31 results about "Propelling nozzle" patented technology

The invention relates to a method and a device for mixing a liquid in a substantially sealed container or a mixture of a liquid and a fine-particle solid, said liquid or mixture only partially filling the internal volume of the container that can be occupied by a fluidic phase and the remaining available internal volume of the container being filled by a gaseous phase. According to the invention,the essentially same liquid or mixture is fed to the container in the form of a propelled stream of a suction device that is situated in the liquid or mixture in the container. In its simplest form, the method according to the invention is implemented by means of an ejector (i.e. according to water jet pump principles) embodied as the suction device. The propelled stream is pumped through a propelling nozzle, which is fitted into the ejector in such a way that gas is sucked from the gaseous phase during the passage of the stream through the nozzle, e.g. by means of a riser tube that projects into the gaseous phase of the container, and is released in the form of dispersed gas bubbles, together with the propelled stream, into the liquid content of the storage container.

The fuel delivery device (12) has a receptacle (16) arranged in a storage tank (10) and a delivery unit (20) delivering fuel from the receptacle (16) to the internal combustion engine (14) of a motor vehicle. Further, there is provided at least one suction jet pump (40) which delivers fuel from the storage tank (10) into the receptacle (16). The suction jet pump (40) is fastened to an upper edge area (17) of the receptacle (16) as a separate constructional unit. The suction jet pump (40) is formed by a constructional unit having a propelling nozzle (41), a connection (43) for a propelling line (44), which connection (43) opens into the propelling nozzle (41), a mixing pipe (42) following the propelling nozzle (41), and a connection (45) for a suction line (46), which connection (45) opens into the mixing pipe (42). Two walls (48) located at a distance from one another project downward from the constructional unit (40), and the constructional unit (40) is mounted on the edge (17) of the receptacle (16) from the top, wherein the edge (17) of the receptacle (16) is introduced between the two walls (48). The suction line (46) connected to the suction jet pump (40) opens into the storage tank (10) remote of the receptacle (16).

The stern hull portion of a sea craft through which main exit flow channels extend to projecting jet propulsion nozzles, is provided with facilities for controlled maneuvering of the sea craft, including steering, stopping, negative thrust backing and docking without substantial hydrodynamic loading and with facilitated installation. Such maneuvering control facilities include a secondary flow channel extending from each of the main exit flow channels having two angularly related subchannel branches for pressurized water outflow through gated openings in the hull from which propulsion jets emerge under maneuvering control. Either control of a subchannel diverting flapper, or by use of selective closure gates and a flow diverting flap within the main exit flow channel, maneuvering may be effected in response to inflow through inlet openings in the hull of water that is pressurized before supply to the main exit flow channels.

A simple propulsion engine utilizing unheated atmospheric air as the propellant, and driven by a single cycle (unicycle) engine with internal combustion cylinder and free piston is disclosed. A plain piston is slidably displaceable in an elongated cylinder containing cylinder heads on opposite ends. The piston receives a combustive impulse at each end of its stroke. The cylinder also has exhaust/inlet ports and propulsive nozzles at each end with relevant valves and actuators to effect the requisite timing of the combustion, air induction, and propulsion functions. During the piston's traverse of the elongated cylinder's midsection, air is induced into the expanding volume of the moving piston/cylinder chamber while air is compressed and expelled through the nozzle of the decreasing volume chamber, producing usable thrust. The large amounts of atmospheric air induced provides inherent internal cooling and exhaust scavenging of the propulsion engine. The preferred embodiment combines a free piston with an annularly arranged thrust piston to divide a dual-diameter cylinder into two combustion chambers and two thrust chambers. Scavenge feeder lines connected the thrust chambers to the combustion chambers via check valves provide exhaust scavenging, additional thrust output through exhaust nozzles, and feeding of fresh air into the combustion chambers. Also, pressure-actuated fuel injectors utilize pressure changes in respective combustion chambers to inject fuel at the appropriate time. The fuel injector includes an intensifier piston and pintle to raise the fuel pressure.

The invention relates to an oil gas exploitation apparatus and method. The apparatus includes at least an exploitation unit, a needle tubing, and a self-propelled nozzle arranged at a second end of the needle tubing. The exploitation unit includes a jet pipe nipple and an adjusting pipe nipple detachably connected to the jet pipe nipple, wherein penetrating installation holes are arranged on a sidewall of the jet pipe nipple, and the adjusting pipe nipple is provided with oil holes for the oil gas flowing from a stratum into an inner cavity of the exploitation unit. In the original state, a first end of the needle tubing is arranged in the inner cavity of the exploitation apparatus. The second end of the needle tubing is inserted in the installation holes. During a process for pumping the liquid to the exploitation apparatus, the needle tubing extends in a storage stratum so as to form an exploitation pore passage. In the oil gas exploitation process, the oil gas exploitation apparatus has high effectiveness for the reconstruction of the storage stratum and good oil gas output.

