A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.

The invention relates to a method for revamping a conventional refinery of mineral oils into a biorefinery, characterized by a production scheme which allows the treatment of raw materials of a biological origin (vegetable oils, animal fats, exhausted cooking oils) for the production of biofuels, prevalently high-quality biodiesel.

This method allows the re-use of existing plants, allowing, in particular, the revamping of a refinery containing a system comprising two hydrodesulfurization units, U1 and U2, into a biorefinery containing a production unit of hydrocarbon fractions from mixtures of a biological origin containing fatty acid esters by means of their hydrodeoxygenation and isomerization, wherein each of the hydrodesulfurization units U1 and U2 comprises: a hydrodesulfurization reactor, (A1) for the unit U1 and (A2) for the unit U2, wherein said reactor contains a hydrodesulfurization catalyst; one or more heat exchangers between the feedstock and effluent of the reactor; a heating system of the feedstock upstream of the reactor; an acid gas treatment unit downstream of the reactor, containing an absorbent (B) for H.sub.2S, said unit being called T1 in the unit U1 and T2 in the unit U2, and wherein said method comprises: installing a line L between the units U1 and U2 which connects them in series; installing a recycling line of the product for the unit U1 and possibly for the unit U2, substituting the hydrodesulfurization catalyst in the reactor Al with a hydrodeoxygenation catalyst; substituting the hydrodesulfurization catalyst in the reactor A2 with an isomerization catalyst; installing a by-pass line of the acid gas treatment unit T2 of the unit U2; substituting the absorbent (B) in the acid gas treatment unit T1 with a specific absorbent for CO.sub.2 and H.sub.2S.

The operative configuration obtained with the method, object of the present invention, also leads to a substantial reduction in emissions of pollutants into the atmosphere, with respect to the original operative mode.

The invention also relates to the transformation unit of mixtures of a biological origin obtained with said conversion method and particularly hydrodeoxygenation and isomerization processes.

A discharge system of a separated twin-flow turbojet for an aircraft, supported by a suspension mast, is disclosed. The system includes a main nozzle delimited by an annular cowl with a slot of annular shape defining upstream and downstream portions of the cowl and which is traversed by the suspension mast. The downstream portion of the cowl of the main nozzle includes a first part extending downstream from the upstream portion of the cowl to a trailing edge of the main nozzle, on either side of the suspension mast along two predefined angular sectors; and a second part formed from an internal contour of the slot and having a trailing edge with a diameter smaller than that of the trailing edge associated with the first part of the downstream portion of the cowl. Connecting walls laterally connect the first and second parts of the downstream portion.

The present invention relates to throttleable propulsion launch escape systems and devices. In one embodiment, the system includes a tower and at least one throttleable motor secured to the tower. The throttleable motor is able to throttle to a reduced power setting during flight. In another embodiment, the system includes at least one throttleable motor and a space vehicle unit that includes a containing structure. In a further embodiment, the throttleable motor may be secured about a boost escape system of a space vehicle unit. In an additional embodiment, the present invention is a three-dimensional nozzle.

A multi-bed catalytic converter (1) with inter-bed heat exchangers, comprising a plurality of superimposed catalytic beds and a common heat exchanger (5) which is shared between two or more consecutive catalytic beds, said common heat exchanger including heat exchange bodies such as a tube bundle (6), and a wall system (9, 10) to define a tube side and a shell side respectively, and the shell side comprising at least a first space (12) and a second space (13), wherein the first space (12) receives the product gas leaving the first of said consecutive beds, and the inter-cooled gas leaving said first space (12) is admitted in the second bed (3-3) for further conversion, and a sealing means (14) preventing a direct gas passage from said first space to said second space.

The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.

The present invention relates to a device that installs in-line in the fuel supply line of fuel usage equipment such as a HVAC system or a large commercial natural gas or diesel generator. The device is suitable for use with liquid or gas hydrocarbon fuels such as gasoline, diesel, propane, or natural gas. The device consists of a hollow cylinder with male ends and that contains a tightly packed copper wire core. The copper wire serves as a catalyst to crack the fuel's carbon chain molecules as the fuel flows through the device. The resulting fuel contains more and shorter fuel molecules, has a higher vapor pressure and burns more efficiently in the vehicle's engine. The copper wire is held in place by perforated copper keepers and the keepers are secured within the cylinder by snap rings that engage circumferential grooves provided internally at the ends of the cylinder.

A toroid pressure vessel includes a toroid body having an inner shell and an outer shell. The toroid body includes a toroid outer perimeter. The outer shell extends along the toroid outer perimeter. A planar exterior face extends along at least a portion of the outer shell and the toroid outer perimeter. A support belt circumscribes the toroid outer perimeter and is coupled along the planar exterior face. The support belt braces and supports the pressure vessel along the toroid outer perimeter against bulging force (and hoop stress) generated by pressurized fluids within the vessel. The support belt facilitates the use of thinner pressure vessel shells and thereby decreases the weight of the pressure vessel while providing a support to the outer shell that substantially prevents deformation of the planar exterior face.

A method includes providing a quantity of sheet metal, press-forming a first panel from the sheet metal to form a first stamped panel, press-forming a second panel from the sheet metal to form a second stamped panel, fixing at least one stiffener to the first stamped panel such that the stiffener extends across a width of the first panel, where a first end of the stiffener is attached to the first stamped panel at a first fixation location, and where a second end of the stiffener is attached to the first stamped panel at a second fixation location, fixing at least one onboard equipment component to the first stamped panel, where at least one of the at least one onboard equipment component is fixed to the stiffener, sealing the first panel to the second panel to form a space vehicle.

A liquid discharge cartridge manufacturing method includes a first step of individually shaping a first shaped member and a second shaped member that form a housing of a liquid discharge cartridge, and a second step of joining the first shaped member and the second shaped member to be bonded to each other with molten resin. The first step includes shaping a wall section in the first shaped member, the wall section forming a recess for accommodating the molten resin, and shaping a projection in the second shaped member, the projection extending such that the projection is located at the outer side of the wall section and adjacent to the wall section, with a predetermined gap being formed between the projection and the wall section, when the first and second shaped members are joined.