Patent Application
20140004293
The present invention relates generally to turbines. More specifically, to a ceramic matrix composite (CMC) component and a method of attaching a metal seal to the ceramic matrix composite component.
A number of techniques have been used in the past to manufacture turbine engine components, such as turbine blades or nozzles using ceramic matrix composites (CMC). One method of manufacturing CMC components relates to the production of silicon carbide matrix composites containing fibrous material that is infiltrated with molten silicon, herein referred to as the Silcomp process. The fibers generally have diameters of about 140 micrometers or greater, which prevents intricate, complex shapes, such as turbine blade components, to be manufactured by the Silcomp process.
Another technique of manufacturing CMC turbine blades is the method known as the slurry cast melt infiltration (MI) process. In one method of manufacturing using the slurry cast MI method, CMCs are produced by initially providing plies of balanced two-dimensional (2D) woven cloth comprising silicon carbide (SiC)-containing fibers, having two weave directions at substantially 90° angles to each other, with substantially the same number of fibers running in both directions of the weave.
Generally, such turbine components require attachment to adjoining metallic hardware and/or metallic surfaces. Two disadvantages associated with attaching a CMC to metallic hardware are the wear of the metallic hardware by the hard, abrasive ceramic material surface, and the lack of load distribution in the CMC. Load distribution is critical in the interfaces between the CMC components and metal surfaces, such as shrouds. Typically, metallic shims or ceramic cloths have been interposed between the CMC and metallic surfaces to improve load distribution. Wear is typically reduced by the application of coatings to the metallic hardware or coatings to the nozzle attachment surfaces.
Therefore, a ceramic matrix composite (CMC) component and a method of attaching a metal seal to a CMC component that do not suffer from the above drawbacks is desirable in the art.
According to an exemplary embodiment of the present disclosure, a ceramic matrix composite component is provided. The ceramic matrix composite component includes a first end and a second end. The ceramic matrix composite component includes a CMC metal interface member attached to the second end. The CMC metal interface member is operable to join to a static seal in a gas turbine.
According to another exemplary embodiment of the present disclosure, a method of attaching a static seal to a ceramic matrix composite component is provided. The method includes providing a ceramic matrix composite component having a first end and a second end. The method includes providing a CMC metal interface member. The method includes attaching the CMC metal interface member to the second end of the ceramic matrix composite component. The method includes providing a static seal and joining the static seal to the CMC metal interface member. The CMC metal interface member forms a plenum for purging rotor air.
Other features and advantages of the present invention will be apparent from the following more detailed description of the preferred embodiment, taken in conjunction with the accompanying drawings which illustrate, by way of example, the principles of the invention.
Wherever possible, the same reference numbers will be used throughout the drawings to represent the same parts.
Provided is a ceramic matrix composite (CMC) component and a method of attaching a metal seal to the CMC component.
One aspect of an embodiment of the present disclosure includes providing a honeycomb seal attachment for a CMC component. Another aspect of the present disclosure is that the system allows for different thermal growth of the CMC component and the CMC metal interface member. Yet another aspect of the present disclosure is that the system provides airfoil cavity sealing. Another aspect of the present disclosure is that the system provides a plenum to feed rotor purge air.
According to one embodiment, CMC component may include a CMC metal interface member attached to second end of CMC component creating a plenum underneath CMC component to distribute air when needed for rotor purge. For example, as shown in
According to one embodiment, CMC metal interface member may include an attachment member. For example, as shown in
According to one embodiment, CMC metal interface member may attach to CMC component by attachment member. For example, as shown in
According to one embodiment, CMC metal interface member may provide a surface to join static seal to CMC component. For example, as shown in
According to one embodiment, a method of attaching a metal seal to a ceramic matrix component may include using a CMC interface member and a static seal. For example,
While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the appended claims.
This patent application claims the benefit of U.S. Provisional Patent Application Ser. No. 61/666,815 filed on Jun. 30, 2012 and entitled “CERAMIC MATRIX COMPOSITE COMPONENT AND A METHOD OF ATTACHING A STATIC SEAL TO A CERAMIC MATRIX COMPOSITE COMPONENT,” the disclosure of which is incorporated by reference as if fully rewritten herein.
| Number | Date | Country | |
|---|---|---|---|
| 61666815 | Jun 2012 | US |
