Patent application number | Description | Published |
20100254821 | INTERMEDIATE-MANUFACTURED COMPOSITE AIRFOIL AND METHODS FOR MANUFACTURING - An intermediate-manufactured composite airfoil includes first and second composite skins each having a plurality of fibers in a polymer matrix. A composite core is removably located between the first and second composite skins. The composite core includes a dry, three-dimensional, woven fiber network. The composite core may alternatively include a three-dimensional, woven fiber network in a fully cured polymer matrix. | 10-07-2010 |
20140069535 | FAN CASE DRAINAGE SYSTEM - A casing for installation in more than one circumferential position, includes a shell into which fluid may drain, a pre-installation bottom dead center of the shell, a first post-installation bottom dead center of the shell wherein the first post-installation bottom dead center of the shell is circumferentially rotated a first number of degrees in a first direction from the pre-installation bottom dead center of the shell. The non-limiting embodiment further discloses a first ramp disposed between the first post-installation bottom dead center of the shell and the pre-installation bottom dead center of the shell for directing fluid from the first post-installation bottom dead center of the shell to the pre-installation bottom dead center of the shell. | 03-13-2014 |
20140072421 | FAN CASE BALLISTIC LINER AND METHOD OF MANUFACTURING SAME - A method of manufacturing a fan case with a liner includes the steps of providing a preform having a circular cross-section with a cut and a first diameter, flexing the preform to reduce the first diameter to a second diameter, and adhering the preform to an inner surface of a fan case. A fan case for a gas turbine engine includes a fan case body having an inner surface. A preform is adhered to the inner surface and has a cut providing a gap. | 03-13-2014 |
20150159508 | CORE DRAINAGE SYSTEMS FOR FAN CASE ASSEMBLIES - A core for a fan containment includes an intermediate core segment and a plenum for fluid passage defined through the intermediate core segment. The intermediate core segment has an axial inlet side, an axial outlet side opposed to the axial inlet side, a radially inner side, and a radially outer side opposed to the radially inner side. The radially outer side is configured to be operatively connected to a cylindrical outer case and the radially inner side is configured to be operatively connected to at least one arcuate panel to form a liner assembly. The plenum extends through the intermediate core segment proximate the radially outer side for fluid passage between the axial inlet side and the axial outlet side. | 06-11-2015 |
20150275692 | REDUCED FAN CONTAINMENT THREAT THROUGH LINER AND BLADE DESIGN - A blade containment system includes a plurality of circumferentially-arranged rotatable blades. Each blade has a blade compliance. An annular containment structure is arranged around the rotatable blades. The containment structure includes a liner that has a liner compliance. The blade compliance and the liner compliance are configured such that a strain induced on a respective one of the blades upon impact with the liner is less than a threshold critical strain beyond which the rotatable blades fracture. | 10-01-2015 |
20150345326 | FLOWPATH CARTRIDGE LINER AND GAS TURBINE ENGINE INCLUDING SAME - A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a containment case and a cartridge liner carried therein. A ballistic liner encircles at least a portion of the cartridge liner and is attached thereto. | 12-03-2015 |
20160076395 | METHOD OF MANUFACTURING ICE PANEL SEGMENTS - The present disclosure relates to methods of manufacturing ice panel segments for turbofan engines. An ice panel material may be wrapped around a mandrel. The ice panel material may include an inner fiberglass layer, a plurality of KEVLAR® layers, and an outer fiberglass layer. The ice panel material may be bagged and cured into a rigid molded cylinder. The rigid molded cylinder may be radially cut into ice panel cylinders. The ice panel cylinders may be axially cut into ice panel segments. The ice panel segments may be bonded to an inner surface of a fan case. | 03-17-2016 |
20160123184 | COMBINED FAN CASE ICE LINER AND REAR LINER - A jet engine fan case is disclosed. The fan case may comprise an ice liner section and a rear liner section, wherein the ice liner section and the rear liner section are constructed from a constructed from a single, integral material. The ice liner section may comprise fiberglass and the rear liner section comprises fiberglass, such that the combined liner comprises a single piece. The combined liner may comprise a plurality of segments in the range of one segment to nine segments. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile. The ice liner section may comprise a first cross-sectional profile and the rear liner section may comprise a second cross-sectional profile that is less than the first cross-sectional profile. The combined liner may comprise an uninterrupted aerodynamic surface. | 05-05-2016 |