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. No. 14/845,337; Ser. No. 14/845,347; Ser. No. 14/845,358; Ser. No. 14/845,347; Ser. No. 14/845,370; Ser. No. 14/845,360; Ser. No. 14/845,378; Ser. No. 14/845,388; Ser. No. 14/845,398; Ser. No. 14/845,411, 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 rotor blades, each of the rotor blades 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 rotor blade airfoil as may be described herein.

FIG. 4 is a cross-sectional view of the rotor blade 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, N.Y., 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 rotor blade configured for use with a compressor 15.

FIG. 3 shows an example of a rotor blade 100 as may be described herein. In this example, the rotor blade 100 includes an airfoil 105. Each of the rotor blades 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 the rotor or rotor wheel 65. 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 rotor blade 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 rotor blade 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., 1½, 10¼, 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 rotor blade 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 rotor blade. Specifically, a second stage rotor blade of, for example, a 9HA.01 compressor and the like:

TABLE 1
SUCTION SIDE	PRESSURE SIDE
X	Y	Z	X	Y	Z
2.3893	−0.8395	−1.8662	−5.0817	3.0176	−1.8662
2.3895	−0.8534	−1.8662	−5.0802	3.0185	−1.8662
2.3875	−0.8718	−1.8662	−5.0771	3.0201	−1.8662
2.3816	−0.8942	−1.8662	−5.0708	3.0229	−1.8662
2.3698	−0.9192	−1.8662	−5.0573	3.0263	−1.8662
2.3466	−0.948	−1.8662	−5.0357	3.027	−1.8662
2.306	−0.9736	−1.8662	−4.9978	3.0184	−1.8662
2.2464	−0.9844	−1.8662	−4.9508	2.9966	−1.8662
2.1732	−0.993	−1.8662	−4.8937	2.9589	−1.8662
2.0858	−1.0021	−1.8662	−4.8272	2.9045	−1.8662
1.9836	−1.0117	−1.8662	−4.7455	2.8282	−1.8662
1.8626	−1.0215	−1.8662	−4.6532	2.738	−1.8662
1.7229	−1.0303	−1.8662	−4.5536	2.6431	−1.8662
1.5643	−1.0364	−1.8662	−4.4395	2.5385	−1.8662
1.3869	−1.0388	−1.8662	−4.3104	2.4247	−1.8662
1.1916	−1.0367	−1.8662	−4.1659	2.3024	−1.8662
0.9785	−1.0286	−1.8662	−4.013	2.1768	−1.8662
0.7572	−1.0136	−1.8662	−3.8507	2.0492	−1.8662
0.5276	−0.9913	−1.8662	−3.679	1.9197	−1.8662
0.29	−0.9612	−1.8662	−3.4979	1.7883	−1.8662
0.0444	−0.922	−1.8662	−3.3077	1.6552	−1.8662
−0.2089	−0.873	−1.8662	−3.1085	1.52	−1.8662
−0.4699	−0.8131	−1.8662	−2.9006	1.3823	−1.8662
−0.7384	−0.7412	−1.8662	−2.6841	1.2421	−1.8662
