AIRFOIL SHAPE FOR A COMPRESSOR BLADE
This application is a continuation in part of US Serial Number 10/911,742 filed August 5, 2004 (GE Docket 149945), the entire contents thereof are incorporated herein.
BACKGROUND OF THE INVENTION
The present invention relates to airfoils for a rotor blade of a gas turbine. In particular, the invention relates to compressor airfoil profiles for various stages of the compressor. In particular, the invention relates to compressor airfoil profiles for either inlet guide vanes, rotors, or stators at various stages of the compressor.
In a gas turbine, many system requirements should be met at each stage of a gas turbine's flow path section to meet design goals. These design goals include, but are not limited to, overall improved efficiency and airfoil loading capability. For example, and in no way limiting of the invention, a blade of a compressor stator should achieve thermal and mechanical operating requirements for that particular stage. Further, for example, and in no way limiting of the invention, a blade of a compressor rotor should achieve thermal and mechanical operating requirements for that particular stage.
BRIEF DESCRIPTION OF THE INVENTION
In accordance with one aspect of the instant invention, an article of manufacture having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S-16S, 1R-17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
In accordance with another aspect of the instant invention, a compressor comprising a compressor wheel. The compressor wheel having a plurality of articles of manufacture. Each of the articles of manufacture including an airfoil having an airfoil shape. The airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S-16S, 1R-17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
In accordance with yet another aspect of the instant invention, a compressor comprising a compressor wheel having a plurality of articles of manufacture. Each of the articles of manufacture including an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a table. The table selected from the group of tables consisting of TABLES 1S-16S, 1R-17R, and IGV. Wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
BRIEF DESCRIPTION OF THE DRAWINGS
FIGURE 1 is a schematic representation of a compressor flow path through multiple stages of a gas turbine and illustrates an exemplary tenth stage rotor blade airfoil according to an embodiment of the invention;
FIGURES 2 and 3 are respective perspective views of a rotor blade according to an embodiment of the invention with the rotor blade airfoil illustrated in conjunction with its platform and its substantially or near axial entry dovetail connection;
FIGURES 4 and 5 are side elevational views of the rotor blade of Figure 2 and associated platform and dovetail connection as viewed in a generally circumferential direction from the pressure and suction sides of the airfoil, respectively;
FIGURE 6 is a cross-sectional view of the rotor blade airfoil taken generally about on line 6-6 in Figure 5;
FIGURE 7 is a perspective views of a rotor blade according to an embodiment of the invention with coordinate system superimposed thereon; and
FIGURE 8 is a perspective views of a stator blade according to an embodiment of the invention with coordinate system superimposed thereon.
DETAILED DESCRIPTION OF THE INVENTION
Referring now to the drawings, Figure 1 illustrates an axial compressor flow path 1 of a gas turbine compressor 2 includes a plurality of compressor stages. The compressor stages are sequentially numbered in the Figure. The compressor flow path comprises seventeen rotor stages and stator stages. However, the exact number of rotor and stator stages is a choice of engineering design. Any number of rotor and stator stages can be provided in the combustor, as embodied by the invention. The seventeen rotor stages are merely exemplary of one turbine design. The seventeen rotor stages are not intended to limit the invention in any manner.
The compressor rotor blades impart kinetic energy to the airflow and therefore bring about a desired pressure rise. Directly following the rotor airfoils is a stage of stator airfoils. Both the rotor and stator airfoils 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 stacked in axial flow compressors to achieve a desired discharge to inlet pressure ratio. Rotor and stator airfoils can be secured to rotor wheels or stator case by an appropriate attachment configuration, often known as a "root", "base" or "dovetail" (see Figures 2-5).
A tenth stage of the compressor 2 is exemplarily illustrated in Figure 1. The tenth stage of the compressor 2 comprises a plurality of circumferentially spaced rotor blades 22 mounted on a rotor wheel 51 and a plurality of circumferentially spaced stator blades 23 attached to a static compressor case 59. Each of the rotor wheels is

attached to aft drive shaft 58, which is connected to the turbine section of the engine. The rotor blades and stator blades lie in the flow path 1 of the compressor. The direction of airflow through the compressor flow path 1, as embodied by the invention, is indicated by the arrow 60 (Figure 1). The tenth stage of the compressor 2 is merely exemplarily of the stages of the compressor 2 within the scope of the invention. The tenth stage of the compressor 2 is not intended to limit the invention in any manner.
