1775 results about "Supersonic speed" patented technology

The present invention relates to a method for removing condensables from a natural gas stream, at a wellhead, downstream of the wellhead choke thereof. In accordance with the invention there is provided a method for removing condensables from a natural gas stream at a wellhead, the method comprising the steps of: (A) inducing the natural gas stream to flow at supersonic velocity through a conduit of a supersonic inertia separator and thereby causing the fluid to cool to a temperature that is below a temperature / pressure at which the condensables will begin to condense, forming separate droplets and / or particles; (B) separating the droplets and / or particles from the gas; and (C) collecting the gas from which the condensables have been removed, wherein the supersonic inertia separator is part of the wellhead assembly downstream of the wellhead choke. There is also provided a device for removing said condensables from said natural gas that is part of the wellhead assembly downstream of the choke, a wellhead assembly comprising said device.

Disclosed is a process for the reprocessing or production of a sputter target or an X-ray anode wherein a gas flow forms a gas / powder mixture with a powder of a material chosen from the group consisting of niobium, tantalum, tungsten, molybdenum, titanium, zirconium, mixtures of two or more thereof and alloys thereof with at least two thereof or with other metals, the powder has a particle size of 0.5 to 150 μm, wherein a supersonic speed is imparted to the gas flow and the jet of supersonic speed is directed on to the surface of the object to be reprocessed or produced.

System and methods for creating shaped, non-circular boreholes in rocks especially for use with geothermal heat pump applications and for increasing wellbore support in applications such as horizontal oil and gas drilling are described. The systems and methods when applied to geothermal heat pumps create an elliptical shaped hole that is optimized for placing heat transfer tubes with a minimum of grout used. The significantly reduced cross-sectional area of the elliptical borehole also increases the overall drilling rate in rock and especially in hard rocks. In horizontal hard-rock drilling, creation of a horizontal non-circular borehole or modification of a circular borehole to a non-circular geometry is used to stabilize the borehole prior to casing insertion, and may also allow the use of lower mud pressures improving drilling rates. The system uses a non-contacting drilling system which in one embodiment uses a supersonic flame jet drilling system with a movable nozzle that swings between pivot points. In a second embodiment the elliptical shaped hole is created by an abrasive fluid or particle bearing-fluid or air jet drill that moves between pivot points. In another embodiment a non-contacting drill can use dual parallel nutating nozzles that create a pair of overlapping circular holes. The non-circular shaped hole is created by either the high temperature flame or water-particle jet or chemically active fluid jet as it removes rock material by erosion, dissolution and or thermal spalling. Modifications of circular boreholes to a generally elliptical shape can also be done using milling or jetting techniques.

There is described a device and method for generating gaseous ions of a sample material such as molecules in solution at atmospheric pressure. The device includes a conduit for receiving a solution containing the material to be ionized and form a stream. A jet of gas at supersonic velocity is directed at the stream and interacts therewith. Droplets are formed and by the adiabatic expansion of the gas and vigorous evaporation of the solution gaseous ions are generated. In the method a stream of the sample solution is delivered from a conduit with an electric potential. A gas jet at supersonic velocity interacts with the delivered solution and through the action of adiabatic expansion of the gas and evaporation of the solution gaseous ions are formed.

System and methods for creating shaped, non-circular boreholes in rocks especially for use with geothermal heat pump applications and for increasing wellbore support in applications such as horizontal oil and gas drilling are described. The systems and methods when applied to geothermal heat pumps create an elliptical shaped hole that is optimized for placing heat transfer tubes with a minimum of grout used. The significantly reduced cross-sectional area of the elliptical borehole also increases the overall drilling rate in rock and especially in hard rocks. In horizontal hard-rock drilling, creation of a horizontal non-circular borehole or modification of a circular borehole to a non-circular geometry is used to stabilize the borehole prior to casing insertion, and may also allow the use of lower mud pressures improving drilling rates. The system uses a non-contacting drilling system which in one embodiment uses a supersonic flame jet drilling system with a movable nozzle that swings between pivot points. In a second embodiment the elliptical shaped hole is created by an abrasive fluid or particle bearing-fluid or air jet drill that moves between pivot points. In another embodiment a non-contacting drill can use dual parallel nutating nozzles that create a pair of overlapping circular holes. The non-circular shaped hole is created by either the high temperature flame or water-particle jet or chemically active fluid jet as it removes rock material by erosion, dissolution and or thermal spalling. Modifications of circular boreholes to a generally elliptical shape can also be done using milling or jetting techniques.