−1.0053	−0.659	−1.8662	−2.4662	1.1039	−1.8662
−1.2694	−0.5669	−1.8662	−2.2469	0.968	−1.8662
−1.5287	−0.4656	−1.8662	−2.0259	0.835	−1.8662
−1.7835	−0.3558	−1.8662	−1.803	0.7053	−1.8662
−2.0341	−0.2378	−1.8662	−1.5784	0.5785	−1.8662
−2.2804	−0.1119	−1.8662	−1.3523	0.4545	−1.8662
−2.5227	0.0218	−1.8662	−1.1246	0.3331	−1.8662
−2.7604	0.1641	−1.8662	−0.8953	0.2152	−1.8662
−2.993	0.3162	−1.8662	−0.6646	0.1016	−1.8662
−3.2202	0.4785	−1.8662	−0.4322	−0.0073	−1.8662
−3.4414	0.6508	−1.8662	−0.198	−0.1107	−1.8662
−3.6474	0.8252	−1.8662	0.0304	−0.2049	−1.8662
−3.839	1.0008	−1.8662	0.2529	−0.2899	−1.8662
−4.0168	1.1767	−1.8662	0.4695	−0.3657	−1.8662
−4.1814	1.3525	−1.8662	0.6803	−0.4326	−1.8662
−4.3337	1.5273	−1.8662	0.8849	−0.4908	−1.8662
−4.474	1.7006	−1.8662	1.0833	−0.5411	−1.8662
−4.6028	1.8722	−1.8662	1.2752	−0.5838	−1.8662
−4.7204	2.0415	−1.8662	1.4522	−0.6177	−1.8662
−4.8213	2.1994	−1.8662	1.6137	−0.6444	−1.8662
−4.9066	2.345	−1.8662	1.7592	−0.6653	−1.8662
−4.9774	2.4772	−1.8662	1.8885	−0.681	−1.8662
−5.0388	2.6037	−1.8662	2.0008	−0.6926	−1.8662
−5.0849	2.7164	−1.8662	2.0959	−0.7012	−1.8662
−5.1114	2.8062	−1.8662	2.1773	−0.7076	−1.8662
−5.1231	2.8801	−1.8662	2.2458	−0.712	−1.8662
−5.1225	2.9364	−1.8662	2.3012	−0.7203	−1.8662
−5.113	2.9774	−1.8662	2.34	−0.7424	−1.8662
−5.1021	2.9982	−1.8662	2.3636	−0.7674	−1.8662
−5.0923	3.0097	−1.8662	2.3767	−0.7897	−1.8662
−5.0865	3.0145	−1.8662	2.3842	−0.8098	−1.8662
−5.0834	3.0166	−1.8662	2.3879	−0.8266	−1.8662
2.37	−0.8356	−1.4154	−5.0906	2.9571	−1.4154
2.3699	−0.8494	−1.4154	−5.0892	2.9581	−1.4154
2.3675	−0.8674	−1.4154	−5.0862	2.9598	−1.4154
2.3611	−0.8894	−1.4154	−5.08	2.9629	−1.4154
2.3487	−0.9137	−1.4154	−5.0668	2.967	−1.4154
2.3247	−0.9412	−1.4154	−5.0454	2.9689	−1.4154
2.2837	−0.9647	−1.4154	−5.0073	2.9624	−1.4154
2.2245	−0.9736	−1.4154	−4.9595	2.9433	−1.4154
2.152	−0.9807	−1.4154	−4.9008	2.9087	−1.4154
2.0657	−0.9881	−1.4154	−4.8323	2.8579	−1.4154
1.9646	−0.9957	−1.4154	−4.748	2.7855	−1.4154
1.8451	−1.0033	−1.4154	−4.653	2.6993	−1.4154
1.7071	−1.0096	−1.4154	−4.5511	2.6081	−1.4154
1.5505	−1.0131	−1.4154	−4.435	2.5072	−1.4154
1.3755	−1.013	−1.4154	−4.3043	2.397	−1.4154
1.1827	−1.0083	−1.4154	−4.1586	2.2781	−1.4154
0.9724	−0.9977	−1.4154	−4.0048	2.1556	−1.4154
0.754	−0.9805	−1.4154	−3.8419	2.0309	−1.4154
0.5274	−0.9563	−1.4154	−3.6698	1.9042	−1.4154
0.2929	−0.9247	−1.4154	−3.4886	1.7755	−1.4154
0.0504	−0.8845	−1.4154	−3.2983	1.6451	−1.4154
−0.1997	−0.835	−1.4154	−3.0991	1.5126	−1.4154
−0.4575	−0.7752	−1.4154	−2.8913	1.3777	−1.4154