The rotor blades 22 are mounted on the rotor wheel 51 forming part of aft drive shaft 58. Each rotor blade 22, as illustrated in Figures 2-6, is provided with a platform 61, and substantially or near axial entry dovetail 62 for connection with a complementary-shaped mating dovetail, not shown, on the rotor wheel 51. An axial entry dovetail, however, may be provided with the airfoil profile, as embodied by the invention. Each rotor blade 22 comprises a rotor blade airfoil 63, as illustrated in Figures 2-6. Thus, each of the rotor blades 22 has a rotor blade airfoil profile 66 at any cross-section from the airfoil root 64 at a midpoint of platform 61 to the rotor blade tip 65 in the general shape of an airfoil (Figure 6).
To define the airfoil shape of the rotor blade airfoil, a unique set or loci of points in space are provided. This unique set or loci of points meet the stage requirements so the stage can be manufactured. This unique loci of points also meets the desired requirements for stage efficiency and reduced thermal and mechanical stresses. The loci of points are arrived at by iteration between aerodynamic and mechanical loadings enabling the compressor to run in an efficient, safe and smooth manner.
The loci, as embodied by the invention, defines the rotor blade airfoil profile and can comprise a set of points relative to the axis of rotation of the engine. For example, a set of points can be provided to define a rotor blade airfoil profile.
A Cartesian coordinate system of X, Y and Z values given in the Tables below defines a profile of a rotor blade airfoil at various locations along its length. The coordinate values for the X, Y and Z coordinates are set forth in inches, although other units of
dimensions may be used when the values are appropriately converted. These values exclude fillet regions of the platform. The Cartesian coordinate system has orthogonally-related X, Y and Z axes. The X axis lies parallel to the compressor blade's dovetail axis, which is at a angle to the engine's centerline, as illustrated in FIGURE 7 for a rotor and Figure 8 for a stator. A positive X coordinate value is axial toward the aft, for example the exhaust end of the compressor. A positive Y coordinate value directed normal to the dovetail axis. A positive Z coordinate value is directed radially outward toward tip of the airfoil, which is towards the static casing of the compressor for rotor blades, and directed radially inward towards the engine centerline of the compressor for stator blades.
By defining X and Y coordinate values at selected locations in a Z direction normal to the X, Y plane, the profile section of the rotor blade airfoil, such as, but not limited to the profile section 66 in Figure 6, at each Z distance along the length of the airfoil can be ascertained. By connecting the X and Y values with smooth continuing arcs, each profile section 66 at each distance Z can be fixed. The airfoil profiles of the various surface locations between the distances Z are determined by smoothly connecting the adjacent profile sections 66 to one another, thus forming the airfoil profile. These values represent the airfoil profiles at ambient, non-operating or non-hot conditions and are for an uncoated airfoil.
The table values are generated and shown to three decimal places for determining the profile of the airfoil. There are typical manufacturing tolerances as well as coatings, which should be accounted for in the actual profile of the airfoil. Accordingly, the values for the profile given are for a nominal airfoil. It will therefore be appreciated that +/- typical manufacturing tolerances, such as, +/-values, including any coating thicknesses, are additive to the X and Y values. Therefore, a distance of about +/-0.160 inches in a direction normal to any surface location along the airfoil profile defines an airfoil profile envelope for a rotor blade airfoil design and compressor. In other words, a distance of about +/- 0.160 inches in a direction normal to any surface location along the airfoil profile defines 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, at the same temperature, as embodied by the invention. The rotor blade airfoil design, as embodied by the invention, is robust to this range of variation without impairment of mechanical and aerodynamic functions.
The coordinate values given in TABLE IS below provide the nominal profile envelope for an exemplary first stage stator.
TABLE 1S
(Table Removed)
The coordinate values given in TABLE 2S below provide the nominal profile envelope for an exemplary second stage stator.
Table 2S
(Table Removed)
The coordinate values given in TABLE 3S below provide the nominal profile envelope for an exemplary third stage stator.
TABLE 3S
(Table Removed)
The coordinate values given in TABLE 4S below provide the nominal profile envelope for an exemplary forth stage stator.
