The disclosure describes the improvement of mobile floating submersible pump systems where such systems are used for rapid deployment water transfer. Such systems are deployed within industrial fire fighting, flood control operations (FIG. 7) and similar water transfer requirements. A floating submersible pump is designed to separate the power system (FIG. 7, item 11), such as a diesel engine, from the pump body (FIG. 7, item 16), which further enables the operator to deploy a pumping system where traditional ground based centrifugal pumps are unable to physically siphon the water. Floating submersible pump systems are cumbersome in nature, requiring heavy equipment and significant manpower to deploy them. The innovation disclosed uses advancements in structural fiber reinforced materials to drastically reduce the weight of such systems, which removes the need for heavy deployment equipment, with the added benefit of corrosion protection from saline environments through the use of chemically inert composites.

An airfoil includes an airfoil wall that defines a leading end, a trailing end, and pressure and suction sides that join the leading end and the trailing end. The airfoil wall includes a wishbone-shaped fiber layer structure that has a pair of arms that merge into a single leg. The pair of arms are formed by first and second S-shaped fiber layers each of which is comprised of a network of fiber tows. The first and second S-shaped fiber layers merge to form the single leg. The single leg comprises fiber tows from each of the first and second S-shaped fiber layers that are interwoven, and the single leg forms at least a portion of the trailing end of the airfoil wall.

The invention relates to a blade (3) of a fan (1) of a turbomachine having a structure made of a composite material comprising a fibrous reinforcement (5) obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement (5) is embedded, the fibrous reinforcement (5) comprising first strands (9) having a predetermined elongation at break, a portion of the fibrous reinforcement (5) further comprising second strands (10) having an elongation at break higher than that of the first strands (9).

A method comprises discharging from a metal vaporization device a vapor of a metal or a metal precursor to a chemical vapor infiltration device where the chemical vapor infiltration device is in fluid communication with the metal vaporization device. The chemical vapor infiltration device contains a preform containing ceramic fibers. The preform is infiltrated with a metallic coating or a coating of a metallic precursor along with a ceramic precursor coating. The metallic coating and/or the metallic precursor coating and the ceramic precursor coating are applied sequentially or simultaneously.

A composite material blade for a fan of a turbine engine, includes a first portion that extends to the root of the blade and that is made of a first material including first fiber reinforcement densified by a first matrix, the blade also including a second portion that extends to the tip of the blade and that is made of a second material that is different from the first material and that includes second fiber reinforcement densified by a second matrix, the second material possessing abrasion resistance that is less than that of the first material.

A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.

A composite aerofoil may include an aerofoil body defining a leading edge and a trailing edge, wherein the body comprises a composite material including a plurality of relatively higher-modulus reinforcement elements, a plurality of relatively tougher polymer-based reinforcement elements, and a matrix material substantially encapsulating the plurality of relatively higher-modulus reinforcement elements and the plurality of relatively tougher polymer-based reinforcement elements. The plurality of relatively higher-modulus reinforcement elements are different from the plurality of relatively tougher polymer-based reinforcement elements. The disclosure also describes techniques for forming composite aerofoils.

A ducted fan device provides enhanced containment capability resulting from a Fan Blade Out (FBO) event. The fan device includes an annular fan shroud (52) and an electric motor disposed at the center driving at least one fan blade (58, 64). The fan shroud (52) has a multilayer structure including a fiber layer (74) and a resin layer (70, 72). The shroud has an opposing section (A) that opposes a tip of at least one of the fan blades (58, 64) and a non-opposing section (B) that does not oppose the tips of the fan blades (58, 64). The opposing and non-opposing sections are arranged in the axial direction. In the non-opposing section (B), the fiber layer (74) is impregnated with part of resin forming the resin layer (70, 72). In the opposing section (A), the fiber layer (74) is not impregnated with the resin forming the resin layer (70, 72).

A fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material including a fibrous reinforcement densified by a matrix, wherein the fibrous texture includes an area of reduced stiffness including warp yarns or strands made of second fibers having a second elongation at break greater than the first elongation at break, the area of reduced stiffness extending in the longitudinal direction from the stilt area and up to a height less than or equal to 30% of the height of the blade, extending in the transverse direction between a first area and a second area, the first area extending over a first length from a first edge of the texture intended to form a leading edge, and the second area extending over a second length from a second edge of the texture intended to form a trailing edge.

An airfoil includes an airfoil wall that defines a leading end, a trailing end, and pressure and suction sides that join the leading end and the trailing end. The airfoil wall includes a wishbone-shaped fiber layer structure that has a pair of arms that merge into a single leg. The pair of arms are formed by first and second S-shaped fiber layers each of which is comprised of a network of fiber tows. The first and second S-shaped fiber layers merge to form the single leg. The single leg comprises fiber tows from each of the first and second S-shaped fiber layers that are interwoven, and the single leg forms at least a portion of the trailing end of the airfoil wall.