−0.7226	−0.7039	−1.4154	−2.6749	1.2404	−1.4154
−0.9862	−0.623	−1.4154	−2.4572	1.105	−1.4154
−1.2471	−0.5329	−1.4154	−2.2381	0.9718	−1.4154
−1.5035	−0.4341	−1.4154	−2.0174	0.8415	−1.4154
−1.7558	−0.3273	−1.4154	−1.7949	0.7144	−1.4154
−2.0041	−0.2126	−1.4154	−1.5708	0.5901	−1.4154
−2.2486	−0.0904	−1.4154	−1.3453	0.4684	−1.4154
−2.4891	0.0394	−1.4154	−1.1184	0.3492	−1.4154
−2.7254	0.1775	−1.4154	−0.8898	0.2331	−1.4154
−2.9567	0.3251	−1.4154	−0.6599	0.1209	−1.4154
−3.183	0.4827	−1.4154	−0.4284	0.0131	−1.4154
−3.4036	0.6501	−1.4154	−0.1953	−0.0895	−1.4154
−3.6099	0.8201	−1.4154	0.0319	−0.1833	−1.4154
−3.8025	0.9918	−1.4154	0.2531	−0.2684	−1.4154
−3.9822	1.1644	−1.4154	0.4683	−0.3446	−1.4154
−4.1492	1.3368	−1.4154	0.6775	−0.4121	−1.4154
−4.304	1.5079	−1.4154	0.8805	−0.4715	−1.4154
−4.4471	1.6771	−1.4154	1.0771	−0.5231	−1.4154
−4.5786	1.8439	−1.4154	1.2673	−0.5674	−1.4154
−4.699	2.0076	−1.4154	1.4425	−0.6031	−1.4154
−4.803	2.1603	−1.4154	1.6023	−0.6316	−1.4154
−4.8916	2.301	−1.4154	1.7461	−0.6544	−1.4154
−4.966	2.4288	−1.4154	1.8739	−0.6719	−1.4154
−5.0312	2.551	−1.4154	1.9852	−0.6852	−1.4154
−5.0811	2.6603	−1.4154	2.0794	−0.6953	−1.4154
−5.1108	2.7475	−1.4154	2.1601	−0.7031	−1.4154
−5.1255	2.8199	−1.4154	2.228	−0.7087	−1.4154
−5.1273	2.8752	−1.4154	2.2832	−0.717	−1.4154
−5.1197	2.9159	−1.4154	2.3219	−0.7388	−1.4154
−5.1099	2.937	−1.4154	2.3453	−0.7637	−1.4154
−5.1006	2.9487	−1.4154	2.3581	−0.7858	−1.4154
−5.0952	2.9538	−1.4154	2.3654	−0.806	−1.4154
−5.0922	2.956	−1.4154	2.3689	−0.8228	−1.4154
2.3571	−0.833	−1.1147	−5.095	2.9207	−1.1147
2.3568	−0.8467	−1.1147	−5.0936	2.9217	−1.1147
2.3541	−0.8646	−1.1147	−5.0906	2.9235	−1.1147
2.3474	−0.8863	−1.1147	−5.0846	2.9267	−1.1147
2.3345	−0.9101	−1.1147	−5.0716	2.9312	−1.1147
2.31	−0.9367	−1.1147	−5.0503	2.9336	−1.1147
2.2686	−0.9588	−1.1147	−5.0122	2.9281	−1.1147
2.2096	−0.9664	−1.1147	−4.9642	2.9103	−1.1147
2.1376	−0.9725	−1.1147	−4.905	2.8775	−1.1147
2.0519	−0.9787	−1.1147	−4.8356	2.8286	−1.1147
1.9515	−0.985	−1.1147	−4.7499	2.7587	−1.1147
1.8329	−0.9911	−1.1147	−4.6536	2.6751	−1.1147
1.6958	−0.9957	−1.1147	−4.5504	2.5864	−1.1147
1.5404	−0.9975	−1.1147	−4.4332	2.4881	−1.1147
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−2.7134	2.0782	17.5322	−1.1177	−0.6512	17.5322
−2.8167	2.3117	17.5322	−1.0095	−0.8805	17.5322
−2.9155	2.5377	17.5322	−0.9025	−1.1007	17.5322
−3.0099	2.7559	17.5322	−0.7967	−1.3117	17.5322
−3.1007	2.9662	17.5322	−0.6924	−1.5136	17.5322
−3.1873	3.1686	17.5322	−0.5899	−1.7066	17.5322
−3.2692	3.3635	17.5322	−0.4895	−1.8908	17.5322
