A metal roofing system contains, in order a roof deck, a fire resistant (FR) fleece, and a metal sheeting system. The second side of the FR fleece faces the roof deck. The FR fleece contains a plurality of FR staple fibers and a plurality of first char scaffold fibers. The FR fleece has a fleece thickness defined as the distance between the first side and the second side. The metal sheeting system contains a plurality of metal sheets having an upper and lower side, where the lower side of the metal sheeting system faces the first side of the FR fleece. The metal sheets have an average metal sheet thickness defined as the distance between the upper and lower sides, where the thickness of the FR fleece is at least about 3 times the average metal sheet thickness. The FR fleece has a density of less 0.5 g/cm.sup.3.

Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.

The present invention has an object of providing a prepreg for producing a laminate suitable as a structural material, and a laminate, which have excellent combustion resistance, compressive strength and interlaminar fractural toughness values, and can be firmly integrated with another structural member by welding. The present invention is a prepreg including structural components: [A] reinforcing fibers, [B] a thermosetting resin, and [C] a thermoplastic resin [C], wherein [B] includes at least one resin selected from a cyanate ester resin having an average cyanate equivalent of 220 or less, a bismaleimide resin having an average maleimide equivalent of 210 or less, and a benzoxazine resin having an average oxazine equivalent of 300 or less, [C] is present on a surface of the prepreg, and the reinforcing fibers [A] are present which are included in a resin area including [B] and a resin area including [C] across an interface between the two resin areas.

A nonwoven fabric sheet exhibiting high flame shielding performance, heat insulating property, and wear resistance is described, where the nonwoven fabric sheet is fabricated and includes at least one fire barrier layer formed of a web containing a non-melting fiber A having a high-temperature shrinkage rate of 3% or less and a thermal conductivity conforming to ISO22007-3 (2008) of 0.060 W/m.Math.K or less and in which the fire barrier layer is coupled with a scrim layer containing a carbide-forming heat resistant fiber B having a LOI value conforming to JIS K 7201-2 (2007) of 25 or more.

A panel includes a first board, a second board, and an edge cap. The first board and the second board each including a core that is sandwiched between and bonded to a first skin and a second skin. The edge cap is positioned between and bonded to the first board and the second board such that a cavity is defined by the first board, the second board, and the edge cap. The cavity is configured to receive an insert and is isolated from forces transferred between the first board and the second board.

A composite film including stacking: a first fiber layer, a metal layer with multiple holes, and a second fiber layer, a stitching structure is arranged along the horizontal direction of the first fiber layer and the second fiber layer within areas of the holes of the metal layer; and the stitching structure in each of the holes is connected, but the stitching structures in different holes are not mutually connected. The stitching structures of this invention pass through the first fiber layer and the second fiber layer, fortifying the stress resistant abilities along the radial direction of the composite film, and thus avoid the peeling off of the stacked structure from the radial direction, and with the independent stitching structure formed independently in each of the holes of the metal layer, the stitching structures would not interact with each other, so that even one of the stitching structure is broken, other stitching structures would not be affected, effectively increasing the durability of the product of this invention.

[Front page view] FIG. 1.

[Brief description of the symbols of front page view] 10 composite film 11 first fiber layer 12 metal layer 121 hole 13 second fiber layer 14 stitching structure

The invention relates to a molding composed of extruded foam, wherein at least one fiber (F) is present with a fiber region (FB2) within the molding and is surrounded by the extruded foam, while a fiber region (FB1) of the fiber (F) projects from a first side of the molding and a fiber region (FB3) of the fiber (F) projects from a second side of the molding, and the extruded foam is produced by an extrusion process comprising the following steps: I) providing a polymer melt in an extruder, II) introducing at least one blowing agent into the polymer melt provided in step I) to obtain a foamable polymer melt, III) extruding the foamable polymer melt obtained in step II) from the extruder through at least one die aperture into an area at lower pressure, with expansion of the foamable polymer melt to obtain an expanded foam, and IV) calibrating the expanded foam from step III) by conducting the expanded foam through a shaping tool to obtain the extruded foam.

Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

A method for bonding composite substrates includes coupling a first co-cure prepreg layer having a first off-set amine to epoxide molar ratio onto a surface of a first composite substrate and coupling a second co-cure prepreg layer having a second off-set amine to epoxide molar ratio onto a surface of a second composite substrate. The first and second composite substrates are cured to the first and second co-cure prepreg layers, respectively, using a first cure cycle (including B-stage and cure temperatures) to form a first and a second co-cure prepreg layer portion. The method further includes coupling the first co-cure prepreg layer portion to the second co-cure prepreg layer portion and applying a second cure cycle to cure the first co-cure prepreg layer portion of the first composite substrate to the second co-cure prepreg layer portion of the second composite substrate to form a monolithic covalently bonded composite structure.

A method of processing ultra high hardness steel is provided to increase its usefulness in armor applications. The method involves slowly cooling the ultra high hardness steel to a cryogenic temperature, slowly returning the steel to an ambient temperature, slowly heating the steel, and again slowly returning it to an ambient temperature.