.75915	−0.9414	−0.489825
−0.8208	−1.113525	−0.489825	0.5562	−0.7218	−0.489825
−0.597375	−1.3338	−0.489825	0.3528	−0.502425	−0.489825
−0.3672	−1.546875	−0.489825	0.149625	−0.282825	−0.489825
−0.1296	−1.75275	−0.489825	−0.0531	−0.063	−0.489825
0.114975	−1.95165	−0.489825	−0.2556	0.157275	−0.489825
0.3663	−2.14335	−0.489825	−0.4581	0.377325	−0.489825
0.6228	−2.327625	−0.489825	−0.6606	0.5976	−0.489825
0.88425	−2.504475	−0.489825	−0.8622	0.81855	−0.489825
1.1412	−2.6685	−0.489825	−1.055475	1.033425	−0.489825
1.39275	−2.820825	−0.489825	−1.240425	1.242675	−0.489825
1.6389	−2.962575	−0.489825	−1.41705	1.44585	−0.489825
1.87875	−3.09465	−0.489825	−1.585125	1.643175	−0.489825
2.111625	−3.21795	−0.489825	−1.745325	1.8342	−0.489825
2.33685	−3.332925	−0.489825	−1.89765	2.018925	−0.489825
2.55375	−3.4407	−0.489825	−2.042325	2.1969	−0.489825
2.7621	−3.5424	−0.489825	−2.173725	2.3598	−0.489825
2.952225	−3.63375	−0.489825	−2.2923	2.507625	−0.489825
3.123225	−3.71565	−0.489825	−2.398725	2.6397	−0.489825
3.2751	−3.789225	−0.489825	−2.493	2.7558	−0.489825
3.416625	−3.85965	−0.489825	−2.5758	2.855475	−0.489825
3.53835	−3.922425	−0.489825	−2.6469	2.939175	−0.489825
3.6315	−3.9717	−0.489825	−2.708775	3.0096	−0.489825
3.70575	−4.011525	−0.489825	−2.76255	3.066975	−0.489825
3.76155	−4.041	−0.489825	−2.810025	3.11085	−0.489825
3.808125	−4.042575	−0.489825	−2.851425	3.1419	−0.489825
3.831525	−4.030875	−0.489825	−2.8854	3.162825	−0.489825
3.843675	−4.019175	−0.489825	−2.912625	3.175425	−0.489825
3.848625	−4.0122	−0.489825	−2.9367	3.181725	−0.489825
3.850875	−4.0086	−0.489825	−2.956725	3.18195	−0.489825
−2.967975	3.048975	0	3.8871	−3.78945	0
−2.980575	3.03975	0	3.888	−3.78765	0
−2.993175	3.0231	0	3.889575	−3.784275	0
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4.034475	−2.67435	19.558125	−2.463075	2.76075	19.558125
4.074525	−2.67975	19.558125	−2.500425	2.786175	19.558125
4.095225	−2.670075	19.558125	−2.531025	2.803275	19.558125
4.10535	−2.6595	19.558125	−2.5551	2.813175	19.558125
4.1094	−2.6532	19.558125	−2.57625	2.8179	19.558125
4.110975	−2.65005	19.558125	−2.593575	2.817	19.558125
−2.529675	2.92905	20.274075	3.846825	−2.7513	20.274075
−2.53935	2.919375	20.274075	3.8475	−2.7495	20.274075
−2.545875	2.9025	20.274075	3.848625	−2.74635	20.274075
−2.5479	2.879775	20.274075	3.849975	−2.7396	20.274075
−2.5461	2.853	20.274075	3.849975	−2.72565	20.274075
−2.539575	2.817675	20.274075	3.842775	−2.7054	20.274075
−2.5272	2.77245	20.274075	3.812625	−2.68155	20.274075
−2.50785	2.71755	20.274075	3.765825	−2.659725	20.274075
−2.481525	2.652075	20.274075	3.7035	−2.6298	20.274075
−2.447325	2.57535	20.274075	3.626325	−2.591325	20.274075
−2.405025	2.486475	20.274075	3.5271	−2.5389	20.274075
−2.3535	2.382075	20.274075	3.41415	−2.475675	20.274075
−2.292525	2.262375	20.274075	3.295575	−2.4057	20.274075
−2.22075	2.1285	20.274075	3.1635	−2.3247	20.274075
−2.138175	1.980225	20.274075	3.018375	−2.231775	20.274075
−2.044125	1.817775	20.274075	2.860425	−2.1267	20.274075
−1.9377	1.64205	20.274075	2.6973	−2.013975	20.274075
−1.8234	1.460475	20.274075	2.529225	−1.8936	20.274075
−1.701	1.273275	20.274075	2.3562	−1.7658	20.274075
−1.57005	1.081575	20.274075	2.178	−1.63035	20.274075
−1.43055	0.8856	20.274075	1.995075	−1.487025	20.274075
−1.282275	0.6858	20.274075	1.8072	−1.33605	20.274075
−1.124775	0.48285	20.274075	1.614375	−1.1772	20.274075