−3.3469	3.5505	17.5322	−0.3918	−2.0665	17.5322
−3.4203	3.7299	17.5322	−0.3013	−2.2264	17.5322
−3.4846	3.8938	17.5322	−0.2188	−2.3705	17.5322
−3.5414	4.0418	17.5322	−0.1446	−2.4994	17.5322
−3.5903	4.174	17.5322	−0.0791	−2.6129	17.5322
−3.6342	4.2986	17.5322	−0.0221	−2.7113	17.5322
−3.6684	4.4078	17.5322	0.0264	−2.7944	17.5322
−3.6905	4.4931	17.5322	0.0679	−2.8653	17.5322
−3.7038	4.5623	17.5322	0.1028	−2.9249	17.5322
−3.7099	4.6148	17.5322	0.1315	−2.974	17.5322
−3.7104	4.6544	17.5322	0.1545	−3.0132	17.5322
−3.7077	4.6762	17.5322	0.1721	−3.0434	17.5322
−3.7032	4.6896	17.5322	0.1853	−3.0661	17.5322
−3.6993	4.6954	17.5322	0.1903	−3.0873	17.5322
−3.6966	4.6978	17.5322	0.1853	−3.1041	17.5322
3.6232	−2.8395	20.6215	−3.1991	2.1716	20.6215
3.6236	−2.8379	20.6215	−3.2042	2.1596	20.6215
3.6241	−2.8345	20.6215	−3.2023	2.142	20.6215
3.6241	−2.8278	20.6215	−3.1958	2.1209	20.6215
3.621	−2.8146	20.6215	−3.1854	2.0966	20.6215
3.6085	−2.7977	20.6215	−3.1693	2.0653	20.6215
3.5735	−2.7819	20.6215	−3.1464	2.0259	20.6215
3.5255	−2.7631	20.6215	−3.1157	1.9778	20.6215
3.4616	−2.7379	20.6215	−3.0768	1.9203	20.6215
3.3817	−2.7063	20.6215	−3.0294	1.8527	20.6215
3.2779	−2.665	20.6215	−2.9729	1.7743	20.6215
3.1583	−2.6171	20.6215	−2.905	1.6825	20.6215
3.0308	−2.5657	20.6215	−2.8257	1.5773	20.6215
2.8877	−2.5071	20.6215	−2.7353	1.4585	20.6215
2.7292	−2.4408	20.6215	−2.6336	1.3262	20.6215
2.5555	−2.3663	20.6215	−2.5201	1.181	20.6215
2.3749	−2.2863	20.6215	−2.3944	1.0231	20.6215
2.1878	−2.2002	20.6215	−2.2621	0.8593	20.6215
1.9944	−2.1075	20.6215	−2.1229	0.69	20.6215
1.7949	−2.0077	20.6215	−1.9763	0.5154	20.6215
1.5894	−1.9007	20.6215	−1.8221	0.336	20.6215
1.3782	−1.786	20.6215	−1.6598	0.152	20.6215
1.1616	−1.663	20.6215	−1.4887	−0.036	20.6215
0.9407	−1.5308	20.6215	−1.3082	−0.2273	20.6215
0.7235	−1.3932	20.6215	−1.1236	−0.4152	20.6215
0.5102	−1.2504	20.6215	−0.9346	−0.599	20.6215
0.3004	−1.1026	20.6215	−0.7409	−0.7779	20.6215
0.0943	−0.9498	20.6215	−0.5433	−0.9507	20.6215
−0.1081	−0.7918	20.6215	−0.3415	−1.1172	20.6215
−0.3064	−0.6282	20.6215	−0.1352	−1.2767	20.6215
−0.501	−0.4593	20.6215	0.0762	−1.4283	20.6215
−0.692	−0.2863	20.6215	0.2936	−1.5708	20.6215
−0.8796	−0.1099	20.6215	0.5171	−1.7039	20.6215
−1.0645	0.0693	20.6215	0.7464	−1.8281	20.6215
−1.2472	0.2507	20.6215	0.9809	−1.9444	20.6215
−1.4221	0.4278	20.6215	1.2118	−2.0503	20.6215
−1.5899	0.5999	20.6215	1.438	−2.1476	20.6215
−1.751	0.7666	20.6215	1.6582	−2.2371	20.6215
−1.9058	0.9274	20.6215	1.8717	−2.3195	20.6215