TABLE 4S
(Table Removed)
The coordinate values given in TABLE 5S below provide the nominal profile envelope for an exemplary fifth stage stator.
TABLE 5S
(Table Removed)
The coordinate values given in TABLE 6S below provide the nominal profile envelope for an exemplary sixth stage stator.
TABLE 6S
(Table Removed)
The coordinate values given in TABLE 7S below provide the nominal profile envelope for an exemplary seventh stage stator.
TABLE 7S
(Table Removed)
The coordinate values given in TABLE 8S below provide the nominal profile envelope for an exemplary eighth stage stator.
TABLE 8S
(Table Removed)
The coordinate values given in TABLE 9S below provide the nominal profile envelope for an exemplary ninth stage stator.
TABLE 9S
(Table Removed)
The coordinate values given in TABLE 10S below provide the nominal profile envelope for an exemplary tenth stage stator.
TABLE 10S
(Table Removed)
The coordinate values given in TABLE IIS below provide the nominal profile envelope for an exemplary eleventh stage stator.
TABLE 11S
(Table Removed)
The coordinate values given in TABLE 12S below provide the nominal profile envelope for an exemplary twelfth stage stator.
TABLE 12S
(Table Removed)
The coordinate values given in TABLE 13S below provide the nominal profile envelope for an exemplary thirteenth stage stator.
TABLE 13S
(Table Removed)
The coordinate values given in TABLE 14S below provide the nominal profile envelope for an exemplary fourteenth stage stator.
TABLE 14S
(Table Removed)
The coordinate values given in TABLE 15S below provide the nominal profile envelope for an exemplary fifteenth stage stator.
TABLE 15S
(Table Removed)
The coordinate values given in TABLE 16S below provide the nominal profile envelope for an exemplary sixteenth stage stator.
TABLE 16S
(Table Removed)
The coordinate values given in TABLE 1R below provide the nominal profile envelope for an exemplary first stage rotor.

Table 1R
(Table Removed)
The coordinate values given in TABLE 2R below provide the nominal profile envelope for an exemplary second stage rotor.
TABLE 2R
(Table Removed)
The coordinate values given in TABLE 3R below provide the nominal profile envelope for an exemplary third stage rotor.
TABLE 3R
(Table Removed)
The coordinate values given in TABLE 4R below provide the nominal profile envelope for an exemplary forth stage rotor.
TABLE 4R
(Table Removed)
The coordinate values given in TABLE 5R below provide the nominal profile envelope for an exemplary fifth stage rotor.
TABLE 5R
(Table Removed)
The coordinate values given in TABLE 6R below provide the nominal profile envelope for an exemplary sixth stage rotor.
TABLE 6R
(Table Removed)
The coordinate values given in TABLE 7R below provide the nominal profile envelope for an exemplary seventh stage rotor.
TABLE 7R
(Table Removed)
The coordinate values given in TABLE 8R below provide the nominal profile envelope for an exemplary eighth stage rotor.
TABLE 8R
(Table Removed)
The coordinate values given in TABLE 9R below provide the nominal profile envelope for an exemplary ninth stage rotor.
TABLE 9R
(Table Removed)
The coordinate values given in TABLE 10R below provide the nominal profile envelope for an exemplary tenth stage rotor.
TABLE 10R
(Table Removed)
The coordinate values given in TABLE 11R below provide the nominal profile envelope for an exemplary eleventh stage rotor.
TABLE 11R
(Table Removed)
The coordinate values given in TABLE 12R below provide the nominal profile envelope for an exemplary twelfth stage rotor.
TABLE 12R
(Table Removed)
The coordinate values given in TABLE 13R below provide the nominal profile envelope for an exemplary thirteenth stage rotor.
TABLE 13R
(Table Removed)
The coordinate values given in TABLE 14R below provide the nominal profile envelope for an exemplary fourteenth stage rotor.
TABLE 14R
(Table Removed)
The coordinate values given in TABLE 15R below provide the nominal profile envelope for an exemplary fifteenth stage rotor.
TABLE 15R
(Table Removed)
The coordinate values given in TABLE 16R below provide the nominal profile envelope for an exemplary sixteenth stage rotor.
