Abstract: A fountain has: a water source; a housing; a vortex chamber defined within the housing, the vortex chamber connected to receive water from the water source; a bubble chamber defined within the housing and connected to receive water from the vortex chamber and cause air bubbles to percolate within the bubble chamber; and a water outlet defined in the bubble chamber. A fountain has: a water source; a housing; a vortex chamber defined within the housing, the vortex chamber connected to receive water from the water source; a second chamber defined within the housing and connected to receive water from the vortex chamber; and a plurality of water outlets defined in the second chamber.

Abstract: A fluid manifold assembly for a gas turbine engine, the fluid manifold assembly including a walled conduit assembly defining a fluid passage therewithin. The fluid passage defines a pair of ends separated by a length. A connecting conduit is coupled to the end of the fluid passage and to the length of the fluid passage.

Abstract: A method for producing dispersions with a defined particle size includes following steps: A) Preparation of a mixed dispersion in a predispersion process, B) introduction of the mixed dispersion into at least one continuously operating separating device, C) separation of the mixed dispersion in the separating device into coarse particles of a coarse-part dispersion and into fine particles of a fine-part dispersion, D) discharging the fine particle dispersion from the separating device into at least one storage tank, E) discharging the coarse particle dispersion from the separating device into at least one disperser, F) grinding the coarse particles of the coarse particle dispersion in the disperser into a dispersed particle mixture and returning the dispersed particle mixture to the mixing tank in the predispersion process, and G) mixing the dispersed particle mixture returned to the predispersion process with the mixing dispersion produced in the predispersion process in the mixing tank.

Abstract: A jet engine includes an inlet and a combustor. the inlet takes in air. The combustor combusts fuel with the air. The combustor (12) includes an injector (20) having a plurality of openings (31a, 31b) from which the fuel is injected. The plurality of openings (31a, 31b) are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor (12). The plurality of openings (31a, 31b) include two types of openings different in area.

Abstract: An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a thermal spray system performing a process associated with a plurality of process attributes. The example system includes a computing device including an acoustic data signal module and a control module. The acoustic data signal processing module may transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. The control module may determine a process attribute of the plurality of process attributes that deviates from a predetermined operating range by identifying at least one characteristic of the frequency-domain spectrum, selecting at least one component of the thermal spray system based on the process attribute, and controlling the thermal spray system to adjust the process attribute toward the predetermined operating range by sending a control signal to the at least one component.

Abstract: A hybrid combustion system, and method of operation, for a propulsion system is provided. The hybrid combustion system defines a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The hybrid combustion system includes a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall. The nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, and the nozzle inlet is configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle.

Abstract: A fountain has: a water source; a housing; a vortex chamber defined within the housing, the vortex chamber connected to receive water from the water source; a bubble chamber defined within the housing and connected to receive water from the vortex chamber and cause air bubbles to percolate within the bubble chamber; and a water outlet defined in the bubble chamber. A fountain has: a water source; a housing; a vortex chamber defined within the housing, the vortex chamber connected to receive water from the water source; a second chamber defined within the housing and connected to receive water from the vortex chamber; and a plurality of water outlets defined in the second chamber.

Abstract: An internal combustion engine that uses stratification of gasses for compressing air is disclosed. The engine uses a combustion chamber that delivers products of combustion into an elongated compression chamber to drive the products of combustion against resident air within the elongated compression chamber, and push the resident air into a compressed air chamber. After driving the resident air into the compressed air chamber, the products of combustion are used with work-producing devices. Air is then driven into the compression chamber by an air pump or low-pressure compressor to once again fill the compression chamber with fresh air. The air in the compressed air chamber is then delivered to the combustion chamber and used for combustion. Fuel is delivered to the combustion chamber by a fuel injector, and ignited by the heat of the compressed air and/or a glow plug, spark plug, or similar ignition device.

Abstract: A power source is provided for use with selective catalytic reduction systems for exhaust-gas purification. The power source includes a first cylinder group with a first air-intake passage and a first exhaust passage, and a second cylinder group with a second air-intake passage and a second exhaust passage. The second air-intake passage is fluidly isolated from the first air-intake passage. A fuel-supply device may be configured to supply fuel into the first exhaust passage, and a catalyst may be disposed downstream of the fuel-supply device to convert at least a portion of the exhaust stream in the first exhaust passage into ammonia.

Abstract: A supersonic combustion apparatus and method of using the same including a side wall cavity having an enhanced mixing system with ground-based oxygen injection for hypersonic material and engine testing.

Abstract: A pulse combustion device has a number of combustors with upstream bodies and downstream nozzles. Coupling conduits provide communication between the combustors. For each given combustor this includes a first communication between a first location upstream of the nozzle thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle of the given combustor.