−2.0546	1.0821	20.6215	2.0782	−2.3954	20.6215
−2.1976	1.2305	20.6215	2.2777	−2.4652	20.6215
−2.3349	1.3725	20.6215	2.4698	−2.5294	20.6215
−2.4608	1.5015	20.6215	2.6542	−2.5886	20.6215
−2.5755	1.6176	20.6215	2.8224	−2.6409	20.6215
−2.6785	1.7209	20.6215	2.9741	−2.6868	20.6215
−2.7698	1.8117	20.6215	3.1091	−2.7269	20.6215
−2.8497	1.8897	20.6215	3.2359	−2.764	20.6215
−2.9181	1.9548	20.6215	3.3458	−2.796	20.6215
−2.9773	2.0097	20.6215	3.4304	−2.8206	20.6215
−3.0276	2.0552	20.6215	3.498	−2.8402	20.6215
−3.0696	2.0919	20.6215	3.5488	−2.8549	20.6215
−3.1039	2.1206	20.6215	3.5869	−2.8654	20.6215
−3.131	2.1416	20.6215	3.6083	−2.8609	20.6215
−3.1522	2.1562	20.6215	3.6184	−2.851	20.6215
−3.1708	2.167	20.6215	3.6217	−2.8447	20.6215
−3.1868	2.1731	20.6215	3.6228	−2.8413	20.6215
3.5007	−2.9524	21.2777	−3.1675	2.2098	21.2777
3.501	−2.9507	21.2777	−3.1728	2.1978	21.2777
3.5014	−2.9473	21.2777	−3.1712	2.1802	21.2777
3.5012	−2.9405	21.2777	−3.1651	2.1591	21.2777
3.4974	−2.9275	21.2777	−3.1552	2.1345	21.2777
3.4843	−2.911	21.2777	−3.1399	2.103	21.2777
3.4491	−2.8955	21.2777	−3.1179	2.063	21.2777
3.4008	−2.877	21.2777	−3.0885	2.0142	21.2777
3.3365	−2.8522	21.2777	−3.0511	1.9557	21.2777
3.2562	−2.8211	21.2777	−3.0056	1.8869	21.2777
3.1519	−2.7804	21.2777	−2.9515	1.807	21.2777
3.0317	−2.733	21.2777	−2.8865	1.7132	21.2777
2.9037	−2.6821	21.2777	−2.8106	1.6056	21.2777
2.76	−2.6239	21.2777	−2.7242	1.4839	21.2777
2.6009	−2.558	21.2777	−2.6272	1.3483	21.2777
2.4265	−2.4838	21.2777	−2.519	1.1992	21.2777
2.2453	−2.4039	21.2777	−2.3994	1.0367	21.2777
2.0577	−2.3178	21.2777	−2.2737	0.8679	21.2777
1.8639	−2.2249	21.2777	−2.1415	0.693	21.2777
1.6642	−2.1246	21.2777	−2.0026	0.5123	21.2777
1.4589	−2.0165	21.2777	−1.8566	0.3261	21.2777
1.2481	−1.9003	21.2777	−1.7028	0.1349	21.2777
1.0324	−1.7749	21.2777	−1.5406	−0.0608	21.2777
0.8126	−1.639	21.2777	−1.3691	−0.2603	21.2777
0.5977	−1.497	21.2777	−1.1932	−0.4564	21.2777
0.3877	−1.3492	21.2777	−1.0124	−0.6484	21.2777
0.1824	−1.1962	21.2777	−0.8271	−0.8348	21.2777
−0.0181	−1.0376	21.2777	−0.6371	−1.0149	21.2777
−0.2135	−0.8731	21.2777	−0.4421	−1.188	21.2777
−0.4037	−0.7027	21.2777	−0.2417	−1.3537	21.2777
−0.5893	−0.527	21.2777	−0.0352	−1.5109	21.2777
−0.771	−0.3468	21.2777	0.1781	−1.6586	21.2777
−0.9494	−0.1628	21.2777	0.3986	−1.7966	21.2777
−1.1252	0.0242	21.2777	0.6258	−1.9253	21.2777
−1.2989	0.2136	21.2777	0.8588	−2.0458	21.2777
−1.4652	0.3985	21.2777	1.0891	−2.1554	21.2777
−1.6246	0.5779	21.2777	1.3148	−2.2555	21.2777
−1.7778	0.7514	21.2777	1.5343	−2.3472	21.2777
