Abstract: The present invention provides an electrical raft comprising a rigid material having multiple electrical conductors embedded therein. The electrical raft comprises an electrical connector having a first set of electrical contacts connected to at least one of the electrical conductors, a second set of electrical contacts for electrical connection to another component, and a housing having a first end and a second end. The first set of electrical contacts is at the first end and the second set of electrical contacts is at the second end. The first end of the housing is at least partly embedded in the rigid material, and the second end of the housing is accessible from outside the electrical raft, allowing the electrical raft to be electrically connected to said other component. The electrical connector has a back-shell which sealingly encloses the first end of the housing to prevent ingress of contaminants into the connector.

Abstract: An electric propulsion system includes a first stationary plasma thruster including a single first cathode, a first anode, and a first gas manifold, and a second stationary plasma thruster including a single second cathode, a second anode, and a second gas manifold. The system further includes an electrical connection device common to the first and second cathodes, first and second gas flow rate control devices with a common fluid flow device for feeding gas, and a selective control device for activating at any given instant only one of the first and second cathodes in co-operation with one or the other of the first and second anodes.

Abstract: Described herein is a shaft assembly for a rotary switch that includes a shaft made from an electrically non-conductive material. The shaft includes at least one circumferential groove that has a generally T-shaped cross-section. The shaft assembly also includes at least one conductive ring segment made from an electrically conductive material positioned within the circumferential groove. The conductive ring segment has a generally T-shaped cross-section. Additionally, the shaft assembly includes a bonding adhesive that is positioned between the circumferential groove and the conductive ring segment.

Abstract: A Hall thruster apparatus having walls constructed from a conductive material, such as graphite, and having magnetic shielding of the walls from the ionized plasma has been demonstrated to operate with nearly the same efficiency as a conventional non-magnetically shielded design using insulators as wall components. The new design is believed to provide the potential of higher power and uniform operation over the operating life of a thruster device.

Abstract: The present invention provides a rigid raft formed of rigid composite material. The raft has an electrical system and/or a fluid system embedded therein. The raft further has a tank for containing liquid integrally formed therewith. The tank can be formed of the rigid composite material. The tank can be for a gas turbine engine.

Abstract: Embodiments of the present disclosure are directed towards a system that includes a recirculation system. The recirculation system includes a compressor discharge air line extending from a compressor to an air intake. The compressor discharge air line is configured to flow a compressor discharge air flow, and the air intake is configured to supply an air flow to the compressor. An ejector is disposed along the compressor discharge air line between the compressor and the air intake. The ejector is configured to receive and mix the compressor discharge air flow and a turbine exhaust flow to form a first mixture.

Abstract: A cryogenic thruster assembly including: a reignitable main thruster; a first cryogenic tank connected to the main thruster to feed the main thruster with a first propellant; a first gas tank; at least one settling thruster; and a first feed circuit for feeding the first gas tank. The feed circuit of the first gas tank is connected to the first cryogenic tank and includes a heat exchanger for using heat given off by the at least one settling thruster to vaporize a liquid flow of the first propellant as extracted from the first cryogenic tank to feed the first gas tank with the first propellant in the gaseous state. A method feeds the first gas tank with the first propellant in the gaseous state.

Abstract: The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure. A drive member may be accessible near a second end of the elongated body, and the drive member may be configured to rotate within the elongated body and to drive the movable arm along a longitudinal axis of the elongated body toward the second end to separate the tubular structure from the second combustor.

Abstract: An apparatus and method for assisting with the combustion of fuel are described. The apparatus includes a swirler assembly and a fuel nozzle. Fuel is directed into a fuel nozzle mixing chamber and combines with air therein to form a fuel-air mixture. At least one plasma generator, at least partially within the fuel nozzle, generates an at least one of an at least partially ionized air-fuel mixture and an at least partially dissociated air-fuel mixture (“at least partially I/D air-fuel mixture”) via a plasma generator discharge. A combustion chamber inlet admits the at least partially I/D air-fuel mixture from the plasma generator into a combustion chamber internal volume. Combustion air flows through the swirler body and into the combustion chamber internal volume. Combustion of the at least partially I/D air-fuel mixture with the combustion air occurs at least partially within the combustion chamber internal volume to responsively produce products.

Abstract: An electrical raft (200) is provided that has electrical conductors (252) embedded in a rigid material (220). The electrical raft is provided with an electrical connector (700). The electrical connector (700) is mounted in the electrical raft (200) at a mounting angle (730). The mounting angle is set such that the electrical conductors (252) can be connected to the electrical connector without having to turn through an angle or a radius of curvature that would subject them to excessive bending stress. Similarly, the mounting angle means that any conductors (766) that may be connected to the electrical connector (700) do not have to turn through an angle or a radius of curvature that would subject them to excessive bending stress. Furthermore, mounting the electrical connector (700) at the mounting angle (730) may allow the assembled electrical raft (200) to be more compact.

