240results about How to "Enhanced blending" patented technology

The invention discloses turbine-based combined cycle engine super-combustion chamber. Key parts of the super-combustion chamber comprise a shunt ring, a rear area-variable deflation valve, a flow guide tongue piece, a square lobe mixer, a first area fuel ejector, a center cone, a second area fuel injection ring, an evaporation tube flame stabilizer, a heat-isolating screen, a super-combustion chamber cylinder, an outer extending groove-width-variable radial flame stabilizer and an inner extending radial flame stabilizer. An internal flow field of the super-combustion chamber is reasonably distributed, the phenomenon of backflow from a punching duct to a turbofan duct can not occur, flow separation can not occur in the square lobe mixer, and the evaporation tube flame stabilizer can achieve soft ignition of the super-combustion chamber. The whole super-combustion chamber is high in mixing efficiency, little in cold flow resistance, high in combustion efficiency, reasonable in temperature distribution, and capable of meeting use requirements in a whole flight envelope of the super-combustion chamber in each work state and the requirement for boost of an turbofan ramjet.

The invention discloses a device for controlling the delivery and the uniform distribution of reaction gas in a MOCVD reaction chamber. By respectively controlling the flow of gas passages non-uniformly distributed radially on a front gas homogenizing plate and input passages at different positions, at least two reaction gases are respectively introduced into two paths which are radially and axially crossed on a spray header, and can be secondarily distributed by nozzles in different shapes, so the uniformly distributed boundary layer concentration, speed and temperature required are achieved on the surface of a rotary epitaxial wafer, the quality of massively produced epitaxial films and the finished product ratio of massively produced epitaxial wafers are improved, the consumption of expensive reaction gases can be effectively controlled and the epitaxial production cost is reduced. By properly increasing the distance between the surface of the spray header and the epitaxial wafer, deposits generated on the surface of the spray header and the nozzles in the epitaxial growth are reduced, the cleaning period is prolonged, and the production efficiency and system capacity are improved. The device also can reduce the processing difficulty and manufacturing cost of the nozzles of the spray header and cooling medium passages.

The invention provides an ultra-high molecular weight polyethylene composition. The ultra-high molecular weight polyethylene composition comprises silicon carbide, modified graphene and ultra-high molecular weight polyethylene, wherein the modified graphene is hyperbranched polyethylene grafted graphene. The material prepared from the composition simultaneously has relatively high cutting resistance and very strong tensile strength.

The invention provides a plasma catalysis ignition integrated nozzle which is a plasma assisted atomization and plasma ignition integrated nozzle formed by a low-temperature plasma discharge assembly, a fuel pressure atomization nozzle assembly and a high-energy plasma ignition assembly. A barrier medium uniformly discharges to ensure that a liquid fuel partially pyrolyzes to generate a large quantity of gas activated components, so that a gas-liquid coexisting plasma microcell is formed, fuel activation energy and ignition energy are reduced, physical conditions of gas assisted atomization are formed, and atomization effect is improved. A plasma ignitor is arranged on the middle of a multi-point nozzle and is positioned in a combustion chamber low-pressure region, plasma and fuel atomized particles are well mixed to generate a chemical reaction, and a stable high-temperature ignition core is easily formed. Ignition is directly carried out by adopting a plasma jet, and because the plasma jet has special discharge characteristics and larger discharge energy and is highly concentrated in energy, the ignition reliability and the ignition concentration limit of a gas turbine are greatly improved. The plasma catalysis ignition integrated nozzle can be applied to a combustion chamber of the gas turbine.

