Patent application number | Description | Published |
20090162539 | METHODS FOR REPAIRING BARRIER COATINGS - Methods for repairing barrier coatings involving providing a component having a barrier coating including at least one damaged portion, removing the damaged portion of the barrier coating leaving a void, applying a replacement tape cast barrier coating to the void of the component, and sintering the component having the replacement tape cast barrier coating layer. | 06-25-2009 |
20090162556 | METHODS FOR MAKING TAPE CAST BARRIER COATINGS, COMPONENTS COMPRISING THE SAME AND TAPES MADE ACCORDING TO THE SAME - Methods for making tape cast barrier coatings involving making a slurry including at least a solvent and a barrier coating composition, depositing the slurry onto a carrier film in a tape casting machine to produce a cast slurry, evaporating the solvent from the cast slurry to produce a tape including the carrier film, and the barrier coating composition, and removing the carrier film from the tape to produce a tape cast barrier coating. | 06-25-2009 |
20090162674 | TAPES COMPRISING BARRIER COATING COMPOSITIONS AND COMPONENTS COMPRISING THE SAME - Tapes including a carrier film, and at least one barrier coating composition applied to the carrier film where the barrier coating composition is an environmental barrier coating composition or a thermal barrier coating composition. | 06-25-2009 |
20090165924 | METHOD OF MANUFACTURING CMC ARTICLES HAVING SMALL COMPLEX FEATURES - A method for forming a ceramic matrix composite (CMC) component for gas turbine engines. The method contemplates replacing a plurality of plies with insert material. The insert material can be partially cured or pre-cured and applied in place of a plurality of small plies or it may be inserted into cavities of a component in the form of a paste or a ply. The insert material is isotropic, being formed of a combination of matrix material and chopped fibers, tow, cut plies or combinations thereof. The use of the insert material allows for features such as thin edges with thicknesses of less than about 0.030 inches and small radii such as found in corners. The CMC components of the present invention replace small ply inserts cut to size to fit into areas of contour change or thickness change, and replace the small ply inserts with a fabricated single piece discontinuously reinforced composite insert, resulting in fewer defects, such as wrinkles, and better dimensional control. | 07-02-2009 |
20090317612 | FUNCTIONALLY GRADIENT SiC/SiC CERAMIC MATRIX COMPOSITES WITH TAILORED PROPERTIES FOR TURBINE ENGINE APPLICATIONS - A ceramic matrix composite with a ceramic matrix and a gradient layering of coating on ceramic fibers. The coating typically improves the performance of the composite in one direction while degrading it in another direction. For a SiC-SiC ceramic matrix composite, a BN coating is layered in a gradient fashion or in a step-wise fashion in different regions of the article comprising the ceramic. The BN coating thickness is applied over the ceramic fibers to produce varying desired physical properties by varying the coating thickness within differing regions of the composite, thereby tailoring the strength of the composite in the different regions. The coating may be applied as a single layer as a multi-layer coating to enhance the performance of the coating as the ceramic matrix is formed or infiltrated from precursor materials into a preform of the ceramic fibers. | 12-24-2009 |
20090324878 | CMC ARTICLES HAVING SMALL COMPLEX FEATURES - A ceramic matrix composite (CMC) component for gas turbine engines, the component having fine features such as thin edges with thicknesses of less than about 0.030 inches and small radii of less that about 0.030 inches formed using the combination of prepreg plies layed up with non-ply ceramic inserts. The CMC components of the present invention replace small ply inserts cut to size to fit into areas of contour change or thickness change, and replace the small ply inserts with a fabricated single piece discontinuously reinforced composite insert, resulting in fewer defects, such as wrinkles, and better dimensional control. | 12-31-2009 |
20110027525 | PREFORMS, COMPOSITE COMPONENTS FORMED THEREWITH, AND PROCESSES THEREFOR - A three-dimensional preform, composite components formed with the preform, and processes for producing the preform and composite materials. The three-dimensional preform includes first and second sets of tows containing filaments. Each tow of the first set has a predetermined polygonal cross-sectional shape and is embedded within a temporary matrix. The preform is fabricated from the first and second sets of tows, in which the second set of tows are transverse to the first set of tows, adjacent tows of the second set are spaced apart to define interstitial regions therebetween, and the polygonal cross-sectional shapes of the first set of tows are substantially congruent to the cross-sectional shapes of the interstitial regions so as to substantially fill the interstitial regions. | 02-03-2011 |
20130167374 | PROCESS OF PRODUCING CERAMIC MATRIX COMPOSITES AND CERAMIC MATRIX COMPOSITES FORMED THEREBY - A process for producing a silicon-containing CMC article. The process entails depositing one or more coating layers on silicon carbide (SiC) fibers, drawing the coated SiC fibers through a slurry to produce slurry-coated fiber material, and then processing the slurry-coated SiC fiber material to form unidirectional prepreg tapes. The tapes are stacked and then fired to yield a porous preform. The porous preform is then further densified by infiltrating the porosity therein to yield a CMC article. Infiltration can be achieved by a series of polymer infiltration and pyrolysis (PIP) steps, by melt infiltration (MI) after filling the porosity in the preform with carbon or one or more refractory metal, by chemical vapor infiltration (CVI), or by a combination of these infiltration techniques. | 07-04-2013 |