Patent Application
20110164981
The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a patterned turbomachine component and a method of forming a pattern on a turbomachine component.
Turbomachine components, such as compressor blades, rotate to generate a high pressure air flow. The high pressure air flow combines with a combustion air flow to rotate turbine blades. Changes in aerodynamic properties of either the compressor blades and/or the turbine blades result in changes to overall operational characteristics of the turbomachine. It has been found that increasing a surface area of compressor and/or turbine blades leads to enhanced turbomachine operation.
Conventional methods of increasing surface area of compressor and/or turbine blades include molding processes and etching or machining, i.e., surface removal, processes. In the molding process, patterns are formed on a mold. When cast, the patterns are formed on a surface of the compressor and/or turbine blades. The patterns are configured and disposed to increase an effective surface area and enhance aerodynamic properties of the compressor and/or turbine blades. In the etching process, chemicals, lasers or other methods are employed to remove specific portions from the surface of the compressor and/or turbine blades. As noted above, the patterns are configured and disposed to increase an effective surface area and enhance aerodynamic properties of the compressor and/or turbine blades.
According to one aspect of the invention, a method of forming a pattern on a turbomachine component includes adding material to selected surface regions of the turbomachine component, the material is arranged in a predetermined pattern.
According to another aspect of the invention, a turbomachine component includes a body portion having an external surface. A pattern is formed on the external surface. The pattern includes material added to the external surface through a direct write (DW) process.
System and computer program products for adding material to selected regions of a turbomachine component are also described and claimed herein.
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.
Referring to
In accordance an exemplary embodiment, airfoil surface 38 includes a patterned zone 47 having a plurality of raised elements, one of which is indicated at 54 that enhance aerodynamic performance for turbine bucket 24. Each raised element 54 includes a body portion 57 having a base portion 59 that extends to a tip portion 61. Although shown having a generally trapezoidal form with base portion 59 being larger than tip portion 61, it should be understood that raised element 54 can take on a variety of forms, including forms having rectangular profiles, curvilinear profiles and the like. In accordance with one aspect of the exemplary embodiment, a coating is applied to patterned zone 47. Coating 65 provides additional protection for each raised element 54. In the exemplary embodiment shown, coating 65 is applied in a substantially linear layer. However, it should be understood that coating 65 could also be contoured. In accordance with another aspect of the exemplary embodiment, a plurality of pores 69 are created in body portion 57. Pores 69 further enhance the surface area of raised elements 54.
In further accordance with the exemplary embodiment, patterned zone 47 is formed using a direct right (DW) process. The direct right process adds material to airfoil surface 38 in a predetermined pattern. In accordance with one aspect of the exemplary embodiment, raised elements 54 are formed from at least one of a polymer, a ceramic, a metal, and a composite. Of course other materials and composites may also be employed. As will be discussed more fully below, depending upon the material employed for raised elements 54, prior to adding patterned zone 47, a bond coat 78 is applied to airfoil surface 38. Bond coat 78 enhances adhesion of the plurality of raised features 54 that are added using the DW process.
Reference will now be made to
After heat-treating, a partial overcoat is applied to the plurality of raised features 54 as indicated in block 100. The overcoat or coating is used to provide additional protection to the plurality raised features as indicated above. Of course the need for an overcoat or coating is also dependent on a particular type of material used in forming patterned zone 47. In addition to adding features, material may be removed to form additional patterns in airfoil surface 48. The material is removed using one or more known techniques such as etching, lasers and the like.
At this point, it should be understood that the exemplary embodiments employs a direct write (DW) process to add material to surface portions of a turbomachine component to form a patterned zone. Of course, once added, portions of the material can be selectively removed to alter/adjust the patterned zone. If desired, the material is selectively removed using a solvent to dissolve portions of the patterned zone, or using a laser to remove/alter portions of the patterned zone. In addition to providing patterns on three-dimensional (3D) surfaces such as turbine buckets described above, exemplary embodiments can be employed to create a patterned zone 110 on two-dimensional (2D) surfaces such as a shroud 120 shown in
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.
