Patent Application
20160102022
The present disclosure relates generally to composite materials, and more specifically to a process for making composite materials.
Gas turbine engines are used to power aircraft, watercraft, power generators, and the like. Gas turbine engines typically include a compressor, a combustor, and a turbine. The compressor compresses air drawn into the engine and delivers high pressure air to the combustor. In the combustor, fuel is mixed with the high pressure air and ignited. Products of the combustion reaction in the combustor are directed into the turbine where work is extracted to drive the compressor and, sometimes, an output shaft. Left-over products of the combustion are exhausted out of the turbine and may provide thrust in some applications.
Economical and environmental concerns, i.e. improving efficiency and reducing emissions, are the main driving force behind the ever increasing demand for higher gas turbine inlet temperatures. A limitation to the efficiency and emissions of many gas turbine engines is the temperature capability of hot section components (example, but not limited to blades, vanes, blade tracks, combustor liners). Technology improvements in cooling, materials, and coatings are required to achieve higher inlet temperatures. As the temperature capability of nickel (Ni)-based superalloys has approached their intrinsic limit, further improvements in their temperature capability have become increasingly difficult. Next generation high temperature materials, such as ceramic-based materials, may be excellent materials for use in gas turbines.
Ceramic based materials such as silicon carbide (SiC/SiC) may replace nickel based superalloys for hot section structural components for next generation gas turbine engines. A benefit of SiC/SiC CMC engine components is their excellent high temperature mechanical, physical and chemical properties which allow gas turbine engines to operate at much higher temperatures than the current engines having superalloy components. SiC/SiC CMCs also provide the additional benefit of damage tolerance, which monolithic ceramics do not possess.
The present application discloses one or more of the features recited in the appended claims and/or the following features which, alone or in any combination, may comprise patentable subject matter.
According to one aspect, a method of producing a silicon carbide (SiC) ceramic matrix composite (CMC) is disclosed. The method includes incorporating yttrium or ybterrium into a CMC via slurry infiltration. In some embodiments, yttrium or ybterrium may be an oxide, silicate, silicide, or aluminum-silicon eutectic alloy. In some embodiments, the method may include aluminum oxide in a slurry during slurry infiltration. Additionally, in some embodiments, the method may include infiltrating the CMC with molten silicon.
According to another aspect, a ceramic matrix composite (CMC) includes a rare earth silicide. in some embodiments, the rare earth silicide may be YSi, Y5Si4, Y5Si3. Yb3Si5, or YbSi.
A method of producing a silicon carbide (SiC) ceramic matrix composite (CMC) may comprise incorporating yttrium or ybterrium into a CMC. The yttrium or ybterrium may be, incorporated into a slurry and delivered via slurry infiltration.
In sonic embodiments, the yttrium or ybterrium is an oxide, silicate, silicide, or aluminum-silicon eutectic alloy.
In some embodiments, the slurry further includes aluminum oxide.
In some embodiments, the method further includes incorporating molten silicon into the CMC. The molten silicon may be included in the slurry.
A ceramic matrix composite (CMC) may comprise a rare earth silicide.
In some embodiments, the rare earth silicide is YSi, Y5Si4, Y5Si3, Yb3Si5, or YbSi.
These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments.
The present application discloses one or more of the features recited in the appended claims and/or the following features which, alone or in any combination, may comprise patentable subject matter.
Silicon carbide-silicon carbide (SiC/SiC) ceramic composites can suffer from active oxidation when exposed to the environment of a turbine engine. As shown in
These concerns are reduced by the application of an environmental barrier coating (EBC) that consists of rear earth oxides. During operation, the EBC protects the underlying SiC/SiC substrate from the combustion. It has been assumed that EBC will remain adhered to the CMC substrate during the full life of the component. This full life, or prime reliant coating, may be difficult to validate for large civil turbine applications that have requirements that range from 5000 to 20,000 hours.
Methods disclosed herein provide a SiC based CMC with enhanced water vapor stability and CMAS resistance. Improved water vapor stability is achieved by incorporating rare earth elements, yttrium and ytterbium into a matrix, improved CMAS-resistance is achieved by incorporating aluminum oxide into a matrix. The rare earth elements can be introduced into the matrix by slurry or melt infiltration techniques. Y and Yb can be introduced into a matrix in the forms of oxides, silicates, silicides, or a Si—Y/Yb eutectic alloy. Aluminum can be introduced into a matrix in a form of oxide, silicate, silicide, or a Al—Si—Y/Yb eutectic alloy. A process can also include additional gadolinium oxide, Erbium oxide Lutetium oxide, silicate, silicide, or silicon eutectic alloy.
Materials produced by processes disclosed herein have advantages over current melt infiltrate SIC CMC protocols. Advantages include:
1. increased component life when compared to current SiC/SiC;
2. removal of the prime reliant status of EBCs;
3. reduced life cycle cost over current SiC/SiC due to increased component life;
4. reduction of manufacturing cost due to removal of EBC in certain areas of a component (potentially complete removal of BBC in some lower temperature (less than 2300° F. applications); and
5. improved adhesion of EBC due to increase material compatibility.