−0.957375	0.27675	20.274075	1.416825	−1.0107	20.274075
−0.785475	0.074925	20.274075	1.220625	−0.842625	20.274075
−0.609075	−0.1224	20.274075	1.02555	−0.672975	20.274075
−0.42795	−0.315675	20.274075	0.8316	−0.501975	20.274075
−0.2421	−0.504225	20.274075	0.639	−0.32985	20.274075
−0.051075	−0.68805	20.274075	0.44775	−0.1557	20.274075
0.145125	−0.8667	20.274075	0.258525	0.020025	20.274075
0.3474	−1.039725	20.274075	0.071325	0.198	20.274075
0.5562	−1.2069	20.274075	−0.11385	0.378225	20.274075
0.771525	−1.367775	20.274075	−0.296775	0.560475	20.274075
0.993375	−1.521675	20.274075	−0.477675	0.744975	20.274075
1.220175	−1.6677	20.274075	−0.65655	0.9315	20.274075
1.4436	−1.8018	20.274075	−0.827775	1.113525	20.274075
1.6632	−1.924875	20.274075	−0.99135	1.290825	20.274075
1.878525	−2.0376	20.274075	−1.147725	1.46295	20.274075
2.088675	−2.140425	20.274075	−1.297125	1.6299	20.274075
2.2932	−2.234025	20.274075	−1.439775	1.79145	20.274075
2.49165	−2.319525	20.274075	−1.576125	1.946925	20.274075
2.683575	−2.397375	20.274075	−1.706175	2.09655	20.274075
2.868525	−2.468025	20.274075	−1.824525	2.23335	20.274075
3.037725	−2.529675	20.274075	−1.93185	2.3571	20.274075
3.19095	−2.583	20.274075	−2.027925	2.467575	20.274075
3.327525	−2.6289	20.274075	−2.113425	2.56455	20.274075
3.45555	−2.671425	20.274075	−2.18745	2.648475	20.274075
3.5667	−2.70855	20.274075	−2.25045	2.71935	20.274075
3.651975	−2.737125	20.274075	−2.30535	2.77875	20.274075
3.72015	−2.7603	20.274075	−2.353275	2.82735	20.274075
3.771225	−2.77785	20.274075	−2.394	2.8656	20.274075
3.810825	−2.782575	20.274075	−2.428875	2.89395	20.274075
3.831075	−2.772675	20.274075	−2.457225	2.913525	20.274075
3.84075	−2.762325	20.274075	−2.47995	2.925675	20.274075
3.844575	−2.75625	20.274075	−2.500425	2.932425	20.274075
3.84615	−2.752875	20.274075	−2.517525	2.933325	20.274075
−2.48175	2.99925	20.682	3.642075	−2.79765	20.682
−2.49165	2.99025	20.682	3.642525	−2.79585	20.682
−2.49885	2.973825	20.682	3.64365	−2.7927	20.682
−2.501775	2.95155	20.682	3.645	−2.78595	20.682
−2.5011	2.924775	20.682	3.645	−2.772225	20.682
−2.495925	2.88945	20.682	3.638025	−2.7522	20.682
−2.48535	2.84445	20.682	3.60855	−2.72835	20.682
−2.46825	2.789325	20.682	3.5622	−2.706525	20.682
−2.4444	2.723625	20.682	3.500775	−2.676825	20.682
−2.4138	2.646	20.682	3.4245	−2.63835	20.682
−2.37555	2.556225	20.682	3.32685	−2.58615	20.682
−2.32875	2.4507	20.682	3.2157	−2.522925	20.682
−2.273175	2.329875	20.682	3.098925	−2.452725	20.682
−2.2077	2.1942	20.682	2.968875	−2.3715	20.682
−2.13255	2.043675	20.682	2.82645	−2.27835	20.682
−2.04615	1.878975	20.682	2.67165	−2.172825	20.682
−1.948275	1.7001	20.682	2.5119	−2.059425	20.682
−1.842975	1.51515	20.682	2.3472	−1.93815	20.682
−1.729575	1.3248	20.682	2.177775	−1.809225	20.682
−1.6083	1.129725	20.682	2.003625	−1.6722	20.682
−1.478925	0.93015	20.682	1.82475	−1.5273	20.682
−1.34055	0.726525	20.682	1.6416	−1.374525	20.682
−1.193175	0.519075	20.682	1.454175	−1.21365	20.682
−1.0359	0.3087	20.682	1.26225	−1.045125	20.682
−0.8739	0.10215	20.682	1.0719	−0.874575	20.682
−0.706725	−0.100125	20.682	0.8829	−0.702675	20.682
−0.534825	−0.298125	20.682	0.695475	−0.5292	20.682
−0.357525	−0.49185	20.682	0.509625	−0.3537	20.682
−0.174825	−0.681075	20.682	0.325575	−0.1764	20.682
0.0135	−0.865125	20.682	0.144	0.003375	20.682
0.20835	−1.044	20.682	−0.035325	0.1854	20.682
0.40995	−1.21725	20.682	−0.21195	0.369675	20.682
