Abstract: A new dual-mode ramjet combustor used for operation over a wide flight Mach number range is described. Subsonic combustion mode is usable to lower flight Mach numbers than current dual-mode scramjets. High speed mode is characterized by supersonic combustion in a free-jet that traverses the subsonic combustion chamber to a variable nozzle throat. Although a variable combustor exit aperture is required, the need for fuel staging to accommodate the combustion process is eliminated. Local heating from shock-boundary-layer interactions on combustor walls is also eliminated.

Abstract: A heat pump system using waste heat has a compression heat pump circuit that uses the shaft output of a power engine as a power source for a compressor for compressing refrigerant, and an absorption heat pump circuit using waste heat of the power engine as a heat source for a regenerator for heating absorbing liquid, refrigerant vaporized in the compression heat pump circuit is circulated to an absorber of the absorption heat pump circuit, the refrigerant is separated after regenerated by the regenerator, and the separated refrigerant is circulated in the compression heats pump circuit. The absorption heat pump circuit has a reverse pump R in a return pipe for absorbing liquid from the regenerator to the absorber, and the rotation energy of the reverse pump R can be withdrawn by a circulation pump P for the absorbing liquid.

Abstract: A retainer provided at lower portion of a pump beam of a jet pump for circulating cooling water to a reactor core or a bolt for fastening the retainer is cut through an underwater-remote control to remove the bolt and the retainer is removed through the underwater-remote control.

Abstract: A method for constructing a thermal management system is provided herein. In accordance with the method, a fan (405) is provided which is adapted to provide a global flow of fluid through the device. A synthetic jet ejector (409) is also provided which is adapted to augment the global flow of fluid over the surfaces of a heat sink (403). The ratio of the flow per unit time of the synthetic jet ejector to the flow per unit time of the fan is selected so as to achieve a desired level of heat dissipation.

Abstract: Some embodiments of a method, apparatus and computer system are described for inverted vortex generator enhanced cooling. In various embodiments an apparatus may comprise a first surface comprising at least one heated component, a second surface in proximity to the first surface, the second surface comprising a non-heated surface, and one or more inverted vortex generators attached to the non-heated surface, a portion of the one or more inverted vortex generators in proximity to and configured to dissipate heat from the at least one heated component. Other embodiments are described.

Abstract: A recirculating liquid jet pump for moving a wide variety of materials is described. The pump is preferably equipped with an intermediate collection reservoir enabling the placement of material to be suctioned into the collection reservoir without bringing together the material to be suctioned with the motive fluid of the liquid jet pump. The collection reservoir may also be connected to a separate container for de-watering solid-liquid mixtures to enable mixture liquid to be separated from the solids without bringing the separated liquid into contact with the motive fluid of the jet pump and without the use of excessive amounts of jet pump motive fluid.

Abstract: An ejector includes a nozzle having therein a throat portion, and a needle valve that extends at least from the throat portion to the outlet of the nozzle. The needle valve is displaced in an axial direction of the nozzle to adjust an opening degree of the throat portion and an opening degree of an outlet of the nozzle. Therefore, even when a flow amount of refrigerant flowing into the nozzle is changed, it can prevent a vertical shock wave from being generated by suitably adjusting both the opening degrees of the throat portion and the opening degree of the outlet of the nozzle. Accordingly, nozzle efficiency can be improved regardless of a change of the flow amount of the refrigerant.

Abstract: A method in which an air mass flow supplied to a compressor in a power plant is divided in a flow divider into a small partial flow and into a larger partial flow. The smaller partial flow is supplied to an ejector via an air cooler and a booster. The larger partial flow is supplied to the suction line of said ejector. Both partial flows are combined in the ejector. The mass flow which is combined at the outlet of the ejector can be used as pressurized air in various components of a power plant.

Abstract: A pump-ejector compression unit is furnished with a receiver, and a mixing chamber of a liquid-gas ejector and a separator are located inside the receiver. An outlet of the mixing chamber is connected to the separator, the receiver is partly filled with a motive liquid, the liquid outlet of the receiver is connected to the suction side of a pump and the gas outlet of the receiver is connected to a consumer of a compressed gas. There is another embodiment of the compression unit, wherein the mixing chamber outlet is connected to a chamber for conversion of a gas-liquid flow. The introduced pump-ejector compression unit has an increased efficiency factor.

Abstract: A water cooled steam jet for transferring fluid and preventing vapor lock, or vaporization of the fluid being transferred, has a venturi nozzle and a cooling jacket. The venturi nozzle produces a high velocity flow which creates a vacuum to draw fluid from a source of fluid. The venturi nozzle has a converging section connected to a source of steam, a diffuser section attached to an outlet and a throat portion disposed therebetween. The cooling jacket surrounds the venturi nozzle and a suction tube through which the fluid is being drawn into the venturi nozzle. Coolant flows through the cooling jacket. The cooling jacket dissipates heat generated by the venturi nozzle to prevent vapor lock.

