The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to an airfoil shape of a turbomachine component.
Many system requirements must be met for each stage of a gas turbine in order to meet design goals including an overall improvement in compressor efficiency. In particular, first stage compressor stator vanes must meet system requirements including airfoil loading and manufacturability. These first stage compressor stator vanes must operate within a particular set of boundary conditions based on operating conditions of the gas turbine while maintaining a shape that meets design specifications.
According to one aspect of the exemplary embodiment, a turbomachine component includes a compressor stator vane having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, 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 are joined smoothly with one another to form a complete airfoil core shape.
According to another aspect of the exemplary embodiment, a turbomachine includes a compressor portion, and at least one compressor vane provided in the compressor portion. The compressor stator vane includes an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, 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 are joined smoothly with one another to form a complete airfoil core shape.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
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In the exemplary embodiment shown, first stage compressor stator vane 22 includes an airfoil core shape 30 having first and second ends 34 and 36. First end 34 is provided with a base member 38 that serves as an anchor point. More specifically, base member 38 is a dovetail portion that interfaces with a second dovetail slot (not shown) to locate it in the compressor flow path. Airfoil core shape 30 has a profile including a three dimensional (3-D) shape that defines a suction side 44 and a pressure side 46 as well as a leading edge 49 and a trailing edge 48.
An important aspect of first stage compressor stator vane 22 is airfoil core shape 30, which in accordance with an exemplary embodiment is configured for enhanced turbine performance. A list of X, Y, and Z coordinates or points for airfoil core shape 30 is presented in TABLE I, and meets compressor requirements for interaction between adjacent stages, aerodynamic efficiency and provides an improved aeromechanics margin over prior shapes. Moreover, the particular airfoil core shape 30 in accordance with the exemplary embodiment meets system requirements for flow dynamics, loading, and frequency response. The points are arrived at by iteration between aerodynamic and mechanical design improvements and are the only loci of points that allow turbomachine 2 to operate in an efficient, smooth manner. As will become more fully evident below, airfoil core shape 30 is represented as a set of 3024 points listed in TABLE 1. The 3024 points represent 27 airfoil sections each containing 112 points, of which 24 sections comprise airfoil core shape 30. The X, Y, and Z coordinates, which represent a profile of airfoil core shape 30, are created in a coordinate system which is defined relative to a cold engine part. The origin of the coordinate system on the cold centerline axis is X=0.0, Y=0.0 and Z=0.0. The Z coordinate axis is defined as a radial line from the Y coordinate axis; the X coordinate axis is defined as being normal to a plane defined by the Y-Z axis. The airfoil sections are cut normal to the Z coordinate axis. X and Y points, which make up the airfoil core profile shape at each section, are in inches. The radial Z values in inches for the section planes have an origin of Z0.
The radial distance between each section varies however a total radial distance of airfoil core shape 30 is 15.4294 inches. The bottom and top sections Zo and Z1, may be obscured by cast-in features, such as base member 38, that are not included in the X, Y, and Z points that define airfoil core shape 30. All of the 3024 points are taken from a nominal cold or room temperature for each airfoil section of airfoil core shape 30. Each airfoil section is joined smoothly with adjacent airfoil sections to form the airfoil core shape 30.
It should be appreciated that as each compressor stator vane 22 heats up during operation of compressor portion 4, the airfoil core profile shape will change as a result of stress and temperature. Thus, the X, Y and Z points are provided at cold or room temperature for manufacturing purposes. Since the manufactured airfoil core shape may be different from a nominal airfoil core shape defined in Table 1, a tolerance of +0.160 and −0.0 inches from the nominal profile is allowed and thus defines an overall design envelope for airfoil core shape 30. The overall design is robust to this design envelope without impairment of mechanical or aerodynamic properties of first stage compressor stator vane 22.
It should also be appreciated that the airfoil core shape 30 can be scaled up or scaled down geometrically for introductions into similar turbine designs, with smaller or larger frame sizes. Consequently, the X, Y, and Z coordinates in inches may be multiplied or divided by the same constant or number/factor to provide a scaled up or scaled down version of first stage stator vane 22 while retaining the airfoil core profile shape and unique properties.
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In no way limiting of the exemplary embodiment, airfoil core shape 30 provides an increased efficiency as much as 0.15% compared to previous individual airfoil core shapes for first stage compressor stator vane 22. Moreover, and in no way limiting of the exemplary embodiment, in conjunction with other airfoil core shapes, which are conventional or enhanced (similar to the enhancements herein), airfoil core shape 30, as embodied by the invention, provides an increased efficiency as much as 0.15% compared to previous individual sets of airfoil core shapes for first stage compressor stator vane 22. This increased efficiency provides, in addition to the above-noted advantages, a power output with a decrease the required fuel, therefore inherently decreasing emissions to produce energy. Of course, other such advantages are within the scope of the exemplary embodiment.
At this point it should be understood that the points disclosed in Table 1 are exemplary, variations/deviations from the points in Table 1 at one or more sections that do not substantially affect the desired properties obtained by the airfoil core shape of the exemplary embodiments fall within the scope of the exemplary embodiments of the invention.
While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.