A supersonic aircraft engine axial fan that includes a rotating blade row having blades that receive a supersonic entry flow in the absolute frame and decelerate the flow to a lower supersonic or subsonic velocity exit flow while adding work to the flow to increase stagnation pressure. It is preferred that the lower velocity be subsonic. When the fan is combined with a suitably designed inlet, the propulsion system is compact and lighter in weight than conventional engines for supersonic aircraft.

The content of the invention comprises a concept of multi-beam ion pre-selection from a single sample, coordinated mobility (against the gas flow) separation, cooling ions in supersonic gas flow and mass separation of thus low divergent ions by single or plural compact high-resolution orthogonal time-of-flight mass spectrometers both linear or reflectron type with controlled collision-induced dissociation (CID) and multi-channel data recording for the optimization of sample use in the analysis, and obtaining as much useful information about the sample as possible in a reasonably short time.

An improved method and apparatus for metal melting, refining and processing, particularly adapted to steel making in an electric arc furnace. The method provides auxiliary thermal energy to the steel making process, particulate injection for the formation of slag and foamy slag, and oxygen injection for the decarburization of the melt, for the formation of foamy slag and for post combustion burning of carbon monoxide. The burner includes two injection barrels for providing finely pulverized particles and for providing either a supersonic or a subsonic primary flow of an oxidizing gas. The barrels are positioned side by side in a nozzle at the entrance of a flame shaping chamber of a fluid cooled combustion chamber. The nozzle also contains a plurality of fuel orifices for the providing pressurized fuel to the combustion chamber and a plurality of oxidizing gas orifices for providing a secondary flow of an oxidizing gas around the periphery of the nozzle. Because all of the flows of fuel, oxidizing gas and particulates pass through the flame shaping chamber, they are all substantially directed to the same location in the electric arc furnace. The directionality of the flows allows the burner to heat a localized spot of the slag with thermal energy from the oxidation of the fuel, from the oxidation of oxidizable components in the slag or the melt by the lancing of supersonic oxidizing gas, or from any combination of these. Once a spot in the slag is sufficiently heated, a flow of carbon is directed to the localized hot spot in the slag to reduce the FeO, and other oxides, in the slag to carbon monoxide and produce foamy slag. The particulate carbon introduction can be accompanied by further oxidizing gas injection before, during or after the carbon injection.

The invention discloses a three-hole transonic speed pressure probe. As a pneumatic technology develops, a transonic speed air flow appears more and more frequently, for instance, many air flows in an aeroengine reach a transonic speed state, so these transonic speed flow fields need to be measured and analyzed during development of engine components. Conventionally, the transonic speed flow fields are measured respectively by use of a total pressure probe and a direction probe so that total pressure and air flow directions can be obtained. When a flow speed reaches a transonic speed, the probes are under great resistance, and the probes are blown bent easily. When the flow speed reaches an ultrasonic speed, due to the existence of shock waves, there is large total pressure loss, and the influences exerted by the probes on the flow fields are quite large. Though these conventional probes can be used in an ultrasonic air flow, the influences exerted by the probes on the flow fields cannot be neglected, and the requirement for the strength of the probes is quite high. The novel three-hole transonic speed pressure probe provided by the invention is used for measuring the transonic speed flow fields. By use of the probe provided by the invention, the intensity of the shock waves in front of the probe can be weakened during measurement, the influences exerted by the probe on the flow fields are reduced, air-flow total pressure, static pressure, a Mach number and an air-flow deflection angle can be measured simultaneously, the resistance acting on the probe can be effectively reduced, and the firmness and reliability of the probe are guaranteed.

Deltoid Main Wing idea provides for several innovative aerodynamic configurations for large subsonic and supersonic civil and military aircraft including “T-tailed Deltoid Main Wing” configuration that allows for design of high-subsonic jumbo jet passenger aircraft with a capacity between 200 and 700 passengers whose outer dimensions fit within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with the same passenger capacity, while further allowing for design of all-size and all-purpose, high-lift-capacity, and long-range unmanned aircraft.

