Abstract: The present invention is ceramic matrix composite gas turbine engine component comprising a plurality of cured ceramic matrix composite plies, each ply comprising ceramic fiber tows, each ceramic fiber tow comprising a plurality of ceramic fibers, the tows in each ply lying adjacent to one another such that each ply has a unidirectional orientation. The component further comprises a layer of a coating on the ceramic fibers. The component further comprises a ceramic matrix material lying in interstitial regions between the fibers and tows of each ply and the interstitial region between the plurality of plies, wherein at least a portion of the component is no greater than about 0.021 inch thick. The present invention is also a method for making such a ceramic matrix composite component.

Abstract: An orthogonal stitch-weave method and fiber architecture. The architecture allows near-net-shape composite preforms to be fabricated, thereby reducing costs associated with complex preform shapes and increasing desired strengths of the composite.

Abstract: An orthogonal stitch-weave method and fiber architecture. The architecture allows near-net-shape composite preforms to be fabricated, thereby reducing costs associated with complex preform shapes and increasing desired strengths of the composite.

Abstract: A composite blading member includes an airfoil and a base of composite material layers and a platform of composite material layers interfused with the airfoil and base. The platform comprises a platform shelf and a plurality of spaced-apart platform supports integral with the platform shelf and interfused with surfaces of the base. Such blading member was made by providing a partially cured airfoil-base preform and a platform preform, including an airfoil shaped opening therethrough and preforms of the platform supports. The airfoil-base preform was inserted through the airfoil shaped opening whereby cooperating surfaces of the platform preform and airfoil-base preform were in juxtaposition. The preforms were heated to partially cure them together. Then they were interfused with a binder compatible with material of the preforms under conditions to substantially fully cure the structures.

Abstract: The present invention is a ceramic matrix composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during normal engine operation. The component includes both coated fiber tows and uncoated fiber tows arranged together into a preselected form, wherein the uncoated fiber tows are located at predetermined regions of expected high interlaminate stress. The invention further includes method of manufacturing a CMC such as a composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during engine operation.

Abstract: The present invention is a ceramic matrix composite turbine engine component, wherein the component has a direction of maximum tensile stress during normal engine operation. The component comprises a plurality of biased ceramic plies, wherein each biased ply comprises ceramic fiber tows, the tows being woven in a first warp direction and a second weft direction, the second weft direction lying at a preselected angular orientation with respect to the first warp direction, wherein a greater number of tows are woven in the first warp direction than in the second weft direction, and wherein a number of tows in the second weft direction allows the biased plies to maintain their structural integrity when handled.

Abstract: The present invention is a hybrid ceramic matrix composite turbine engine component comprising an outer shell section(s) and an inner core section(s), wherein the outer shell section(s) and the inner core section(s) were bonded together using an MI process. The outer shell section(s) comprises a SiC/SiC material that has been manufactured using a process selected from the group consisting of a slurry cast MI process and a prepreg MI process. The inner core section(s) comprises a material selected from the group consisting an Si/SiC composite material and a monolithic ceramic material. The Si/SiC composite material may be manufactured using the Silcomp process. The present invention may be a high pressure turbine blade, a high pressure turbine vane, a low pressure turbine blade, or a low pressure turbine vane. The present invention is also a method of manufacturing a hybrid ceramic matrix composite turbine engine component.

Abstract: A method of manufacturing a turbine engine component comprising the steps of providing and laying up a plurality of ceramic plies comprising woven ceramic fiber tows to form a turbine engine component shape, inserting a plurality of tows of oxidizable fugitive fibers into the component shape, such that each fugitive fiber tow passes through a preselected number of ceramic plies, burning off the fugitive fiber tows, the burning producing through-thickness void regions, rigidizing the component shape with a layer of BN and a layer of SiC to form a coated component preform using chemical vapor infiltration, and partially densifying the coated component preform using carbon-containing slurry and filling the through thickness void regions, and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component with in-situ ceramic matrix plugs formed where the through-thickness void regions were located.

Abstract: A method of manufacturing a turbine engine component is disclosed. The method includes the steps of providing a plurality of ceramic cloth plies, each ply having woven ceramic fiber tows and at least one fugitive fiber tow, laying up the plurality of plies in a preselected arrangement to form a turbine engine component shape, oxidizing the fugitive fibers to produce fugitive fiber void regions in the ply, rigidizing the component shape to form a coated component preform using chemical vapor infiltration, partially densifying the coated component preform using carbon-containing slurry, and further densifying the coated component preform with at least silicon to form a ceramic matrix composite turbine engine component having matrix rich regions.