The muzzle brake attaches to a distal end of the barrel of a firearm, typically a handgun, either built into the firearm or as an accessory attachable to the firearm. The muzzle brake includes a propelling nozzle in the form of a central chamber aligned with proximal and distal openings aligned with a barrel of the firearm. This propelling nozzle extends upward, generally expanding in cross-section, to a rim where it opens above the firearm near a distal end of the barrel. The shape of the propelling nozzle (or series of nozzles) is preferably selected to optimize downward reactive force when expanding gases discharged from firearm discharge expand upward out of the propelling nozzle. A downward reactive force is thus created which counteracts recoil of the firearm.

The invention relates to an electric drive jet engine and belongs to the field of aero-engines. The electric drive jet engine is characterized by comprising a gas inlet, a gas compressor, a combustion chamber, a propelling nozzle, and a power system, wherein a motor is installed in the gas compressor to drive the gas compressor, a rotor of the motor and a rotor of the gas compressor are coaxial, the power system comprises a solar cell, an accumulator and a power controller, the solar cell and the accumulator are respectively connected with the power controller through a circuit, the solar cell converts the solar energy into electric energy, the accumulator is used for storing the electric energy, and the power controller inputs the electric energy into the motor in the gas compressor through the circuit. The electric drive jet engine has the advantages that 1) no turbine is used, 2) the motor is used to drive the gas compressor; and 3) the solar cell and the accumulator are used together to supply electric energy.

The invention relates to the field of propulsion nozzles, and in particular to a device (105) for connecting together first and second segments (103a, 103b) of a propulsion nozzle that are made of thermally dissimilar materials. The device (105) comprises at least one pin (106) and an eccentric bushing (107). The pin (106) presents both a first axisymmetric surface (106a) that is to be housed in a radial orifice (108) of the first nozzle segment (103a) and also a second axisymmetric surface (106b) that is eccentric relative to said first axisymmetric surface (106a).

VTOL aircraft with a thrust-to-weight ratio smaller than 0.08, during vertical take-off/landing, obtains most vertical lift, besides traditional small vertical lift by high-temp bypass slot outlet (6) directing, under its opening, the closing of the tail of the power-off jet engine (3) by the valve (7) in tail cone, the closing and the stretching of the propelling nozzle (5), high-temp air (8) to spout out along the inclined downward direction of the wingspan, by a centrifugal impeller (13) accelerating, under the connecting of the transmission shaft (11) with a jet engine (4), and the opening of the cabin doors (15, 17) of the inlet (18) of the low-temp duct (16) and the auxiliary engine's inlet (14), low-temp air (21) to flow through the low-temp duct (21) and flow over the upper surface of the wing but not burn up it along the wingspan direction, thereby generating most vertical lift and enabling ailerons (1, 2) to control balances of the aircraft.

The invention discloses an external combustion propelling engine. The external combustion propelling engine comprises a liquid working medium pressure-bearing storage tank, a working medium heating fluid channel, a combustion chamber and a propelling nozzle. The bearing capacity of the liquid working medium pressure-bearing storage tank is larger than 2MPa. The combustion chamber transfers heat to the working medium heating fluid channel. The working medium heating fluid channel is communicated with the propelling nozzle. The propelling nozzle outputs power. The liquid working medium pressure-bearing storage tank is communicated with the working medium heating fluid channel in an automatically flowing mode. The combustion chamber transfers heat to the liquid working medium pressure-bearing storage tank or the pressure-bearing storage tank is communicated with the working medium heating fluid channel and the combustion chamber transfers heat to the liquid working medium pressure-bearing storage tank. The external combustion propelling engine is small in size, high in power density, low in manufacturing cost and capable of being used as an engine of aircrafts such as a target drone.

A self-propelled infrared emission aerial target has an aircraft- or a missile-shaped body and a nose, wings and/or control surfaces, a system for feeding fuel and oxidizer to a combustion chamber in which combustion gases are produced and for supplying the combustion gases to a propulsion nozzle, and an infrared radiation emitter. The target has at least one conduit connecting the combustion chamber or propulsion nozzle of the propulsion system to a nose, wing and/or control surface of the target, or to an outside element attached thereto.

