Patent Grant
7534092
The present invention is related to the following Ser. Nos. 11/286,087, 11/591,692, filed on Oct. 25, 2006, Nov. 2, 2006, respectively.
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.
In accordance with one exemplary 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 TABLE 1. 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 exemplary aspect of the instant invention, a compressor comprises a compressor wheel. The compressor wheel has a plurality of articles of manufacture. Each of the articles of manufacture includes an airfoil having an airfoil shape. The airfoil comprises a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1, 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 exemplary another aspect of the instant invention, a compressor comprises a compressor wheel having a plurality of articles of manufacture. Each of the articles of manufacture includes an airfoil having an uncoated nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in TABLE 1, 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.
Referring now to the drawings,
The compressor rotor blades impart kinetic energy to the airflow and therefore bring about a desired pressure rise across the compressor. 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. The configuration of the airfoil (along with its interaction with surrounding airfoils), including its peripheral surface provides for stage airflow efficiency, enhanced aeromechanics, smooth laminar flow from stage to stage, reduced thermal stresses, enhanced interrelation of the stages to effectively pass the airflow from stage to stage, and reduced mechanical stresses, among other desirable aspects of the invention. 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
A stage of the compressor 2 is exemplarily illustrated in
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
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 Table below defines a profile of a rotor blade airfoil at various locations along its length. The airfoil, as embodied by the invention, could find an application as a 3rd stage airfoil rotor blade. 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
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
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
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 thickness, 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 1 below provide the nominal profile envelope for an exemplary 3rd stage airfoil rotor blade.
It will also be appreciated that the exemplary airfoil(s) disclosed in the above Table 1 may be scaled up or down geometrically for use in other similar compressor designs. Consequently, the coordinate values set forth in the Table 1 may be scaled upwardly or downwardly such that the 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 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.
| Number | Name | Date | Kind |
|---|---|---|---|
| 20060073014 | Tomberg et al. | Apr 2006 | A1 |
| 20070048143 | Noshi | Mar 2007 | A1 |
| 20070177980 | Keener et al. | Aug 2007 | A1 |
| 20070231147 | Tomberg et al. | Oct 2007 | A1 |
| 20080101940 | LaMaster et al. | May 2008 | A1 |
| 20080101941 | LaMaster et al. | May 2008 | A1 |
| 20080101942 | McGowan et al. | May 2008 | A1 |
| 20080101944 | Spracher et al. | May 2008 | A1 |
| 20080101945 | Tomberg et al. | May 2008 | A1 |
| 20080101946 | Duong et al. | May 2008 | A1 |
| 20080101947 | Shrum et al. | May 2008 | A1 |
| 20080101948 | Latimer et al. | May 2008 | A1 |
| 20080101949 | Spracher et al. | May 2008 | A1 |
| 20080101950 | Noshi et al. | May 2008 | A1 |
| 20080101951 | Hudson et al. | May 2008 | A1 |
| 20080101952 | Duong et al. | May 2008 | A1 |
| 20080101953 | Huskins et al. | May 2008 | A1 |
| 20080101954 | Latimer et al. | May 2008 | A1 |
| 20080101955 | McGowan et al. | May 2008 | A1 |
| 20080101956 | Douchkin et al. | May 2008 | A1 |
| 20080101957 | Columbus et al. | May 2008 | A1 |
| 20080101958 | Latimer et al. | May 2008 | A1 |
| 20080107534 | Cheruku et al. | May 2008 | A1 |
| 20080107535 | Radhakrishnan et al. | May 2008 | A1 |
| 20080107536 | Devangada et al. | May 2008 | A1 |
| 20080107537 | Devangada et al. | May 2008 | A1 |
| Number | Date | Country | |
|---|---|---|---|
| 20080101943 A1 | May 2008 | US |