The invention aims to provide a gas circuit axial grading type dual-fuel nozzle which comprises a gas circuit outer wall and a main oil circuit wall arranged inside the gas circuit outer wall. An auxiliary oil circuit wall is arranged inside the main oil circuit wall. A main oil circuit channel is formed between the main oil circuit wall and the auxiliary oil circuit wall. An auxiliary oil circuit channel is formed inside the auxiliary oil circuit wall. A gas circuit is formed between the gas circuit outer wall and the main oil circuit wall. The gas circuit comprises a gas circuit front cavity, a gas circuit laryngeal and a gas circuit rear cavity in sequential communication. A first level gas circuit gas ejection hole is formed in a position, arranged on the gas circuit front cavity, of the gas circuit outer wall. A laryngeal gas ejection hole is formed in the gas circuit laryngeal. A second level gas circuit gas ejection hole is formed in the gas circuit rear cavity. Due to the fact that a gas circuit axial grading type structure is adopted, the gas circuit axial grading type dual-fuel nozzle has the advantages of reducing the radial size of the nozzle, simultaneously increasing gas circuit flow area, enhancing mixing of fuel and air, strengthening burning, shortening flame, and simultaneously not burning the wall surface of a flame tube. When liquid fuel is burned, water vapor reinjection is conducted by the gas circuit.

The invention discloses a special device for waste fermentation, which comprises a fermentation cylinder (2) connected with a driving mechanism (4); wherein, the fermentation cylinder (2) is rotationally connected with a riding wheel frame component (3); the fermentation cylinder (2) is respectively provided with a feed inlet (21), a discharging hole (23), an air inlet (24) and an air outlet (22); a copy board (11) and a baffle (12) are arranged in the fermentation cylinder (2), and the baffle (12) is provided with at least one via hole aperture of which can be adjusted the. A waste fermentation method by utilizing the device is also provided by the invention, the fermentation cylinder (2) with an inner cavity which is 32 meters in length and 3.2 meters in diameter is selected, the rotational speed of the fermentation cylinder (2) is controlled to be 2r/min, and the angle between the central axis of the fermentation cylinder (2) and the horizontal plane of the fermentation cylinder (2) is 2 degrees; heated air is input from the air inlet (24) and the ventilation rate is 10000m<3>/h. Treating wastes by the device of the invention ensures that the waste fermentation period is shorter and the fermentation is more full.

The invention provides a device for improving jetting uniformity of nozzles. The device comprises an oxidizing agent nozzle and a fuel nozzle which are connected with each other and constitute a two-component jetting unit, wherein an oxidizing agent nozzle inlet throttling hole is embedded in an inlet of the oxidizing agent nozzle, and an outlet of the oxidizing agent nozzle is formed in the fuel nozzle; multiple rows of radial inlet holes are radially formed in the fuel nozzle, multiple rows of small holes are further axially formed in the fuel nozzle, and an annular cavity is formed in the lower end of the fuel nozzle; during working, an oxidizing agent enters the oxidizing agent nozzle inlet throttling hole via the inlet of the oxidizing agent nozzle, fuel enters the radial inlet holes of the fuel nozzle, is subjected to primary flow equalization, is subjected to secondary flow equalization by the aid of the annular cavity and is sprayed out via an outlet of the fuel nozzle finally, and uniform distribution along the circumferential height can be obtained. With the adoption of the device, the jetting uniformity of the fuel is improved, mixing and burning effects of the fuel and the oxidizing agent are enhanced, and then the burning efficiency of a thrust chamber is improved.

The invention relates to a turbine blade compound cooling structure with sunken internal pins, comprising a blade passage and a pin; the cooling structure is characterized by further comprising a sunken part, pins are arranged in the blade passage, the blade passage has at least one internal wall surface provided with sunken parts; the sunken parts are arranged in the blade passage in a dislocation way; the sunken parts are of semisphere or part of the semisphere or cone with top part cut off. In the invention, the pins are respectively connected with two wall surfaces in the blade passage, thus on one hand increasing heat exchange area of cooling fluid and on the other hand consolidating the passage; the sunken parts cause the flowing through to generate vortex, thus improving convection and heat exchange effect between the air stream and wall surface of the blade passage and pin surface; meanwhile, when the air stream flows through the sunken parts, direct impact on the pins by the lower reaches of the fluid body is reduced, thus avoiding increase of flow losses while increasing heat exchange area.