0.618975	−1.383975	20.682	−0.3861	0.556425	20.682
0.83385	−1.542825	20.682	−0.557775	0.745425	20.682
1.054125	−1.693575	20.682	−0.7272	0.936675	20.682
1.27215	−1.832175	20.682	−0.888975	1.1232	20.682
1.487025	−1.95885	20.682	−1.0431	1.305225	20.682
1.6983	−2.07495	20.682	−1.19025	1.482075	20.682
1.904625	−2.180475	20.682	−1.330425	1.65375	20.682
2.105775	−2.27655	20.682	−1.46385	1.819575	20.682
2.3013	−2.36385	20.682	−1.5912	1.97955	20.682
2.490525	−2.442825	20.682	−1.712475	2.133675	20.682
2.67345	−2.5146	20.682	−1.822725	2.274525	20.682
2.840625	−2.576925	20.682	−1.9224	2.4021	20.682
2.99205	−2.630475	20.682	−2.011725	2.51595	20.682
3.127275	−2.676375	20.682	−2.09115	2.6163	20.682
3.254175	−2.7189	20.682	−2.159775	2.702925	20.682
3.3642	−2.755575	20.682	−2.2185	2.776275	20.682
3.4488	−2.78415	20.682	−2.269575	2.837925	20.682
3.516525	−2.806875	20.682	−2.313675	2.88855	20.682
3.56715	−2.824425	20.682	−2.3517	2.928825	20.682
3.6063	−2.8287	20.682	−2.3841	2.958975	20.682
3.626325	−2.819025	20.682	−2.4111	2.9799	20.682
3.636	−2.808675	20.682	−2.4327	2.993175	20.682
3.639825	−2.802375	20.682	−2.452725	3.00105	20.682
3.6414	−2.799225	20.682	−2.469375	3.00285	20.682
−2.43135	3.06765	21.087	3.4146	−2.8368	21.087
−2.4417	3.0591	21.087	3.41505	−2.835225	21.087
−2.449575	3.043125	21.087	3.416175	−2.83185	21.087
−2.45385	3.0213	21.087	3.417525	−2.825325	21.087
−2.4543	2.99475	21.087	3.417525	−2.811825	21.087
−2.4507	2.95965	21.087	3.410775	−2.7918	21.087
−2.4417	2.91465	21.087	3.381975	−2.76795	21.087
−2.426625	2.85975	21.087	3.3363	−2.74635	21.087
−2.4057	2.7936	21.087	3.275775	−2.716875	21.087
−2.378475	2.71575	21.087	3.20085	−2.6784	21.087
−2.34495	2.625075	21.087	3.10455	−2.6262	21.087
−2.30355	2.51865	21.087	2.995425	−2.56275	21.087
−2.253825	2.396925	21.087	2.880675	−2.49255	21.087
−2.195325	2.259675	21.087	2.753325	−2.4111	21.087
−2.12805	2.10735	21.087	2.6136	−2.317725	21.087
−2.050425	1.940175	21.087	2.462175	−2.21175	21.087
−1.961775	1.758825	21.087	2.306025	−2.0979	21.087
−1.86615	1.571175	21.087	2.14515	−1.97595	21.087
−1.7631	1.3779	21.087	1.979775	−1.846125	21.087
−1.6524	1.1799	21.087	1.81035	−1.707975	21.087
−1.533375	0.97695	21.087	1.63665	−1.56195	21.087
−1.406025	0.769725	21.087	1.458675	−1.4076	21.087
−1.26945	0.55845	21.087	1.276875	−1.244925	21.087
−1.1232	0.343575	21.087	1.091025	−1.0746	21.087
−0.971775	0.13275	21.087	0.906975	−0.902025	21.087
−0.815175	−0.07425	21.087	0.7245	−0.72765	21.087
−0.65295	−0.2772	21.087	0.543825	−0.551475	21.087
−0.485325	−0.475875	21.087	0.3654	−0.373275	21.087
−0.311625	−0.67005	21.087	0.189675	−0.192825	21.087
−0.13185	−0.859725	21.087	0.016425	−0.009675	21.087
0.0549	−1.044225	21.087	−0.1539	0.17595	21.087
0.24885	−1.223325	21.087	−0.3213	0.364275	21.087
0.449775	−1.39545	21.087	−0.485775	0.555075	21.087
0.657	−1.559025	21.087	−0.647775	0.74835	21.087
0.8703	−1.7145	21.087	−0.807075	0.9441	21.087
1.082025	−1.856925	21.087	−0.9585	1.13535	21.087
1.291725	−1.98765	21.087	−1.102275	1.32165	21.087
1.49805	−2.106675	21.087	−1.2393	1.502775	21.087
1.7001	−2.214675	21.087	−1.369125	1.6785	21.087
1.89765	−2.313	21.087	−1.492875	1.8486	21.087
2.090025	−2.401875	21.087	−1.610325	2.01285	21.087
2.27655	−2.481975	21.087	−1.721925	2.1708	21.087
2.45655	−2.554425	21.087	−1.8234	2.315475	21.087
2.6217	−2.6172	21.087	−1.91475	2.446425	21.087
2.7711	−2.670975	21.087	−1.99665	2.56365	21.087
