Abstract:
A propulsion system for an unmanned underwater vehicle includes at least one fuel storage tank. A plurality of combustors is connected to the at least one fuel storage tank. Each of the combustors is connected to a turbine via a corresponding nozzle. An output shaft is connected to the turbine and configured to output rotational energy from the turbine.
Abstract:
A propulsion system for an unmanned underwater vehicle includes a turbine engine having a combustor, a turbine, and a mechanical output shaft. The propulsion system further includes an electrical generator having a rotational input connected to the mechanical output shaft, and a poly phase electrical output. A direct current (DC) bus is connected to the poly phase electrical output via a rectifier/inverter. A DC to alternating current (AC) motor drive includes a DC input and a poly phase motor drive output, and a motor connected to the poly phase motor drive output.
Abstract:
An electrical power generation system for a directed energy weapon includes a fuel pump configured to disperse a liquid fuel. Also included is an oxidizer pump configured to disperse a liquid oxidant. Further included is a combustor fluidly coupled to the fuel pump and the oxidizer pump to receive the liquid fuel and the liquid oxidant for combustion therein to form a combustion mixture. Yet further included is a turbine fluidly coupled to the combustor to receive the combustion mixture to generate mechanical energy. Also included is a generator operatively coupled to a rotor shaft of the turbine to convert the mechanical energy to electrical power for the directed energy weapon.
Abstract:
According to an aspect, a shaft internal lubrication system includes a shaft body having an outer wall and a central bore defining an inner wall. The shaft internal lubrication system also includes a plurality of lubrication holes axially distributed along the central bore and fluidically connecting the inner wall and the outer wall. At least one rifling groove on the inner wall forms a lubrication flow path to two or more of the lubrication holes. The shaft internal lubrication system further includes a feed tube within the central bore operable to drip feed a lubricant to the inner wall.
Abstract:
A propulsion system includes a gas turbine engine, an electric motor system having a motor drive electrically connected to the electric machine and an electric motor electrically connected to the motor drive where the electric motor drives a propulsion unit, an electric machine rotatably attached to the gas turbine engine and electrically connected to the electric motor system, an energy storage system having bi-directional electrical connections with the electric motor system and the electric machine, and an Rankine cycle system in communication with the gas turbine engine for recovering waste heat from the gas turbine engine.
Abstract:
A hybrid-electric propulsion system includes a gas turbine engine, an electric machine coupled to and rotatably driven by the gas turbine engine to produce AC electric power, an energy storage system, and a propulsion unit. The gas turbine engine includes a combustor and a recuperator that places an exhaust air flow that is downstream from the combustor in a heat exchange relationship with a compressed air flow that is upstream from the combustor to transfer thermal energy from the exhaust flow to the compressed flow. The propulsion unit includes a fan and an electric motor rotably coupled to the fan, the electric motor being driven by electric power from one of the electric machine or the energy storage system.
Abstract:
A turbine pump assembly includes a centrifugal pump including an inlet cavity with an inlet pressure, a control section having a turbine flow rate control spool valve, a shut off biasing mechanism located at a first end of the control section, and an inlet pressure piston located at a second end of the control section, and an inlet pressure fluid line fluidly connecting the inlet cavity with the inlet pressure piston. When the inlet pressure is above a predetermined threshold, the inlet pressure is configured to maintain the turbine flow rate control spool valve in an operational mode. When the inlet pressure is below the predetermined threshold, the shut off biasing mechanism is configured to apply a closing force to disable the turbine flow rate control spool valve thereby reducing a speed of a turbine of the turbine pump assembly.
Abstract:
A pump system includes a turbine shaft including a turbine disposed thereon to rotate the turbine shaft at a turbine shaft speed due to fluid flow through the turbine, a centrifugal pump directly connected to the turbine shaft and configured to pump hydraulic fluid at the turbine shaft speed, a bleed port disposed downstream of the centrifugal pump, and a valve configured to be fluidly connected to the bleed port and configured to meter flow to the turbine to regulate the turbine shaft speed at least partially as a function of pressure from the bleed port.
Abstract:
A power converter includes a first set of transistors electrically connected in series, a second set of transistors electrically connected in series, and an AC link. The second set of transistors is electrically connected in parallel with the first set of transistors to form an H-bridge. The AC link is electrically connected between the first and second sets of transistors. A plurality of H-bridges are connected in parallel and a three-wire DC bus is electrically connected to the H-bridges.
Abstract:
A turbine pump assembly has a turbine, a centrifugal pump, a passive electrical speed control system, and a pneumatic circuit breaker. The pneumatic circuit breaker has a plurality of elements that are configured to move to a position blocking an outlet duct of the turbine when a flow velocity exceeds a predetermined threshold. A rocket thrust vector control system is also disclosed.