Abstract: In accordance with at least one embodiment of an exhaust treatment system whereby parallel sections of exhaust filters such as Diesel particulate filters (DPF's) and a catalyst such as a selective catalytic reduction (SCR) system are integrated together while efficiently maintaining the temperature requirements of both. The parallel exhaust filter sections that may be heated and/or regenerated individually thereby facilitating catalyst temperature control and modulation of pressure drop across the exhaust filters.

Abstract: A liquid conservation device that utilizes a heat exchanger to condense water vapor from exhaust gas emanating from an exhaust treatment. Water evaporated during the emissions control process is recovered and returned for reuse, thereby significantly reducing the water requirement of the exhaust treatment. This is especially helpful for a mobile emissions control system that is normally not directly connected to a water utility.

Abstract: A positionable emissions control watercraft that may be placed near a serviced watercraft in a location that is away from the risk of falling cargo, while also eliminating a need for a spacer or a spacer barge, and allowing other service watercraft to access the serviced watercraft.

Abstract: A customizable firearm lower receiver includes a lower receiver body having a forward end and a rearward end, the forward end having a first lateral sidewall and an opposing second lateral sidewall, with a forward end wall between the first lateral sidewall and the second lateral sidewall. The opposing lateral sidewalls at least partially surround a magazine well. A mounting surface is configured on the lower receiver body along one of the forward end wall, first lateral sidewall, and second lateral sidewall. A custom face is removably attachable to the mounting surface.

Abstract: An aircraft environmental control system (4) for controlling a temperature of a fluid, the control system comprising: a temperature sensor (30) configured to measure a temperature of the fluid and generate a signal indicative of that temperature; a control signal generator (52) configured to, using control laws (78) and the first signal, generate a control signal for controlling the temperature of the fluid; a memory (56) for storing performance data; a transmitter (60) configured to transmit, from the aircraft environmental control system (4), the performance data; a receiver (60) configured to receive, responsive to transmitting the performance data, update information; and an update module (58) configured to, using the update information, update the control laws (78).

Abstract: An aircraft environmental control system (4) for controlling a temperature of a fluid, the control system comprising: a temperature sensor (30) configured to measure a temperature of the fluid and generate a signal indicative of that temperature; a control signal generator (52) configured to, using control laws (78) and the first signal, generate a control signal for controlling the temperature of the fluid; a memory (56) for storing performance data; a transmitter (60) configured to transmit, from the aircraft environmental control system (4), the performance data; a receiver (60) configured to receive, responsive to transmitting the performance data, update information; and an update module (58) configured to, using the update information, update the control laws (78).

Abstract: In accordance with one embodiment, a servicing watercraft that may be safely secured to a serviced watercraft. The servicing watercraft comprises at least one auxiliary section that may be positioned to either a) increase the effective width of the servicing watercraft thus reducing rolling motion while the servicing watercraft is stationary or in operation, OR b) decrease the width of the servicing watercraft thus reducing drag while the watercraft is moving through the water. Furthermore, the auxiliary section(s) help the servicing watercraft to be positioned in an optimum location adjacent to the serviced watercraft as to avoid impact from accidently dropped cargo or shipping containers from the serviced watercraft.

Abstract: An aircraft environmental control system (4) for controlling a temperature of a fluid, the control system (4) comprising: a first temperature sensor (30) configured to measure a first temperature and to generate a first signal, the first temperature being a temperature of the fluid, the first signal being indicative of the measured first temperature; an amplifier (76) configured to amplify the first signal; one or more processors (64) configured to, using the amplified first signal, generate a control signal for controlling the temperature of the fluid; and a second temperature sensor (68) configured to measure a second temperature, the second temperature being a temperature of an operational environment of the amplifier (76); wherein the one or more processors (64) are further configured to, responsive to the determining that the measured second temperature satisfies one or more predetermined criteria, modify a gain of the amplifier (76) and wherein: the aircraft environmental control system (4) further comp

Abstract: A liquid conservation device that utilizes a heat exchanger to condense water vapor from exhaust gas emanating from an exhaust treatment. Water evaporated during the emissions control process is recovered and returned for reuse, thereby significantly reducing the water requirement of the exhaust treatment. This is especially helpful for a mobile emissions control system that is normally not directly connected to a water utility.

Abstract: In accordance with at least one embodiment of an exhaust treatment system whereby parallel sections of exhaust filters such as Diesel particulate filters (DPF's) and a catalyst such as a selective catalytic reduction (SCR) system are integrated together while efficiently maintaining the temperature requirements of both. The parallel exhaust filter sections that may be heated and/or regenerated individually thereby facilitating catalyst temperature control and modulation of pressure drop across the exhaust filters.

