One aspect of the invention provides a composite refrigeration line set including at least one selected from the group consisting of: a suction line and a return line, characterized in that one or more of the suction line and the return line are a composite refrigeration line set tube include: an inner plastic tube; a first adhesive layer positioned about the inner plastic tube; an aluminum layer positioned about the first adhesive layer and coupled to the inner plastic tube via the first adhesive layer; a second adhesive layer positioned about the aluminum layer; and an outer plastic layer positioned about the aluminum layer coupled to the aluminum layer via the second adhesive layer. The inner plastic tube is polyethylene of raised temperature. The outer plastic tube is polyethylene of raised temperature. The aluminum layer comprises AL 3005-O.

The invention relates to a coated multilayer metal cooking vessel compatible with induction heating, comprising a metal body having a heating face bearing a protective coating and a cooking face bearing a non-stick coating forming a cooking surface.

According to the invention, the metal body comprises an aluminum sheet which is metallurgically bonded to a double-faced aluminized low-carbon ferromagnetic steel sheet forming the heating face, the double-faced aluminized low-carbon ferromagnetic steel sheet comprising a low-carbon ferromagnetic steel substrate having on each of its two faces an outer layer comprising an aluminum-based matrix, an intermediate layer comprising iron/aluminum intermetallic compounds which are arranged between the low-carbon ferromagnetic steel substrate and the outer layer, and, at least on the bottom of the heating face, the outer layer has a thickness of less than 27 gm, preferably less than 20 μm, and more preferably less than 18 μm.

The invention also relates to a cookware article, an electrical cooking appliance and a method for obtaining a coated metal cooking vessel.

One of the objects of the present invention is to provide a thermally conductive silicone resin composition which has good thermal conductivity, a light weight (namely, a light weight per unit volume), and good reliability in high humidity, and a molded body thereof. The present invention provides a thermally conductive silicone resin composition comprising the following components (A) to (E): (A) an organopolysiloxane having at least two alkenyl groups each bonded to a silicon atom in an amount of 100 parts by mass, (B) an organohydrogen polysiloxane having at least two hydrogen atoms each bonded to a silicon atom in an amount such that a ratio of the number of the hydrogen atom bonded to a silicon atom relative to the number of the alkenyl group in component (A) is 0.1 to 2, (C) a thermally conductive filler in an amount of 2500 to 6000 parts by mass, (D) a catalytic amount of an addition reaction catalyst, and (E) an addition-reaction controlling agent in an amount of 0.01 to 1 part by mass, wherein the thermally conductive filler (C) comprises magnesium oxide having a specific surface area of 0.4 m.sup.2/g or less in an amount of 20 to 50 wt % and aluminum hydroxide in an amount of 10 to 30 wt %, relative to a total weight of component (C).

An approach to seeker windows for aircraft comprises a window layer comprising an IR transparent material, the window layer comprising a first side and a second side substantially opposite the first side; and a heating layer on the first side or the second side of the window layer, the heating layer configured to apply a heating profile to the window layer to reduce thermal shock imparted to the window layer when the seeker window is exposed to hypersonic flight conditions.

The invention relates to a pre-impregnated fibre-reinforced composite material in laminar form, obtained impregnating a fibrous mass with a polymeric binder composition and intended to be subjected to successive forming and complete curing operations to produce a fibre-reinforced composite material. The polymeric binder composition comprises one or more resins chosen in the group consisting of siloxane resins and silsesquioxane resins, and can optionally comprise one or more organic resins. The polymeric binder composition appears as a liquid with viscosity between 55000 and 10000 mPas at temperatures between 50° C. and 70° C. The polymeric binder composition forms a polymeric binder matrix, not cross-linked or only partially cross-linked, that fills the interstices of the fibrous mass. The invention also relates to a method for making said pre-impregnated fibre-reinforced composite material in laminar form. The invention also relates to a manufactured article obtained by hot forming and complete curing of the aforesaid pre-impregnated fibre-reinforced composite material, as well as a method for making said manufactured article.

Provided is anisotropic graphite for producing an anisotropic graphite composite having excellent thermal conduction property and excellent long-term reliability as a heat dissipating member. Given an X axis, a Y axis orthogonal to the X axis, and a Z axis perpendicular to a plane defined by the X axis and the Y axis, and a crystal orientation plane of the anisotropic graphite is parallel to an X-Z plane, and a specific number of holes each having a specific size are formed in at least one surface out of surfaces of the anisotropic graphite which are parallel to an X-Y plane.

Forming systems and assemblies as disclosed herein comprise a composite material comprising a structural component and a resin component combined with the reinforcing component. A forming element is disposed within the composite material and has a coefficient of thermal expansion that is greater than that of the composite material. The forming element is positioned to provide a desired integral structural reinforcement and/or surface feature to the composite. The composite material may comprise one or more passages extending from a surface thereof to the forming element. The composite material may be cured by heat to take a set configuration and then allowed to cool. The cooling of the composite material and the forming element enables the forming element to contract relative to the composite material and become delaminated therefrom to facilitate easy removal, and thereby provide an improved method and assembly for making structural reinforcing features in composite structures.

A patient securing overlay is provided that includes a sheet of fabric for supporting a patient's torso on a surgical table. The sheet of fabric has an upper surface configured to face the patient and a lower surface configured to face a surgical table mattress or underbody support. The sheet of fabric includes friction enhancing elements applied to at least a portion of the upper surface thereof. The sheet of fabric can include an extension at a foot end of the sheet of fabric that provides material to be tucked under a foot end of the surgical table mattress or underbody support for securing the foot end of the sheet of fabric to the surgical table mattress or underbody support. The extension can include one or more friction enhancing elements.

One aspect of the invention provides a system including: a length of energy-dissipative tubing; a first sealing device coupled to a first end of the length of energy-dissipative tubing; and a second sealing device coupled to a second end of the length of energy-dissipative tubing. Exposure to one or more selected from the group consisting of: fault currents or lightning strikes at an exposure point along the length of energy-dissipative tubing will produce arcs at the exposure point and at least one of the first end and the second end.

A ceramic circuit board includes a ceramic base material, a metal layer (first metal layer), and a marker portion. The marker portion is formed on the surface of the first metal layer. The surface of the metal layer (first metal layer) may be plated. When the surface of the metal layer (first metal layer) is plated, the marker portion may be formed on the plating.