Teledyne Scientific and Imaging, LLC

The Boeing Company

Boeing North American, Inc.

Brian Nelson Cox

David Bruce Marshall

Janet B Davis

Olivier H Sudre

Julia Jeannine Mack

Sergio Luis Dos Santos E Lucato

Vivek Mehrotra

Rahul Ganguli

Mohsen Khoshnevisan

Peter E Morgan

Ten-Luen T Liao

Min Zhou Berbon

Douglas G Smith

Brock S McCabe

Janet D Davis

An integral textile structure for 3-D CMC turbine airfoils includes top and bottom walls made from an angle-interlock weave, each of the walls comprising warp and weft fiber tows. The top and bottom walls are merged on a first side parallel to the warp fiber tows into a single wall along a portion of their widths, with the weft fiber tows making up the single wall interlocked through the wall's thickness such that delamination of the wall is inhibited. The single wall suitably forms the trailing edge of an airfoil; the top and bottom walls are preferably joined along a second side opposite the first side and parallel to the radial fiber tows by a continuously curved section in which the weave structure remains continuous with the weave structure in the top and bottom walls, the continuously curved section being the leading edge of the airfoil.

Integral textile structure for 3-D CMC turbine airfoils

In one embodiment, a morphable composite three-dimensional structure is disclosed. The morphable composite three-dimensional structure comprises a flexible fiber-reinforced ceramic composite comprising a fiber preform and a ceramic matrix material infused therein. The flexible fiber-reinforced ceramic composite defines a flowpath having a three-dimensional cross-section. The cross-section of the flowpath is variable along the length of the flowpath. A plurality of anchors are integrally formed in the fiber preform. The plurality of anchors extend through a thickness of the ceramic matrix. The plurality of anchors are configured to couple to at least one actuator. The at least one actuator is actuatable to vary the three-dimensional cross-section of the flowpath.

Morphing ceramic composite components for hypersonic wind tunnel

Provided is a method for in-situ coating a substrate or matrix with magnetic metal nanoparticles. A metal salt, which may be organic or inorganic, is introduced into a solution of liquid polyol. In the presence of mechanical stirring and heat, a reduction process occurs wherein the magnetic metal nanoparticles precipitate out of solution and deposit or attach to one or more surfaces of the substrate. The concentration of reaction precursors, combined with the polyol, may be varied to control the size and shape of the magnetic nanoparticles.

In-situ growth of magnetic metal nanoparticles in a matrix

Provided is a prosthesis system for indirectly coupling a prosthesis to the skeletal structure of a person. The system includes a plurality of individual magnets and magnet sets attached to a prosthetic socket of a prosthetic device. The magnets may be permanent magnets or electromagnets. A second plurality of magnets is embedded within a residual limb of a person, mounted to or within a sub-dermal strut. In operation, the magnetic fields generated by the magnets of the prosthetic socket, which may be dynamic magnetic fields, interact with the magnetic fields generated by the magnets anchored beneath the skin of the person, to hold the prosthetic device in position during use. A power supply provides current to any electromagnets, and a controller alters any required magnetic fields based on input received from both load and position sensors in the sub-dermal strut.

Indirect skeletal coupling and dynamic control of prosthesis

An actuable truss with ordered or disordered planar or strut elements or pore walls may be seeded with tissue cells, wherein application of a magnetic field may result in mechanical strain on the cells and increased fluid flow in and out of the truss structure. Modified polymers, such as &#x3b3;-FeO/PLGA, may be used to form actuable scaffolds suitable for tissue engineering. It is also disclosed a device with a trap-door that may be remotely actuated by applying a magnetic field. Such a device may be employed to deliver and control the release of other micro-devices or materials such as drugs to a specific location inside the body of a human or an animal.

Actuable structures and methods of fabrication and use

An exemplary morphable ceramic composite structure includes a flexible ceramic composite skin and a truss structure attached to the skin. The truss structure can morph shape of the skin from a first shape to a second shape that is different than the first shape. The flexible ceramic composite skin may include a single-layer of three-dimensional woven fabric fibers and a ceramic matrix composite. The truss structure may include at least one actuatable element or an actuator may move a portion of the truss structure from a first position to a second position. A cooling component may be disposed in thermal communication with the skin. The cooling component may include thermal insulation or a cooling system that circulates cooling fluid in thermal communication with the skin. The morphable ceramic composite structure may be incorporated into any of an air inlet, combustor, exhaust nozzle, or control surfaces of a hypersonic aircraft.

Morphable ceramic composite skins and structures for hypersonic flight

A self-transpiring hot skin for a hypersonic or reusable space vehicle that can provide protection to the vehicle during short periods of abnormally high heat flux (either planned in the flight profile or an off-nominal event). The hot skin includes a ceramic composite structure having an internal cavity that is coupled either to the insulating layer or directly to the support structure of the hypersonic vehicle. The internal cavity includes a material system that vaporizes, sublimes or decomposes into a gas when the temperature exceeds the upper temperature capability of the composite material. The gas transpires through the outer layer of the composite material to provide cooling to the outer layer below the upper temperature capability. Cooling may occur both by conduction of heat from the composite material to the transpiring gas and by the interaction of the transpiring gas with the boundary layer of hypersonic flow over the outer surface, leading to a reduction of the heat flux entering the surface.

Materials for self-transpiring hot skins for hypersonic vehicles or reusable space vehicles

A woven preform for a ceramic composite has a plurality of layers and structural members. The plurality of layer are of woven yarns of fibrous material. The structural members extend between the layers. The layers and members define interlayer spaces. One or more of the layers may have a plurality of openings extending therethrough. Low density ceramic insulation made be deposited in the interlayer spaces via a slurry that enters the preform, or the preform after it has been made a part of a composite, through the openings. The carrier of the slurry exits the preform, leaving the randomly packed fibers in the interlayer spaces. The structural members may be walls that, along with the layers, define channels. The channels may be used to direct fluid through so as the composite functions as an insulator. The channels may be directed in the warp direction for achieving increased benefits.

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Thousand Oaks, CA, United States of America

Brian Nelson Cox