A mounting block and an improved mounting arrangement for apparatus used in metal melting, refining and processing, particularly those apparatus adapted to steel making in an electric arc furnace, such as burners, lances and the like with supersonic oxygen lancing capability. The mounting block is fluid cooled to survive the hostile environment of the electric arc furnace and is designed to rest on the step between the side wall and hearth of the furnace without any substantial change to the structure of the furnace. The mounting block comprises a plurality of fluid cooling conduits surrounding an aperture which is formed through the block and adapted to mount the apparatus. The mounting arrangement includes utilizing the mounting block to mount an apparatus with supersonic oxidizing gas or lancing capability in an electric arc furnace. The apparatus is mounted by passing it through an aperture in a water cooled side panel aligned with the mounting aperture in the mounting block. Because the mounting block is approximately the width of the step, the discharge opening of the apparatus is moved closer to the surface of the melt and toward the center of the furnace thereby providing increased efficiency. The discharge opening will now also extend past the inner edge of the step so that the oxidizing gas flow pattern does not degrade the hearth material and other furnace equipment mounted nearby.

A method and apparatus are provided for removing solid particles from a particle containing stream of fluid, the method including the steps of: inducing the stream to flow at supersonic velocity through a conduit; inducing a swirling motion to the supersonic stream of fluid thereby causing the particles to flow to a radially outer section of a collecting zone in the stream; and extracting the solid particles into an outlet stream from the radially outer section of the collecting zone. The apparatus is an apparatus effective for performance of this method.

Method for preparing a target substance in particulate form, comprising introducing into a particle formation vessel, through separate first and second fluid inlets respectively, (a) a "target solution / suspension" of the substance in a fluid vehicle and (b) a compressed fluid anti-solvent, and allowing the anti-solvent to extract the vehicle so as to form particles of the substance, wherein the anti-solvent fluid has a sonic, near-sonic or supersonic velocity as it enters the vessel, and wherein the anti-solvent and the target solution / suspension enter the vessel at different locations and meet downstream (in the direction of anti-solvent flow) of the second fluid inlet. Also provided is apparatus for use in such a method.

A burner for melting glass forming batch material includes a burner assembly constructed and arranged with a first passage for providing a fuel stream and a second passage for providing an oxidant stream, the first and second streams coacting to produce a supersonic combustion jet flame penetrable into glass melt. A method for melting glass forming batch material is also provided and includes providing a fuel stream; providing an oxidant stream; mixing the fuel and oxidant streams with sufficient force for providing a supersonic combustion jet flame; directing the supersonic combustion jet flame to contact the glass forming batch material; and penetrating the glass forming batch material to a select depth with the supersonic combustion jet flame.

The invention relates to a high-entropy alloy powder material for supersonic spraying and a manufacturing method thereof. The high-entropy alloy powder material for the supersonic spraying can be obtained and is characterized in that the high-entropy alloy powder material comprises, by atomic percent, 10-20% of Al, 15-20% of Fe, 15-20% of Co, 15-20% of Ni, 15-20% of Cr and 15-20% of Cr, and total percent is 100%. The high-entropy alloy powder material is made by a gas atomization rapid solidification process. Particles of high-entropy alloy powder are spherical or ellipsoidal, a phase structure is composed of a solid solution phase with a simple face-centered cubic or body-centered cubic structure, ingredients and tissues are even, alloy solid solubility is high, and segregation is small. The manufacturing method of the high-entropy alloy powder material is controllable in powder size, good in mobility, low in oxygen content, small in environment pollution, high-entropy alloy coating with excellent combination property or a block high-entropy alloy material with more excellent performance can be obtained through a supersonic spraying process.

The present invention provides a flight control system and method for various models of aircraft, including thin-winged, long range, transonic and low supersonic aircraft, and may be beneficial on supersonic and hypersonic aircraft as well. One embodiment of the flight control system comprises a plurality of lifters for generating lift or drag, the plurality of lifters mechanically associated with a lower surface of each wing in a pair of wings. During operation, the lifters may be selectively deployed alone or in combination with other flight control devices, such as ailerons and spoilers, to provide various operative benefits such as improved roll control, speed braking functionality, and maneuver load alleviation.

A supercharged internal combustion engine system wherein the supercharger assembly includes an ejector pump driven by high-pressure air for pumping intake air into engine combustion chamber. The ejector pump uses a supersonic driving nozzle and a diffuser, each of which can be provided either with a fixed throat area or with a variable throat area. The system includes means for sensing engine power demand and controlling the supercharging action. Effective supercharging with fast response to demand is achieved even at low engine speeds. During periods of natural engine aspiration the ejector pump can be by-passed to reduce flow impedance. The invention permits increasing power output from small displacement engines. As a result, acceleration and grade ascent capabilities of automotive vehicles with small displacement engines having good fuel economy is improved. The system can be also operated to reduce engine exhaust emissions during cold start.