The invention discloses a debris-flow drainage canal with energy dissipation and drainage functions and an application of the debris-flow drainage canal with energy dissipation and drainage functions. The drainage canal comprises a fully-lining drainage canal bottom plate and drainage canal side walls on two sides of the drainage canal bottom plate; the drainage canal bottom plate is in the shape of continuously-connected multiple-stage steps, the steps are provided with grooves; the width of the grooves on the top surfaces of the steps increases gradually along the flow direction of the debris flow, and the width of the grooves on the vertical surfaces of the steps decreases gradually; and the maximum width of the grooves on the top surfaces of the steps coincide with the maximum width B on the vertical surfaces of the steps. Compared wit the prior art, the step shape design is adopted to dissipate the energy of the debris flow all the way and the groove design is adopted to drain the debris flow, so the debris-flow drainage canal disclosed by the invention has high efficiency and good drainage capacity. By adjusting the height and the length of the steps and the size and the shape of grooves, the debris-flow drainagedrainage canal can be used for preventing the debris flow with any gradient and any nature.

A submerged cyclone shaft sluice tunnel comprises a sluice tunnel and an aerated cyclone shaft with double volute chambers installed at the closed end of the sluice tunnel and communicated with the sluice tunnel; the sluice tunnel is internally provided with a stop part and a middle part slope; the top of the sluice tunnel is provided with an air exit hole; the aerated cyclone shaft with double volute chambers is positioned at the top of the sluice tunnel, and the central line thereof is vertical to the central line of the sluice tunnel; the stop part is installed on the bottom plate of the sluice tunnel; the distance L2 between the beginning end of the stop part and the central line of the aerated cyclone shaft with double volute chambers is equal to 5H7 to 10H7; the air exit hole is positioned in the middle of the stop part and the middle part slope; the distance L3 between the central line of the air exit hole and the central line of the aerated cyclone shaft with double volute chambers is equal to 7H7 to 15H7; the middle part slope is installed at the top of the sluice tunnel; the distance L4 between the beginning end of the middle part slope and the central line of the aerated cyclone shaft with double volute chambers is equal to 8H7 to 15H7; and the H7 in each formula is the height of the upright wall of the gate-shaped sluice tunnel.

The invention aims to provide an active control type fully-immersed liquid-cooled power battery thermal management system. A compressor, a condenser, a refrigeration electromagnetic valve, an expansion valve and an evaporator are connected in series to form a compressor unit main refrigeration unit; a manual valve and a liquid spraying electromagnetic valve are led out from a pipeline in front of the refrigeration electromagnetic valve to form a spraying branch; a thermal manual valve and a thermal electromagnetic valve are led out from a pipeline between the compressor and the condenser to the evaporator to form a thermal bypass branch; and a first three-way reversing valve and a second three-way reversing valve are connected with a plate heat exchanger and the evaporator and are connected in parallel to form a plate heat exchanger auxiliary cooling unit, the first three-way reversing valve is connected with a drying filter and the manual valve to a cooling liquid tank, and the second three-way reversing valve is connected with an electronic circulating pump, a temperature sensor and a flow sensor to the cooling liquid tank. The direct contact type fully-immersed liquid-cooled mode is adopted, the heat loss in the heat exchange process of the whole heat management system can be greatly reduced and improved, the heat exchange resistance of the system is reduced, and the heat exchange efficiency is improved.

The invention provides a combustion chamber fuel nozzle device. The combustion chamber fuel nozzle device comprises a nozzle rod part and a fuel nozzle shell; a main combustion level oil line and a pre-combustion level oil line are arranged in the nozzle rod part; one end of the pre-combustion level oil line is connected into the fuel nozzle shell and provided with a pre-combustion level nozzle; one end of the main combustion level oil line is annularly distributed on the periphery of the fuel nozzle shell and provided with a plurality of main combustion level nozzles which are machined independently so that fuel oil in the main combustion level oil line can be ejected rotationally; and the fuel nozzle shell is connected with a main swirler and located at the outlet ends of the main combustion level nozzles and the outlet end of the pre-combustion level nozzle. According to the combustion chamber fuel nozzle device, the main combustion level nozzles are machined independently and then welded to the fuel nozzle shell, the oil injection mode of the main combustion level nozzles is adjusted, thus, the oil injection mode of the main combustion level nozzles is converted from the direct-injection mode into the centrifugal mode, the atomization effect is strengthened, mixing of fuel oil and air in a main combustion zone is facilitated, and finally, pollutant discharge of a combustion chamber is reduced.

