35results about How to "Efficient blending" patented technology

A rotary drum configuration for the efficient blending, cooling, and screening of granular products having an outer cylindrical shell, an intake end, and a discharge end. The rotary drum is normally rotated at a predetermined speed by means of a conventional drive package. Disposed on an inner surface of the cylindrical shell are a plurality of compound helical flights and scoops, configured to blend granular product as it cascades from the intake end to the discharge end of the rotary drum. A coaxially disposed cylindrical air passage adjacent the discharge end of the rotary drum directs a counter flow of cooling air through the rotary drum towards the intake end, cooling the cascading granular product as it approaches the discharge end, and plurality of discharge ports and grading screens in the surface of the outer cylindrical shell adjacent the discharge end provide a entrance for a second counter flow of cooling air while simultaneously providing passage for the granular product to drop downwards towards a outer coaxial discharge passage.

The invention discloses a radial rim sealing structure with damping holes and flow guide blades. The radial rim sealing structure is characterized in that the radial rim sealing structure is arranged in a gas turbine rotor-stator cavity or a gas turbine rotor-rotor cavity and comprises an outer tooth and a radial inner tooth which are matched; a plurality of damping holes are evenly formed in the upper end face of an inner tooth body of the radial inner tooth in the circumferential direction, and a plurality of flow guide blades are evenly arranged on the radial end face of the inner tooth body of the radial inner tooth in the circumferential direction; furthermore, the damping holes are in a cellular shape and are evenly distributed in a sealing tooth face in the circumferential direction; the flow guide blade are arranged on the end face of the sealing radial inner tooth with equal arcs, and the blades are provided with gradually-shrunk channels. The rim sealing structure can effectively lower the high-temperature gas invading degree and improve the sealing performance of rim sealing, and therefore the overheat failure of a turbine disc is avoided, the use amount of low-temperature cooling air flow introduced from the position of an air compressor can also be reduced, and the efficiency of a unit can be improved.

A tumbling container is mounted for rotation with a curved screen fixedly mounted within the tumbling container. A multiple vane paddle is mounted to a shaft that is rotatably mounted to the tumbling container. The paddle vanes are formed with angular edges. As the tumbler rotates and the paddle rotates, powder is repeatedly dropped onto the screen to be sifted with the aid of the paddle. Rotating the tumbler further drops unsifted portions of the powder from the screen to mix with additional powder in the tumbler body. Thus, sifting and blending of powders is accomplished in one single operation. The invention utilizes an apparatus having a multiple section screen and a multiple section paddle to enable assembly through the openings in the tumbling container. The screen of a second embodiment has a cowl adjacent to each screen opening to optimize powder lump disintegration.

The invention relates to a thrust chamber injector, in particular to a liquid oxygen methane thrust chamber injector, and aims to solve the problems that in the working process of an existing liquid oxygen methane injector, both liquid oxygen and methane belong to liquid low-temperature propellants, a direct-current shear type nozzle or an impact type injector structure is adopted and consequently the propellant mixing effect of the thrust chamber injector is poor, and the combustion efficiency is insufficient. The liquid oxygen methane thrust chamber injector comprises a plurality of injection units, a middle bottom, a top cover, a fluid director and an inner bottom, wherein the top cover, the fluid director and the inner bottom are coaxially and sequentially arranged on the middle bottom. The multiple injection units are fixed to the middle bottom, the fluid director and the inner bottom; a liquid oxygen cavity is formed among the top cover, the middle bottom and the multiple injection units, and a methane cavity is formed among the middle bottom, the inner bottom and the multiple injection units; and the multiple injection units are provided with nozzles with retraction chambers, and the nozzles comprise a central area nozzle, a main combustion area nozzle and an edge area nozzle.

The invention belongs to the technical field of gas turbines, and particularly relates to a multi-stage partitioned combustion structure for a gas turbine. The multi-stage partitioned combustion structure for the gas turbine comprises a combustion chamber casing, a flame tube, a plurality of cyclones and a diverter. The cyclones are divided into an on-duty cyclone, a flame transfer cyclone, a first main combustion cyclone and a second main combustion cyclone, each cyclone is provided with a first fuel gas channel, and the first fuel gas channels convey fuel gas used for premixed combustion. A second fuel gas channel is further arranged at the on-duty cyclone, and the second fuel gas channel is used for conveying fuel gas for diffusive combustion. The installation angles of blades of the cyclones are different, and the flow fields of rotating airflow generated by the cyclones are relatively independent, so that the cyclones participate in independent partitioned combustion. According to the multi-stage partitioned combustion technology in the scheme, the four stages of different cyclones are combined with the diverter, multi-stage partitioned organization combustion is formed in a staged fuel supply mode, the requirements of all working conditions are met, the ignition and flameout performance and combustion stability of a combustion chamber are guaranteed, and the requirement for low emission of nitric oxide is met.