The invention discloses a process for repairing water erosion damage of a flow passage component of a steam turbine and protecting the flow passage component of the steam turbine. In the process, molded lines of the flow passage component of the steam turbine are repaired by adopting copy overlaying of manual argon tungsten arc welding aiming at the phenomenon of the water erosion damage existing in the flow passage component of the steam turbine. A water erosion resistant coating is prepared by supersonic speed flame spraying so as to achieve the purposes of repairing the molded lines of the flow passage component of the steam turbine and protecting the molded lines at large area on line and prolonging the service life of the flow passage component of the steam turbine. Through the process of the invention, the flow passage component of the steam turbine can be repaired and protected at large area on line in a short time without changing vibration characteristic, steam-driven characteristic and strength characteristic of the flow passage component of the steam turbine, so that the process has the advantages of high on-site operability, small deformation of the repaired workpiece, remarkable improvement on water erosion resistance and the like, can solve the common problem of water erosion in the flow passage component of the power station steam turbine in service on site, improves the running safety and efficiency of units and increases economic benefit of a power plant.

The invention disclosed herein provides a subsonic wind tunnel capable for accurately maintaining a desired Mach number, pressure and temperature for use in aerothermal testing of materials. The invention allows the Mach number to be precisely controlled in the test section of the wind tunnel by employing a restricted outlet acting as a sonic throat for the wind tunnel. In the preferred embodiment, the restricted outlet is constructed to be variable in cross sectional area allowing a range of Mach numbers to be tested. The variable outlet is varied during the operation of the wind tunnel so that an actual trajectory with changing Mach numbers, pressure, and temperature is simulated.

This invention provides a constant geometrical supersonic and hypersonic speed adjustable inlet channel which has fixed geometrical shape and simple structure and can adjust the wave system and the effective passage throat area in the inlet channel. Its features lie in that it includes the inlet channel subject, liplike cap, pipeline, valve, porous or multi-crevicel plate, stabilized voltage tune, water-spreading plate and tune. It extracts a small quantity of relatively high pressure secondary fluid through the water-spreading plate and tune fixed in the high-pressure area of the inner inlet channel. The fluid is then carried through the pipe to the stabilized voltage tune fixed in the all-level constricted sloping plate of the inlet channel subject. After that it pours along the distribution and preinstalled way in the flow field of the inlet channel through the porous or multi-crevice plate which achieves the real-time adjustment of the wave system and the effective passage throat area in the trophy of the inlet channel. The merits of this invention are not only the high resistance value in the wide Mach number, the low coefficient of drag relative to the conventional inlet channel, but also the fixed geometrical shape, simple structure and being apt to achieve.

A Brayton-cycle rotary ramjet engine (10) operated within the confines of a helically elongated pass-through duct formed between a preferably stationary radially outward surface (14) and an outer rotating flow channel (36). The flow channel (36) is contoured between its inlet (34) and outlet (38) to include a supersonic diffuser (40), a combustor (42) and an expansion nozzle (44). Gaseous fuel, or liquid fuel atomized by a fuel slinger (58) within a housing (46), or solid fuel in the form of fine particulates, is inter-mixed with an oxidizer prior to being directed to the flow channel inlets (34). The air and fuel are combusted in the flow channels (36) and exhausted through the rear of the housing (46). A generator (22) can be coupled to a power shaft (18) to convert net shaft power into electricity. Preferably, the rotor (24) and stator (12) are fabricated from a ceramic or other high-temperature material so that combustor exit temperatures (T3) can be operated at highly efficient levels.

A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having means for producing exhaust gas and a gas exhaust nozzle for generating thrust for supersonic flight speeds, and at least one separate auxiliary propulsion assembly dissociated from said engine, having no gas generator, and capable of generating thrust for takeoff, landing, and subsonic flight speeds. The system further comprises gas flow tapping means movable between a position in which they tap off at least a fraction of the exhaust gas produced by said engine and feed it to said propulsion assembly to enable it to generate thrust for takeoff, landing, and subsonic cruising flight, and a position in which the gas produced by the engine is directed solely to the engine nozzle for supersonic cruising flight.

The content of the invention comprises a concept of reactor for isolated ion transformations induced by collisions with neutral species. This reactor is also an interface between mobility cell and orthogonal injection TOFMS based on supersonic adiabatic gas flow with variable controlled composition directed along the axis of a multipole ion guide with sectioned rods for possibility of creating of controlled distributions of RF, DC and AC rotating fields.