TABLE 16R
(Table Removed)
The coordinate values given in TABLE IGV below provide the nominal profile envelope for an exemplary inlet guide vane.
TABLE IGV
(Table Removed)
In the exemplary embodiments, as embodied by the invention, for example the tenth stage compressor rotor blade, there are sixty-six (66) rotor blade airfoils, which are
un-cooled. For reference purposes only, there is established point-0 passing through the intersection of the airfoil and the platform along the stacking axis, as illustrated in Figure 5. In the exemplary embodiment of the tenth stage rotor blade hereof, the point-0 is defined as the reference section where the Z coordinate of the table above is at 0.000 inches, which is about 31.737 inches from the engine or rotor centerline. The rotor blade radial height is about 5.626 inches from point-0 to the tip of the airfoil. Consequently, the rotor blade radial height from the engine centerline is about 37.365 inches. The airfoil sections end at about Z =5.588 inches from point-0. Other blades, as embodied by the invention, and set forth in the above tables are also
It will also be appreciated that the exemplary airfoil(s) disclosed in the above Tables may be scaled up or down geometrically for use in other similar compressor designs. Consequently, the coordinate values set forth in the Tables may be scaled upwardly or downwardly such that the airfoil profile shape remains unchanged. A scaled version of the coordinates in Tables would be represented by X, Y and Z coordinate values of Tables multiplied or divided by a constant.
While various embodiments are described herein, it will be appreciated from the specification that various combinations of elements, variations or improvements therein may be made by those skilled in the art, and are within the scope of the invention.

WHAT IS CLAIMED IS:
1. An article of manufacture, the article having a nominal profile substantially in
accordance with Cartesian coordinate values of X, Y and Z set forth in a table, the
table selected from the group of tables consisting of TABLES 1S-16S, 1R-17R, and
IGV, and wherein X and Y are distances in inches which, when connected by smooth
continuing arcs, define airfoil profile sections at each distance Z in inches, the profile
sections at the Z distances being joined smoothly with one another to form a complete
airfoil shape.
2. An article of manufacture according to Claim 1, wherein the article comprises
an airfoil.
3. An article of manufacture according to Claim 2, wherein said article shape lies
in an envelope within ±0.160 inches in a direction normal to any article surface
location.
4. An article of manufacture according to Claim 1, wherein the article comprises
a rotor.
5. An article of manufacture according to Claim 1, wherein the article comprises
a stator.
6. An article of manufacture according to Claim 1, wherein the article comprises
an inlet guide vane.
7. A compressor comprising a compressor wheel having a plurality of articles of
manufacture, each of said articles of manufacture including an airfoil having an airfoil
shape, said airfoil having a nominal profile substantially in accordance with Cartesian
coordinate values of X, Y and Z set forth in a table, the table selected from the group
of tables consisting of TABLES 1S-16S , 1R-17R, and IGV, wherein X and Y are
distances in inches which, when connected by smooth continuing arcs, define the
airfoil profile sections at each distance Z in inches, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
8. A compressor according to Claim 7, wherein the article of manufacture article
comprises a rotor.
9. A compressor according to Claim 7, wherein the article of manufacture
comprises a stator.
10. A compressor according to Claim 7, wherein the article of manufacture
comprises an inlet guide vane.
11. A compressor comprising a compressor wheel having a plurality of articles of
manufacture, each of said articles of manufacture including an airfoil having an
uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate
values of X, Y and Z set forth in a table, the table selected from the group of tables
consisting of TABLES 1S-16S, 1R-17R, and IGV, wherein X and Y are distances in
inches which, when connected by smooth continuing arcs, define airfoil profile
sections at each distance Z in inches, the profile sections at the Z distances being
joined smoothly with one another to form a complete airfoil shape, the X and Y
distances being scalable as a function of the same constant or number to provide a
scaled-up or scaled-down rotor blade airfoil.
12. A compressor according to Claim 11, wherein the article of manufacture
article comprises a rotor.
13. A compressor according to Claim 11, wherein the article of manufacture
comprises a stator.
14. A compressor according to Claim 11, wherein the article of manufacture
comprises an inlet guide vane.
15. A compressor according to Claim 11 wherein said airfoil shape lies in an envelope within ±0.160 inches in a direction normal to any airfoil surface location.