The invention provides a medium-low pressure hydrogen-containing pipeline experiment system and method. The medium-low pressure hydrogen-containing pipeline experiment system comprises a mixing device, a medium-low pressure test pipeline, a control terminal and a terminal test element connected with the control terminal, the mixing device comprises a plurality of input ports, at least one first input port is communicated with a hydrogen source, at least one second input port is communicated with a non-hydrogen source, and an output port of the mixing device is communicated with a terminal test element through a medium and low pressure test pipeline; the output port of the mixing device is provided with a hydrogen concentration detection element connected with the control terminal, and the middle and low pressure test pipeline is connected with at least one sensing element connected with the control terminal; the control terminal controls the pressure and/or flow of the mixing device and the outlet pressure and/or flow of each gas source according to the hydrogen concentration detection result; blending, flowing and utilization experiments of a pure hydrogen pipeline and a hydrogen-doped pipeline can be carried out more efficiently.

The invention provides a fuel gas generator. The fuel gas generator is composed of an injector, an eccentric turbulent flow ring, a spherical-cone-shaped combustion chamber and a three-way bent pipe. The injector is in a round cake shape, the whole injector is printed through a 3D printer, the upper half part of the eccentric turbulent flow ring is a cylindrical ring, the top face of the cylindrical ring is fixedly welded with the edge of the bottom face of a lower boss of the injector, the bottom edge of the side face of the cylindrical ring is fixedly welded with the hole wall of a side hole of the spherical-cone-shaped combustion chamber, and the lower half part of the eccentric turbulent flow ring is a conical ring with an eccentric opening. The spherical-cone-shaped combustion chamber comprises a spherical cavity and a cone cavity, a side hole is formed in the side face of the spherical cavity, an outlet is formed in the top of the cone cavity and fixedly welded with a middle inlet of the three-way bent pipe, the three-way bent pipe is integrally in a side T shape, a left port is formed in the left side of the three-way bent pipe, a flange structure connection mode is adopted, a right port is formed in the right side of the three-way bent pipe, a middle inlet is formed in the middle part of the three-way bent pipe, and a boss positioning form is adopted. The structure of the fuel gas generator is optimized, propellants can be efficiently atomized, mixed and combusted, and the combustion efficiency is improved.

The invention provides a high-reliability multiblade cold/hot air flow mixed spoiler which comprises an outer ring and a spoiling component, wherein the outer ring can be connected with the inner wall of the pipeline through screws, and the spoiling component is arranged on the inner wall of the outer ring; the spoiling component comprises a plurality of flat blades and a spacing ring, and the blades are uniformly distributed in the circumferential direction; one end of each blade is welded on the inner wall of the outer ring and forms a certain included angle with the approach flow direction, and the other end of each blade is a free end and extends towards the central axis of the outer ring to form a center hole; the free end of each blade is provided with a spacing hole of which the cross-sectional shape is greater than that of the spacing ring; and the spacing ring orderly penetrates through the spacing hole of each blade. The invention overcomes the defect that the air flow temperature field uniformity of the existing high-flow high-temperature simulated ground equipment can not satisfy the requirements, provides a static mixed mode of multiblade spoiling and variable cross-section pipelines, and has the advantages of high flow, high temperature difference and high reliability.

The invention discloses a double-stage axial swirler capable of strengthening oil-gas mixing in a cavity. The double-stage axial swirler comprises a first-stage swirler and a second-stage swirler, a venturi tube is arranged between the first-stage swirler and the second-stage swirler, a sleeve is arranged on the second-stage swirler, the first-stage swirler is arranged on a center nozzle in a sleeving manner, and a flow mixing part and a cooling part are further included. The flow mixing part is arranged at the end part of the sleeve and is used for fully mixing oil and gas in a combustion chamber again; and the cooling part is arranged on the sleeve and is used for conveying cooling gas and carrying out cooling protection on a combustion chamber swirler shell, and meanwhile, the problems that combustion instability is caused, the stability of the flame of the combustion chamber is reduced and flame stability is not facilitated due to the fact that unstable vortex core precession (PVC) flow generally exists in a flow field of a double-stage axial swirler are solved.