−1.9252	0.9186	21.2777	1.7473	−2.4312	21.2777
−2.067	1.0793	21.2777	1.9537	−2.5082	21.2777
−2.2035	1.2332	21.2777	2.1531	−2.5787	21.2777
−2.3349	1.3802	21.2777	2.3453	−2.6433	21.2777
−2.4555	1.5138	21.2777	2.53	−2.7027	21.2777
−2.5654	1.634	21.2777	2.6985	−2.755	21.2777
−2.6643	1.7411	21.2777	2.8505	−2.8008	21.2777
−2.7521	1.835	21.2777	2.9858	−2.8407	21.2777
−2.829	1.9157	21.2777	3.1128	−2.8777	21.2777
−2.8948	1.9832	21.2777	3.223	−2.9094	21.2777
−2.9519	2.0401	21.2777	3.3078	−2.9336	21.2777
−3.0005	2.0872	21.2777	3.3757	−2.953	21.2777
−3.0411	2.1255	21.2777	3.4266	−2.9674	21.2777
−3.0742	2.1553	21.2777	3.4648	−2.9779	21.2777
−3.1006	2.1772	21.2777	3.4861	−2.9736	21.2777
−3.1212	2.1925	21.2777	3.4961	−2.9639	21.2777
−3.1394	2.204	21.2777	3.4993	−2.9575	21.2777
−3.1551	2.2107	21.2777	3.5003	−2.9541	21.2777
3.3784	−3.0651	21.9339	−3.1353	2.2953	21.9339
3.3786	−3.0634	21.9339	−3.1411	2.2836	21.9339
3.3789	−3.06	21.9339	−3.1401	2.2659	21.9339
3.3783	−3.0532	21.9339	−3.1348	2.2444	21.9339
3.3738	−3.0403	21.9339	−3.1258	2.2195	21.9339
3.3599	−3.0242	21.9339	−3.1117	2.1872	21.9339
3.3243	−3.0092	21.9339	−3.0912	2.1463	21.9339
3.2757	−2.9911	21.9339	−3.0636	2.0961	21.9339
3.2109	−2.9668	21.9339	−3.0284	2.036	21.9339
3.1301	−2.9363	21.9339	−2.9856	1.9651	21.9339
3.0251	−2.8962	21.9339	−2.9347	1.8826	21.9339
2.9042	−2.8494	21.9339	−2.8737	1.7857	21.9339
2.7755	−2.7988	21.9339	−2.8025	1.6744	21.9339
2.6311	−2.7409	21.9339	−2.7213	1.5485	21.9339
2.4713	−2.675	21.9339	−2.6301	1.4081	21.9339
2.2963	−2.6006	21.9339	−2.5284	1.2536	21.9339
2.1145	−2.5203	21.9339	−2.4161	1.0851	21.9339
1.9262	−2.4335	21.9339	−2.2981	0.9098	21.9339
1.732	−2.3396	21.9339	−2.1741	0.7279	21.9339
1.5322	−2.238	21.9339	−2.044	0.5398	21.9339
1.3268	−2.1283	21.9339	−1.9071	0.3456	21.9339
1.1163	−2.01	21.9339	−1.7629	0.1458	21.9339
0.9012	−1.8821	21.9339	−1.6106	−0.0588	21.9339
0.6823	−1.743	21.9339	−1.4491	−0.2676	21.9339
0.4687	−1.597	21.9339	−1.2829	−0.473	21.9339
0.2612	−1.4445	21.9339	−1.1112	−0.6743	21.9339
0.0591	−1.286	21.9339	−0.9335	−0.8709	21.9339
−0.1369	−1.1208	21.9339	−0.7501	−1.0609	21.9339
−0.3265	−0.9485	21.9339	−0.5608	−1.2432	21.9339
−0.51	−0.7694	21.9339	−0.3652	−1.4173	21.9339
−0.688	−0.5844	21.9339	−0.1625	−1.5824	21.9339
−0.8616	−0.3944	21.9339	0.0479	−1.7376	21.9339
−1.0316	−0.2005	21.9339	0.2664	−1.8823	21.9339
−1.1986	−0.0034	21.9339	0.4926	−2.0171	21.9339
−1.3631	0.1959	21.9339	0.7257	−2.143	21.9339
−1.5203	0.39	21.9339	0.9562	−2.2568	21.9339
−1.671	0.5783	21.9339	1.1817	−2.36	21.9339
