Abstract: A system for substantially continuously providing a solid material, for example pulverized coal, to a pressurized container. The system provides the solid material to a first container of a first pressure elevated above an initial pressure of the solid material. Generally, a screw conveyor augmented with a jet port is used to move the material where the jet port provides a gas to provide a make-up volume of the solid material. The system also provides the material to a second high pressure container after the material has been formed into a slurry. Therefore, the solid material may be substantially continuously provided in a system to a high pressure container.

Abstract: A method and apparatus for producing electrical energy from a thermal dynamic cycle. The apparatus can include a heat exchange apparatus portion that allows for a large surface area for thermal energy collection while maintaining an efficiency of the thermal dynamic cycle engine. For example, a Stirling engine can include a large heater head portion that can be contained within the pressure vessel of the thermal dynamic engine yet maintain the selected size of the various pistons of the thermal dynamic cycle engine.

Abstract: A damper that provides damping to the motion caused by flow induced vibration of a bellows type expansion joint. The damper is at least partially filled with a damping medium and located at a root region of the bellows type expansion joint convolutions. The damper is manufactured in segments which have an attachment structure therebetween to facilitate retrofitting of the damper to various conduits that are experiencing or are expected to experience flow induced vibration.

Abstract: A rechargeable battery assembly includes a battery array and a battery controller. The battery array includes a number of batteries, and each battery includes a battery module and an integral module controller. The batteries may be connected in various configurations to form a battery array that is able to provide a power supply of almost any desired voltage. The module controller regulates charging of the battery module and is able to disconnect defective battery modules from the circuit. During a charging cycle, the module controller disconnects fully-charged modules from the charging circuit. During a discharging cycle, if a battery module becomes inoperative, the module controller disconnects the inoperative module, so that the battery array does not become inoperative because of one or more inoperative battery modules.

Abstract: A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.

Abstract: A bearing cup having a ring and a shoulder extending radially inward from an inner surface of the ring. At least one tang extends axially outward from a first side of the ring. At least one tab extends axially outward from a second side of the ring opposite the first side. And, at least one slot is formed in the second side. The bearing cup prevents the outer race of a conventional rolling element bearing from rotating while allowing the bearing to move in an axial direction. The assembly is designed for use with either a single rolling element bearing or a set of two bearing assemblies or any number of closely spaced bearings. The advantage of the device is that it eliminates spinning of the bearing assembly outer race. The device also prevents frictional sliding between a bearing assembly outer race and a preload spring. Frictional sliding imposed on a bearing outer race can induce galling and subsequently lead to part failure.

Abstract: A method of fabricating a rolling bladder propellant tank assembly includes providing a pair of half-domes comprising a nanophase metallic material and a bladder formed of a ductile metallic material. A bladder support ring extends from at least one of the pair of half-domes. The pair of half-domes are positioned together to form a cavity therein with a portion of the bladder trapped between the pair of half-domes adjacent to the bladder support ring, wherein the bladder is positioned within the cavity. A seal is formed between the pair of half-domes and the bladder by friction stir welding. A friction stir welding pin used to form the seal is aligned with the bladder support ring during the friction stir welding operation.

Abstract: An ignition system for a rocket engine utilizes the pressure energy in a propellant flow. The propellant flow generates an oscillating pressure force in a resonance system which is then transmitted to a piezoelectric system. The electrical pulses are utilized to generate a spark in an igniter system spark gap, resulting in ignition. Since the spark energy production is driven by the resonance of the propellant flow, a fully passive auto-ignition system is provided. Once ignition occurs, the resultant backpressure in the combustion chamber “detunes” the resonance phenomena and spark production stops. Furthermore, should the engine flame out, spark production would automatically resume as the propellant valves remain open thereby providing relight capability.

Abstract: A connector assembly includes a connector mounted within a backshell and a biasing member that forces the connector into contact with a surface of the backshell to improve ground shield junction performance. The biasing member extends into an internal space defined by the backshell and exerts a biasing force to reduce resistance between the connector and the backshell. The reduced resistance provided by the biasing member improves ground shield junction performance against electromechanical interference (EMI) and radio frequency interference (RFI).

