395 results about "High-pressure area" patented technology

A device for transferring EGR gasses from the exhaust collector of a supercharged internal combustion engine to its inlet conduit includes, besides a supercharge unit, a venturi device having the purpose of sucking the EGR gasses from the exhaust collector into the inlet conduit in order to overcome the high gas pressure in the pressurized charging air in this conduit. In order to adjust the amount of sucked-in EGR gas to the different load points, under which the engine works, an injector tube is arranged in the inlet section to the canal of the venturi device, through which injector tube the EGR gasses are led into the inlet conduit. The free end of this injector tube delimits, together with the surrounding canal wall, a ring-shaped passage, whose cross-sectional area may be varied by an axial relative motion between the injector tube and the venturi device.

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.

The invention relates to a high-temperature comprehensive property evaluation experimental device of a sealing spacer, comprising a spacer loading system, a flange lifting separation system, a spacerdeformation measuring system, a heating and temperature control measuring system, a cooling heat insulation system, a medium setting system, a medium sealing and leakage rate measuring system and a data acquisition system. The invention has the advantages of high parameter, convenient experiment, compact structure of a whole experimental machine, small occupying area, and the like, takes a low-pressure area as a leakage measuring cavity, enhances the measuring precision of the pressure of the leakage measuring cavity and also effectively avoids the problem of pipeline leakage caused by takinga high-pressure area as a leakage cavity so that the measurement of the sealing property of the spacer is more accurate; and in addition, the flange lifting separation system can solve the problem ofthe difficult bonding and separation of the high-temperature experimental spacer and a flange.

Air pressure distribution for airfoil lower and upper surfaces is utilized to divert airflow using ducts formed in space-curve shapes placed inside the airfoil volume, through span-wise located inlets from high pressure areas on the airfoil lower surface near the leading edge and through chord-wise spaced inlets on the side face of the airfoil wing tip correspondingly to the side face of the airfoil wing tip through chord-wise spaced outlets on the side face of the airfoil wing tip and to span-wise located outlets to the low pressure areas on the airfoil upper surface. Triboelectric materials on the wing surfaces are employed to static charge the air in drag. Inside the ducts, the employment of either triboelectric linings and materials, or HV-supplied electrodes, or both, help to static charge the diverted air flow to and from the airfoil wing tip side face to diffuse wing tip vortex core early.

A particle-optical apparatus, such as an ESEM®, for simultaneous observing a sample with particles and photons. A pressure limiting aperture (PLA) is placed in a diaphragm between the objective lens of the ESEM® and the sample position. The distance between the sample position and the aperture is sufficiently small to allow a large collection angle of the photons through this aperture. A mirror is placed between the diaphragm and the objective lens. Due to the large collection angle for photons a large NA is achieved. The small distance between sample position and aperture also result in less scattering of electrons than occurs in ESEM's where a mirror is placed between aperture and sample position, as the electrons have to travel through only a limited length in a high pressure area. Embodiments describe combinations where e.g. an immersion lens is used.

The invention provides a centrifugal pump with an impeller rotation boosting structure, the centrifugal pump comprises a motor, a pump body, an impeller, and a front end cover and a rear end cover at the front and rear sides of the impeller, the impeller is provided with a rear seal ring, the rear end cover is provided with a seal baffle ring which extends toward the impeller and covers at the periphery of the rear seal ring, a seal cavity is formed between the seal baffle ring of the rear end cover and the rear seal ring of the impeller, and the rear seal ring is provided with a plurality of slip sheets capable of slipping into the seal cavity. Compared with the prior art, through adopting the improved design of the end cover and the impeller of the centrifugal pump and utilizing the improved structures (such as the seal cavity and the slip sheets) between the seal baffle ring and the rear seal ring, pressure difference between a high pressure area and a low pressure area at two ends of the seal cavity is converted into power for pushing the impeller to rotate during the rotation of the impeller, so that the torque output of the motor is reduced.