Abstract: In one embodiment, a data storage media comprises: a substrate comprising at least one plastic portion, an edge lift height of less than about 8?, and an axial displacement peak of less than about 500? under shock or vibration excitation; and at least one data layer on said substrate. The data layer can be at least partly read from, written to, or a combination thereof by at least one energy field, and, when the energy field contacts the storage media, the energy field is incident upon the data layer before it could be incident upon the substrate. In another embodiment, the data storage media comprises: a substrate comprising at least one plastic portion and an axial displacement peak of less than about 500? under shock or vibration excitation, and an areal density of about 10 Gbit/in2; and at least one data layer on the substrate.

Abstract: 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.

Abstract: The integral layer provides a ductile interface for attachment locations of a turbine engine component where a metallic surface is adjacent the attachment location. The ductile layer provides a favorable load distribution through the composite at the attachment location, and eliminates the need for a metallic shim.

Abstract: The present invention is a ceramic matrix composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during normal engine operation. The component includes both coated fiber tows and uncoated fiber tows arranged together into a preselected form, wherein the uncoated fiber tows are located at predetermined regions of expected high interlaminate stress. The invention further includes method of manufacturing a CMC such as a composite turbine engine component, wherein the component has a region of expected higher interlaminate stress during engine operation.

Abstract: An orthogonal stitch-weave method and fiber architecture. The architecture allows near-net-shape composite preforms to be fabricated, thereby reducing costs associated with complex preform shapes and increasing desired strengths of the composite.

Abstract: In one embodiment, the data storage media can comprise: a substrate, a data layer, and a reflective layer disposed between the data layer and the substrate. The substrate can comprise a substrate material selected from the group consisting of polyphenylene ether, blends comprising polyphenylene ether, copolymers comprising polyphenylene ether, mixtures comprising polyphenylene ether, reaction products of a compostion comprising polyphenylene ether, and composites comprising polyphenylene ether. The data layer can comprise a material selected from the group consisting of organic dye and inorganic phase change materials. The storage media can comprise imprinted features. In another embodiment, the first surface data storage media can comprise: a substrate, a reflective layer on a first side of the substrate, and a protective layer disposed on a side of the substrate opposite the first side. The protective layer can comprise silicon dioxide. The first surface data storage media comprises imprinted features.

Abstract: The present invention is a ceramic matrix composite turbine engine component, wherein the component has a direction of maximum tensile stress during normal engine operation. The component comprises a plurality of biased ceramic plies, wherein each biased ply comprises ceramic fiber tows, the tows being woven in a first warp direction and a second weft direction, the second weft direction lying at a preselected angular orientation with respect to the first warp direction, wherein a greater number of tows are woven in the first warp direction than in the second weft direction, and wherein a number of tows in the second weft direction allows the biased plies to maintain their structural integrity when handled.

Abstract: The present invention is a hybrid ceramic matrix composite turbine engine component comprising an outer shell section(s) and an inner core section(s), wherein the outer shell section(s) and the inner core section(s) were bonded together using an MI process. The outer shell section(s) comprises a SiC/SiC material that has been manufactured using a process selected from the group consisting of a slurry cast MI process and a prepreg MI process. The inner core section(s) comprises a material selected from the group consisting an Si/SiC composite material and a monolithic ceramic material. The Si/SiC composite material may be manufactured using the Silcomp process. The present invention may be a high pressure turbine blade, a high pressure turbine vane, a low pressure turbine blade, or a low pressure turbine vane. The present invention is also a method of manufacturing a hybrid ceramic matrix composite turbine engine component.

Abstract: A method and apparatus are provided for use in a transceiver of a wireless system that enable analog mode operations to be performed using in-phase (I) and quadrature (Q) values. When operating in the analog mode, the apparatus comprises a processor that receives digital I, Q pairs relating to audio or data signals and performs FM demodulation to generate information content relating to the audio or data signals. When receiving data in the analog mode, the data is in a particular format.

Abstract: The damping performance of an article and a polycarbonate composition is improved and a storage medium for data is provided which comprises the use of at least one ortho-methyl substituted polycarbonate structure.

Abstract: Disclosed herein is a method for retrieving data from a storage media. The method comprises: rotating a storage media having a substrate comprising at least one plastic resin portion and at least one data layer disposed on at least one surface of said substrate, wherein said substrate has a surface roughness of less than about 10 Å, and an axial displacement peak of less than about 500&mgr; under shock or vibration excitation; directing an energy field at said storage media such that said energy field is incident upon the data layer before it can be incident upon the substrate; and retrieving information from the data layer via said energy field.