Patent application number | Description | Published |
20080206575 | Thermal oxidative barrier coatings for organic matrix composite substrates and coated articles - A thermal oxidative barrier coating for organic matrix composites includes a bond coat having nano-particles dispersed in a polyimide matrix and a thermal barrier layer comprising a silsesquioxane or an inorganic polymer. The nano-particles may include clay platelets, graphite flakes or a polyhedral oligomeric silsesquioxane. The coated article may be utilized in gas turbine engine applications, particularly for a flow path duct adapted for exposure to high temperature, oxygen-containing environments. | 08-28-2008 |
20080213486 | Methods for forming thermal oxidative barrier coatings on organic matrix composite substrates - Methods for forming thermal oxidative barrier coatings for organic matrix composites include applying a bond coat having nano-particles dispersed in a polyimide matrix to a hot side surface of a component and overlying the bond coat with a thermal barrier layer comprising a silsesquioxane or an inorganic polymer. The nano-particles may include clay platelets, graphite flakes or a polyhedral oligomeric silsesquioxane. The bond coat may be applied as a liquid. The thermal barrier layer may be applied as a liquid, film, prepreg, molding compound, or a spray. | 09-04-2008 |
20090142496 | METHOD FOR FABRICATING REINFORCED COMPOSITE MATERIALS - A method for fabricating a reinforced matrix composite comprising the step of providing a composite preform having a fibrous structure and applying matrix material onto the preform in locations along the preform. A barrier material is applied to at least a portion of the coated preform to direct the flow of matrix material into the preform. The composite preform is heated to a temperature sufficient to render the matrix material viscous and insufficient to cure the matrix material. The pressure to the interior of the composite preform is reduced, while the pressure to the barrier material is increased. The temperature is maintained to flow the matrix material into the composite preform and to force gases from the fibrous structure. The composite preform is then cured and cooled to form a reinforced matrix composite having a low void content and a substantially uniform matrix distribution. | 06-04-2009 |
20090162533 | METHODS ALLOWING FOR IMPROVED INSPECTION OF COMPONENTS HAVING A BARRIER COATING - Methods allowing for improved inspection of components having a barrier coating involving providing a component, and applying a barrier coating having at least one layer to the component where the layer of the barrier coating comprises a taggant. | 06-25-2009 |
20090162561 | METHODS FOR MAKING BARRIER COATINGS COMPRISING TAGGANTS AND COMPONENTS HAVING THE SAME - Methods for making barrier coatings including a taggant involving providing a barrier coating, and adding from about 0.01 mol % to about 30 mol % of a taggant to the barrier coating wherein the taggant comprises a rare earth element selected from lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, ytterbium, and lutetium, salts thereof, silicates thereof, oxides thereof, zirconates thereof, hafnates thereof, titanates thereof, tantalates thereof, cerates thereof, aluminates thereof, aluminosilicates thereof, phophates thereof, niobates thereof, borates thereof, and combinations thereof. | 06-25-2009 |
20090162632 | BARRIER COATINGS COMPRISING TAGGANTS AND COMPONENTS COMPRISING THE SAME - Tagged barrier coatings including an environmental barrier coating, a thermal barrier coating, or a combination thereof, and from about 0.01 mol % to about 30 mol % of a taggant. | 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 |
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 |
20100196729 | Autoclave Cure Cycle Design Process and Curing Method - Method includes forming a preform utilizing a polyimide resin-impregnated fiber-reinforced layers; removing solvent from the system at initial vacuum, pressure, and temperature conditions for an initial time interval sufficient to remove substantially all the solvent; imidizing the polyimide resin system under second vacuum, pressure, and temperature conditions for a second time interval sufficient to substantially completely imidize the polyimide resin; consolidating the preform following imidization under third vacuum, pressure, and temperature conditions and including applying pressure to the preform when the preform is at a predetermined temperature; and solidifying the preform under fourth vacuum, pressure, and temperature conditions to provide a cured laminate structure having a shape of a turbine engine component. A method is provided for designing the polyimide resin overall cure cycle dependent on the desired outcome at the solvent removal stage, the imidization stage, the consolidation stage, and the solidification stage. | 08-05-2010 |