The invention relates to a supercritical water oxidation reaction apparatus, which comprises a case body produced by an overpressure-resistant material; an inner case body produced by a heatproof material, wherein the inner case body is supported in the outer case body, an interval zone is provided between the inner case body and the outer case body, and the interval zone is isolated with cavity fluid; an end cap arranged at the open end of the inner case body and the outer case body in a sealing mode; a reactant nozzle arranged on the end cap and used for injecting an oxidizing agent and a reaction raw material into the inner case body, so that the oxidizing agent and the reaction raw material are subjected to an oxidation reaction near the reactant nozzle to form a reaction zone and generate the reaction products; and a products outlet arranged on the inner case body and extended to the outside part of the outer case body to discharge the reaction products outwardly. A cooling medium is provided in the interval zone. The invention also provides a supercritical water oxidation reaction method. The effective separation is carried out through a high-temperature region and a high-pressure area supported by the wall of a reactor by using the inner case body and the outer case body; the material selection difficulty and manufacture difficulty of the supercritical water oxidation reaction apparatus can be reduced, and the cost is effectively reduced.

The present invention relates to a reconfigurable porous technology for fluid flow control system and more particularly to reconfigurable porosity fluid flow control system for vehicles such as aircraft, missiles, ground and water vehicles to improve the performance of such vehicles. The present invention further relates to a method of operating the reconfigurable fluid flow control system.In one embodiment, the present invention includes a reconfigurable porosity system for fluid flow control on the surface of an aircraft, missile, water-craft or ground vehicle comprising a porous outer skin comprising individual pores; individually addressable valves corresponding and connected to the individual pores for opening and closing the pores; and a pneumatic system for connecting the pores wherein fluid from a high pressure area of the porous outer skin can be directed to a low pressure area of the porous outer skin by opening and closing the individually addressable valves. In another embodiment, the present invention includes a method of fluid flow control using reconfigurable porosity.

The invention discloses electronic skin with irregular surface microspikes. The electronic skin comprises a substrate, a support layer, a pressure-sensitive sensing layer, an electrode layers and a flexible protective layer in sequence from bottom to top, wherein the edge of the flexible protective layer is bonded with the substrate through a double-side viscous layer, so as to package the support layer, the pressure-sensitive sensing layer and the electrode layer; the microspikes are formed on the surfaces of both the support layer and the pressure-sensitive sensing layer. The electronic skin is obtained by treating a material with non-uniform surface microscopic height as a mold plate according to a chemical solution method. The electronic skin has the characteristics of double sensitivity; the sensitivity in a low-pressure area reaches up to 909 kPa<-1>; the sensitivity in a high-pressure area reaches up to 46 kPa<-1>; the total sensitivity in the pressure sensitive area can reach up to 20 kPa or higher. The electronic skin and a preparation method thereof have the advantages of being novel and simple, obvious in effect, excellent in performance and low in cost, thereby having huge potential and superiority in the field of robots.

The invention relates to a magnetic pump, which comprises a pump body, a pump bonnet, a pump spindle, an impeller, an internal magnetic rotor, an external magnetic rotor, a separation sleeve, a driving shaft, a driving shaft bearing box; the cooling medium of the rotor internal cavity thereof is drawn into from the high pressure area of the pump chamber and reflows; the medium smoothly flow and does not generate gasification and evacuation to the pump chamber; particulate matters such as sand grains and the like in the medium do not generate aggregation to wear the bottom of the separation sleeve around the bottom of the separation sleeve; a pressure balancing cavity (D designed between the rear side of the impeller (13) and the pump bonnet to automatically balance the axial balancing force of the impeller on the pump spindle (12) and cause the pump spindle to bear the minimum axial acting force; a corrugation cushion collar is arranged on a sliding bearing and a sliding bearing bush to play the elastic protection and cause that the performance of the pump is be increased, the pump is safe in utilization and has long service life.

A cooking appliance incorporates a convection heating system including a housing having an interior portion, a fan assembly, a heating element and an exhaust outlet duct. The exhaust outlet duct, within which is arranged a plurality of controlled vent openings, is positioned in a high pressure area of the convection heating system established about a periphery of the fan assembly and heating element. Oven gases are forced by the high pressure through the exhaust duct, thereby creating a corresponding reduction in pressure. The reduction in pressure establishes a low pressure area within the fan assembly which draws in fresh air in an amount equal to that exhausted through the exhaust duct.