Abstract: A combustor assembly for a gas powered turbine includes a premix section to mix a first selected volume of fuel with a selected oxidizer. The premix section includes an injector plate that includes a porosity according to selected characteristics, such as pore size, pore density, pore distribution, and other selected characteristics. Therefore, the fuel may be provided through the porous plate to the premix area in a selected uniform flux.

Abstract: A variable-ratio neutron-gamma ray source comprises a neutron generator, a shield, a collimator, and an external gamma target. The neutron generator generates neutrons and the shield reduces external radiation exposure. The collimator collimates the neutrons into a neutron beam that traverses the shield. The external gamma target generates a dual neutron-gamma ray beam from the neutron beam, wherein the dual neutron-gamma ray beam has a variable neutron-gamma ratio as a function of a thickness of the external gamma target.

Abstract: A dual neutron-gamma ray source comprises a compact neutron generator, a shield, a collimator, and an internal gamma target. The shield surrounds the compact neutron generator. The collimator traverses the shield from the compact neutron generator to a collimator port. The internal gamma target is positioned within the collimator to generate gamma rays from the neutrons.

Abstract: A neutron-gamma ray tomography system comprises a source, a detector array, and an image processor. The source illuminates an object with a dual neutron-gamma ray beam. The detector array characterizes neutron and gamma ray attenuation in the object. The image processor generates tomography as a function of the neutron and gamma ray attenuation.

Abstract: In some embodiments fastening apparatus includes a threaded fastening element adapted to be threaded into a hole provided in a first component, the threaded fastening element including a locking collar that is defined by at least one outer peripheral surface, and a locking washer adapted to fit within a recess formed in the component to limit rotation of the threaded fastening element once the element is threaded into the component hole, the washer including an inner opening defined by at least one inner peripheral surface and a non-circular outer shape defined by an outer peripheral surface, the inner opening being adapted to receive the locking collar such that the at least one outer peripheral surface of the collar can contact the at least one inner peripheral surface of the washer.

Abstract: A structure and a method of forming the structure in high temperature sections of next generation nuclear and solar power plants where the structure consists of piping, ducting and enclosures fabricated from oxide dispersion strengthened (ODS) alloys joined by friction stir welding (FSW) to other ODS alloys or any alloy.

Abstract: A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements.

Abstract: A solar-powered hydrogen production system includes a thermochemical system and solar heating system. The thermochemical system produces hydrogen. The solar heating system has a molten salt heat transfer medium for providing thermal energy to the thermochemical system.

Abstract: An ultra-compact aerovortical swirl-enhanced combustion (ASC) system features an aerovortical swirl generator for use in rocket thrusters utilizing hypergolic or non-hypergolic propellants. The ACS thruster can be sized for diameters ranging from about 0.5 to about 2.0 inches, and producing thrust levels of approximately 5 lbf to about 250 lbf. A plurality of helicoid flow channels in the swirl generator introduces swirl into a flow stream of a first propellant within ultra-compact sized rocket thrusters. The ASC system also includes injectors for introducing a second liquid propellant into the swirling flowfield to promote rapid and efficient atomization, mixing and vigorous combustion, which, results in major improvements in combustion and propulsion performance over current rocket thrusters, but in much shorter combustor systems.

Abstract: A compact rocket engine with advanced swirl combustion can generate vacuum thrust in the 500 lbf to 100,000 lbf range. The rocket engine includes a feed system, combustor assembly, swirl generator and nozzle. The feed system delivers the oxidizer and fuel to the combustor assembly in the proper phase suitable for use with the swirl generator, which is positioned within the combustor assembly. This causes a highly turbulent three-dimensional swirling flowfield produced for rapid and efficient mixing and burning of the fuel/oxidizer combustion products, which are expanded through the nozzle to produce thrust. The aerothermochemical processes are extremely efficient, and consequently produce nearly ideal thrust levels. Swirl enhanced combustion significantly reduces combustor length, weight, complexity and cost, yet provides high propulsion efficiencies and wide rocket engine throttling operability.

Abstract: A cutback flow straightener comprises a plurality of flow straightener vanes positioned in a flow duct. The flow straightener vanes are cut back as a function of a radius of the flow duct, such that an axial length of the vanes decreases with the radius.