Abstract: An absorption cycle system uses a hydrokinetic amplifier as an absorber, and the hydrokinetic amplifier merges a working vapor stream with a working liquid stream to condense the vapor and absorb it in a working mixture that is output at a higher temperature and pressure than either input. Since the hydrokinetic amplifier absorber does not discard heat, the retained heat is used to help power the system and reduce heat waste that would otherwise occur.

Abstract: A gas compressor is provided which can be utilized in a jet engine for propulsion of a flight vehicle at velocities ranging from static to very high Mach numbers. The jet engine includes a housing with an inlet, a mixing chamber in fluid communication with the inlet, a diffuser section in fluid communication with the mixing chamber, a combustion chamber in fluid communication with the diffuser section and an outlet in communication with the combustion chamber. Auxiliary gas injection nozzles located downstream of the mixing chamber direct a high velocity gas stream toward the outlet to induce a region of sufficiently low pressure within the mixing chamber to cause a supersonic flow of gas from the inlet section through the mixing chamber. Cryogenic fuel is injected into the mixing chamber to modify the stagnation enthalpy, pressure and temperature of the supersonic flow therethrough.

Abstract: A hydrokinetic amplifier 10 having a primary liquid input formed into a primary liquid jet surrounded by a motivating vapor that transfers vapor momentum to the primary liquid jet and accelerates the primary liquid jet through a minimum cross-sectional area 20 upstream of a diffuser is provided with a secondary inlet that admits a secondary fluid to merge with the primary liquid jet in a diffuser 16 beyond the minimum cross-sectional area. Without varying the primary inflows of liquid and vapor, the secondary flow varies inversely with the fluid flow resistance of the output load; and this can be used to vary the volume, pressure, and temperature of the output. The product of the pressure and volume of the combined flows can exceed the product of the pressure and volume of the primary flow, and change in the load resistance can be used to turn the secondary flow on and off for adding a material to the primary flow.

Abstract: The invention does away with the necessity of moving parts such as a check valve in a nuclear reactor cooling system. Instead, a jet pump, in combination with a TEMP, is employed to assure safe cooling of a nuclear reactor after shutdown. A main flow exists for a reactor coolant. A point of withdrawal is provided for a secondary flow. A TEMP, responsive to the heat from said coolant in the secondary flow path, automatically pumps said withdrawn coolant to a higher pressure and thus higher velocity compared to the main flow. The high velocity coolant is applied as a driver flow for the jet pump which has a main flow chamber located in the main flow circulation pump. Upon nuclear shutdown and loss of power for the main reactor pumping system, the TEMP/jet pump combination continues to boost the coolant flow in the direction it is already circulating.

Abstract: A gas compressor is provided having a source of supersonic velocity gases acting to accelerate inlet gases through a mixing region and diffuser. The inlet gas is introduced into the mixing chamber through a converging-diverging nozzle, causing said gas to accelerate to supersonic velocity. An injection of coolant is provided into the resulting gas stream to cause a decrease in its stagnation temperature and an increase in its stagnation pressure. Also provided is a means for modifying the nuclear spin orientations of the gases involved in the mixing region upstream of the combustion chamber to increase the stagnation pressure and decrease the stagnation temperature of the gas flowing into the combustion chamber. The gas compressor can be utilized in a jet engine for producing a flow of pressurized gases which may be expanded through a thrust producing nozzle.

Abstract: A vane type pump having vanes 9 slidingly confined in radial slots 8a in a rotor 8 operating eccentrically in a cylindrical casing 6 rotatably disposed in the housing 4 of the pump. A clutch 10 engages and disengages the rotor with the pump shaft 2 according to the speed of the shaft. The provision of the frictionally rotatable casing and the clutch enables the pump to operate at high speed with minimal vane wear and with reduced or no lubricating oil.

Abstract: The turbine section of a gas turbine engine includes structure in the disc cavity for separating high pressure air into cooling air for delivery to cooled blades and sealing air for preventing hot motive fluid from entering the cavity. A disc cavity seal is provided to minimize leakage of the sealing air into the motive gas path resulting in increased air pressure on the air separator structure (which is integrally attached to the rotor) and providing a balance piston for counteracting the normal thrust on the rotor and reducing the thrust bearing load. The resultant decrease in leakage of high pressure air also improves the engine performance efficiency.

Abstract: The system removes heat from a vessel containing the source of heat, utilizing heat energy from water circulating through the vessel. The circulating water passes through a subcooler and into a convergent-divergent nozzle of a flash jet pump. Cooled water is drawn into the flash jet pump by the high-velocity flow generated, mixes with the water flashed into steam and condenses it. The mixture flows to the inlet connection of the pressure vessel. A second flash jet pump is utilized to initially fill the vessel with coolant water. Steam in the vessel is condensed in a shock condenser.