The present invention relates to differential thrust balance device, and is one kind of differential thrust balance device for rotary fluid machinery. The present invention includes thrust balance device connected to the rotating shaft of rotary fluid machinery, leakage interval for fluid medium to flow from the high pressure area to the low pressure area, thrust detecting unit, controller and flow regulator. The shaft displacement sensor, the oil film thickness sensor and the thrust detecting sensor are installed on the rotary fluid machinery. The flow regulator receives the control signal from the controller to regulate the flow rate through the fluid passage so as to regulate the pressure difference across the balance disc and thus the balance thrust. The present invention is used in the axial force balance of rotary fluid machinery to avoid the damage of the apparatus caused by axial thrust change.

A sanitary centrifugal pump with a hygienic mechanical seal flushing system. The pump has a housing with a pumping chamber defined therein. An impeller is at least partially contained in the housing and is connected to a shaft for rotation. The rotation of the impeller creates a first liquid flow path through the pumping chamber between the inlet port and the outlet port, and the first liquid flow path creates a high pressure area in the pumping chamber. The pump includes additional seal flushing passages by which liquid is delivered to the seal cavity from the pumping chamber and returned back to the pumping chamber, to cool and flush at least a portion of the mechanical seal in the seal cavity.

Air pressure distribution for airfoil lower and upper surfaces is utilized to divert airflow using ducts formed in space-curve shapes placed inside the airfoil volume, through span-wise located inlets from high pressure areas on the airfoil lower surface near the leading edge and through chord-wise spaced inlets on the side face of the airfoil wing tip correspondingly to the side face of the airfoil wing tip through chord-wise spaced outlets on the side face of the airfoil wing tip and to span-wise located outlets to the low pressure areas on the airfoil upper surface. Triboelectric materials on the wing surfaces are employed to static charge the air in drag. Inside the ducts, the employment of either triboelectric linings and materials, or HV-supplied electrodes, or both, help to static charge the diverted air flow to and from the airfoil wing tip side face to diffuse wing tip vortex core early.

A seat cushion for a chair having a contoured, padded base with an inflatable air cell pad positioned securely within the base and encased within a cover. The air cell pad is optimally located in the base so as to be positioned under the user's buttocks, particularly under the areas of high-pressure areas on the buttocks of a normally positioned user. The inflatable air cell pad is operatively connected to a pump device positioned on the chair for access by a seated user of the chair. The user can sit on the cushion and inflate or deflate the air cell pad for optimal support and comfort. In one aspect of the invention the pump comprises a bulb and valve combination.

The invention relates to a method for the laser beam cutting at an angle of a workpiece (1). According to said method, a supersonic cutting gas stream (4) emerging from a cutting gas nozzle (3) is oriented at an oblique cutting angle (alpha) in relation to the workpiece surface (1a), the workpiece (1) and the laser cutting beam (2) being displaced in relation to each other during laser beam cutting at an angle. The oblique cutting angle (alpha) extends perpendicular to the direction of advance (Y). During the relative movement, the position (P) of the laser cutting beam (2) on the surface of the workpiece (1a) is adjusted such that the laser cutting beam (2) is incident on the surface of the workpiece (1a) in a high pressure area (5) formed within the supersonic cutting gas stream (4). The invention also relates to a laser machining tool for carrying out said method.

A seal apparatus includes at least one pair of gears; a side plate arranged adjacent to the pair of gears; and a housing sandwiching the side plate. At least one of the side plate and the housing includes a shoulder portion. The seal apparatus further includes a seal member arranged between the housing and the side plate and arranged at the shoulder portion. The seal member separates a low pressure area from a high pressure area in a radial direction of the gear. The shoulder portion is located in the low pressure area. At least a part of the seal member faces the high pressure area. The seal apparatus further includes a backup member reinforcing the seal member and facing a tip portion of the shoulder portion; and a containing portion formed between a root portion of the shoulder portion and the seal member to be capable of containing a part of the seal member at least when the seal member is elastically deformed.

