A non-metallic tailcone (202) in a tip turbine engine includes a tapered wall structure disposed (208) about a central axis. The non-metallic tailcone is fastened to a structural frame (44) 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 H2S, 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 A1 with a hydrodeoxygenation catalyst; substituting the hydrodesulfurization catalyst in the reactor A2 with an isomerization catalyst; installing a y-pass line X 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 C02 and H2S. 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.

Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.

A method of forming a hydrocarbon product, the method comprising a first step of enriching a carrier liquid with carbon monoxide and hydrogen and a subsequent step of bringing the enriched carrier liquid into contact with a catalyst in a first reaction zone of a reactor, wherein the catalyst catalyzes reaction of the carbon monoxide and hydrogen to form the hydrocarbon product.

An alignment tool for use in a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a clamp portion, a component engagement portion and an arm portion that extends between the clamp portion and the component engagement portion. The clamp portion establishes a fixed datum surface for positioning a component within the gas turbine engine.

An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

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.

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.

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 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.