Abstract: A compact and lightweight electric generator for portable power applications employs a new engine design and integration approach for reducing engine, generator, and starter weight. A unique flywheel alternator/starter configuration that generates electrical power, rotates the engine for starting, provides inertia for smooth engine operation, pressurized air for cooling, and inertia for the alternator. An engine cowling provides rotating component protection, a fan shroud mechanism, cooling air ducts, and a cooling mechanism for handling large quantities of heat produced by rectified power conversion. An electrical hook up that allows the generator to provide transient surge capacity for starting inductive loads, or improved load leveling and fuel efficiency.

Abstract: A secondary flow lobe mixer increases the total-to-static pressure ratio across a Ram Air Turbine (RAT) by developing a localized pressure drop near the discharge of the turbine rotor exhaust. This pressure drop allows for additional power generation for a given free-stream flight condition.

Abstract: The total-to-static pressure ratio is increased across a Ram Air Turbine (RAT) by developing a localized accelerated flow of free-stream air near the discharge of the turbine rotor exhaust. This localized accelerated flow decreases the static pressure at the exit of the turbine and allows for additional power generation for a given free-stream flight condition. Lobe mixers in various locations improves mixing between the accelerated flow and the turbine exhaust flow, and the combined exhaust flow and the free-stream air surrounding the aerodynamic body.

Abstract: A method for increasing the total-to-static pressure ratio across a Ram Air Turbine (RAT) has designed and experimentally tested. The invention develops a localized accelerated flow of free-stream air near the discharge of the turbine rotor exhaust. This localized accelerated flow decreases the static pressure at the exit of the turbine and allows for additional power generation for a given free-stream flight condition. Full-scale wind tunnel experimenting testing shows that creating this low static pressure region behind the turbine resulted in significant increases in turbine output power when compared to a turbine that is not subjected to this invention. The invention showed the ability to increase the total-to-static pressure ratio across the turbine.