Abstract: A process for collecting oxygen-enriched air during a phase of aerobic flight of a space launch for combustion inside at least one cryotechnic rocket engine is provided. The launch rocket comprises at least one turbofan. The turbofan comprises a high-pressure spool comprising a high pressure compressor, a combustion chamber, turbines, and a low-pressure spool surrounding the high-pressure spool. The spools comprise a blower for collecting the external fluid in the form of a main flow and a derived flow. The main flow follows compression, combustion and depressurization in the turbofan engine. The derived flow is separated into oxygen-enriched air and oxygen-depleted air. The oxygen-enriched air is stored for combustion in a rocket engine, while the oxygen-depleted air is ejected.

Abstract: A system configured to deliver dry pressurized air, derived from ambient air, to underground or outdoor cables, conduit, waveguides, plenums or other air spaces for the purpose of preventing the ingress of moisture or contamination. The system includes a housing and a modular membrane pressurization unit removably received within an interior space of the housing. The housing has a base configured for being at least partially buried below ground level and an air intake above ground level. The modular membrane pressurization unit intakes humid ambient air from the environment surrounding the housing and generates a continuous supply of dry pressurized air housing that is routed to the underground air space.

Abstract: A reduction in the emission of infrared radiation by the engine of a jet aircraft can be achieved by employing a low molecular weight monohydric alcohol, having a luminometer number of at least about 200 as at least a portion of the fuel. Additional reduction in emission of infrared radiation can be achieved by passing a low molecular weight monohydric alcohol in indirect heat exchange relationship with the hot exhaust nozzle prior to its introduction to the combustion chamber of the engine.

Abstract: This invention provides a valve for diverting fluid flow in a tandem fan type engine. The valve comprises an axially displaceable sleeve 38 which is provided with two circumferentially extending sealing lands 40, 42 which in operation cooperate with two locating surfaces 50, 52 provided on the duct 22 between the first and second compressors 20, 24 of said engine to seal an outlet opening 36. The free unsprung length between the sealing lands 40, 42 is greater than the length between the locating surfaces 50, 52. Gas pressure is used to compress a contractable portion 54 in said sleeve and hence ensure sealing takes place between both pairs of locating surfaces and sealing lands. This apparatus ensures centralisation of the upstream and downstream ends of the sleeve 38 is independently obtainable and accommodates thermal expansion differentials between the sleeve 38 and the duct 22.

Abstract: Solid fuel gas generator compositions for use in ducted rockets, in which fullerenes or substituted fullerenes are used. Fullerene compounds in which easily oxidizable groups, oxidizing groups, or salts of oxidizing acids are attached to the spherical carbon skeleton of the fullerene.

Abstract: A high density liquid hydrocarbon fuel composition singularly suited for propelling turbojet limited volume missile systems designed for shipborne deployment. The contemplated fuels are basically composed of the saturated analogues of dimers of methyl cyclopentadiene and of dicyclopentadiene and optionally include the saturated analogues of the co-trimers of said dienes or the trimers of cyclopentadiene. The various dimers and trimers are combined in a relative relationship to provide optimal performing fuels for the indicated purpose.

Abstract: A method for catalytically isomerizing a mixture of hexacyclic dimers obtained by dimerizing norbornadiene in the presence of a zero valent iron complex whereby the hydrogenated derivatives of the resultant isomerization product exhibits substantially lower freeze point than that associated with the hydrogenated derivatives of said precursor dimer mixture, the latter representing the highest energy liquid hydrocarbon fuel commercially available.

Abstract: A castable solid propellant composition suitable for use as a fuel generator for a ducted rocket motor is provided. The binder for the composition is a crosslinked polysiloxane. The polysiloxane polymer which is crosslinked to form the binder has a viscosity measured at 77.degree. F. of from about 12 poise to about 50 poise. The metal fuel for the composition is a mixture of spherical and flake magnesium. The composition contains from about 16% to about 20% polysiloxane binder and from 55% to 63% magnesium fuel. The oxidizer is principally ammonium perchlorate.

Abstract: Hydrogenolysis of a saturated endo-endo dihydronorbornadiene hexacyclic dimer involves the use of a catalytic amount of a Group VIII metal and the presence of hydrogen. The resulting pentacyclic isomers can be used as a diluent for depressing the freezing point of the saturated hexacyclic dimer which is a component of a high density missile fuel.

Abstract: A method for converting endo-tetrahydrodicyclopentadiene to the corresponding exo isomeric form which is advantageously carried out in the presence of aluminum chloride catalyst and the spent nickel hydrogenation catalyst utilized in hydrogenating an endo dimer of cyclopentadiene to provide said tetrahydro derivative thereof.