The invention provides a high-efficiency pneumatic layout structure of synergistic jet for a high-altitude propeller and a control method. The high-efficiency pneumatic layout structure is characterized in that a plurality of synergistic jet devices are distributed along propeller blades of the propeller in a spanwise sectional manner; each synergistic jet device comprises an air blowing opening formed in a negative-pressure area of the front edge of the upper surface of the propeller, an air suctioning opening formed in a high-pressure area of the rear edge of the upper surface of the propeller, an airflow pipeline arranged in the paddle and an air pump arranged in the airflow pipeline; the air blowing opening and the air suctioning opening are communicated by the airflow pipeline to form an air-blowing and air-suctioning loop; the air pump is used for driving air suctioning and air spraying to be implemented simultaneously, and by control of the air pump, the air suctioning amount and the air spraying amount are same. The high-efficiency pneumatic layout structure provided by the invention has the advantages that the defects of the traditional propeller layout and the common flow control technology can be made up, and the working efficiency of a propelling system of the high-altitude propeller can be improved.

The invention relates to a soft foundation discharge fixing technique, used to quickly fix and strengthen soft foundation. The invention combines high-pressure tube device and upright discharge device, to force high pressure on the high-pressure tube, to repeatedly expand the high-pressure tube to sideward press soil, to quickly solidify the soil step from step, and improve the soil strength, to strength the foundation. The strengthen depth of foundation is not limited by soil saturated degree, to confirm the strength quality. The time cost by the invention is 1 / 4-1 / 2 of traditional discharge strengthen method, while its cost is 50-70% of traditional discharge strengthen method, with simple operation, non additional construction field, and repeated used tools, non pollution and waste, and significant economic and social benefits.

A sock having a low pressure area made of a first knit density and at least one high pressure area made of a variable knit density portion. The variable knit density has portions that are made of a second knit density greater than the first knit density. The at least one variable knit density portion is arranged transverse to an orientation of major strain. A sock may also have hydrophobic fibers located substantially across a surface of the sock adapted to be adjacent to skin when worn and hydrophilic fibers located substantially across the hydrophobic fibers and extending therefrom to form loop structures adapted for wicking moisture away from the hydrophobic fibers.

A high lift stepped aerofoil section, incorporating a leading edge 1, trailing edge 3 and a step 2 to provide a higher vertical component in its construction; the aerofoil has greater perceived root thickness giving greater lift through compression 4 on the aerofoil under surface. The section has high pressure area 5 below the aerofoil and low pressure area 6 above the aerofoil. The aerofoil has much higher strength on all axes than conventional aerofoil sections.

At a boundary area between a high-pressure portion in which a discharge port of a fuel pump is disposed and a low-pressure portion in which an intake port is disposed, a pressure relief groove extending along the boundary area is formed so as to be communicated with the outside of the pump by means of pressure relief hole. Alternatively, a slit is formed communicated with the outside. Accordingly, a fuel at a high-pressure area portion can be drained with reliability. Further, by communicating the above pressure relief groove with a positioning pin insertion port, a single hole can serve both as a positioning pin insertion hole and a pressure relief hole.

The invention relates to a horizontal-type piston-type two-stage air compressor used for a vehicle. The horizontal-type piston-type two-stage air compressor used for the vehicle comprises a horizontally arranged crankcase, and a piston cylinder is placed on one side of the crankcase; a rear end cover is connected to the tail portion of the crankcase, and a motor is fixed to the tail portion of therear end cover; a motor spindle is connected with a double-crank crankshaft through an elastic coupling; a high-pressure cylinder piston connecting rod assembly and a low pressure piston connecting rod assembly are correspondingly connected to left-right symmetrically arranged cranks of the crankshaft; and a low-pressure cylinder vent pipe is arranged on the outer side of a cylinder head; a middle cold air outlet pipe is connected with the high pressure area of the cylinder head; and compressed air after cooling enters the cylinder through a high-pressure air inlet valve piece on a valve plate, and secondary compression is completed under combined action of the high-pressure cylinder piston and an air exhaust valve piece. According to the horizontal-type piston-type two-stage air compressor used for the vehicle, the small-sized lightweight two-stage piston type air compressor can meet high pressure demands of the vehicle, working pressure can reach above 1.5 MPa, air is clean, operation is smooth, air pumping efficiency is high, the size is small, the weight is small, the life is long, and mounting and arranging are convenient.

