Alliant Techsystems Inc.

The Boeing Company

Orbital Atk, Inc.

Jason S Tyll

Florin Girlea

John C Leylegian

Vladimir Balepin

Dean Modroukas

Robert Bakos

Sabrina A Hawkins

Gary K Lund

Anthony Gus Castrogiovanni

Thomas Russell Smith

Richard I Perlman

Lawrence G Piper

Joseph Anthony Alifano

Andrew Robertson

Ighor K Uzhinsky

Angel M Espinosa

Daniel J Farrell

Randy S M Chue

Ralph Woelfel

John I Endos

Marten Byl

Wallace Chinitz

Disclosed herein are systems and methods for vortex tube desulfurization of jet fuels. Also disclosed are processes for separation of closely boiling species in a mixture of miscible fluids.

Methods of separating mixtures of miscible fluids

A solid feed system may comprise a supersonic nozzle, an isolated injection section having a port for injection of solid feedstock positioned downstream from the supersonic nozzle, and a supersonic diffuser positioned downstream from the isolated injection section. Additionally, a gasification system may comprise such a solid feed system and a reaction chamber downstream thereof. Furthermore, a method of reacting a solid feedstock under pressure may include directing a fluid flow through a supersonic nozzle to provide a supersonic flow stream, and directing the supersonic flow stream through an isolated injection section at a static pressure at least fifty percent (50%) lower than an operating pressure within a reaction chamber (e.g., at a static pressure near ambient pressure).

Solid feed systems for elevated pressure processes, gasification systems and related methods

A fuel processing system for converting a logistical fuel and air into a liquid product comprising methanol. One such system comprises a fuel injection system configured to combine a logistical fuel and ambient air to produce a logistical fuel and air mixture, a synthesis gas production system configured to convert the logistical fuel and air mixture to synthesis gas, and a methanol synthesis system configured to convert the synthesis gas to a crude methanol liquid. Related methods are additionally disclosed.

Fuel processing system and related methods

A fuel reformulation system for an engine comprising an annular body for a flow of fluids therethrough connected to the engine, a source of fuel for flowing through at least a portion of the annular body, and a catalytic member connected to the annular body for the flow of any fluids thereacross from the annular body.

Fuel reformulation systems

Methods and systems of providing a source of hydrogen and oxygen with high volumetric energy density, as well as a power systems useful in non-air breathing engines such as those in, for example, submersible vehicles, is disclosed. A hydride reactor may be utilized in forming hydrogen from a metal hydride and a peroxide reactor may be utilized in forming oxygen from hydrogen peroxide. The high temperature hydrogen and oxygen may be converted to water using a solid oxide fuel cell, which serves as a power source. The power generation system may have an increased energy density in comparison to conventional batteries. Heat produced by exothermic reactions in the hydride reactor and the peroxide reactor may be transferred and utilized in other aspects of the power generation system. High temperature water produced during by the peroxide reactor may be used to fuel the hydride reactor.

Methods and systems of producing hydrogen and oxygen for power generation, and power source

Hypersonic inlet systems and methods are disclosed. In one embodiment, an inlet for an airbreathing propulsion system includes an inboard surface at least partially shaped to conform to a plurality of streamline-traces of a design flowfield approaching an aperture, an outboard surface spaced apart from the inboard surface, an upper surface extending between the inboard and outboard surfaces, and a lower surface extending between the inboard and outboard surfaces, wherein leading edges of the inboard, outboard, upper, and lower surfaces cooperatively define the aperture.

Hypersonic inlet systems and methods

A cooling system for a high-speed vehicle may comprise a combustor wall at least partially enclosing a combustor and which is cooled using a coolant circulating in a Brayton cycle. The heated coolant may be expanded in a turbine, transfer heat to a fuel within a heat exchanger, and be compressed by a compressor before returning to the combustor wall. The combustor wall may be capable of withstanding high temperatures, higher than the temperature at which fuel coking may take place. Heat transfer takes place between the coolant and the combustor wall, and between the coolant and the fuel. A method of cooling an engine for a high-speed vehicle is also disclosed.

Cooling system for high-speed vehicles and method of cooling high-speed vehicles

A scramjet has a cowl, a center structure, and a plurality of wide pylons connecting the cowl to the center structure, with scramjet engines positioned between adjacent pylons. Leading surfaces of adjacent pylons converge to one another to provide side wall compression to air entering the engines. The center structure includes a fore body, a center body and an aft body that, with the pylons, define a basic structure either formed entirely from one piece or several securely connected pieces. A method of testing the scramjet projectile comprises using a gun to accelerate the scramjet projectile to the takeover velocity of the engines.

Projectile structure

Growing community of inventors

Blue Point, NY, United States of America

Jason S Tyll