The invention discloses a cut-in direct-rotation mixed jet self-propelled nozzle, and belongs to the technical field of oilfield oil production engineering. The nozzle comprises a flow mixing body, and a flow mixing cavity, a central hole communicating with the flow mixing cavity and at least two cut-in grooves communicating with the flow mixing cavity are formed in the flow mixing body; and the central hole is used for forming a liquid straight flow in the flow mixing cavity, the cut-in grooves are used for forming a liquid swirling flow in the flow mixing cavity, and the two jet flows form adirect-rotation mixed jet flow in the flow mixing cavity. The invention aims to provide the cut-in direct-rotation mixed jet self-propelled nozzle, which can break the rock in a reliable structure and a direct-rotation mixed jet mode, and improve the rock breaking efficiency while prolonging the service life of the nozzle.

The invention provides an airflow heat insulation airspace ramjet comprising an air inlet passage (diffuser), an ignition device, a combustion chamber and a propelling nozzle. The airflow heat insulation airspace ramjet is characterized in that the propelling nozzle is composed of a shell (2) and an inner pipe (4), an air chamber (C) is formed between the shell (2) and the inner pipe (4), and an air inlet is arranged in the A-section of the inner pipe (4); when an aircraft flies, kinetic energy is converted into pressure energy in the process that head-on airflow passes through the air inlet passage, compressed air enters the combustion chamber to be mixed with fuel for constant-pressure combustion, and generated high-temperature combustion gas swells and accelerates in the inner pipe (4) prior to being discharged so as to generate thrust. The original advantages of the ramjet are retained, and meanwhile energy conservation and efficiency improvement are achieved.

The invention discloses an underwater cleaning robot for the outer wall of a ship. The underwater cleaning robot comprises a robot body; the cleaning brush assembly is mounted at the front end of the robot main body through a mechanical arm; the camera is used for shooting the cleaning range of the cleaning brush assembly; the cavitation bubble device is arranged in the robot main body and emits high-pressure cavitation bubbles to the cleaning range through a propelling nozzle mounted at the front end of the robot main body; the spraying assembly is used for spraying the cleaned area when the coating of the outer wall of the ship is damaged after cleaning is completed; the four permanent magnet universal wheel assemblies are arranged on the two sides of the bottom of the robot body correspondingly and used for being attracted to the outer wall of the ship and driving the robot body to move. The robot firstly adopts a cleaning brush and then adopts a cavitation device for cleaning, so that the loss of the outer wall coating of the ship can be reduced. And by arranging the spraying assembly, repairing and spraying can be conducted in time after the coating is lost, and seawater is prevented from corroding the damaged position of the coating.

The invention relates to a hydraulic jet grouting drill bit. The hydraulic jet grouting drill bit is characterized in that the hydraulic jet grouting drill bit comprises a drill bit steel body, a jackscrew and a mandrel, a cutting blank block is arranged at one end of the drill bit steel body, the other end of the drill bit steel body is connected with a rotating body, and one end of the mandrel penetrates through a hollow part of the rotating body to be connected with the jackscrew. The jackscrew is arranged in the hollow part of the drill bit steel body, and a central hole of the jackscrew,a central hole of the mandrel and a central hole of the cutting blank block share the same central line. A rotational flow cavity is formed in the rotating body and communicates with the center hole of the mandrel, and one or more sets of eccentric rotating nozzles are further arranged on the rotating body and communicate with the rotational flow cavity. A plurality of propelling nozzles are further arranged at the tail of the drill bit and communicate with the central hole of the mandrel. High-pressure liquid flow is adopted as a driving source to generate rotating power, rear propelling force and front-end high-pressure jet flow, the jet flow rock breaking capacity is achieved, the drilling efficiency and the drilling depth can be improved, and extra large power system driving is not needed.

The invention relates to a single-stage or multistage suction jet pump comprising a propelling nozzle (5), one or more suction nozzles (2), a diffuser (7), and a volume flow limiting valve in or directly in front of the propelling nozzle. The volume flow limiting valve has a valve element (4) in the overpressure region (1) of the suction jet pump, said valve element having an opening (8) with a cross-sectional area which is smaller than the cross-sectional area of the propelling nozzle (5). The valve element spans at least one additional gap opening (9) which first releases the cross-section of the gap opening (9) when the pressure difference between the overpressure region (1) and the suction region (2) increases and which switches in the event of a defined large pressure drop and the valve element (4) reduces or closes the cross-section of the gap opening (9) such that the volume flow flowing over the opening (8) is limited to a defined level even in the event of a further increasing pressure difference.