2.90475	−2.7171	21.087	−2.0691	2.666925	21.087
3.0303	−2.759175	21.087	−2.1321	2.75625	21.087
3.1392	−2.795625	21.087	−2.185875	2.831625	21.087
3.2229	−2.82375	21.087	−2.232675	2.895525	21.087
3.289725	−2.846475	21.087	−2.272725	2.9484	21.087
3.3399	−2.863575	21.087	−2.307375	2.9907	21.087
3.378825	−2.868075	21.087	−2.337525	3.022425	21.087
3.39885	−2.8584	21.087	−2.362725	3.0447	21.087
3.408525	−2.847825	21.087	−2.383425	3.0591	21.087
3.41235	−2.84175	21.087	−2.40255	3.067875	21.087
3.413925	−2.838375	21.087	−2.4192	3.07035	21.087
−2.352375	3.170475	21.7062	3.04965	−2.891925	21.7062
−2.363175	3.16305	21.7062	3.050325	−2.89035	21.7062
−2.3724	3.147975	21.7062	3.051225	−2.8872	21.7062
−2.37825	3.126825	21.7062	3.052575	−2.880675	21.7062
−2.380725	3.10095	21.7062	3.052575	−2.8674	21.7062
−2.3796	3.066075	21.7062	3.046275	−2.847825	21.7062
−2.3733	3.0213	21.7062	3.018825	−2.82375	21.7062
−2.36115	2.9664	21.7062	2.97405	−2.802375	21.7062
−2.34405	2.90025	21.7062	2.914875	−2.7729	21.7062
−2.322675	2.8215	21.7062	2.841525	−2.734425	21.7062
−2.2968	2.729925	21.7062	2.747925	−2.682225	21.7062
−2.264175	2.62215	21.7062	2.6415	−2.61855	21.7062
−2.224575	2.498625	21.7062	2.5299	−2.5479	21.7062
−2.177325	2.359125	21.7062	2.40615	−2.466	21.7062
−2.1222	2.204325	21.7062	2.270925	−2.372175	21.7062
−2.0583	2.034	21.7062	2.12445	−2.2653	21.7062
−1.984725	1.849275	21.7062	1.9737	−2.15055	21.7062
−1.90485	1.65825	21.7062	1.818675	−2.027475	21.7062
−1.818225	1.4616	21.7062	1.6596	−1.89585	21.7062
−1.72395	1.2591	21.7062	1.49715	−1.7559	21.7062
−1.622025	1.051425	21.7062	1.3311	−1.607625	21.7062
−1.511775	0.838575	21.7062	1.16145	−1.451025	21.7062
−1.392525	0.621225	21.7062	0.98865	−1.28565	21.7062
−1.2636	0.3996	21.7062	0.81225	−1.11195	21.7062
−1.128825	0.181125	21.7062	0.6381	−0.936	21.7062
−0.987975	−0.033525	21.7062	0.465975	−0.75825	21.7062
−0.840825	−0.2448	21.7062	0.296325	−0.578025	21.7062
−0.687375	−0.45225	21.7062	0.1296	−0.394875	21.7062
−0.527175	−0.65565	21.7062	−0.03375	−0.209025	21.7062
−0.36	−0.855	21.7062	−0.1935	−0.020475	21.7062
−0.186075	−1.048275	21.7062	−0.349425	0.171	21.7062
−0.0063	−1.234125	21.7062	−0.501975	0.365175	21.7062
0.180225	−1.4121	21.7062	−0.650925	0.56205	21.7062
0.3735	−1.581525	21.7062	−0.7965	0.7614	21.7062
0.57375	−1.742625	21.7062	−0.938925	0.963225	21.7062
0.774	−1.89	21.7062	−1.0737	1.160775	21.7062
0.973575	−2.025225	21.7062	−1.20105	1.353375	21.7062
1.17135	−2.148525	21.7062	−1.321425	1.540575	21.7062
1.367325	−2.2608	21.7062	−1.435275	1.722375	21.7062
1.5597	−2.3625	21.7062	−1.542825	1.898325	21.7062
1.74735	−2.454075	21.7062	−1.6443	2.0682	21.7062
1.929825	−2.5362	21.7062	−1.7406	2.231775	21.7062
2.106675	−2.61	21.7062	−1.82745	2.381625	21.7062
2.268675	−2.67345	21.7062	−1.90575	2.5173	21.7062
2.415825	−2.7279	21.7062	−1.9755	2.639025	21.7062
2.547225	−2.774025	21.7062	−2.03625	2.7468	21.7062
2.67075	−2.8161	21.7062	−2.089575	2.839725	21.7062
2.778075	−2.8521	21.7062	−2.13525	2.91825	21.7062
2.86065	−2.879775	21.7062	−2.174625	2.985075	21.7062
2.926575	−2.902275	21.7062	−2.208375	3.040875	21.7062
2.976075	−2.918925	21.7062	−2.238075	3.085425	21.7062
3.014775	−2.9232	21.7062	−2.264175	3.1194	21.7062
3.03435	−2.9133	21.7062	−2.2869	3.14325	21.7062
3.0438	−2.90295	21.7062	−2.30625	3.158775	21.7062
3.047625	−2.896875	21.7062	−2.32425	3.168675	21.7062
3.048975	−2.893725	21.7062	−2.340225	3.1725	21.7062