Embodiments of methods disclosed herein utilize a process 10 shown in
As shown in
Step (2) of the process 10 includes fiber interface coating. The coating is 1 to 10 vol % of the total composite. Fiber coating includes, but is not limited to one or more layer of carbon, carbon nitride, boron nitride, silicon doped boron nitride, silicon nitride, or SINC. A fiber coating as described herein is about 0.1 μm to about 1.0 μm, about 0.1 to about 0.75 μm, about 0.1 μm to about 0.5 μm, wherein the coating can be about 1.0 μm, about 0.9 μm, about 0.8 μm, about 0.7 μm, about 0.6 μm, about 0.5 μm, about 0.4 μm, about 0.3 μm, about 0.2 μm, or about 0.1 μm.
Step (3) of the process 10 includes deposition of a SiC layer around individual layer/tows by chemical vapor infiltration (CVI). Coating of SiC by CVI is about 5 vol % to about 70 vol % of the total composite.
As shown in
Step (5) of the process 10 includes incorporating additives to a composite via melt infiltration (MI). MI additives comprise about 5 vol % to about 20 vol % or about 5 vol % to about 30 vol % of the total composite. MI can utilize a molten silicon, a Y—Al—Si eutectic alloy or Yb—Al—Si eutectic alloy. A molten silicon reacts with yttrium oxide and/or yterrium oxide to form a Y/Yb—Si—O compound. Final composition of a composite depends on amounts of yttrium oxide and yterrium oxide added to the slurry in step (4) of the process 10 shown in
A molten silicon reacts with silicates to form a Si—Y/Yb—O alloy. Final composition of a composite depends on amounts of yttrium oxide and yterrium oxide added to the slurry in step (4) of the process 10. A composite comprising a Si—Y/Yb—O alloy will form an oxide layer containing SiO2 and yttrium/ytterbium silicate during engine operation. As operations continue. such a composite forma yttrium or ytterbium monosilicate or disilicate layer.
When the slurry contains metallic yttrium or metallic ytterbium, the reaction during MI can produce yttrium and/or ytterbium silicides, which can include high temperature rare earth silicides (e.g., YSi, Y5Si4, Y5Si3, Yb3Si5, YbSi, etc).
In this example, steps (1) through (3) were performed. The slurry contained a mixture of SiC and yttrium oxide, ytterbium oxide, or a combination of the two oxides.
The slurry contained 3% to 100% by volume of yttrium or ytterbium oxide, with SiC being added to the slurry when oxide content is below 100%. SiC was added to obtain the desired volume percentage of matrix that is introduced during the slurry infiltration. After slurry infiltration, the part is infiltrated with molten silicon during step (5) of the process 10 shown in
The slurry contains yttrium or ytterbium monosilicate or disilicate. The amount of yttrium silicate or ytterbium silicate in the slurry ranges from 3% to 100% by volume. The yttrium or ytterbium silicate added separately would be mixed in various ratios. In addition to these silicates, the slurry contained 0 to 97% silicon carbide by volume. SiC would be added to obtain the desired amount of matrix that is introduced during the slurry infiltration. During melt infiltration in step (5) of the process 10, molten silicon is introduced to the composite. During the infiltration, the molten silicon reacts with the silicate(s) to form a Si—Y/Yb—O alloy. Due to the higher stability of the silicate under vacuum, higher levels of oxygen will remain in the composite during melt infiltration. The increase oxygen will stabilize a higher melting temperature Si—Y/Yb—O alloy when compared to product formed in Example 1.
In this example, the melt infiltration (MI) step of process 10 (i.e., step (5)) and the slurry (step (4)) are modified. In this example, the molten silicon in step (5) is replaced with either an yttrium-Si eutectic alloy (see
In addition to the Ml alloy modification. step (4) of the process 10 is modified to stabilize a higher melting temperature phase. This is achieved by introducing yttrium or ytterbium into the slurry used in step (4). The metallic element is added to provide a reaction during melt infiltration to form yttrium or ytterbium silicides. The amount of yttrium or ytterbium depends on the amount MI product introduced. The slurry contains sufficient material to form a high temperature rare earth silicide (YSi, Y5Si4, Y5Si3, Yb3Si5, YbSi).
In the example, formation of Y5Si4 is desired, and the eutectic alloy contained 59% silicon by weight. The assumed density for the Y—Si eutectic is 2.90 g/cm3. The reaction to form the final product of Y5Si4 is the following:
4.88 Y0.18SI0.82+4.12 Y→Y5SI4
The slurry contained 57 vol % yttrium and 43 vol % SiC.
The constituents used in process step (4) depend on the desired final product and the amount and type of alloy introduced during process step (5). During engine operations, the composite of Example 3 form a rare earth monosilicate or disilicate. The oxidation product depended on the rare earth suicide and content within the composite.
In this example, the same process as Example 1 is used except for the following modification. The slurry contains a mixture of a) SiC, b) alumina and yttrium oxide, c) ytterbium oxide, d) aluminum oxide, or e) a combination of yttrium oxide and ytterbium oxide.
In this example, the same process of Example 3 is used except for the following modification. The molten silicon of process step (5) is replaced with either an yttrium- or ytterbium-Al—Si eutectic alloy.
While the disclosure has been illustrated and described in detail in the foregoing drawings and description, the same is to be considered as exemplary and not restrictive in character, it being understood that only illustrative, embodiments thereof have been shown and described and that all changes and modifications that come within the spirit of the disclosure are desired to be protected.
This application claims priority to and the benefit of U.S. Provisional Patent Application No. 61/794,581, filed 15 Mar. 2013, the disclosure of which is now incorporated herein by reference.
| Number | Date | Country | |
|---|---|---|---|
| 61794581 | Mar 2013 | US |