Abstract: The removal of color bodies from an olefinic or saturated endo-endo hexacyclic homodimer of norbornadiene or mixtures thereof is accomplished by the use of a serpentine clay. Also acid bentonite clay or a montmorillonite clay can be used to remove the color bodies from the saturated dimer. The saturated dimer has a high density and a high heat of combustion making it useful as a missile fuel. Removal of the color bodies avoids possible catalyst poisoning in the hydrogenation of the olefinic to the saturated dimer. Also removal of the color bodies from the saturated dimer eliminates the possible problem of a material precipitating out on engine turbine blades and causing maintenance or operational problems.

Abstract: Novel codimer (I) of norbornadiene and 1,3-cyclohexadiene and its hydrogenated derivative (II), having the following structures: ##STR1## and processes for preparing both are disclosed. Product (II) can be used as a high energy fuel. Process for codimer I involves use of three component homogeneous catalytic system of cobaltic or cobaltous acetylacetonate, 1,2-bisdiphenylphosphino ethane and one of three alkyl aluminum chlorides.

Abstract: Isomerization of a liquid, saturated endo-endo norbornadiene hexacyclic dimer involves the use of a catalytic amount of acidic alumina or a montmorillonite. The resulting isomeric product is solid, at ambient temperature, and can be used as a missile fuel.

Abstract: The endo-endo olefinic hexacyclic dimer of 2,5-norbornadiene is isomerized using an acidic alumina catalyst. The isomerization temperatures ranges from between about an ambient temperature to about 300.degree. C. The isomerized product, after hydrogenation, can be used as a high density missile fuel.

Abstract: Binor-S is prepared by the catalytic dimerization of norbornadiene (bicyclo[2.2.1]hepta-2,5-diene) using a homogeneous catalyst system of cobaltic acetylacetonate and diethylaluminum chloride and triphenyl phosphine. Ethylaluminum dichloride or aluminum ethylsesquichloride can be used in lieu of the diethylaluminum chloride. The reaction rate is rapid at an ambient temperature. Binor-S can be used as a precursor for hydrocarbons having utility as a high energy fuel.

Abstract: Dimethyldicyclopentadiene is continuously hydrogenated to tetrahydrodimethyldicyclopentadiene and then the latter is continuously isomerized to a missile fuel. Both the hydrogenation and the isomerization steps use a nickel on silica-alumina catalyst. The temperature of the hydrogenation is in the range of about 70.degree.-260.degree. C., and the temperature of the isomerization is in the range of about 200.degree.-280.degree. C. The space velocity of the hydrogenation is about 0.1 to about 2.0 volumes of the diene charged per volume of catalyst per hour and the space velocity of the isomerization is about 0.1 to about 3.0 volumes of the hydrocarbon charged per volume of catalyst per hour. The pressure range for hydrogenation is between about 200 psig to about 3000 psig and for isomerization between from about 10 psig to about 1500 psig. Hydrogen is present during the isomerization.

Abstract: The overall efficiency of a reaction engine having primary and secondary combustion chambers is greatly improved by reducing the primary exhaust velocity to subsonic speed. This is accomplished in a preferred embodiment by using an exhaust tube downstream of the primary nozzle. A tube diameter of about six times that of the primary throat diameter and a tube length of about five to ten times that of the tube diameter is considered optimum.

Abstract: Endo-tetrahydroalkyldicyclopentadienes are mildly isomerized with AlCl.sub.3 whereby the changes in pour point and viscosities are such that the resulting isomeric mixture can be used as a diluent for a higher viscosity hydrocarbon missile fuel. The isomerication is such that essentially no alkyl-adamantanes are formed. The mole ratio of AlCl.sub.3 to the tetrahydrodienes is in the range from between about 0.001 to about 0.5. The temperature is in the range between from about 0.degree. C to about 100.degree. C.

Abstract: Mixed tetrahydropolycyclopentadienes are isomerized in the presence of anhydrous aluminum trichloride to form an additive suitable for use with a high energy missile fuel. The amount of aluminum trichloride present is such that the weight ratio of trichloride to the tetrahydropolydiene is in the range between from about 0.005 to about 0.75. Also the isomerization involves an inert solvent and is at a temperature between from about -20.degree. C to about 25.degree. C. Also anhydrous hydrogen chloride is present to facilitate the isomerization.

Abstract: Endo-tetrahydrodicyclopentadiene is isomerized to its exo-isomer in the presence of aluminum trichloride at a temperature in the range between from about -.degree. C to about 90.degree. C. The mole ratio of AlCl.sub.3 to the tetrahydrodiene is in the range between from about 0.001 to about 0.75. An inert solvent may also be used. The very facile isomerization is essentially quantitative. The exoisomer has utility as a relatively high BTU/gallon, viscosity-lowering difluent for a missile fuel.