−1.8157	0.7604	21.9339	1.4015	−2.4542	21.9339
−1.955	0.9357	21.9339	1.6152	−2.5403	21.9339
−2.0892	1.1041	21.9339	1.8225	−2.6188	21.9339
−2.2185	1.2654	21.9339	2.0227	−2.6905	21.9339
−2.3431	1.4194	21.9339	2.2158	−2.756	21.9339
−2.4575	1.5595	21.9339	2.4014	−2.816	21.9339
−2.5617	1.6857	21.9339	2.5707	−2.8686	21.9339
−2.6555	1.7982	21.9339	2.7235	−2.9145	21.9339
−2.7388	1.897	21.9339	2.8597	−2.9544	21.9339
−2.8117	1.9819	21.9339	2.9875	−2.9911	21.9339
−2.8743	2.0531	21.9339	3.0984	−3.0225	21.9339
−2.9285	2.1132	21.9339	3.1837	−3.0463	21.9339
−2.9746	2.1633	21.9339	3.2521	−3.0653	21.9339
−3.0131	2.2039	21.9339	3.3034	−3.0795	21.9339
−3.0447	2.2357	21.9339	3.3419	−3.0899	21.9339
−3.07	2.2591	21.9339	3.3636	−3.0865	21.9339
−3.0898	2.2756	21.9339	3.374	−3.0768	21.9339
−3.1074	2.288	21.9339	3.3771	−3.0704	21.9339
−3.1228	2.2956	21.9339	3.3781	−3.0669	21.9339
3.2666	−3.1681	22.5339	−3.1062	2.3769	22.5339
3.2668	−3.1664	22.5339	−3.1124	2.3653	22.5339
3.2669	−3.163	22.5339	−3.112	2.3475	22.5339
3.266	−3.1562	22.5339	−3.1073	2.3258	22.5339
3.2608	−3.1434	22.5339	−3.0991	2.3003	22.5339
3.2462	−3.1279	22.5339	−3.0861	2.2674	22.5339
3.2102	−3.1132	22.5339	−3.0669	2.2256	22.5339
3.1613	−3.0955	22.5339	−3.041	2.1742	22.5339
3.0961	−3.0718	22.5339	−3.0078	2.1126	22.5339
3.0148	−3.0418	22.5339	−2.9674	2.0397	22.5339
2.9092	−3.0023	22.5339	−2.9194	1.9549	22.5339
2.7877	−2.956	22.5339	−2.8619	1.8551	22.5339
2.6584	−2.9058	22.5339	−2.7949	1.7403	22.5339
2.5135	−2.8481	22.5339	−2.7184	1.6105	22.5339
2.3531	−2.7823	22.5339	−2.6325	1.4657	22.5339
2.1777	−2.7076	22.5339	−2.5369	1.3062	22.5339
1.9954	−2.6268	22.5339	−2.4313	1.132	22.5339
1.8067	−2.5392	22.5339	−2.3204	0.9507	22.5339
1.6121	−2.4441	22.5339	−2.2041	0.7624	22.5339
1.4118	−2.3411	22.5339	−2.0818	0.5674	22.5339
1.2063	−2.2294	22.5339	−1.9533	0.3659	22.5339
0.9957	−2.1087	22.5339	−1.8177	0.1586	22.5339
0.7815	−1.9783	22.5339	−1.6742	−0.0541	22.5339
0.5648	−1.8371	22.5339	−1.5216	−0.2714	22.5339
0.3537	−1.6887	22.5339	−1.364	−0.4854	22.5339
0.1484	−1.5328	22.5339	−1.2006	−0.6954	22.5339
−0.0512	−1.3695	22.5339	−1.0305	−0.9008	22.5339
−0.2446	−1.1983	22.5339	−0.8541	−1.0994	22.5339
−0.4314	−1.0186	22.5339	−0.6711	−1.2902	22.5339
−0.6115	−0.8304	22.5339	−0.4808	−1.4724	22.5339
−0.7846	−0.636	22.5339	−0.2825	−1.6452	22.5339
−0.9516	−0.4368	22.5339	−0.0754	−1.8076	22.5339
−1.1137	−0.2338	22.5339	0.1411	−1.959	22.5339
−1.272	−0.0277	22.5339	0.3667	−2.0996	22.5339
−1.4272	0.1807	22.5339	0.6001	−2.2305	22.5339