The invention discloses a turbine stator blade with an interstage combustor, and relates to turbine stator blades of aero-engines or gas turbines. The turbine stator blade comprises an inner ring, an outer ring and multiple guide blades, wherein the guide blades are provided with a guide blade main body and a guide blade cover; the guide blade cover is arranged on the upper end of the guide blade main body, and the guide blade main body is provided with a front oil injection cavity, a middle backflow cavity and a rear cooling cavity; another cooling cavity is formed at the rear of the guide blade cover, and the oil injection cavity is internally provided with a spraying rod slot; the cooling cavity of the guide blade main body and the cooling cavity of the guide blade cover respectively have cooling holes; the turbine stator blade is also provided with ignition devices and multiple spraying rod devices, and the ignition devices are provided with ignition bases and ignition electric nozzles; the spraying rod devices are arranged on the guide blades, the outer ends of the spraying rod devices pass through and are exposed of the outer ring, and the inner ends of the spraying rod devices stretch into oil injection cavities of the guide blades; and the spraying rod devices are provided with oil pipes, gas pipes and nozzles, oil spraying ports and multiple gas spraying ports are formed in the nozzles, and the oil pipes and the air pipes are respectively connected with an oil supplying pipe and a gas supplying pipe.

The invention belongs to the technical field of combustion chambers of gas turbines, and particularly relates to a coaxial staged combustor for a low-pollution combustion chamber of a gas fuel gas turbine. According to the coaxial staged combustor, air flow is accelerated by adopting a tapered rotational flow channel. A tapered mixing section is arranged behind each stage of rotational flow blades, so that the mixing between fuel and air is enhanced. First-stage fuel enters a hub fuel ring cavity from a fuel pipe through a fuel branch, second-stage fuel and third-stage fuel enter a rectification fuel ring cavity before entering the hub fuel ring cavity and enter the hub fuel ring cavity from four fan-shaped hub fuel ring cavity inlets of the hub fuel ring cavity after being rectified, it is guaranteed that the fuel flow in flow channels between blades of the same stage is uniform, and the premixing effect is enhanced. First-stage premixing-stage fuel is sprayed out from fuel spraying holes in a hub and enters a backflow area along with first-stage premixing-stage air along a first-stage outer hub, the fuel is prevented from being gathered at an outlet of a swirler, and the phenomena of tempering and combustor ablation are effectively prevented.

The invention relates to a wingtip vortex fast weakening device which designs the back edge of an alula at the wingtip of an airfoil into a sawtooth structure and leads the sawtooth structure to be parallel with the back edge of the alula at the wingtip. The structure of the invention is simple and is improved based on the original alula structure at the wingtip, which can not bring any additional quantity to an airplane. Simultaneously, the invention runs stably, does not need to be provided with power when running and is convenient for being maintained. The wingtip vortex fast weakening device of the alula at the wingtip in the sawtooth shape of the back edge designed by the invention has physical characteristic scales of the wingtip vortex, can speed up and induce the mixing between a high speed air flow and a low speed air flow generated by the wingtip vortex and can lead the wingtip vortex to fast break into a vortex with a small scale, thus achieving the effect of speeding up the dissipation of the wingtip vortex and fast weakening the wingtip vortex.

The invention relates to the technical field of biomaterials, particularly to a bio-based nylon composite PLA material and a preparation method thereof, wherein the raw materials comprise, by weight,10-20 parts of a filler, 40-60 parts of polylactic acid, 1-5 parts of an antioxidant1010, 0.5-2 parts of a plasticizer, 4-8 parts of a compatibilizer, 4-8 parts of a coupling agent, 40-60 parts of a bio-based nylon, 1-5 parts of a polyolefin elastomer, 1-3 parts of modified glass fiber, and 0.01-1 part of glycidyl methacrylate. According to the present invention, the mechanical strength and the size stability of the PLA material are improved by filling the modified glass fiber with the bio-based nylon and the polylactic acid while the bio-based nylon and polylactic acid compounding process isfilled and grafted by using the filler and the high-toughness grafting agent glycidyl methacrylate, such that the bio-based nylon composite PLA material meets the performance requirements of engineering plastics and has good degradability.