The invention relates to a production device for steam explosion pretreatment of biomass, in particular to a pretreatment device for the industry of biomass utilization, and provides a numerically controlled continuous steam explosion machine, which can complete supersonic steam explosion in milliseconds (0.00875s) based on the principle of a sliding cover. Since the cross-sectional area of the steam explosion machine for gas discharging, i.e. the cross-sectional area of the sliding cover, is equal to the cross-sectional area of a high-pressure cylinder, the cross-sectional area of the steam explosion machine for gas discharging and the steam explosion treatment volume form a fixed ratio, the problem that the gas discharging time is prolonged along with increase in the treatment volume in the traditional hot blowing process can be solved, and the power and density of steam explosion can be increased by three orders of magnitude. Moreover, the 'rawness and maturity' of materials which are subjected to batch treatment can be kept identical, and a foundation is laid for the consistency of industrial biochemical treatment. Meanwhile, the machine has the function of feeding and discharging materials automatically and the continuous steam explosion production can be realized.

The content of the invention comprises a concept of multi-beam ion pre-selection from a single sample, coordinated mobility (against the gas flow) separation, cooling ions in supersonic gas flow and mass separation of thus low divergent ions by single or plural compact high-resolution orthogonal time-of-flight mass spectrometers both linear or reflectron type with controlled collision-induced dissociation (CID) and multi-channel data recording for the optimization of sample use in the analysis, and obtaining as much useful information about the sample as possible in a reasonably short time.

The invention provides a supersonic condensation and cyclone separation device, which leads air flow to generate powerful rotation in a blade-guiding manner at an entrance; then, a laval nozzle is used for coordinating with the separation device to lead the air flow to reach a supersonic speed and reduce temperature thereof greatly, thus condensing components with higher dew points and achieving the separation between the gas phase and the liquid phase under the action of the centrifugal force generated by the rotation of the air flow; and a highly-efficient liquid trap and a cyclone-recovering booster are arranged at the tail part of the nozzle. Compared with the existing supersonic separating device, the supersonic separation device of the invention has higher efficiency of separation and cyclone recovery under the same working conditions of low flow rate, for the device has the advantages that the flow channel of the device in a high-speed flow field area is smooth, the fractional resistance of the wall surface is low and the device is provided with the cyclone recovering booster suitable for the conditions of low flow rate. Since quite a lot of inland gas fields has low single-well flow rate in China, the device of the invention has wide application prospect in the field of natural gas treatment for the inland gas fields in China.

The invention provides a treatment method of oily sludge, which comprises the steps of: introducing overheated vapor into a high temperature treatment groove to roast the oily sludge so as to evaporate the liquid containing oil and water in the oily sludge to gas; separating the solid granules from the oily sludge and contained in the gas in a gas-solid separator, and conveying the solid granules to a drying machine to be dried and burnt so as to be discharged; condensing the gas separated from the gas-solid separator to liquid state oil and water, separating the liquid state oil and water in an oil-water separator to be respectively recycled, wherein the oily sludge is introduced into the high temperature treatment groove in a pumping manner, the overheated vapor is introduced into the high temperature treatment groove by supersonic jet flow and is vertically collided with the oily sludge. The invention further provides a treatment apparatus of oily sludge for executing the method; the treatment method and treatment apparatus provided by the invention have the advantages of guaranteeing high crude oil recovery, and small water content and oil content of finally generated dry residues.

Three dimensionally large metallic structures comprised of submicron grain sizes are produced by a process which includes directing a supersonic powder jet against a substrate such that the powder adheres to the substrate and to itself to form a dense cohesive deposit. The powder jet may be comprised of refractory metal powders. The powder may be deposited by a supersonic jet and may be extruded by Equi channel angular extrusion.

A system and method which enable efficient, rapid and safe transition between rotary-wing and fixed-wing flight mode in rotor / wings aircrafts is disclosed. The aircraft comprises of two rotor / wings on the same axis of rotation, one above the fuselage and the other one under the fuselage. During rotary-wing mode, the rotor / wings rotate coaxially and provide vertical lift. During transition between rotary-wing and fixed-wing modes, the synchronised operation of the two rotor / wings maintains lateral symmetry of lift on the aircraft. The reaction of the rotor / wings on the fuselage is also canceled. During fixed-wing flight mode, the two rotor / wings are stopped and locked in a biplane configuration, both providing lift as fixed wings. The rotor / wings may be further reconfigured for higher subsonic or supersonic speed. Tandem and multiple rotor / wings aircrafts with increased cargo capacity, speed and range, comprise of multiple of these coaxial rotor / wings.