It will be appreciated that the airfoil 105 disclosed in the above scalable TABLE 1 may be non-scaled, scaled up, or scaled down geometrically for use in other or similar turbine/compressor designs. Consequently, the coordinate values set forth in TABLE 1 may be non-scaled, scaled upwardly, or scaled downwardly such that the general airfoil profile shape remains unchanged. A scaled version of the coordinates in TABLE 1 would be represented by X, Y, and Z coordinate values of TABLE 1, with the X, Y, and Z non-dimensional coordinate values converted to inches or millimeters (or any suitable dimensional system), multiplied or divided by a constant number. The constant number may be a fraction, decimal fraction, integer or mixed number.

The disclosed airfoil shape thus may increase reliability and may be specific to the machine conditions and specifications. The airfoil shape provides a unique profile to achieve (1) interaction between other stages in the compressor; (2) aerodynamic efficiency; and (3) normalized aerodynamic and mechanical blade or vane loadings. The disclosed loci of points allow the gas turbine and the compressor or any other suitable turbine/compressor to run in an efficient, safe and smooth manner. As also noted, any scale of the disclosed airfoil may be adopted as long as (1) interaction between other stages in the compressor; (2) aerodynamic efficiency; and (3) normalized aerodynamic and mechanical blade loadings are maintained in the scaled compressor.