The invention discloses a solid rocket scramjet engine adopting a multi-stage combustion enhancing device. The engine comprises an isolation section, a combustion chamber, a plurality of flow disturbing devices, concave cavities and a group of wedge units; the isolation section is a cavity body with a gas inlet end and a gas outlet end; the combustion chamber is a cavity body with a gas inlet endand a gas outlet end, and the gas inlet end of the combustion chamber is integrally connected with the gas outlet end of the isolation section; the flow disturbing devices are combinations of the concave cavities and one group of wedge units; the concave cavities are formed in the upper wall and the lower wall of the combustion chamber in an axially spaced mode, and the concave cavities in the upper wall and the concave cavities in the lower wall surface are arranged in a staggered manner; and one group of wedge units are arranged between two adjacent concave cavities in the same wall surfaceand correspond to the concave cavities in the opposite side wall in position. According to the solid rocket scramjet engine, the mixing degree between fuel-rich gas generated by a solid rocket and thesupersonic-velocity air flow is enhanced, the range of a combustible area is expanded, the combustion efficiency of the rocket fuel-rich gas is improved, so that the overall performance of the engineis improved.

The invention provides a continuous rotation detonation ramjet engine capable of supplying oil and gas in the radial direction, and belongs to the technical field of aero-engines, the continuous rotation detonation ramjet engine comprises an oxidant injection mandrel used for oxidant inflow, a fuel pressure stabilization cavity used for fuel pressure stabilization and a combustion chamber, and a pressure stabilization space is formed in the oxidant injection mandrel; a plurality of first gaps are evenly distributed in the oxidizing agent injection mandrel, oxidizing agents enter the combustion chamber through the first gaps, and a plurality of second gaps used for introducing fuel into the combustion chamber are evenly distributed in the radial direction of the fuel pressure stabilizing cavity. According to the ramjet engine, the feeding direction of fuel is changed into the radial direction, so that the fuel and an oxidizing agent are subjected to radial hedging in the combustion chamber, and good mixing is achieved; the oxidant and the fuel cavity are respectively provided with a pressure stabilizing structure, and gap flow channels which are uniformly distributed at 360 degrees also play a role in flow equalization; and the combustion chamber is self-cooled by adopting fuel required by the combustion chamber, so that stable work of the detonation combustion chamber in a long-time detonation state is realized, and the problem of long-time reliable work of the detonation ramjet engine is solved.

The invention provides a fuel nozzle of a gas turbine. The fuel nozzle comprises a cylindrical center body, an outer wall surface, an annular gas channel, a swirl vane, a support sleeve, a mounting flange, a rear cover plate, a main fuel pipe and an on-duty fuel pipe, wherein the annular gas channel is arranged between the outer wall surface and the center body; the swirl vane is arranged in the annular gas channel; a fuel channel and a first fuel tank communicated with the surface of the swirl vane are arranged in the wall of the support sleeve; a second fuel tank is arranged in the mountingflange; the rear cover plate is provided with a first fuel pipe interface and a second fuel pipe interface; the main fuel pipe is connected with the first fuel pipe interface and the second fuel tank;and the on-duty fuel pipe is connected with the second fuel pipe interface and a flow guide pipe. According to the invention, the main fuel pipe and the on-duty fuel pipe are introduced, and when thedistance between the interface of the nozzle on a combustion chamber and a gas turbine shell is larger, fuel and air are well mixed, so that low-pollution energy-saving and environment-friendly combustion is realized, and the fuel nozzle can be applied to a ground gas turbine with strict pollutant emission limitation; and the nozzle also has the advantages of simple structure, convenience in disassembly and maintenance and low manufacturing cost.

The invention discloses a low pressure rear cylinder water spray hole of turbine and a design method of the low pressure rear cylinder water spray hole. According to the invention, a traditional roundwater spray hole water outlet is changed to a variable section star shape. After incoming water drops pass through the star-shaped hole, the expansion range is enlarged, so that mutual mixture of theincoming water drops and high temperature discharged steam is enhanced. At the same time, local gradually expanding treatment is performed on an inclined channel of the incoming hole and optimizationis performed on the inclination angle of the channel, so that the incoming speed of the incoming water drops decrease after passing through the channel and the incoming position becomes more adjacentto a high temperature area, and the turbulent mixing of the water drops and the high temperature discharge steam is improved further. Through a method of expanding the expansion range of the incomingwater drops in the air cylinder, reducing the incoming speed of the water drops and ensuring the proper direct spray direction of the water drops, requirements for high-efficiency mixture of the water drops and the high temperature discharged steam are met and aims of improving performance of a water spray system and improving the low pressure tail stage safety and stability are achieved.