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 value are defined from a point data origin which is a midpoint 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 an airfoil.

3. The article of manufacture according to claim 1, wherein the article of manufacture comprises a rotor blade configured for use with a compressor.

4. The article of manufacture according to claim 1, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least 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 about 1 inch to about 20 inches (about 2.54 centimeters to about 50.8 centimeters).

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 at least one of a non-scaled, scaled-up, and scaled-down airfoil profile, wherein the X, Y, and Z value are defined from a point data origin which is a midpoint of a suction side of a base of the airfoil shape.

7. The article of manufacture according to claim 6, wherein the article of manufacture comprises an airfoil.

8. The article of manufacture according to claim 6, wherein the article of manufacture comprises a rotor blade configured for use with a compressor.

9. The article of manufacture according to claim 6, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least 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 about 1 inch to about 20 inches (about 2.54 centimeters to about 50.8 centimeters).

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, 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 pressure-side airfoil shape, the X, Y, and Z values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up, and scaled-down airfoil.

12. A compressor comprising a plurality of rotor blades, each of the rotor blades 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 value are defined from a point data origin which is a midpoint of a suction side of a base of the airfoil shape.

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

14. The compressor according to claim 12, wherein a height of each rotor blade is about 1 inch to about 20 inches (about 2.54 centimeters to about 50.8 centimeters).

15. The compressor according to claim 12, further comprising each of the plurality of rotor blades 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, 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, wherein the X, Y, and Z value are defined from a point data origin which is a midpoint of a suction side of a base of the airfoil shape.

16. The compressor according to claim 15, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, a decimal fraction, an integer, and a mixed number.