Abstract: A hybrid firearm receiver includes a receiver body having a first end, a second end opposite the first end, a substantially planar bottom surface extending from the first end to the second end and transitioning to two upwardly extending opposing sidewalls, and a top end, the receiver body extending along a longitudinal axis from the first end to the second end. The first end is integrally formed with the receiver body and includes a circular first cavity and a smaller circular second cavity below the circular first cavity. The second end includes an aperture. The axis extends through a center of the circular first cavity and through the aperture and is below the top end. The circular first cavity may be configured to receive a portion of an AR-15 rifle stock assembly. The aperture may be configured to receive an AK pattern rifle barrel.

Abstract: A hybrid firearm receiver includes a receiver body having a first end, a second end opposite the first end, a substantially planar bottom surface extending from the first end to the second end and transitioning to two upwardly extending opposing sidewalls, and a top end, the receiver body extending along a longitudinal axis from the first end to the second end. The first end is integrally formed with the receiver body and includes a circular first cavity and a smaller circular second cavity below the circular first cavity. The second end includes an aperture. The axis extends through a center of the circular first cavity and through the aperture and is below the top end. The circular first cavity may be configured to receive a portion of an AR-15 rifle stock assembly. The aperture may be configured to receive an AK pattern rifle barrel.

Abstract: This invention relates to a method of injection moulding a multi-planter having multiple apertures in the sides thereof, and an cap piece integrally formed with the tubing, the method characterised by the step of inserting supports through the apertures to provide support for the internal core portion of the tool used in the injection moulding.

Abstract: A jet engine includes a shaft rotatably supported in a bearing arrangement, a compressor and a turbine arranged on the shaft, and an electromechanical unit arranged centrally about the shaft axis to provide a motor function for starting the jet engine and/or a generator function for a power supply, and a function of an active magnetic bearing arrangement. The electromechanical unit is embodied as a transverse flux machine. The electromechanical unit preferably includes a rotor carrying permanent magnets and a stator with an undulating profiled stator surface.

Abstract: A dispenser closure (A) for a container including a storage chamber (2), a flexible diaphragm (3) and a membrane opening device (6) attached to the flexible diaphragm (3), whereby the membrane opening device (6) includes a support structure (7) in the form of an open structure with cutting teeth (11) in which a substance, additive, ingredient or powder to be dispensed may flow and out through the opened membrane. The open support structure results in mixing to occur immediately when the membrane is open, enables free movement of the substance, and facilitates complete mixing as there are fewer surfaces to trap the substance. Upon depression of the flexible diaphragm, the cutting teeth (11) of the opening device (6) moves to cut the membrane (5) thereby opening the storage chamber to allow the substance to mix with water, a solution or a sports drink contained in an attached container or bottle.

Abstract: A hole saw arbor system includes a tool-bit holder comprising a body having a proximal end and a distal end, the proximal end configured to be coupled to and driven by a driving device. A substantially longitudinal tool-bit holder bore may extend from the proximal end to the distal end of the body, the bore configured to receive a drill bit. The system further includes an arbor configured to be releasably coupled to a portion of the drill bit. The arbor may include a body having a proximal end and a distal end, the proximal end configured to matingly engage the distal end of the tool-bit holder when the arbor is coupled to the drill bit. The distal end may be configured to be coupled to a hole saw. A substantially longitudinal arbor bore may extend from the proximal end to the distal end of the body, the arbor bore being configured to receive the drill bit.

Abstract: Vertical axis turbine apparatus is described in which a rotating blade turbine member mounted on a fixed base includes one to fifty, preferably two or three, upwardly and outwardly inclined spars. On each spar is set at least one aerofoil or hydrofoil section blade. If there is more than one spar, the spars are preferably held to one another via a plurality of guy wires.

Abstract: A jet engine, in particular for an aircraft, having a high-pressure compressor that is situated inside a compressor housing, the high-pressure compressor having blade elements that, through their rotational motion, compress air flowing into the high-pressure compressor via an intake channel, the high-pressure compressor having a plurality of compressor stages on which the blade elements are situated, and the jet engine also having an integrated electric motor/generator unit, wherein the motor/generator unit is situated in the rotational plane of the at least first compressor stage of the high-pressure compressor, and includes a stator that extends around the periphery of the compressor housing, as well as a runner that is formed by the blade elements of the at least first compressor stage, and that the motor/generator unit has an output power of 100 kVA to 150 kVA.

Abstract: Jet engine (1), especially for an aircraft, with at least one hollow shaft (7) and/or low pressure shaft (8) rotatably supported in at least one bearing arrangement about a center axis, on which shaft at least respectively one high and/or low pressure compressor (2, 12) as well as at least respectively one high and/or low pressure turbine is arranged, whereby the jet engine (1) further comprises an electromechanical unit (10), in order to provide at least a motor function for starting the jet engine (1) and/or a generator function for the power supply, whereby the electromechanical unit (10) is arranged centrally about the center axis, whereby the electromechanical unit (10) furthermore encompasses the function of an active magnetic bearing arrangement, in order to form at least one bearing arrangement of the at least one hollow shaft (7) and/or low pressure shaft (8), and whereby the electromechanical unit (10) is embodied as a transverse flux machine.