The airfoil 105 described herein thus improves overall compressor efficiency. Specifically, the airfoil 105 may provide the desired turbine/compressor efficiency lapse rate (ISO, hot, cold, part load, etc.). The airfoil 105 also meets all aeromechanics, loading and stress requirements.

It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.

Claims

1. An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape, wherein the X, Y, and Z values are defined from a point data origin which is a mid-point of a suction side of a base of the airfoil shape.

2. The article of manufacture according to claim 1, wherein the article of manufacture comprises a stator vane configured for use with a compressor.

3. The article of manufacture according to claim 1, wherein the airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to an airfoil surface location.

4. The article of manufacture according to claim 1, wherein the number, used to convert the non-dimensional values to dimensional distances, is one of a fraction, a decimal fraction, an integer, and a mixed number.

5. The article of manufacture according to claim 1, wherein a height of the article of manufacture is 1 inch to 20 inches.

6. An article of manufacture having a suction-side nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape, the X, Y, and Z coordinate values being scalable as a function of the number to provide one of a non-scaled, scaled-up, and scaled-down airfoil profile, wherein the X, Y, and Z values are defined from a point data origin which is a mid-point of a suction side of a base of the airfoil profile.

7. The article of manufacture according to claim 6, wherein the article of manufacture comprises a stator vane configured for use with a compressor.

8. The article of manufacture according to claim 6, wherein the suction-side airfoil profile lies in an envelope within +/−5% of a chord length in a direction normal to a suction-side airfoil surface location.

9. The article of manufacture according to claim 6, wherein the number, used to convert the non-dimensional values to dimensional distances, is one of a fraction, a decimal fraction, an integer, and a mixed number.

10. The article of manufacture according to claim 6, wherein a height of the article of manufacture is 1 inch to 20 inches.

11. The article of manufacture according to claim 6, further comprising the article of manufacture having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y, and Z set forth in the scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by the number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape, the X, Y, and Z values being scalable as a function of the number to provide one of a non-scaled, scaled-up, and scaled-down airfoil.

12. A compressor comprising a plurality of stator vanes, each of the plurality of stator vanes including an airfoil having a suction-side airfoil shape, the airfoil having a nominal profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape, wherein the X, Y, and Z values are defined from a point data origin which is a mid-point of a suction side of a base of the airfoil shape.

13. The compressor according to claim 12, wherein the suction-side airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to a suction-side airfoil surface location.

14. The compressor according to claim 12, wherein the number, used to convert the non-dimensional values to dimensional distances, is one of a fraction, a decimal fraction, an integer, and a mixed number.

15. The compressor according to claim 12, wherein a height of each stator vane is 1 inch to 20 inches.

16. The compressor according to claim 12, further comprising each of the plurality of stator vanes having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y, and Z set forth in the scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by the number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape.

17. The compressor according to claim 16, wherein the complete pressure-side airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to a pressure-side airfoil surface location.

18. The compressor according to claim 16, wherein the number, used to convert the non-dimensional values to dimensional distances, is one of a fraction, a decimal fraction, an integer, and a mixed number.