A seal device 25B has a wear-ring 31 fixed to a casing 2 of a centrifugal pump and a floating ring 32. An annular gap 36 between an inner peripheral surface of a through bore 32a formed in the floating ring 32 and an outer peripheral surface of a mouth ring portion 19 of an impeller 5B is smaller than an annular gap 35 between an inner peripheral surface of a through bore 31a formed in the wear-ring 31 and the outer peripheral surface of the mouth ring portion 19. Fluid leakage from a high pressure area to a low pressure area in the casing 2 through the gaps is prevented.

The invention discloses a gas cylinder surface sealing device with a cantilever support and a spiral chute. The device comprises a sealing retainer, a rotor journal, a floating sealing ring and a cantilever supporting plate, wherein a dynamic pressure cylindrical sealing area is formed between the cylindrical sealing interface of the floating sealing ring and the cylindrical surface of the rotor journal, a high-pressure area and a low-pressure area are respectively arranged on two sides of the floating sealing ring, and the rotor journal and the floating sealing ring rotate relatively; and the floating sealing ring is supported by a plurality of cantilever sheets which are distributed circumferentially, and the cantilever sheets are fixed by the sealing retainer. The cylindrical surface gas film sealing device realizes non-contact and small-leakage sealing while adapting to the deformation in position sealing work process through the flexibility of the support and a dynamic pressure gas film, and is adaptive to the installation space requirement on non-shaft end position sealing through the cylindrical surface structure.

The invention provides a start method for quickly discharging pressure of a compressor of a refrigeration system. The start method comprises the following step of: opening an expansion valve to a preset opening for preset time when the compressor is stopped and / or started. The expansion valve is opened to the preset opening for the preset time when the compressor is stopped and / or started, so a high pressure area and a low pressure area at both sides of the expansion valve are quickly communicated, the pressure difference between the high pressure area and the low pressure area of the refrigeration system is quickly reduced, and even the pressure is balanced; and the compressor can be normally started when restarted after waiting for a short time, so that the compressor is quickly started. The method has the advantages of simpleness, easy use and low cost, is particularly suitable for application occasions such as a heat pump water heater and the like in which the compressor is needed to be frequently started.

The invention discloses a hybrid bearing. The hybrid bearing comprises a bearing body (1). At least two oil grooves (2) are formed in the annular inner wall of the bearing body (1) in the radial direction of the bearing body (1) in an inwards concave mode. The hybrid bearing is characterized in that the bearing body (1) is provided with circulation channels (3), and the two ends of each circulation channel (3) communicate with two ends corresponding to the oil grooves (2) in the circumferential direction of the bearing body (1) correspondingly. According to the hybrid bearing provided by the invention, the pressure difference of an oil liquid high-pressure area and an oil liquid low-pressure area in an oil cavity can be balanced, accordingly, the purpose of reducing the radial acting force on a rotating shaft is achieved by reducing the pressure of oil liquid in the oil liquid high-pressure area, finally, the rotation speed of the rotating shaft is high, and the load of a driving motor is small.

A hybrid plasma reactor includes a reactor body having a plasma discharge space, a gas inlet, and a gas outlet; a hybrid plasma source including an inductive antenna inductively coupled to plasma formed in the plasma discharge space and a primary winding coil transformer coupled to the plasma and wound in a magnetic core; and an alternating switching power supply for supplying plasma generation power to the inductive antenna and the primary winding coil. The hybrid plasma reactor induces a plasma discharge using the inductively coupled plasma source and the transformer coupled plasma source, so that it has a wide operational area from a low pressure area to a high pressure area.