Abstract: An electrical raft 200 is provided that has electrical conductors 252 embedded in a rigid material 220. The electrical raft 200 may have other embedded components, such as embedded fluid pipes 210. The electrical raft 200 is provided with a raft map 400 that indicates the location and/or path of components embedded in the electrical raft 200. The raft map 400 can be used to identify the positions of the embedded components, and may also be provided with active elements, such as LEDs, which may be used to indicate an operating state of the systems/components embedded in the electrical raft 200. The raft map 400 may be useful in assembly, repair and fault diagnosis, for example.

Abstract: A micro-nozzle thruster comprising a micro-nozzle having an inlet at a first end perpendicularly aligned gas supply channel at a first end, and a thruster outlet at a second opposed end; said inlet in fluid communication with a gas supply channel, said gas supply channel perpendicularly aligned with a longitudinal axis of the micro-nozzle; a cathode within the gas supply channel and an anode external to the gas supply channel and proximate to the inlet, so as to create a plasma flow from said gas.

Abstract: A late lean injection combustor assembly may include a first interior in which a first fuel supplied thereto is combustible, a flow sleeve annulus including a second interior in which a second fuel supplied thereto is combustible, at least one fuel injector disposed about the second interior, and at least one elongate premixing conduit disposed about the flow sleeve annulus and in fluid communication with the at least one fuel injector. The at least one elongate premixing conduit may be in fluid communication with a compressor discharge air and the second fuel such that the compressor discharge air and the second fuel are premixed within the elongate premixing conduit before entering the second interior by way of the at least one fuel injector.

Abstract: In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter which is larger than a minor diameter such that the shrouds define an oblong shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds.

Abstract: A chemical-electromagnetic hybrid propeller with variable specific impulse. Fuel gas ejected out from a spraying tube of the chemical propeller through chemical propulsion enters an ionization chamber through a first magnetic mirror tube for ionization. The fuel gas after ionization is heated up by radio-frequency ion cyclotron waves in an ion cyclotron wave heating chamber so as to improve the kinetic energy. Then a second magnetic mirror tube is used, so that ions in the fuel gas after the ionization are heated up many times in a reciprocating manner between the magnetic mirror tubes, and ejected to generate forward propulsion force. By means of the propeller, the propulsion force and the specific impulse are greatly increased.

Abstract: Torque boxes and thrust reversers are disclosed. Torque boxes include a torque box comprising a hinge beam, a forward wall having a bullnose profile connected to the hinge beam to support a torque load, an aft wall having a bullnose profile connected to the hinge beam to support the torque load, the aft wall located aft of the forward wall, and a vane connected to an aft surface of the forward wall and a forward surface of the aft wall, wherein the aft surface of the forward wall and the forward surface of the aft wall are configured to direct air flow in a forward direction and the vane is configured to direct air flow radially outward. Thrust reversers include a translating sleeve, a blocker door mounted to the translating sleeve, and a torque box.

Abstract: A premixing apparatus for a gas turbine system includes non-swirl elements around a periphery of a face of a premixing apparatus and a swirl assembly located substantially at a center of the face. The non-swirl elements premix a premixture prior to the premixture being delivered to a combustor of the gas turbine system. The swirl assembly disturbs a flow of fluid prior to the fluid being delivered to the combustor. The premixture includes fuel and oxidant, and the fluid disturbed by the swirl assembly includes the oxidant or the premixture.

Abstract: A thruster designed to produce thrust by introducing a propellant to a catalyst layer from a propellant valve via a propellant introduction member and spurting out a gas resulting from decomposition of the propellant occurring on the catalyst layer, wherein the thruster comprises a chamber of an Ni alloy for holding the catalyst layer inside, the propellant introduction member is made of an Ni alloy and connects the propellant valve and the chamber, and a propellant valve flange of a Ti alloy with a plurality of columns of a Ti alloy is arranged between the chamber and the propellant valve to support the chamber by the columns.

Abstract: This disclosure generally relates to a hybrid solid-state propulsion system for aerial vehicles. The hybrid propulsion system includes a combustor, a thermophotovoltaic generator, and a thermoelectric generator. The combustor burns a chemical based fuel to produce radiation and heat that are converted into electricity used to power the aerial vehicle. The thermophotovoltaic generator is positioned to receive radiation and remnant heat generated by flames in the combustor while the thermoelectric generator receives heat from exhausted flue gases from the combustor.

Abstract: Embodiments of a Gas Turbine Engine (“GTE”) are provided, as are embodiments of a plasma flow-controlled intake system for deployment on a GTE. In one embodiment, the GTE includes a turbine section, a combustion section upstream of the turbine section, a compressor section upstream of the combustion section, and intake section upstream of the compressor section. The intake section includes a plenum, a first inlet fluidly coupled to the plenum, and a flow-obstructing structure projecting into the plenum and having an outer surface impinged by the airflow directed into the plenum through the first inlet during operation of the GTE. A first array of plasma actuators is disposed on flow-obstructing structure and, when activated, suppresses vortex shedding of the air flowing over the outer surface of the flow-obstructing structure.